DE102015017127A1 - Multifunctional flap as a return flap for aviation - Google Patents

Abstract

Device for a safety system and / or resource-energy efficiency improvement system for influencing the flow of an aerodynamic or hydrodynamic body (3), preferably a wing (3), according to the principle of a return flap (4), characterized in that it is connected to the aerodynamic or hydrodynamic body (3), in particular wing (3), at least a partial displacement of the flap area delimitation (21) by the return flap (4) and its demarcation member (5) in partial and / or complete installation of the return flap (4) and thereby affecting the end-edge separation vortices (1) and / or flap-detachment vortices (2) and that the flap area boundary (21) extends all the way to or over the profile end edge (6). shifts or only up to a part in front of the profile end edge (6) shifts, and that this with a base member (23) on the wing (3) movably connected, preferably permanently and / or for maintenance purposes detachable, is attached, thereby allowing a long life of the wing and / or the wind turbine and / or the flap system, preferably> 5 years, more preferably> 10 years, most preferably> = 20 years and / or possibly a simple removal / replacement allows.

Description

TECHNICAL FIELD OF THE INVENTION

Flaps are natural birds. Thereafter, the operation of these valves can be interpreted as follows:
By erecting the flap forms before this a stationary flap vortex, the direction of flow on the wing top side facing from back to front. The valve vortex reaches the front almost into the nasal area. As it were, it fills the triangular area between the top of the wing, the top of the flap and the flow around it. The flow is deflected downwards by this valve vortex compared to the detached bare profile. One can take this valve vortex as profile change (with free flow limit). Just behind or under the flap is a second vortex area, which includes a larger, but possibly weaker, end-edge vortex. Also in this end edge vortex, the flow along the wing surface is directed from back to front. So the two vortices turn in the same direction. Both are stationary.

Through flow visualization using smoke and thread probes, these vortices were examined more closely ( 1 ). A model wing a: with detached flow; b: with detached flow with flap (off Hours. T. Pantone G ET AL )
( 2 ) Simulated flow conditions on a wing with return flap (off Hours. T. Meyer Robert KJ )

The invention relates in particular to a return flap on a wing, in which the lift is further increased by displacement and / or reduction of the end edge separation vortex and / or the minimum (start) speed is reduced than in conventional return flow flaps (improvement area A + B. in 1 ). Further, by providing a combination of a passive and an active return flap, a precautionary / avoidive response to an impending gust situation as a safety system is enabled (Enhancement Area D: Overspeed Control). In particular, the lower permanent alternating load (in particular the maximum values) of the long wings that can be achieved in this way has great significance with regard to their actual service life due to fatigue phenomena, in particular of GFRP or CFRP materials used there (it has been found that e.g. B. the wing deformation increases over the life and this must remain in a limited framework). In addition, for such situations, as well as an easy-to-operate active backflow flap with braking effect allows (improvement range A: traction help + D: Ouerspeed-Control). This allows for improved energy efficiency at z. B. takeoff and landing in aircraft or at z. B. weak (by more buoyancy) and strong wind situations (especially in very large wind turbines with more than 50 m long wings) in wind power generation plants (by shorter off times = cut-off). Also, the increased buoyancy at low fluid velocities may either reduce the minimum speed and / or size the wing may be smaller, resulting in material savings and cost savings (resource and material efficiency improvement).

In addition, the device according to the invention in the form of a wing with a passive and / or active flap system has to improve the yield at least in the areas of improvement A and / or B and / or C and / or D, in the form of a fluid-inflatable (inflatable ) Actuator element, and possibly a flap if necessary very easy to retrofit and / or attachable and / or interchangeable,
functioning as a system of increasing the stiffness and / or travel of the flap, and / or system having a long service life and retrofitting capability, and / or a wing-reinforcing base element and / or lightning protection, and / or noise-reducing buoyancy and / or base element, and / or Vibration damping system with at least one vibration-damping element, and / or storm protection / Overspeed protection, and / or traction help in light wind, and / or Overspeedschutz and / or vibration damping system by means of at least one buoyancy-reducing buoyancy element and possibly with closable pressure equalization openings and / or ice and snow Removal system, can be used, characterized in that means for increasing the stiffness of the flap and / or means for Wegbegrenzung are used, and that, the Wegbegrenzung the opening angle of the Flaps of <90 degrees, preferably <75 degrees, most preferably <60 degrees, limited and that at least one Aktua Tor element and / or a component thereof with a fluid can be filled (inflated), and this can be folded at least simultaneously in the initial state.

STATE OF THE ART

In Patone G ET AL: "Aeroflexible Surface Flaps as Backflow Brakes" in Technical Report TR-96-05, 1.5.1996 Passive return valves made of elastic material are described, which come very close to the bird feathers in nature. Through flow visualization using smoke and thread probes, these vortices were examined more closely ( 1 ). A model wing a: with detached flow; b: ditto. with flap. These have a relatively large buoyancy-enhancing effect and In slightly air-permeable form have a low hysteresis when lifting and lowering the flap. There was a delay in the separation / tearing off of the flow on the top of the profile. Disadvantages of these embodiments are the short life of the materials used under real weather conditions such as ice, rain, sand, UV radiation. In addition, the low mechanical stability under conditions of use, such as in strong gusts and winds and the possibly necessary cleaning of an aircraft wing is disadvantageous.

On surface wing aircraft, experimental studies have been carried out with surface flaps / return flaps in the wind tunnel to explore their potential as an influence on flow separation (see Meyer, Robert KJ, Experimental investigations on airfoils to influence flow separation , The return valves used here have a solid plate as a flap and are hinged with elastic connecting elements. Medium lift value increases up to 15% were measured. There was a delay in the separation / tearing off of the flow on the top of the profile. A stabilizing effect on the wake and the vortex structures forming there was determined. There was a significant hysteresis when lifting and lowering the flaps found, which brings significant disadvantages in the operation with the optimal buoyancy. Dissertation TU Berlin Hermann Föttinger Institute for Fluid Mechanics, Mensch & Buch Verlag, ISBN 3-89820-205-4 ).

In the DE 102010041111 is a wing for a driven horizontal rotor of a lifting or support screwdriver having at least one flap integrated in the wing, which is pivotable relative to a main body of the wing about a longitudinal direction of rotation of the horizontal rotor longitudinal axis of the wing. The invention has for its object to show a wing in which is displaced by passive measures of the dynamic stall to higher angles of attack or to higher speeds. This is realized by means of an elastic return flap. In the new wing, the flap has a basic position in which it lies flat against the top of the main body. In other words, it is a so-called surface flap. This flap is passively pivoted away from its upper position from the top of the main body against an elastic restoring force. That is, the flap is not actively brought by any actuators into a functional position pivoted away from the top of the main body, but by forces resulting from the operation of the wing, ie aerodynamic forces and possibly inertial forces. Accordingly, it is sufficient to match the elastic restoring force on the flap of the new wing on its location, shape and dimensions. There is no need to provide an actuator for the flap and also no control for such an actuator.

In the DE 102010041111 a wing for a wind turbine is described. The gist of the invention is that at least one aerodynamic element is mounted on the surface of the wing by means of a pivot joint, and that the aerodynamic element is so arranged and designed on the surface of the wing that the aerodynamic element is driven solely by the force of a flow the surface of the wing pivots automatically at a predetermined flow. In this way, advantageously, the enlargement of a detachment zone on the wing can be reduced or completely prevented, especially at steeper angles of attack. The aerodynamic element is hereby a passive aeroelastic return flow flap. Disadvantage is in reality a flutter of the return flap, which can also produce noise and is a lifetime problem.

In the JP2004183640 a wing for a wind turbine is described which has an active flaps with a arranged on the wing bottom return flap, which increases the buoyancy and thereby the energy efficiency. Furthermore, the breakage of the wing is prevented in strong winds. Disadvantage here is the use of movable flaps that firstly must be very elastic and are maintenance-intensive (experience from the aircraft industry). Furthermore, these moving parts of the flap are very expensive to produce. The icing problem is also present.

In the US7293959B2 / EP1623111B1 a wing is described consisting of an active elastic (brake) flap (for buoyancy reduction only) and an activation device for a wind turbine, which forms part of a buoyancy control device. By means of wind measurement and wind wing load measurement, the buoyancy control device can control and advantageously influence the return flow flaps. Disadvantage of this solution is that the advantages of the passive return flap can not be used by their aerodynamic self-regulation and in particular the lift increase and energy efficiency improvement.

OBJECT OF THE INVENTION

• a) Luftfahrzeugen durch höheren Flügelauftrieb (zumindest bei Hochauftriebssituationen wie Start und Landung)

sowie bei hohen Fluid-/Windgeschwindigkeiten durch Auftriebsverringerung/Bremswirkung durch eine höhere Verfügbarkeit des Luftfahrzeuges, zu verbessern.The invention is based on the object, the energy efficiency of aerodynamic / hydrodynamic bodies, in particular

• a) Aircraft due to higher wing lift (at least in high-lift situations such as take-off and landing)

and at high fluid / wind speeds by increasing the lift / braking effect by increasing the availability of the aircraft.

The invention is also based on the object, if necessary simultaneously show a safety device on a wing, in which by reducing the gust vulnerability of the wing, in particular strong wind, by an active operated return flap with z. B. slowly increasing braking effect. If necessary, this can also react quickly, so that it can be compensated for individual gusts, even in this way. Furthermore, a multifunctional flap / flap is provided which additionally can compensate / dampen different modes of vibration of the wind turbine / wing by means of an active return flap by means of actuators and / or by means of inertia elements (weights). This can lead to an increased life of components and the wind turbine itself. Furthermore, this can proactively, at least partially eliminate snow and ice. The embodiments according to the invention can in particular be retrofitted and in many variants require no major changes to the aircraft. This can also with noise reducing measures on the buoyancy and / or base element after the St. d. T. such. B. a toothing can be combined. The base element may in this case assume a reinforcing function of the return flow flap and / or the wing / wing. In addition, the device according to the invention in the form of a wing with a passive and / or active flap system has to improve the yield at least in the areas of improvement A and / or B and / or C and / or D, in the form of a fluid-inflatable (inflatable ) Actuator element, and possibly a flap if necessary very easy to retrofit and / or attachable and / or interchangeable,
functioning as a system of increasing the stiffness and / or travel of the flap, and / or system having a long service life and retrofitting capability, and / or a wing-reinforcing base element and / or lightning protection, and / or noise-reducing buoyancy and / or base element, and / or Vibration damping system with at least one vibration-damping element, and / or storm protection / Overspeed protection, and / or traction help in light wind, and / or Overspeedschutz and / or vibration damping system by means of at least one buoyancy-reducing buoyancy element and possibly with closable pressure equalization openings and / or ice and snow Removal system, can be used,
characterized in that means for increasing the stiffness of the flap and / or means are used for travel limitation, and that, the travel limit the opening angle of the flap of <90 degrees, preferably <75 degrees, most preferably <60 degrees, limited and that at least one actuator Element and / or a component thereof with a fluid fillable (inflatable), and this can be folded at least simultaneously in the initial state.

The object of the invention is also to take advantage of the advantageous properties of existing techniques (St. D. T. a return flap on a wing in order to obtain an overall optimal design due to requirements, especially in wind turbines, the invention.

SOLUTION

The object of the invention is to demonstrate a return flow flap on a wing, in which the lift is further increased and / or the minimum speed is reduced, in particular by reducing and / or acting on the end edge separation vortex. Further, by providing a passive passive recirculation damper combination, a precautionary / avoidive response to an impending gust situation as a safety system or part of a safety system is made possible. This can be done well in a period of a few seconds / minutes with appropriate reaction times of the active backflow valve. In addition, an easy-to-operate active return flap is shown with a braking effect. The combination of an active and passive return valve allows a multifunctional flap / flap system with the possibility to compensate / dampen various vibrations of the wing, especially in the stable mode and in the overspeed area.

DESCRIPTION OF THE INVENTION

Area of application: The devices and methods according to the invention can be used in all aerodynamic and / or hydrodynamic objects, preferably wings of vehicles, in particular in aircraft. In general, it should be distinguished that an embodiment designated as a reflux flap is suitable for higher angles of attack Alpha (FIG. 17 ) of the wing to produce a higher lift coefficient C _A than with a conventional wing. The return flow flaps ( 8th . 9 . 10 ) are suitable, by displacement of the Endkantenwirbels ( 1 ) even to produce an even higher lift coefficient C _A. In general, such return valves ( 8th . 9 . 10 ) in an active form with an actuator element ( 22 ) also suitable for higher speeds and small wing angle alpha than Used to brake flap. In 1 are the areas of improvement / potentials A, B, C, D shown in a diagram with a typical curve, which represents the wind speed on the X-axis and the Y-axis output of the wind turbine, which in the inventive variants of the invention for carrying can come, that can have a favorable energy efficiency. The hitherto known return flaps in aviation have a fixed or flexible flap and a second component to a joint. Furthermore, if necessary stop / Wegbegrenzungsmittel be used by means of cords or bends. This may result in techniques after St. d. T. the rear detachment vertebrae, here as end edge detachment vertebrae ( 1 ), under the return flap ( 4 ) after St. d. T. in the size shown above the profile end edge ( 6 ) of the wing profile ( 3 ) with the angle of attack Alpha ( 17 ) train ( 2 ). The flap area delineation ( 21 ) = Limit of the range of action of the Endkanten-Ablösewirbels is there seen. In 3 is computational 3D simulation of the return flow visible.

4 in the variations a, b, c: In general, all variants of the inventive backflow flaps ( 8th . 9 . 10 ) the property that these with the aerodynamic or hydrodynamic body, in particular wings, at least partially a displacement of the flap area delineation ( 21 ) through the return flap ( 8th . 9 . 10 ) and their demarcation component (s) ( 5 ) in the case of partial and / or complete installation of the return flap ( 8th . 9 . 10 ) so that thereby the end edge release vortices ( 1 ) and / or flap detachment vertebrae ( 2 ) is / are influenced. The left edge (position) of the end edge separation vortex ( 1 ) corresponds to the flap area delineation ( 21 ). The flap area delineation ( 21 ) of the inventive return flap ( 8th . 9 . 10 ) shifts, as it were, from the area of the return flap ( 4 ) to St. d. T. by their spatial extent / effect of the inventive Rückströmklappe ( 8th . 9 . 10 ) from left to right, towards the profile end edge ( 6 ) or in extreme cases even beyond. Furthermore, the inventive backflow flap ( 8th . 9 . 10 ), due to their additional components, higher relative rigidity and a higher damping of vibrations, since the fluid, preferably gas, such as air, of the actuator element ( 22 ) also acts vibration-damping. This inventive novelty then also results in a higher lift coefficient C _A than in a return flow flap ( 4 ) to St. d. T. Here, the flap area delineation ( 21 ) Completely ( 5 ) to or over the profile end edge ( 6 ) or only partially to the left in front of the profile end edge ( 6 ) ( 5 ). This creates a more or less large distance between flap-Ablösewirbel ( 2 ) and the end edge separation vortices ( 1 ), which at a return flap ( 4 ) after St. d. T. only the thickness of the Rückströmklappen material ( 4 ) having. Already the partial shift of the flap area delineation ( 21 ) ( 5 ) leads to a displacement (position) and / or reduction of the end edge separation vortex ( 1 ) and / or flap detachment vertebrae ( 2 ) which leads to an increase in lift (lift coefficient C _A ) and / or resistance reduction. Thus, in comparison to a return flap ( 4 ) after St. d. T. not only 2 pressure areas in front of and behind the return flow flap ( 4 ), but 3 pressure ranges before, in the actuator / Rückströmklappe (Active: pressure of the fluid / Gasfüllbereiches ( 14 ) or passive: Ambient pressure at the (openings of eg a passive parallelogram return flap ( 10 )) and behind the return flap ( 8th . 9 . 10 ).

In 4 is the complete displacement of the valve area boundary ( 21 ) by the demarcation component ( 5 ) in an erected state exemplified on a (a) triangular ( 8th ) and (b) parallelogram-shaped ( 9 ) and (c) circular segment-shaped ( 10 ) Return flap. In this case, this return flow flap ( 8th . 9 . 10 ) at least from the flap ( 4 ) and the demarcation component ( 5 ) and a joint ( 7 ) be formed. In addition, this may consist of the bearing surface / connection point ( 16 ) and / or parallelogram or triangular or circular segment (area) shaped demarcation components ( 5 ) consist. This bearing surface / connection point ( 16 ) be arranged opposite to the flow direction in front of the return flow flap ( 7 ). This bearing surface / connection point ( 16 ) as in 17 and 18 from a base element projecting beyond the end edge ( 23 ) and a fastening means ( 27 ) consist. In principle, the backflow flap according to the invention ( 8th . 9 . 10 ) Be made of several of these components, as well as polygon.

Prerequisite as for the return valve after St. d. T. is that this is itself movable and / or movable attached.

Furthermore, this is done by the joints ( 7 ), preferably of elastic materials ( 11 ) such. As films or textiles or adhesive tapes, Klettverscgluss, preferably textile or fiber reinforced adhesive tapes. In particular textile fiber, glass or aramid fiber joints are very durable and smooth. In particular, the weather resistance with respect to UV radiation plays an important role here for the lifetime. Also, conventional hinges, joints, such. As piano bands or ball joints, or other thin-walled elastic materials are used. There are materials for the return flap / flap with a thickness of max. 4 mm, preferably with max. 2 mm thickness and most preferably with max. 1 mm Thickness for use. The materials used here must also be weather-resistant and reasonably light. Here are preferably lightweight materials such as aluminum, plastics, GRP, CFRP, aramid or Basaltfaserverstärkte plastics are used, wherein the plastic matrix, preferably a high weather resistance as z. B. PMMA, and at the same time simply warm moldable / deformable / thermoformable. In particular, textiles in woven, knitted, knitted and nonwoven form can be used here. This also edge stiffeners and / or beads and / or hinges can be easily realized on the return flap. Also, a kind of wing scissors for attachment in a particular area, by z. B. clamping and / or friction forces (anti-slip material / mat) are releasably secured again. This can then be used as a base element for z. B. the in 19 - 21 variants described, in particular used for retrofitting. The outer shape of the return flap / flap can conventionally be in a rectangular shape, but preferably due to the rotational flow (oblique flow on the profile) on the wing of the wind turbine a parallelogram-shaped outer contour (top view in the folded state). This can then preferably still 2 or 3 dimensionally deformed / curved to fit optimally to the profile. This curvature can preferably be so strong that the return flap module can be applied to the largest possible areas of the wing (due to the curvature of the profile) (also so that the hose fits well below it, with parallelogram-shaped return flap without additional hose only a slight Warping makes sense for this to be on the profile), since this slight to moderate warping at speeds above V _{nominal has} little aerodynamic influence. (At the prevailing profile accuracies at several cm deviations of the profile thickness in the construction of the wind turbine wings this plays a minor role, since the system from V _nominal = 8-12 m / sec brings their full performance and then usually on the pitch Control / regulation of the angle of attack is gradually reduced with higher wind speed, until shutdown at V _MaxNormal at usually 25 m / sec). In very safe systems, a double-walled hose or the combination of the closed parallelogram-shaped return flap and an internal hose can be used, resulting in a redundant and diverse, and thus very high security. Also, a magneto-rheological actuator could be combined with a pneumatic emergency actuation system. The control of actuation of actuator elements ( 22 ) can be realized via known sensor technology in wired or wireless form. Preferably, an optical camera system is used, which controls all return valves on one wing and, if necessary, simultaneously monitors the wing / wing loading.

The return flap ( 4 . 8th . 9 . 10 ) can be controlled by means for path limitation ( 26 ) z. B. by ropes, rubber, wires, rods, levers, bands, nets, springs, walls, foils, folding elements have stops (especially lateral) for a travel limit. Also, the travel limit can be made by the actuator itself by the return flap is attached thereto or integrated. In this case, the actuator element ( 22 ) be significantly smaller than the return valve to z. B. cause a braking effect of the return flap in strong winds. The generation of the corresponding forces then takes place via the hydraulic or pneumatic or magneto-rheological pressure in the actuator element ( 22 ) and its lever arm translation to the flap, which is exposed to the dynamic pressure of the return flap. Also, the back pressure can be used as a sensor size for the pressure actuation / control / regulation.

The bearing surface / joint / n ( 16 ) of the return flap to the wing are in 6c and 7 exemplified and can, for. B. by large-area bonding very durable, in particular also subsequently, even removable, safe to be realized (Resolutable adhesives, eg., Under the effect of temperature or electromagnetic fields as they are used, for example, in the automotive industry). The bearing surface / joint / n ( 16 ) of the return flow flap can also be used as a basic element ( 23 ), from a contact surface of 5% of the return flap surface, in particular from a contact surface of 10% of the return flap surface, very special from a contact surface of 20% of the return flap surface, preferably from a contact surface of 30% of the return flap surface. Furthermore, this can also be done in front of the return flow flap ( 4 . 8th . 9 . 10 ), as occurs during subsequent attachment an elevation, which as in 7 illustrated, optionally in combination with the oblique or curved flow-favorable flap transition ( 20 ) from z. B. a resilient material ( 12 ) can be realized. Another alternative is the attachment directly to the joint ( 7 ) (eg screwing, riveting, gluing) or z. B. elastic joint itself by means of high-performance adhesive tapes.

In 5 is the partial displacement of the flap area delineation ( 21 ) by the demarcation component / e ( 5 ) in an erected state exemplified on a triangular ( 8th ) and kreissegment-shaped ( 9 ) and parallelogram-shaped ( 10 ) Return flap. It can be seen that here the end edge separation vortices ( 1 ) in its position in the direction of the profile end edge ( 6 ) is shifted. This results in the aero / hydrodynamic advantages of increasing the lift and / or reducing the minimum speed (for the flow of the approach to the Wind turbine to produce sufficient lift for start-up). This results in part of the improvements in energy efficiency, especially in the areas of improvement A + B ( 1 ) due to the increase in the lift coefficient C _A. Also, the demarcation component may only allow for temporary / situational delineation of the end edge detachment vertebrae and / or valve detachment vertebrae ( 2 ) in the form of a roller blind and / or blind and / or shutter.

In 6 is the complete displacement of the valve area boundary ( 21 ) by the demarcation component ( 5 ) in the closed state at a profile end edge ( 6 ) exemplified on a triangular ( 8th ) and kreissegment-shaped ( 9 ) and parallelogram-shaped ( 10 ) Return flap. The flow and the return flow flaps are at small angles of incidence α ( 17 ), which occur at higher speeds, on the profile, as it does with the return valves after the St. d. T. is known.

The area delineation by the delimitation component ( 5 ) as well as all components of the return flow flap ( 4 . 8th . 9 . 10 ) can also be made of fluid-permeable materials with small (micro) or larger openings (macro), such. As toothed plate, perforated films, slit films or fabrics or nonwovens or plates, as well as in the form of gratings and nets. The effect achieved by a better / smaller hysteresis of the return flow flaps, can also be done by channels due to embossing / punching. Also known vapor-permeable materials, such as those used in the construction or clothing sector, which are correspondingly weather-resistant and durable, can be used here. Also called flutter valves (primitive valves that open and close by air pressure differences) can be used. Furthermore, for this purpose, active or passive articulated rods or levers, possibly in addition, for the displacement of the flap range demarcation ( 21 ) are used. Furthermore, flap areas in the longitudinal direction of the wing (from wing root to wing edge arch) with known techniques of rowing, possibly additionally demarcated, z. B. with winglets, flow straightener, flow divider, turbulators such. As vortex turbulators or spiral turbulators.

The material for the return flow flaps consists z. B. made of flexible and / or elastic thin materials z. As of films made of metal, in particular with stiffening / embossing, Völbstruktur as stiffening and preferably made of plastic, very particularly preferably Kunstatffe, very light and stiff fiber-reinforced plastics made of GRP, CFRP, basalt, aramid fiber reinforced. As a result, flexible and stiff return valves can be formed. Due to the rigidity or partial flexibility, vibrations of the return flap are suppressed or damped and a low adjustment hysteresis is achieved. Also, metal and / or plastic materials z. B. with small-scale (mm to several cm large honeycomb structures) and large-scale (Flügelwölbung) camber structures are used as stiffeners with. This is a very material efficient way of saving material and increasing rigidity. In the case of highly elastic return flow flaps, this rigidity is correspondingly lower, which may be advantageous in the edge region of the return flow flap (see 11 and 12 ). Also, a return flap ( 4 . 8th . 9 . 10 ) be designed so that the material thickness z. B. wedge-shaped decreases to increase the flexibility in the edge area outside. This can of course also be stepped.

In 7 the exemplary combination of several return valves is shown. Here are return flow flaps ( 4 ) according to the prior art with a parallelogram-shaped return flow flap according to the invention ( 10 ) combined at a profile end edge shown. There is the free combination option such. B. the attachment of the joint to the wing ( 16 ) of the return flow flaps ( 4 ) according to the prior art on the parallelogram-shaped passive backflow flap according to the invention ( 10 ). Furthermore, the parallelogram-shaped return flap ( 10 ) made of a resilient material ( 12 ) include and / or exist, which z. B. the parallelogram-shaped return flap ( 10 ) returns to the closed position by spring force. This can also be done vice versa and the parallelogram-shaped return flap ( 10 ) is kept closed only by means of negative pressure and raises again by ventilation by spring force. This is z. B. for a control and / or emergency operation conceivable in which the parallelogram-shaped return flap ( 10 ) is permanently installed (Special stall operation of the wind turbine with return flap ( 8th . 9 . 10 )). Here is a reduced noise compared with wind turbines with stable operation / regulation. A corresponding variable control / regulation of the return flow flap ( 8th . 9 . 10 ) is described in the topic Overspeed-Control.

In 8th the exemplary combination of several return valves is shown. Here are return flow flaps ( 4 ) according to the prior art with a parallelogram-shaped return flow flap according to the invention ( 10 ) combined at a profile end edge shown. Here is also the application of a more flexible end edge of the return flap ( 4 . 8th . 9 . 10 ) possible. Also, the components of the return flap ( 4 . 8th . 9 . 10 ), in particular this end edge slotted, jagged, serrated, wavy or otherwise altered to positively influence the flow (also bionic effects such as aerodynamically favorable sharkskin structure). This can positively influence the aerodynamics and also the flutter / vibration inclination of the flaps.

Furthermore, in 8th an actuator for active actuation of the return flap ( 10 ), z. B. shown in the form of a hydraulic or pneumatic cylinder. In principle, any form of an actuator, for. As mechanical (levers, ropes, gears, timing belt) and / or electrical (linear or rotary electric motor, e-Magente, piezo actuators) and / or pneumatic / hydraulic (cylinder, pneumatic-muscles, hoses, balloons, Pillow) find application. Preferably, however, is the advantageous embodiment of the hydraulically or pneumatically or magneto-rheologically actuated actuator element ( 22 ) in the form of a, preferably foldable hose ( 13 ). In this way, in addition to the targeted lift increase, the lift-reducing and / or resistance-generating and / or braking variants of the return flow flap can also be realized in the form of a brake flap (in particular at smaller angles of incidence). 17 )). This comes especially at high fluid / wind speeds z. B. for braking the wing against overload in the context of a security system for the application (improvement area D, 1 ). This can be achieved by shorter shutdown in strong winds such as in particular z. B. in offshore, coastal and mountain near onshore wind turbines can be achieved. This increases the annual energy yield. and this improves energy efficiency.

Further, by providing a passive passive recirculation damper combination, a precautionary / avoidive response to an impending gust situation as a safety system or part of a safety system is made possible. This can be done with appropriate reaction times of the active backflow flap ( 8th . 9 . 10 ) Depending on the actuator type and design in a period of time in fractions of seconds or preferably a few seconds and in z. B. predictive actuation cases in minutes. A reset of the active return flap may take longer depending on the type of actuation and target (system-optimized technology). Preferably, however, is the advantageous embodiment of the hydraulically or pneumatically or magneto-rheologically actuated actuator element ( 22 ) in the form of a, preferably foldable hose ( 13 ). The passive return flap ( 4 . 8th . 9 . 10 ) reacts to changes in the angle of incidence of the currents, in particular by gusts that lead to high angles of attack, relatively quickly within a few seconds / second fractions. Exemplary variants of the active backflow flap ( 8th . 9 . 10 ) are in 9 . 10 . 11 . 12 shown. These can also z. B. by fluid / air supply through the fluid flow (back pressure) without external energy z. B. be activated by means of air inlets in the flow direction. It is equally conceivable that their deactivation by vacuum-generating nozzles / tubes such. B. the Venturi nozzle, Prandl tube, Reichman nozzle, Brunswick nozzle, Pitot tube through the ambient air flow. This has the advantage that no external energy is necessary and thus only a fluid-speed measurement a relatively simple triggering of the establishment of the return flap ( 8th . 9 . 10 ) is necessary by known techniques. This could be done with foresight, since the setup time will take a bit more time due to slightly increased dynamic pressure (a hysteresis between setting up and creating seems to make sense). When from a z. B. fluid overpressure or. Vacuum reservoir supplied actuator this can be done comparatively very quickly.

9 shows a backflow flap according to the prior art ( 4 ) combined with a demarcation component ( 5 ) in the form, for. B. a balloon or hose or cushion ( 13 ), which is actuated simultaneously as an actuator hydraulically or pneumatically or magneto-rheologically and thereby to an active return flap ( 8th . 9 . 10 ) becomes. The fluid / gas filling area ( 14 ) is hatched here. A fluid / gas compound ( 18 ) with z. B. air can be filled z. B. in subsequent cultivation via a hose z. B. at the profile / wing end edge ( 6 ) Flow and cost appropriate. Also, a connection within the wing may serve to carry out the fluid supply. In principle, the demarcation component can be designed as desired.

10 shows a triangular-shaped return flap ( 8th ) which z. B. an aforementioned hose ( 13 ) has been incorporated as an active actuator.

11 shows a triangular-shaped return flap ( 8th ) which z. B. in its three-dimensional design is completely closed to a fluid / gas connection ( 18 ) with z. B. air to be filled and thereby acts as an actuator itself. Also here can be a corresponding z. B. triangular shaped or folded tube are used. This is a very simple and safe actuator.

12 shows a parallelogram-shaped return flap ( 8th ) which z. B. is completely closed in its three-dimensional design to a fluid / gas connection ( 18 ) with z. B. air to be filled and thereby acts as an actuator itself. Also here a corresponding parallelogram or round or flat shaped or folded hose (especially at the ends) can be used. Here is also the integrated combination with a flexible fixed to the parallelogram-shaped return flap ( 8th ) attached Return flap ( 4 ) shown in the prior art, which can be at the same time by their direct attachment with erecting when active actuation.

13 Surprisingly Advantageous, is a particularly preferred and simple embodiment of the return flap ( 10 ), in particular active backflow flap according to the invention ( 10 ), which only by a flattened and / or folded, in particular closed hose ( 13 ) is formed. By inflating the plastic tube, z. B. at one end via a fluid / gas connection ( 18 ) this hose ( 13 ) similar to a parallelogram-shaped return flap ( 10 ) on. Thus, this hose is at the same time flap, limiting component ( 5 ) and Aktutor ( 22 ). This is particularly advantageous for cost-effective retrofitting z. B for wind turbines. In a fixed position, this or similar embodiment can also be used as a turbulator / vortex generator. This can be z. B. by the back pressure of the flow at higher speeds in height and thus easily adapt in its intensity of the small-vortex generation, thus enabling the desired small-turbulence generation at lower speeds. In principle, other actuators such as levers and rods, electromagnets, steering gear drives (eg model construction) can also be used for this purpose. The magneto-rheological actuator variant is also interesting here, because if you use the electromagnetic field generator on the hose ( 13 ) or even integrated, this would be very easy to retrofit by applying to the wing / wing. It is also conceivable to erect a somewhat stiffer outer and larger tube through a smaller actuator tube, so that the outer and larger tube acts as a return flow flap (approximately parallelogram-shaped). It is also conceivable that this aforementioned outer and larger hose is composed of 2 curved half-shells and z. B. residual stress and thus resilient, the approximate parallelogram-shaped form assumes as a return flow flap and is brought by negative pressure in a flat, possibly slightly curved shape.

14 shows a return flap ( 8th . 9 . 10 ), in particular active backflow flap according to the invention ( 8th . 9 . 10 ), to improve the braking effect, this with a fluid / gas compound ( 18 ) are connected between wing top and wing bottom. This has the consequence that the higher pressure from the bottom with the lower pressure of the wing / profile top at least partially compensates and thereby the buoyancy is greatly reduced. This effect is known in Schempp-Hirt-brake flaps, which can be mounted on the wing top and bottom and require a complete penetration of the wing. This above-mentioned penetration is a strong weakening of the wing construction and must be compensated by costly and expensive construction / construction technique. With the inventive active backflow flap ( 8th . 9 . 10 ), this serious disadvantage can be avoided by using this fluid / gas compound ( 18 ) through the closed return flap ( 8th . 9 . 10 ) is closed (ineffective) and only when the return flap ( 8th . 9 . 10 ) is activated and makes this advantage usable. In particular, selectively designed / arranged fluid / gas compounds ( 18 ) lead to a small weakening of the wing construction. These can be like the return flap ( 8th . 9 . 10 ) yourself arbitrarily, such. B. in one or more rows under the closed return flap ( 8th . 9 . 10 ) can be arranged. It is also conceivable that the profile top with the profile end edge ( 6 ) by the fluid / gas compound ( 18 ) is connected. Preferably, a base element attached to the end edge (FIG. 23 ) are used, on the one hand, the return flap ( 4 . 8th . 9 . 10 ) with a hinge or elastic hinge ( 7 . 11 ) and, second, to provide a large attachment surface with end edge reinforcing properties. It could possibly also include the fluid / gas connections ( 18 ) with marked / attached. Also, this fluid / gas compound ( 18 ) lead from the wing top only in the hollow wing interior, which possibly with a central opening elsewhere to the outside, z. B. edge bow, is provided to achieve this pressure equalization effect.

15 shows the exemplary arrangements / positions of the passive and / or active return valves ( 4 . 8th . 9 . 10 ). In particular, the arrangement in the region of the profile end edge at the top or bottom ( 6 ) for increasing buoyancy and the area of greatest profile thickness ( 19 ), especially for use with braking / buoyancy reduction / resistance increase is advantageous. Also, the passive and / or active return flap ( 4 . 8th . 9 . 10 ) in the wing profile ( 3 ) be integrated so that no flap transition ( 20 ) in the form of a slope or curve is required (Spaltarm / -frei). Due to the small thickness of the passive and / or active return valves ( 4 . 8th . 9 . 10 ) is an integration without significant penetration of the shell / sandwich structure of the wing ( 3 ) as a rule feasible. The flap transition ( 20 ) is preferably realized aerodynamically advantageous with an elastic, slightly curved plastic band.

• a) Fluid-Strömungs-Geschwindigkeitsmessung im Umfeld des Flügels und/oder
• b) direkte und/oder indirekte Flügel-Belastungsmessung erfolgt,
• c) um dadurch eine aktive und/oder passive Strömungsbeeinflussung des Aero- oder Hydrodynamischen Körpers (3), insbesondere des Flügels (3) zu Steuern und/oder zu Regeln.

There is also a new method of a safety system for avoiding hazardous operating conditions and / or resource / energy efficiency improvement system for influencing the flow of an aerodynamic or hydrodynamic body ( 3 ), in particular of buoyancy wings equipped aircraft (eg aircraft) according to the principle of a return flap ( 4 . 8th . 9 . 10 ) which allows one

• a) fluid flow velocity measurement in the vicinity of the wing and / or
• b) direct and / or indirect wing load measurement takes place,
• c) in order thereby to actively and / or passively influence the flow of the aerodynamic or hydrodynamic body ( 3 ), in particular the wing ( 3 ) on taxes and / or rules.

• a) Fluid-Strömungs-Geschwindigkeitsmessung im Umfeld des Flügels und/oder
• b) direkte und/oder indirekte Flügel-Belastungsmessung erfolgt, und/oder
• c) um dadurch eine aktive und/oder passive Strömungsbeeinflussung zu Steuern und/oder zu Regeln. Dies kann z. B. durch Rückstromklappen und/oder Spoiler/Klappen und/oder Bremssysteme (z. B. Bremsschirme und/oder Bremsklappen und/oder Über- und Unterdruck-Ausgleichenden Systemen) des Flügels (3) erfolgen

There is also a new method of a safety system for avoiding hazardous operating conditions and / or resource / energy efficiency improvement system for influencing the flow of an aerodynamic or hydrodynamic body ( 3 ), in particular of turbines equipped with buoyancy wings (eg aircraft), according to the principle of a return flow flap ( 4 . 8th . 9 . 10 ) which allows one

• a) fluid flow velocity measurement in the vicinity of the wing and / or
• b) direct and / or indirect wing load measurement takes place, and / or
• c) to thereby control and / or regulate an active and / or passive flow influencing. This can be z. By return valves and / or spoilers / flaps and / or brake systems (eg brake screens and / or brake flaps and / or overpressure and underpressure compensating systems) of the wing ( 3 ) respectively

• a) Fluid-Strömungs-Geschwindigkeitsmessung im Umfeld des Flügels und/oder
• b) direkte und/oder indirekte Flügel-Belastungsmessung erfolgt,
• c) Messsysteme zur Erkennung weiterer Gefahren-Betriebszuständen
• d) um dadurch eine aktive und/oder passive Strömungsbeeinflussung durch Rückstromklappen und/oder Spoiler/Klappen und/oder Bremssysteme (Bremsschirme und/oder Bremsklappen und/oder Über- und Unterdruck-Ausgleichenden Systemen) des Flügels (3) zu Steuern und/oder zu Regeln.

There is also a new method of a safety system for avoiding hazardous operating conditions and / or resource / energy efficiency improvement system for influencing the flow of an aerodynamic or hydrodynamic body ( 3 ), in particular of turbines equipped with buoyancy wings (eg aircraft), according to the principle of a return flow flap ( 4 . 8th . 9 . 10 ) which allows one

• a) fluid flow velocity measurement in the vicinity of the wing and / or
• b) direct and / or indirect wing load measurement takes place,
• c) measuring systems for the detection of further danger operating conditions
• d) thereby active and / or passive flow control by return valves and / or spoiler / flaps and / or braking systems (brake screens and / or airbrakes and / or overpressure and negative pressure compensating systems) of the wing ( 3 ) on taxes and / or rules.

• a) Strömungs-Geschwindigkeitsmessung im Umfeld des Flügels mittels mindestens einem Kamerasystem und/oder
• b) direkte und/oder indirekte Flügel-Belastungsmessung mittels mindestens einem Kamerasystem pro Flügel (3) erfolgt,
• c) Messsysteme zur Erkennung weiterer Gefahren-Betriebszuständen
• d) um dadurch eine aktive und/oder passive Strömungsbeeinflussung durch Rückstromklappen und/oder Spoiler/Klappen und/oder Bremssysteme (Bremsschirme und/oder Bremsklappen und/oder Über- und Unterdruck-Ausgleichenden Systemen) des Flügels (3) zu Steuern und/oder zu Regeln.

Method of a safety system for avoiding hazardous operating states and / or resource efficiency improvement system for influencing the flow of an aerodynamic or hydrodynamic body (10), in particular of turbines equipped with buoyancy wings (eg aircraft), according to the principle of a return flow flap ( 4 ), characterized in that a

• a) flow velocity measurement in the vicinity of the wing by means of at least one camera system and / or
• b) direct and / or indirect wing load measurement by means of at least one camera system per wing ( 3 ) he follows,
• c) measuring systems for the detection of further danger operating conditions
• d) thereby active and / or passive flow control by return valves and / or spoiler / flaps and / or braking systems (brake screens and / or airbrakes and / or overpressure and negative pressure compensating systems) of the wing ( 3 ) on taxes and / or rules.

• 1) Belastungs-Zustand des Flügels durch Verformung (Biegung, Verdrehung, Schwingungen, Materialspannungen, Klappen-Stand/-Zustand, Unter- und Überdruckmessung): a) Dehnungsmessung mittels Dehn-Messstreifen oder LWL-Fasern b) Verformungsmessung mittels Kamera und/oder Laserpunkten/Linien/Liniengittern und/oder Markierungen z. B Punkten/Bauteilen/Prismen für die Oberflächen-Vermessung, Entfernungsmessung c) Schwingungs- und Oberflächenwellenmessung d) Kraftmessung mittels Kraftsensoren e) Drucksensoren
• 2) Witterungszustand: Vereisung, Schnee, Regen, Nebel, Hagel, Verwirbelung, Temperatur, Luftfeuchtigkeit/Taupunkt, Wolken/-höhe, Sonneneinstrahlung a) Kamera-Messsysteme, insbesondere Intelligente Kameras oder Webcams b) mechanische und elektronische Wind- und/oder Wetter-Messsysteme (Lidar, Sodar, Radar, Ultraschall, Unterdruckdüsen mit Drucksensoren, mechanisch, u. a.)
• 3) Anlagen- und/oder Flügelzustand bzgl. Beschädigungen, Verschmutzung, Verschleiß, Alterung: a) Ultraschall-Messysteme b) Radar-Messysteme c) Kameras, insbesondere auch IR-Kameras und/oder Lasermesssysteme für die Oberflächen-Vermessung d) Schwingungs-Messsysteme e) Oberflächenwellen-Messsysteme

Hazardous operating states can be disruptions or other relevant influences on the system. The following exemplary measuring systems for recognizing further exemplary hazard operating states are applicable:

• 1) Loading condition of the sash due to deformation (bending, torsion, vibrations, material tensions, flap state / condition, under- and overpressure measurement): a) Strain measurement by means of strain gauges or fiber optic fibers b) Deformation measurement by means of camera and / or Laser points / lines / line grids and / or markings z. B points / components / prisms for surface measurement, distance measurement c) vibration and surface wave measurement d) force measurement using force sensors e) pressure sensors
• 2) Weather conditions: icing, snow, rain, fog, hail, turbulence, temperature, humidity / dew point, clouds / altitude, solar radiation a) camera measuring systems, especially intelligent cameras or webcams b) mechanical and electronic wind and / or weather Measuring systems (lidar, sodar, radar, ultrasound, vacuum nozzles with pressure sensors, mechanical, etc.)
• 3) System and / or wing condition with regard to damage, dirt, wear, aging: a) Ultrasonic measuring systems b) Radar measuring systems c) Cameras, in particular also IR cameras and / or laser measuring systems for surface measurement d) Vibration Measuring systems e) Surface wave measuring systems

The measuring systems can in particular by fixed and / or moving / moving Mounts (eg wing scissors, winglets, wires, strips, profiles) on the wing ( 3 ) and / or on the spinner (wing nose) and / or mast and / or ground and / or moved, in particular along the wing ( 3 ) become. The movement can be done by common actuators. The speed measurement of the fluid / air / wind can directly z. B. done directly or with a small distance (environment) to the wing. Preferably, however, the measurement is at least one point of the wind power and / or wind farm, most preferably at least 3 points of the wind farm. The positions of the return flow flaps can also be determined by means of one of these measuring systems, and from this also hazard states can be derived and warnings can be forwarded therefrom. In general, a mechanical visual and / or, wired and / or wireless communication are applicable for this purpose.

In 16 is a preferred embodiment of the active parallelogram return valve ( 10 ) on the wing top, to improve noise reduction with St. d. T-methods with a noise-reducing buoyancy element ( 25 ) with basic element ( 23 ) for attachment to the wing ( 3 ). The basic element ( 23 ) is with the example in this case toothed parallelogram return valve ( 10 ) via an elastic hinge ( 11 ) connected. The parallelogram return flap ( 10 ) is designed so that it acts as an actuator by this includes a foldable hose, which has exactly the contours of the actuator (folded parallelogram-shaped hose). Here, the non-equilateral parallelogram is folded outwards.

In 17 is an active parallelogram return valve ( 10 ) on the wing top and bottom with integrated hose ( 13 ), to improve noise reduction with St. d. T methods with a noise-reducing base element ( 25 . 23 ) which in this example is V-shaped and pushed onto the end edge of the wing and then attached / attached. The attachment can also by spring force of the base element ( 23 ) and / or possibly frictional forces and / or adhesive forces. In addition, the attachment of the base element ( 23 ) by means of mechanically known detachable and insoluble means ( 27 ) such. B. rivets and screws, as well as by means of high-performance Velcro. In addition, the demarcation component ( 5 ) of the parallelogram return flap ( 10 ) the path boundary ( 26 ) of the parallelogram return flap ( 10 ) itself. A folded tube ( 13 ) serves as an actuator element ( 22 ). The fastening means ( 27 ) of the base element ( 23 ) is here in each case an upper side and lower surface adhesive bond to the wing ( 3 ).

In 18 is an active parallelogram return valve ( 10 ) on the bottom of the wing and the simplest variant with hose ( 8th ) and combined with St. d. T. return flap ( 4 ) on the wing top, with noise-reducing base element ( 25 . 23 ). In particular, the simplest variant on the top of the wing ( 3 ) with an actuator element ( 22 ) as a folded tube ( 13 ), which is mounted on a V-shaped base element ( 23 ) and this even on the wing ( 3 ), is very simple. On the hose or on the base element ( 23 ) is the return flow flap ( 4 ) movable on a hinge ( 11 . 7 ) attached. The damper may operate as a combined active and passive damper / flap, depending on how and where the return damper is mounted.

In 19 is a passive and active triangular reflux valve ( 8th ) (in the actuated position) with vibration damping system based on the inertia on the wing top (in one direction only), with V-shaped base elements ( 23 ) at the wing noses and wing end edge. The aim is in particular accelerations by wind gusts (storm control) at higher wind speeds from V _nominal (improvement range C + D) in the plane of the profile ( 3 ) to equalize / dampen perpendicular to the chord. This is done by the fact that at the base element ( 23 ) the wing nose a lever ( 29 ) at a joint ( 7 ) and at this lever ( 29 ) an inertia element ( 28 ) in the form of a weight, preferably an aerodynamically shaped steel or lead weight, is attached. Furthermore, the here shown simple triangular return flap ( 8th ) also with a lever ( 29 ), so that over 2 more levers ( 29 ) creates a kinematics, which equals a movable parallelogram lever system. Will the wing ( 3 ) now in the direction of the profile top moves / accelerates the inertia element ( 28 ) (Initial position in neutral position in the direction of the chord) now due to the inertia in its spatial position back and the attached lever ( 29 ) moves towards profile bottom as shown here. About the lever mechanism ( 29 ), the movement of the inertia element ( 28 ) on the triangular return valve ( 8th ), so that it moves upwards and thereby a braking effect as a brake flap with buoyancy reduction takes place. This buoyancy reduction leads to a corresponding counter-movement of the wing ( 3 ) which was generated by the gust of wind. Of course, this principle can also be applied on the other side. This very simple principle is self-regulating (possibly with a return spring mechanism) and in conjunction with the basic elements ( 23 ) this can also be retrofitted. Of course, such a solution can also be directly integrated directly into a new wind turbine.

In 20 is a passive and active parallelogram return valve ( 8th ) beyond the profile end edge with vibration damping system based on the inertia on the wing upper side (in both directions), with basic elements ( 23 ) at the wing noses and wing end edge. The aim is in particular accelerations by wind gusts (storm control) at higher wind speeds from V _nominal (improvement range C + D) in the plane of the profile ( 3 ) perpendicular to the chord (as in 19 ) and in addition to balance / dampen yawing vibrations with a direction approximately in chord. This is done as in 19 in that at the base element ( 23 ) the wing nose a lever ( 29 ) at a joint ( 7 ) and at this lever ( 29 ) an inertia element ( 28 ) in the form of a weight, preferably an aerodynamically shaped steel or lead weight, is attached. Furthermore, the parallelogram backflow flap shown here ( 10 ) also with a lever ( 29 ), so that over 2 more levers ( 29 ) creates a kinematics, which equals a movable parallelogram lever system. Will the wing ( 3 ) now in the direction of the profile top moves / accelerates the inertia element ( 28 ) (Initial position in neutral position in the direction of the chord) now due to the inertia in its spatial position back and the attached lever ( 29 ) moves towards profile bottom as shown here. About the lever mechanism ( 29 ), the movement of the inertia element ( 28 ) to the parallelogram return valve ( 10 ), so that it moves upwards and thereby a braking effect as a brake flap with buoyancy reduction takes place. This buoyancy reduction leads to a corresponding counter-movement of the wing ( 3 ) which was generated by the gust of wind. This works with appropriate design of the joints and the parallelogram return flap ( 10 ) also in the opposite direction of the acceleration through the gust of wind. To compensate for the yawing vibrations is on the long lever ( 29 ) also an inertia element ( 28 ), which remains at a leading acceleration in the direction of the profile nose in the direction of inertia to the profile end edge and thereby the parallelogram return flap ( 10 ) (Part behind the profile end edge) moves downwards and thus generates more buoyancy and also more profile resistance. As a result, there is a countermovement to the causing wind gust and a damping of this yaw movement / acceleration. Of course, this system can also be used individually or only in certain wing areas. This very simple principle is self-regulating (possibly with a return spring mechanism) and in conjunction with the basic elements ( 23 ) this can also be retrofitted. Of course, such a solution can also be directly integrated directly into a new wind turbine.

In the 19 and 20 illustrated variants of the return flow flaps invention can of course also with a normal rudder / flap (possibly additionally recognized) are combined, so that this is interesting for new wind turbines. Also, the variants can be combined with an active actuator element so that passive and active actuation can take place.

In 21 is a passive and active parallelogram return valve ( 10 ) on a rotatably mounted wing or wing part with vibration damping system on the basis of inertia on the wing top (in one direction only), with basic elements ( 23 ) at the wing noses and wing end edge. The aim is in particular accelerations by wind gusts (storm control) at higher wind speeds from V _nominal (improvement range C + D) in the plane of the profile ( 3 ) perpendicular to the chord (as in 19 ) compensate / dampen. Here, the function of the shown active triangular reflux flap ( 8th ) (in non-actuated position) quite conventionally functioning. To compensate for these vibrations is on the lever ( 29 ) an inertia element ( 28 ) attached. Will the wing ( 3 ) now in the direction of the profile top moves / accelerates the inertia element ( 28 ) (Initial position in neutral position in the direction of the chord) now due to the inertia in his Spatial position back and the here z. B. at the moment zero point of the profile / wing ( 31 ) mounted wing or wing part undergoes a moment by the inertia element ( 28 ) and therefore also remains slightly behind, which leads to a reduction in the angle of attack and thus a reduction in lift. This counteracts the gust of wind thus dampening / compensating. Due to the bearing in moment-zero point of the profile / wing ( 31 ) the buoyancy forces F _A ( 32 ) at this point unaffected. In principle, by means of an additional actuator, in particular actuator according to the invention, a kind of outer wing can additionally be actively activated / controlled / regulated. This is particularly an interesting solution for new wind turbines with long and split wings (transport advantage shorter wing parts).

In 22 is an end piece of a folded tube on the example of the bottom / tail of a Soup bag exemplified as a folded tube, z. B. can be effectively closed by friction welding, so that it permanently participates in the folding process or Entfaltvorgang under pressure and possibly negative pressure. Preference is given to a hose of composite material made of aluminum and plastic film or different plastic films with each other.

In 23 an end piece of an unfolded hose is exemplified by the example of the bottom / tail of a soup bag, such as a folded tube, e.g. B. can be effectively sealed by friction welding, so that it permanently participates in the folding process or unfolding under pressure and possibly negative pressure.

In 24 the end piece of a folded tube is exemplified by the example of the bottom / tail of a foldable beverage container with a vaulted bottom, such as a folded tube, e.g. B. can be effectively sealed by friction welding, so that it permanently participates in the folding process or unfolding under pressure and possibly negative pressure.

In 25 the tail of a unfolded hose is exemplified by the example of the bottom / tail of a foldable beverage container with a curved bottom, such as a folded tube, e.g. B. can be effectively sealed by friction welding, so that it permanently participates in the folding process or unfolding under pressure and possibly negative pressure. Also can be used as a hose end, any shaped plug, shaped element (possibly with vaulted floor), which then z. B. by gluing, shrinking, welding, etc. can be permanently closed. Also, such a plug can be conical or otherwise mechanically designed to take over its permanent sealing function. (If necessary, the connecting piece can be attached to it). Also, this plug can be aerodynamically shaped to produce little or much vortex. Also can be attached directly to a control and / or pressure control valve.

The in the 1 to 25 , especially 22 to 25 Variants shown can also be combined with the magneto-rheological actuator type. For this purpose, a magnetic field generating element is preferably in the immediate vicinity of the hose ( 13 ) to influence this. In the hose ( 13 ) is the magneto-rheological fluid or polymer, which then in the presence of the electromagnetic field, the fluid and thus the actuator element ( 22 ). This has very short reaction times in the range of fractions of seconds. The magnetic field generating element is preferably on and / or in the hose ( 13 ) attached / integrated.

• – DE102010041111A1
• – US7293959B2
• – DE102012000431A1
• – JP2004183640
• – Und die als Stand der Technik dargestellte Literatur

The following property rights and literature are part of this application and can be freely combined with their contents:

• - DE102010041111A1
• - US7293959B2
• - DE102012000431A1
• - JP2004183640
• - And the literature presented as prior art

A device in the form of a wing with a passive and / or active flap system which can be used to improve the yield at least in the areas of improvement A and / or B and / or C and / or D, which is retrofittable and / or again easily removable and has a long life,
characterized in that the wing structure by attachment by means of adhesive bond (large adhesive surface), z. B. at the base element ( 23 ), Rivet, screw, shearing, hanging, clamping or plug connection is statically not or insignificantly impaired, thereby allowing a long life of the wing and / or the wind turbine and / or the flap system, preferably> 5 years , Particularly preferably> 10 years, very particularly preferably> = 20 years and / or possibly allows easy removal / replacement. For the amortization of a z. B. Retrofit system whose life is of great importance. Payback periods of <= 4 years are common.

B + C device in the form of a wing with a passive and / or active flap system ( 8th . 9 . 10 ) which can be used to improve the yield, at least in the areas of improvement A and / or B and / or C and / or D, in the form of a fluid-inflatable (inflatable) actuator element ( 22 ), and if necessary, a flap can easily be retrofitted and / or attached and / or replaced if necessary,
characterized in that at least one actuator element ( 22 ) and / or a component thereof can be filled (inflated) with a fluid, and this at the same time can be folded at least in the initial state.

B1 device according to one of the preceding claims, characterized in that the flap itself or a hose ( 13 ) can be filled (inflated) pneumatically and / or hydraulically and / or magneto-rheologically and thereby 2-dimensional (without significant elongation of the tubing), possibly 3-dimensional (with significant elongation of the tubing), deformed and thereby the flap / Buoyancy element ( 4 . 8th . 9 . 10 ) by the actuator element ( 22 ), and in that the flap and / or actuator element consists of a triangular, parallelogram, tube or polygon, RS-flap-shaped buoyancy elements ( 4 . 8th . 9 . 10 ), and that, Flap and / or actuator element is enhanced by a macrostatics, z. B. triangular, parallelogram, hose or polygon, plan RS-flaps, camber-shaped structures, u. ä.

B3.2: Device according to one of the preceding claims with static and / or aerodynamic effect,
characterized in that, that the flap ( 4 . 8th . 9 . 10 ) and / or actuator element ( 22 ) by a microstatics is reinforced by z. As lasered, pressed, embossed, stamped, printed, etched, printed, surface structures, such. B. similar to bird feathers, as well as textile reinforcing fibers such as GRP, CFK, Kevlar, basalt, (possibly integrated) u. Ä. Such surface structures may also include small or larger channels which the Aufstellhysterese the return flap ( 4 . 8th . 9 . 10 ) positively influenced.

B3.6: Device according to one of the preceding claims with static and / or aerodynamic effect,
characterized in that the flap ( 4 . 8th . 9 . 10 ) has at least one stop means, such as. B. kevlar, wire, bands, levers, buoyancy element itself, lamella, hose, grid, bellows (preferably laterally), which limits the maximum rash. For safety reasons, the path limit is necessary for air vehicles with dangerous flight conditions and the service life.

B3.7: Device according to one of the preceding claims with static and / or aerodynamic effect,
characterized in that that the flap and / or actuator element consists of at least one buoyancy element, which consists of at least one curved or multi-curved plate (3D plate) such. B. from a blind slat o. Ä. This is for the adaptation to the profile curvature of advantage.

B2: Device according to one of the preceding claims, characterized in that the actuator element ( 22 ) can be filled and / or emptied very quickly if necessary by means of an overpressure and / or vacuum storage system. This is particularly advantageous for quick and easy fluid delivery and allows a double-acting hydraulic and / or pneumatic actuator that reacts quickly. Preferably, this overpressure and / or vacuum storage system in the wing nose / spinner / wing root on and / or. accommodated.

D: device in the form of a wing with a passive and / or active flap system which can be used to improve the yield, at least in the areas of improvement A and / or B and / or C and / or D, in the form of a wing, reinforcing base element ( 23 )
characterized in that, this by z. B. a wing trailing edge reinforcement with at least one triangular or Z or V or Nasebar or polygonal-shaped base element ( 23 ) is formed and the wing structure thereby statically reinforced (possibly repaired) and / or protects against external influences, in particular at the trailing edge and possibly at the front edge (wing nose) and possibly at certain sections of the wing / locations on leaf segments, if necessary for the attachment of vortex generators and / or other base elements and / or flaps and / or lightning protection. For V-shaped trailing edge base elements ( 23 ) can z. As a small channel with about the thickness of the trailing edge itself, are provided, which can serve for the pneumatic, hydraulic, electrical supply and / or the lightning arrester derivation. Also, the base member or parts thereof may serve as lightning protection.

E device in the form of a wing with a passive and / or active flap system which can be used to improve the yield at least in the improvement areas A and / or B and / or C and / or D, in the form of at least a noise-reducing buoyancy element and / or base element characterized in that by a flexible and / or solid shaped, in particular corrugated, serrated, serrated, bristly, perforated, most preferably slotted, thread, bird feather, finger-shaped (kinked rod or tube) and spiral-shaped ( 2 or 3D-shaped spiral) trailing edge of the buoyancy element and / or the base element (front and rear possible) and that thereby generates less noise, or as in the original state of the wing (when retrofitting). Also, such correspondingly shaped elements may be attached to complete parts of wings, in particular outer wings and / or rudders.

F: wings with a passive and / or active flap system which can be used to improve the yield at least in the areas of improvement A and / or B and / or C and / or D, and to reduce the loads on the wing and possibly hub structure and dynamic wing vibrations across the chord and (dynamic yawing vibrations) are excited parallel to the chord of the wing and can lead to considerable peak loads on the wing and can lead to material fatigue in the long term (shortened service life if necessary),
characterized in that at least one vibration damping element is applied, which takes the form of at least one active and / or passive flap and that, this wing by mass balance and / or pneumatically and / or hydraulically and / or magneto-rheologically responsive, and by at least a passive and / or active buoyancy element has a dampening effect and, as a result, if necessary, the service life of the wing and / or the wind energy plant and / or the flap system is increased.

G: device in the form of a wing with a passive and / or active flap system which can be used to improve the yield, at least in the improvement areas C and / or D, and in function of a storm protection / overspeed protection works, avoids overloading of the wings and an increase in output at speeds due to a higher strong-wind running time at higher V _Max-normal enables sufficient gust / thermal overload protection to be provided, eg at <50% of the nominal power, preferably at <70% the nominal power, more preferably <= 95% of the rated power, most preferably <= 100% of the rated power, characterized in that this is achieved by at least one lift reducing (top and possibly bottom) Flap / buoyancy element of the wing and that at about The speed V _Max-normal no cut-off takes place, but at least the top of the wind turbine, at least the top of the wind turbine, by increasing the resistance and / or buoyancy reduction, at least as far as slowed down that the rated power is not exceeded and / or overloading does not occur and / or the network stability is not disturbed and that, this actuated and / or controlled and / or regulated by actively actuated Flaps possibly also by vane and / or Zentrifugalkraft- / measurement and / or inertia / acceleration measurement and / or speed measurement. The flap can also be operated passively by inertia forces / moments, as in 19 - 21 is apparent and described.

H: device and method in the form of a wing with a passive and / or active flap system which can be used to improve the yield at least in the areas of improvement A and / or B in the function as traction help in light wind and yield improvement, by at least one buoyancy increasing buoyancy element, which significantly increases the lift coefficient and thus the energy yield at high angles of attack (up to approx. V _nominal ),
characterized in that this buoyancy element is preferably mounted on the upper side, particularly preferably on the trailing edge of the upper side of the wing and by passively and / or actively actuated Flaps pneumatically and / or hydraulically and / or magneto-rheologically actuated and / or controlled and / or and that, just prior to V _nominal, the pitch control / and / or the lift-controlling flap control can be used to control the system to maximum power, or that slightly before V _nominal the pitch control ) and the buoyancy-controlling flap control (coarse control) can be used to regulate the system to the maximum power or that just before V _nominal the pitch control (coarse control) and the lift-controlling flap control (fine control) Control) can be used to regulate the system to the maximum power.

I: device in the form of a wing with a passive and / or active flap system which can be used for improving the yield at least in the areas of improvement C and / or D in the overspeed and / or vibration damping and buoyancy-reducing buoyancy element,
characterized in that by the flap and / or buoyancy element and / or actuator ( 22 ) and / or a hose ( 13 ), openable and closable openings ( 18 ) between the overpressure leading upper side and the negative pressure leading underside, for buoyancy reduction, at least in part by means of pressure compensation, can be used that, the flap and / or actuator element ( 22 ) and / or a hose ( 13 ) and the openable and closable openings ( 18 ) and / or valves, preferably in the region of the greatest thickness of the profile ( 19 ), particularly preferably at the trailing edge of the profile / wing, are mounted. Preferably, the active actuator element ( 22 ) the revealable and closable openings ( 18 ) and / or valves.

Device and method in the form of a wing with a passive and / or active flap system which can be used for improving the yield at least in the areas of improvement A and / or B and / or C and / or D in the function of ice and snow removal system,
characterized in that by the forces and / or movement of the active flaps of the snow and / or ice extension of the wing, at least in part, possibly early proactive, removed and thus possibly at least partially avoided and that, by actively operated (raised) Flaps, which are pneumatically and / or hydraulically and / or magneto-rheologically operated and / or controlled and / or regulated, the snow and / or ice at least in part, if necessary early proactively removed and thus possibly at least partially avoided and / or that, by the at least temporarily heated base elements ( 23 ) and / or buoyancy elements and / or flaps are provided with a non-stick film or coating to reduce environmental influences such as mosquito root and damage by bird strike. It is known that just the wing nose over time by weathering experiences a rougher surface (deteriorated aerodynamics and life) and that this purpose a glued anti-adhesive film of z. As PTFE also prevents the numerous, especially in spring mosquito approach at least in part and protects the wing from weathering and bird strike and salt water atmosphere (in coastal or offshore wind turbines). This weathering protection can also be used as a basic element ( 23 ) act in which it has reinforcements in certain areas where components are attached.

K = 0 + D + H + J: device in the form of a wing with an active and / or passive flap system which can be used for improving the yield at least in the improvement areas A and / or B and / or C and / or D, and / or in the function as a system of increasing the rigidity and / or limiting the travel of the flap, and / or a wing-reinforcing base element and / or lightning protection, and / or traction help in light wind, and / or ice and snow removal system,
characterized in that means for increasing the stiffness of the flap and / or means for Wegbegrenzung are used and that, at least a portion of the flap has a high rigidity and preferably a stiffness in the form of a tensile modulus of at least 50 GPa and / or a tensile strength of at least 0.4 GPa.

L = 0 + A + D + E + F + G + H + I + J / 0: device in the form of a wing with a passive and / or active flap system which improves the yield at least in the areas of improvement A and / or B and / or C and / or D, in the function of a system for increasing the rigidity and / or limitation of the flap, and / or system having a long service life and retrofitting capability, and / or a wing-reinforcing base element and / or lightning protection, and / or noise-reducing buoyancy and / or base element, and / or vibration damping system with at least one vibration-damping element, and / or Storm protection / Overspeed protection, and / or traction help in light wind, and / or Overspeedschutz and / or vibration damping system by means of at least one buoyancy-reducing buoyancy element and possibly with closable Pressure equalization holes and / or ice and snow removal system, can be used,
characterized in that means for increasing the stiffness of the flap and / or means for travel limitation are used, and in that the travel limit the opening angle of the flap of <90 degrees, preferably <75 degrees, most preferably <60 degrees limited. The opening angle of the flap is defined so that the front and rear edge of the flap define the opening angle, which is then also possible with highly flexible or partially flexible flaps.

M = A + D + E + F + 0 + H + I + J / B or C: device in the form of a wing with a passive and / or active flap system which improves the yield at least in the areas of improvement A and / or B and / or C and / or D, in the function as a system of increasing the rigidity and / or limitation of the flap, and / or system with high durability and retrofitting capability, and / or a wing-reinforcing base element and / or lightning protection, and / or noise-reducing buoyancy and / or base element, and / or vibration damping system with at least one vibration-damping element, and / or Storm protection / Overspeed protection, and / or traction help in light wind, and / or Overspeedschutz and / or vibration damping system by means of at least one buoyancy-reducing buoyancy element and possibly with closable Pressure equalization holes and / or ice and snow removal system, can be used,
characterized in that a fluid (inflatable) and / or foldable element that can be filled with a fluid can be used, preferably a component of the actuator element or the buoyancy element itself, can be used.

N = 0 + A + D + E + F + G + H + I + J / B or C: device in the form of a wing with a passive and / or active flap system to improve the yield at least in the areas of improvement A and / or B and / or C and / or D, in the function as a system of increase in rigidity and / or travel limitation of the flap, and / or system with high life and retrofit capability, and / or a wing-reinforcing base member and / or lightning protection, and / or noise reducing Buoyancy and / or base element, and / or vibration damping system with at least one vibration-damping element, and / or Sturmschutz / Overspeed protection, and / or traction help in light wind, and / or Overspeedschutz and / or vibration-damping system by means of at least one buoyancy-reducing buoyancy element and possibly with closable pressure compensation openings and / or ice and snow removal system, can be used,
characterized in that a fluid (inflatable) or foldable element that can be filled with a fluid can be used, preferably a component of the actuator element or the buoyancy element itself, can be used

O = bypass EP1623111B1 Apparatus and method in the form of a wing, comprising:
adjustable flaps or buoyancy elements, which are arranged on or on the surface of the wing and are arranged in the longitudinal direction of the wing, and by
Activation devices can be adjusted and thereby change the aerodynamic properties of the wing, wherein the Flaps or buoyancy elements and the activation devices are designed and arranged to reduce the activation in a zone by the activation of the activation devices,
and / or at least high angles of attack of the wing and at least at a position of the angle of attack, the buoyancy in this zone and the yield can be significantly increased,
extending from a first location near the wing tip to a second location between the first location and the blade root, this second location being variable in the longitudinal direction of the wing by adjusting the activation means,
characterized in that the buoyancy control means of at least, a flexible Flap and / or rigid flap, and / or, a plurality of small rigid and / or flexible flaps are formed,
wherein the at least one flap or at least a plurality of small flaps is arranged in the longitudinal direction of the blade and is adjustable by means of one or more activating means to allow the lift varying position of the flap or the plurality of small flaps in the longitudinal direction of the flap or the flap Variety of small flaps,
fast and / or gradual change.

P = bypass EP1623111B1 Apparatus and method in the form of a wing, comprising:
adjustable flaps or buoyancy elements which are arranged on or on the surface of the wing and are arranged in the longitudinal direction of the wing, and
Activation devices can be adjusted and thereby the aerodynamic properties, and / or noise reducing properties of the buoyancy and / or base element, and / or vibration damping properties with at least one vibration-damping element, and / or storm-protective properties / Overspeed protection, and / or as traction help in light wind, and / or as overspeed protection and / or vibration damping properties by means of at least one lift-reducing buoyancy element and optionally with closable pressure equalization openings, and / or ice and snow removal properties
of the wing, wherein the flaps or buoyancy elements and the activation means are designed and arranged so that reduces the buoyancy in a zone by the activation of the activation means, and / or at least high angles of attack of the wing and at least at a position of the angle of attack the buoyancy , in this zone and the yield can be increased significantly,
extending from a first location near the wing tip to a second location between the first location and the blade root, this second location being variable in the longitudinal direction of the wing by adjusting the activation means, characterized in that the lift regulation means comprise at least one flexible flap and / or rigid flap, and / or, a plurality of small rigid and / or flexible flaps are formed,
wherein the at least one flap or at least a plurality of small flaps is arranged in the longitudinal direction of the blade and is adjustable by means of one or more activating means to allow the lift varying position of the flap or the plurality of small flaps in the longitudinal direction of the flap or the flap Variety of small flaps,
fast and / or gradual change.

Q = bypass EP1623111B1 Apparatus and method in the form of a wing, comprising:
adjustable flaps or buoyancy elements disposed on or on the surface of the wing and are arranged in the longitudinal direction of the wing, and
Activation devices can be adjusted and thereby the aerodynamic properties, and / or noise reducing properties of the buoyancy and / or base element, and / or vibration damping properties with at least one vibration-damping element, and / or storm-protective properties / Overspeed protection, and / or as traction help in light wind, and / or as overspeed protection and / or vibration damping properties by means of at least one lift-reducing buoyancy element and optionally with closable pressure equalization openings, and / or ice and snow removal properties
of the wing, wherein the flaps or buoyancy elements and the activation means are designed and arranged so that reduces the buoyancy in a zone by the activation of the activation means, and / or at least high angles of attack of the wing and at least at a position of the angle of attack the buoyancy , in this zone and the yield can be increased significantly,
extending from a first location near the wing tip to a second location between the first location and the blade root, this second location being variable in the longitudinal direction of the wing by adjusting the activation means,
characterized in that the buoyancy control means are formed of at least one flexible flap and / or rigid flap, and / or a plurality of small rigid and / or flexible flaps, the at least one flap or at least a plurality of small flaps being in the longitudinal direction of the flap Sheet is adjustable and is adjustable by means of one or more activation devices, so that the lift-changing position of the flap or the plurality of small flaps in the longitudinal direction of the flap or the plurality of small flaps that the activating device is filled with a fluid (inflatable) and / or foldable element, preferably part of the buoyancy element or the buoyancy element itself, can be used, and can be changed quickly and / or gradually.

R = bypass EP1623111B1 Apparatus and method in the form of a wing, comprising:
adjustable flaps or buoyancy elements which are arranged on or on the surface of the wing and are arranged in the longitudinal direction of the wing, and
Activation devices can be adjusted and thereby the aerodynamic properties, and / or noise reducing properties of the buoyancy and / or base element, and / or vibration damping properties with at least one vibration-damping element, and / or storm-protective properties / Overspeed protection, and / or as traction help in light wind, and / or as overspeed protection and / or vibration damping properties by means of at least one lift-reducing buoyancy element and optionally with closable pressure equalization openings, and / or ice and snow removal properties
of the wing, wherein the flaps or buoyancy elements and the activation means are designed and arranged so that reduces the buoyancy in a zone by the activation of the activation means, and / or at least high angles of attack of the wing and at least at a position of the angle of attack the buoyancy can be significantly increased in this zone and the yield extending from a first location near the wing tip to a second location between the first location and the blade root, this second location in the longitudinal direction of the wing by adjusting the activation means is variable,
characterized in that the buoyancy control means are formed of at least one flexible flap and / or rigid flap, and / or a plurality of small rigid and / or flexible flaps,
and that these flaps have an increased stiffness of the flap and / or means for travel limiting, in particular foldable,
wherein the at least one flap or at least a plurality of small flaps is arranged in the longitudinal direction of the blade and is adjustable by means of one or more activating means to allow the lift varying position of the flap or the plurality of small flaps in the longitudinal direction of the flap or the flap Variety of small flaps,
fast and / or gradual change. As a high angle of attack, these are considered to produce at least approximately the maximum lift coefficient C _A , preferably at least 70% of the maximum lift coefficient C _A , particularly preferably at least 80% of the maximum lift coefficient C _A.

S = hose not integrated in the sash. Device and method in the form of a sash comprising:
adjustable flaps or buoyancy elements which are arranged on or on the surface of the wing and are arranged in the longitudinal direction of the wing, and
Activation devices, which is not integrated in the wing tube, can be adjusted and thereby the aerodynamic properties, and / or noise reduction properties of the buoyancy and / or base element, and / or vibration damping properties with at least one vibration-damping element, and / or storm-protective properties , and / or as traction help in light wind, and / or as Overspeedschutz and / or vibration damping properties by means of at least one buoyancy-reducing buoyancy element and possibly with closable pressure equalization openings, and / or ice and snow removal properties
of the wing, wherein the flaps or buoyancy elements and the activation devices are designed and arranged such that the activation of the activation devices reduces the buoyancy in a zone,
and / or at least high angles of attack of the wing and at least at a position of the angle of attack, the buoyancy, in this zone and the yield can be significantly increased, extending from a first location near the wing tip to a second location between the first location and the blade root extends, this second location being variable in the longitudinal direction of the wing by adjusting the activation means,
characterized in that the buoyancy control means are formed of at least one flexible flap and / or rigid flap, and / or a plurality of small rigid and / or flexible flaps, and in that the activating means consists of at least one fluid-fillable tube, which in particular is foldable is and when filling, preferably only 2-dimmensional deformed
and that the activation device system comprises at least one fluid-fillable hose, a line system, at least one pressure accumulator or vacuum accumulator and at least one control valve,
wherein the at least one flap or at least a plurality of small flaps is arranged in the longitudinal direction of the blade and is adjustable by means of one or more activating means to allow the lift varying position of the flap or the plurality of small flaps in the longitudinal direction of the flap or the flap Variety of small flaps,
fast and / or gradual change.

Device of a safety system and / or resource energy efficiency improvement system for influencing the flow of an aerodynamic or hydrodynamic body ( 3 ), preferably a wing ( 3 ), according to the principle of a return flap ( 4 ), characterized in that they are connected to the aerodynamic or hydrodynamic body ( 3 ), in particular wings ( 3 ), at least a partial displacement of the flap area delineation ( 21 ) through the return flap ( 4 ) and its demarcation component ( 5 ) in the case of partial and / or complete installation of the return flap ( 4 ) and thereby causing the end-edge separation vertex (s) ( 1 ) and / or flap detachment vertebrae ( 2 ), and that the flap area delineation ( 21 ) completely up to or over the profile end edge ( 6 ) or only up to a part in front of the profile end edge ( 6 ), and that thereby further increases the lift coefficient C _A.

Device of a safety system and / or resource energy efficiency improvement system for influencing the flow of an aerodynamic or hydrodynamic body ( 3 ), preferably a wing ( 3 ), according to the principle of a return flap ( 4 ), characterized in that they are connected to the aerodynamic or hydrodynamic body ( 3 ), in particular wings ( 3 ), at least a partial displacement of the flap area delineation ( 21 ) through the return flap ( 4 ) and its demarcation component ( 5 ) in the case of partial and / or complete installation of the return flap ( 4 ) and thereby causing the end-edge separation vertex (s) ( 1 ) and / or flap detachment vertebrae ( 2 ), and that the flap area delineation ( 21 ) completely up to or over the profile end edge ( 6 ) or only up to a part in front of the profile end edge ( 6 ), and that thereby increases the lift coefficient C _A , and / or that the number of pressure ranges on the profile of 2 to 3 areas, further.

Device of a safety system and / or resource energy efficiency improvement system for influencing the flow of an aerodynamic or hydrodynamic body ( 3 ), preferably a wing ( 3 ), according to the principle of a return flap ( 4 ), characterized in that they are connected to the aerodynamic or hydrodynamic body ( 3 ), in particular wings ( 3 ), at least a partial displacement of the flap area delineation ( 21 ) through the return flap ( 4 ) and its demarcation component ( 5 ) in the case of partial and / or complete installation of the return flap ( 4 ) and thereby causing the end-edge separation vertex (s) ( 1 ) and / or flap detachment vertebrae ( 2 ), and that the flap area delineation ( 21 ) completely up to or over the profile end edge ( 6 ) or only up to a part in front of the profile end edge ( 6 ) and that this with a base element, ( 23 ) on the wing ( 3 ) is movably connected, preferably permanently and / or releasably secured for maintenance purposes, thereby allowing a long service life of the wing and / or the wind turbine and / or the flap system, preferably> 5 years, particularly preferably> 10 years, completely particularly preferably> = 20 years and / or possibly allows easy removal / replacement.

Device according to one of the preceding claims, characterized in that this return flow flap ( 4 ) with the wing ( 3 ) or alone, at least one parallelogram-shaped ( 10 ), and / or triangular-shaped ( 8th ) and / or circular segment-shaped area ( 9 ), in particular self-moving return flap ( 8th . 9 . 10 ), and thereby at least one passive and / or active return flap ( 8th . 9 . 10 ) arises.

Device according to one of the preceding claims, characterized in that one side of the return flow flap ( 4 . 8th . 9 . 10 ) in the basic position (fitting) of an approximate parallel direction (horizontal) to the profile surface or at an angle of> 30 degrees, preferably at an angle of> 45 degrees, particularly preferably at an angle of> 60 degrees, to the profile surface as a return flow flap ( 4 . 8th . 9 . 10 ) and / or spoiler / rudder flap and / or brake flap is formed.

Device according to one of the preceding claims, characterized in that the attachment of the return flap ( 4 . 8th . 9 . 10 ) at any point on / on and / or in the wing ( 3 ) and / or their aero- or hydrodynamic integration, does not require complete penetration of the shell and / or sandwich construction.

Device according to one of the preceding claims, characterized in that the elevation in a subsequent and / or external attachment of the return flap ( 4 . 8th . 9 . 10 ) on the wing ( 3 ) by means of an aero- or hydrodynamically designed flap transition ( 20 ) z. B. in the form of a slope or curve, preferably with a curved and elastic cover strip occurs.

Device according to one of the preceding claims, characterized in that the joints ( 7 ) of the demarcation components ( 5 ) of the return flow flap ( 4 ) by a rotating and / or elastic hinge ( 11 ) and / or elastic component material can be formed.

Device according to one of the preceding claims, characterized in that the active backflow flap ( 4 ) by means of at least one actuator ( 15 ), z. Mechanically (eg via levers, rods, cables, springs) and / or electrically (eg via electromagnets, linear or rotating electric motors) and / or hydraulically (eg via cylinders or motors) and / or or pneumatically (eg via cylinders, hoses ( 13 ), Parallelogram tube ( 10 ), Triangle hose ( 8th ), Flat hose, circular segment hose ( 9 ) or pneumatic motors / actuators) and / or magneto-rheological fluid or polymer is moved.

Device according to one of the preceding claims, characterized in that the return flow flap ( 4 ) z. As by ropes, wires, rods, levers, bands, springs, walls, foils, folding structure and / or actuator element ( 22 ) experiences a travel limit.

Device according to one of the preceding claims, characterized in that the components of the return flow flap ( 4 ) At least partially to the stiffening (static improvement against vibrations) one of z. B. bulge / embossing and / or bionic (sharkskin structure) and / or otherwise known reinforcing and / or aerodynamic improvement structure receives.

• a) Fluid-Strömungs-Geschwindigkeitsmessung im Umfeld des Flügels und/oder
• b) direkte und/oder indirekte Flügel-Belastungsmessung erfolgt,
• c) um dadurch eine aktive und/oder passive Strömungsbeeinflussung des Flügels (3) zu Steuern und/oder zu Regeln.

Method of a safety system for avoiding hazardous operating states and / or resource / energy efficiency improvement system for influencing the flow of an aerodynamic or hydrodynamic body ( 3 ), in particular of turbines equipped with buoyancy wings (eg aircraft), according to the principle of a return flow flap ( 8th . 9 . 10 ), characterized in that a

• a) fluid flow velocity measurement in the vicinity of the wing and / or
• b) direct and / or indirect wing load measurement takes place,
• c) to thereby actively and / or passive flow control of the wing ( 3 ) on taxes and / or rules.

• a) Fluid-Strömungs-Geschwindigkeitsmessung im Umfeld des Flügels und/oder
• b) direkte und/oder indirekte Flügel-Belastungsmessung erfolgt,
• c) um dadurch eine aktive und/oder passive Strömungsbeeinflussung durch Rückstromklappen und/oder Spoiler/Klappen und/oder Bremssysteme (Bremsschirme und/oder Bremsklappen und/oder Über- und Unterdruck-Ausgleichenden Systemen) des Flügels (3) zu Steuern und/oder zu Regeln.

Method of a safety system for avoiding hazardous operating states and / or resource / energy efficiency improvement system for influencing the flow of an aerodynamic or hydrodynamic body ( 3 ), in particular of turbines equipped with buoyancy wings (eg aircraft), according to the principle of a return flow flap ( 8th . 9 . 10 ), characterized in that a

• a) fluid flow velocity measurement in the vicinity of the wing and / or
• b) direct and / or indirect wing load measurement takes place,
• c) thereby active and / or passive flow control by return valves and / or spoiler / flaps and / or brake systems (brake screens and / or airbrakes and / or overpressure and negative pressure compensating systems) of the wing ( 3 ) on taxes and / or rules.

• a) Fluid-Strömungs-Geschwindigkeitsmessung im Umfeld des Flügels und/oder
• b) direkte und/oder indirekte Flügel-Belastungsmessung erfolgt, und/oder
• c) Messsysteme zur Erkennung weiterer Gefahren-Betriebszuständen
• d) um dadurch eine aktive und/oder passive Strömungsbeeinflussung durch Rückstromklappen und/oder Spoiler/Klappen und/oder Bremssysteme (Bremsschirme und/oder Bremsklappen und/oder Über- und Unterdruck-Ausgleichenden Systemen) des Flügels (3) zu Steuern und/oder zu Regeln.

Method of a safety system for avoiding hazardous operating states and / or resource / energy efficiency improvement system for influencing the flow of an aerodynamic or hydrodynamic body ( 3 ), in particular of turbines equipped with buoyancy wings (eg aircraft), according to the principle of a return flow flap ( 8th . 9 . 10 ), characterized in that a

• a) fluid flow velocity measurement in the vicinity of the wing and / or
• b) direct and / or indirect wing load measurement takes place, and / or
• c) measuring systems for the detection of further danger operating conditions
• d) thereby active and / or passive flow control by return valves and / or spoiler / flaps and / or braking systems (brake screens and / or airbrakes and / or overpressure and negative pressure compensating systems) of the wing ( 3 ) on taxes and / or rules.

• a) Fluid-Strömungs-Geschwindigkeitsmessung im Umfeld des Flügels mittels mindestens einem Kamerasystem und/oder
• b) direkte und/oder indirekte Flügel-Belastungsmessung erfolgt, mittels mindestens einem Kamerasystem pro Flügel (3) erfolgt, und/oder
• c) Messsysteme zur Erkennung weiterer Gefahren-Betriebszuständen
• d) um dadurch eine aktive und/oder passive Strömungsbeeinflussung durch Rückstromklappen und/oder Spoiler/Klappen und/oder Bremssysteme (Bremsschirme und/oder Bremsklappen und/oder Über- und Unterdruck-Ausgleichenden Systemen) des Flügels (3) zu Steuern und/oder zu Regeln.

Method of a safety system for avoiding hazardous operating states and / or resource / energy efficiency improvement system for influencing the flow of an aerodynamic or hydrodynamic body ( 3 ), in particular of turbines equipped with buoyancy wings (eg aircraft), according to the principle of a return flow flap ( 8th . 9 . 10 ), characterized in that a

• a) fluid flow velocity measurement in the vicinity of the wing by means of at least one camera system and / or
• b) direct and / or indirect wing load measurement, by means of at least one camera system per wing ( 3 ), and / or
• c) measuring systems for the detection of further danger operating conditions
• d) thereby active and / or passive flow control by return valves and / or spoiler / flaps and / or braking systems (brake screens and / or airbrakes and / or overpressure and negative pressure compensating systems) of the wing ( 3 ) on taxes and / or rules.

A fluid flow velocity measurement in the vicinity of the wing can be carried out by means of a distance at the outer wing, possibly at a Bassiselement ( 23 ) attached pneumatic and / or electrical pressure probes and / or acceleration sensors (especially for gusts of wind) are measured.

Advantageous developments of the invention will become apparent from the claims, the description and the drawings. The advantages of features and of combinations of several features mentioned in the introduction to the description are merely exemplary and can come into effect alternatively or cumulatively, without the advantages having to be achieved by embodiments according to the invention. Other features are the drawings - especially the shown geometries and the relative dimensions of several components to each other and their relative arrangement and operative connection - to refer. The combination of features of different embodiments of the invention or of features of different claims is also possible deviating from the chosen relationships of the claims and is hereby stimulated. This also applies to those features which are shown in separate drawings or are mentioned in their description. These features can also be combined with features of different claims. Likewise, in the claims listed features for further embodiments of the invention can be omitted.

The invention will be explained below with reference to examples and drawings. Show it

1 :
WEA for improvement
WEA improvement potential: A = weak wind from V _StartNew -V _Start
WEA improvement potential: B = weak wind from V _Start -V _Nom
WEA improvement potential: C = _mean wind of V _nominal -V _Maxnormal
WEA improvement potential: D = strong wind from V _Maxnormal -V _max35m

2 :
Model wing a: with detached flow; b: ditto. with flap

3 :
Simulated flow conditions on a wing with return flap

• a) Flügelprofil mit aufgestellter dreiecks-förmiger Rückstromklappe (8) mit vollständiger Verschiebung der Klappen-Bereichsabgrenzung (21)
• b) Flügelprofil mit aufgestellter Kreisbogen-förmiger Rückstromklappe (8) mit vollständiger Verschiebung der Klappen-Bereichsabgrenzung
• c) Flügelprofil mit aufgestellter parallelogramm-förmiger Rückstromklappe (8) mit vollständiger Verschiebung der Klappen-Bereichsabgrenzung

4 :

• a) Wing profile with erected triangular-shaped return flap ( 8th ) with complete displacement of the flap area delineation ( 21 )
• b) Wing profile with erected arc-shaped return flap ( 8th ) with complete displacement of the flap area boundary
• c) sash profile with erected parallelogram-shaped return flap ( 8th ) with complete displacement of the flap area boundary

• a) Flügelprofil mit aufgestellter dreiecks-förmiger Rückstromklappe (8) mit teilweiser Verschiebung der Klappen-Bereichsabgrenzung (21)
• b) Flügelprofil mit aufgestellter Kreisbogen-förmiger Rückstromklappe (8) mit teilweiser Verschiebung der Klappen-Bereichsabgrenzung (21)
• c) Flügelprofil mit aufgestellter parallelogramm-förmiger Rückstromklappe (8) mit teilweiser Verschiebung der Klappen-Bereichsabgrenzung (21)

5 :

• a) Wing profile with erected triangular-shaped return flap ( 8th ) with partial displacement of the flap area delineation ( 21 )
• b) Wing profile with erected arc-shaped return flap ( 8th ) with partial displacement of the flap area delineation ( 21 )
• c) sash profile with erected parallelogram-shaped return flap ( 8th ) with partial displacement of the flap area delineation ( 21 )

• a) Flügelprofil mit geschlossener dreiecks-förmiger Rückstromklappe (8) mit vollständiger Verschiebung der Klappen-Bereichsabgrenzung (21)
• b) Flügelprofil mit geschlossener Kreisbogen-förmiger Rückstromklappe (8) mit vollständiger Verschiebung der Klappen-Bereichsabgrenzung (21)
• c) Flügelprofil mit geschlossener parallelogramm-förmiger Rückstromklappe (8) mit vollständiger Verschiebung der Klappen-Bereichsabgrenzung (21)

6 :

• a) Wing profile with closed triangular-shaped return flap ( 8th ) with complete displacement of the flap area delineation ( 21 )
• b) sash profile with closed arc-shaped return flow flap ( 8th ) with complete displacement of the flap area delineation ( 21 )
• c) Wing profile with closed parallelogram-shaped return flap ( 8th ) with complete displacement of the flap area delineation ( 21 )

7 :
Combination of several return valves

8th :
Combination of several return valves with actuator

9 :
Return flap according to the prior art ( 4 ) combined with a demarcation component ( 5 ) in the form, for. B. a balloon or hose or cushion ( 13 )

10 :
Triangular-shaped return flap ( 8th ) which z. B. a hose ( 13 ) has been installed as an active actuator.

11 :
Triangular-shaped return flap ( 8th ) which is completely closed in its three-dimensional design to a fluid / gas connection ( 18 ) with z. B. to be filled with air

12 :
Parallelogram-shaped return flap ( 8th ) which z. B. in its three-dimensional design is completely closed to a fluid / gas connection ( 18 ) with z. B. to be filled with air

13 :
active return flap ( 10 ), which is formed only by a flattened closed tube

14 :
active return flap ( 8th . 9 . 10 ), to improve the braking effect with a fluid / gas compound ( 18 ) between wing top and wing bottom

15 :
exemplary arrangements / positions of the passive and / or active return valves ( 4 . 8th . 9 . 10 )

16 :
active parallelogram return flap ( 10 ) on the wing top, for improvement with noise-reducing buoyancy element ( 25 ) with base element

17 :
active parallelogram return flap ( 10 ) on the wing top and bottom with integrated hose ( 13 ), for improvement with noise-reducing base element ( 25 . 23 )

18 :
active parallelogram return flap ( 10 ) on the bottom of the wing and the simplest variant with hose ( 8th ) and combined with St. d. T. return flap ( 4 ) on the wing top, with noise-reducing base element ( 25 . 23 )

19 :
Passive and active triangular return flap ( 8th ) with vibration damping system based on the inertia on the wing top (in one direction only), with V-shaped base elements ( 23 )

20 :
Passive and active parallelogram return valve ( 8th ) beyond the profile end edge with vibration damping system based on the inertia on the wing upper side (in both directions), with basic elements ( 23 )

21 :
active parallelogram return flap ( 10 ) on a rotatably mounted wing or wing part with vibration damping system on the basis of inertia on the wing top (in one direction only), with basic elements ( 23 )

22 :
End piece of a folded tube using the example of the bottom / end piece of a soup bag

23 :
End piece of a unfolded hose using the example of the bottom / end piece of a soup bag

24 :
End piece of a folded tube on the example of the bottom / tail of a foldable beverage container with arched base

25 :
End piece of a unfolded hose using the example of the bottom / end piece of a foldable beverage container with a curved bottom

LIST OF REFERENCE NUMBERS

1

Endkanten-Ablösewirbel

2

Klappen-Ablösewirbel

3

Aero-/Hydrodynamischer Körper/Flügel/-profil

4

Rückstromklappen nach St. d. T. (Auftriebselement)

5

Abgrenzungs-Bauteil

6

Profil-Endkante

7

Gelenke

8

Dreiecks-förmige Rückstromklappe (Flap/Auftriebselement)

9

Kreisbogen-förmige Rückstromklappe (Flap/Auftriebselement)

10

Parallelogramm-förmige Rückstromklappe (Flap/Auftriebselement)

11

Elastisches Material/Scharnier

12

Federndes Material

13

Schlauch

14

Fluid-/Gas-Füllbereich

15

Zylinder Hydraulisch/Pneumatisch oder anderer Aktor

16

Auflagefläche/Verbindungsstelle zum Flügel

17

Anstellwinkel α des Flügels

18

Fluid/Gas-Verbindung

19

Stelle der Größten Profildicke

20

Klappenübergang

21

Klappen-Bereichsabgrenzung

22

Aktuator-Element

23

Basiselement

24

Blitzschutzsystem

25

Lärmreduzierendes Auftriebselement und/oder Basiselement

26

Mittel zur Wegbegrenzung

27

Befestigungsmittel

28

Massenträgheitselement

29

Hebel

30

Drehpunkt

31

Momenten-Nullpunkt des Profils

32

Auftriebskraft FA (resultierende)

to FIGS. 1 to 25:

1

End edge separation vortices

2

Flap release vortexes

3

Aero / hydrodynamic body / wing / profile

4

Return flow flaps to St. d. T. (buoyancy element)

5

Deferral component

6

Profile-end edge

7

joints

8th

Triangular-shaped return flap (flap / buoyancy element)

9

Arc-shaped return flap (flap / buoyancy element)

10

Parallelogram-shaped return flap (Flap / buoyancy element)

11

Elastic material / hinge

12

Feathering material

13

tube

14

Fluid / gas filling area

15

Cylinder hydraulic / pneumatic or other actuator

16

Support surface / connection point to the wing

17

Angle of attack α of the wing

18

Fluid / gas connection

19

Place the largest profile thickness

20

Fold transition

21

Flap area demarcation

22

Actuator element

23

base element

24

Lightning protection system

25

Noise-reducing buoyancy element and / or base element

26

Means for limiting the path

27

fastener

28

Inertia element

29

lever

30

pivot point

31

Moments zero of the profile

32

Buoyancy FA (resulting)

QUOTES INCLUDE IN THE DESCRIPTION

This list of the documents listed by the applicant has been generated automatically and is included solely for the better information of the reader. The list is not part of the German patent or utility model application. The DPMA assumes no liability for any errors or omissions.

Cited patent literature

• DE 102010041111 [0007, 0008]
• JP 2004183640 [0009, 0055]
• US 7293959 B2 [0010, 0055]
• EP 1623111 B1 [0010, 0074, 0075, 0076, 0077]
• DE 102010041111 A1 [0055]
• DE 102012000431 A1 [0055]

Cited non-patent literature

• Hours. T. Pantone G ET AL [0002]
• Hours. T. Meyer Robert KJ [0002]
• Patone G ET AL: "Aeroflexible Surface Flaps as Backflow Brakes" in Technical Report TR-96-05, 1.5.1996 [0005]
• Meyer, Robert KJ, Experimental investigations on airfoils to influence flow separation [0006]
• Dissertation TU Berlin Hermann Föttinger Institute for Fluid Mechanics, Mensch & Buch Verlag, ISBN 3-89820-205-4 [0006]

Claims (10)

Device in the form of a wing with a passive and / or active flap system which can be used to improve the yield, at least in the areas of improvement A and / or B and / or C and / or D, in the form of, the wing, reinforcing base element, characterized characterized in that, this by z. As a wing-trailing edge reinforcement with at least one triangular or Z- or V- or Nasenleisten- or polygonal-shaped base element is formed and the wing structure thereby statically reinforced (possibly repaired) and / or protects against external influences, in particular the trailing edge and possibly at the leading edge (wing nose) and possibly at certain portions of the wing / locations on leaf segments, possibly for attachment of vortex generators and / or other base elements and / or flaps and / or lightning protection. Device in the form of a wing with a passive and / or active flap system which can be used for improving the yield at least in the improvement areas A and / or B and / or C and / or D, in the form of an at least noise-reducing buoyancy element and / or base element, characterized in that by a flexible and / or solid-shaped, in particular serrated, serrated, bristly, perforated, most preferably slotted, thread, bird feather, finger-shaped (kinked rod or tube) and spiral-shaped (2 or 3D shaped spiral) trailing edge of the buoyancy element and / or the base element (front and rear possible) and that thereby generates less noise, or as in the original state of the wing (when retrofitting). Wings with a passive and / or active flap system which can be used to improve the yield at least in the areas of improvement A and / or B and / or C and / or D, and to reduce the loads on the wing and possibly hub structure and thereby dynamic wing vibrations transversely to the chord (Flapwise, dynamic yaw vibrations) and parallel to the profile chord of the wing (edgewise) excited and can lead to significant peak loads of the wing and what in the long term can lead to material fatigue (possibly shortened life), characterized in that that at least one vibration-damping element is applied, which takes the form of at least one active and / or passive flap and that, this wing by mass balance and / or pneumatically and / or hydraulically and / or magneto-rheologically reactive, and by at least one passive and / or active buoyancy element acts damping and thereby possibly the life of the wing and / or the wind turbine and / or the flap system is increased. Device in the form of a wing with a passive and / or active flap system that can be used to improve the yield at least in the areas of improvement C and / or D, and operates as a storm protection / overspeed protection, prevents overloading of the wings and an increase in yield at speeds by a higher strong-wind running time at greater VMax-normal allows sufficient overburden protection for gusts / thermals is present, for example at <50% of the rated power, preferably at <70% of the rated power, more preferably <= 95% of the rated power, all particularly preferably <= 100% of the rated power, characterized in that this is achieved by at least one lift- reducing (top and possibly bottom) Flap / buoyancy element of the wing and that at the speed VMax-normal no cut-off takes place, but on the active Flapsystem, on at least the top of the wind turbine, by Widerstandserhöhun g and / or buoyancy reduction, at least as slowed down that the rated power is not exceeded and / or overloading is not carried out and / or the network stability is not disturbed and that, by actively actuated Flaps possibly also by vane and / or centrifugal force - / Measurement and / or inertia / acceleration measurement and / or speed measurement is operated and / or controlled and / or regulated. Device in the form of a wing with a passive and / or active flap system which can be used to improve the yield at least in the areas of improvement A and / or B in the function as traction help in light wind and yield improvement, by at least one buoyancy increasing the buoyancy element, which the lift coefficient and thereby the energy yield at high angles of attack (up to about VNen) significantly increased, characterized in that this buoyancy element is preferably attached to the top, more preferably at the trailing edge of the top of the wing and by passively and / or actively actuated flaps pneumatic and / or hydraulically and / or magneto-rheologically actuated and / or controlled and / or regulated, and that, just before VNn, the pitch control and / or the lift-controlling flap control can be used to increase the plant to the maximum power or something before VNenn the pitch control / regulation (fine control) and the lift-controlling flap control (coarse control) can be used to regulate the system to the maximum power or that slightly before VNenn the pitch control (coarse control) and the lift-controlling flap control (fine control) can be used to control the system to the maximum power. Device in the form of a wing with an active and / or passive flap system which can be used for improving the yield at least in the areas of improvement A and / or B and / or C and / or D, and / or in the function as a system of increasing stiffness and / or or Wegbegrenzung the Flap, and / or a wing-reinforcing base element and / or lightning protection, and / or traction help in light wind, and / or ice and snow removal system, characterized in that means for increasing the rigidity of the flap and / or means used for travel limitation and that, at least part of the flap has a high rigidity and is preferred and exceeds a stiffness in the form of a tensile modulus of at least 50 GPa and / or a tensile strength of at least 0.4 GPa. Device in the form of a wing with a passive and / or active flap system to improve the yield at least in the areas of improvement A and / or B and / or C and / or D, in function as a system of increase in rigidity and / or travel limitation of the flap, and or system with high durability and retrofit capability, and / or a wing-reinforcing base element and / or lightning protection, and / or noise-reducing buoyancy and / or base element, and / or vibration damping system with at least one vibration-damping element, and / or Sturmvers / Overspeed protection , and / or traction in light wind, and / or Overspeedschutz and / or vibration damping system by means of at least one buoyancy- reducing buoyancy element and possibly with closable pressure equalization openings and / or ice and snow removal system, can be used, characterized in that means for increasing the rigidity of the Flaps and / or means for Wegbegrenzung be used, and that, the path limit the opening angle of the flap of <90 degrees, preferably <75 degrees, most preferably <60 degrees limited. Device in the form of a wing comprising: adjustable flaps or buoyancy elements arranged on or at the surface of the wing and arranged in the longitudinal direction of the wing and allowing activation devices to be adjusted, thereby reducing the aerodynamic properties and / or noise reducing properties of the buoyancy and / or base element, and / or vibration-damping properties with at least one vibration-damping element, and / or Sturmversützenden properties / Overspeed protection, and / or as traction help in light wind, and / or as Overspeedschutz and / or vibration damping properties by means of at least one buoyancy-reducing buoyancy element and possibly ., with closable pressure compensation openings, and / or ice and snow removal properties of the wing, wherein the flaps or buoyancy elements and the activation devices are designed and arranged such that by d Activation of the activation devices reduces the buoyancy in a zone, and / or at medium to high angles of attack of the wing and at least at a position of the angle of attack, the buoyancy in this zone, and the yield can be significantly increased, extending from a first location near the wing tip to a second location between the first setting and the blade root, said second location in is variable in the longitudinal direction of the wing by adjusting the activation means, characterized in that the buoyancy control means are formed from at least one flexible flap and / or rigid flap, and / or a plurality of small rigid and / or flexible flaps, the at least one Flap or at least a plurality of small flaps in the longitudinal direction of the sheet is arranged and adjustable by means of one or more activating means, so that the lift changing position of the flap or the plurality of small flaps in the longitudinal direction of the flap or the plurality of small flaps that the acti vierungsseinrichtung a fillable with a fluid (inflatable) and / or foldable element, preferably part of the buoyancy element or the buoyancy element itself, can be used, and can be changed quickly and / or gradually. Device in the form of a wing comprising: adjustable flaps or buoyancy elements arranged on or at the surface of the wing and arranged in the longitudinal direction of the wing, and allowing activation devices to be adjusted and thereby the aerodynamic properties and / or noise reducing properties of the buoyancy and / or base element, and / or vibration-damping properties with at least one vibration-damping element, and / or Sturmversützenden properties / Overspeed protection, and / or as traction help in light wind, and / or as Overspeedschutz and / or vibration damping properties by means of at least one buoyancy-reducing buoyancy element and possibly ., with closable pressure compensation openings, and / or ice and snow removal properties of the wing, wherein the flaps or buoyancy elements and the activation devices are designed and arranged such that by d Activation of the activation devices reduces the buoyancy in a zone, and / or at medium to high angles of attack of the wing and at least at one position of the angle of attack, the buoyancy in this zone, and the yield can be significantly increased, extending from a first position in the Extending the wing tip to a second location between the first setting and the blade root, said second location being variable in the longitudinal direction of the wing by adjusting the activating means, characterized in that the buoyancy control means comprise at least one flexible flap and / or rigid flap , and / or, a plurality of small rigid and / or flexible flaps are formed, and that these flaps have an increased stiffness of the flap and / or means for Wegbegrenzung, in particular foldable, wherein the at least one flap or at least a plurality of small Flaps in the longitudinal direction of the sheet is arranged and is adjustable by means of one or more activation devices, so that the buoyancy changing position of the flap or the plurality of small flaps in the longitudinal direction of the flap or the plurality of small flaps, quickly and / or gradually change. Device in the form of a wing comprising: adjustable flaps or buoyancy elements arranged on or on the surface of the wing and arranged in the longitudinal direction of the wing, and enabling activation means, which is not a hose integrated in the wing, and thereby the aerodynamic properties , and / or noise-reducing properties of the buoyancy and / or base element, and / or vibration damping properties with at least one vibration-damping element, and / or Sturmversützenden properties / Overspeed protection, and / or as traction help in light wind, and / or as Overspeedschutz and / or Vibration damping properties by means of at least one buoyancy-reducing buoyancy element and possibly with closable pressure equalization openings, and / or change ice and snow removal properties of the wing, the flaps or buoyancy elements and the activation devices are designed and arranged such that the activation of the activation devices reduces the buoyancy in a zone, and / or increases the buoyancy in this zone at least at a position of the angle of attack, and the yield can be significantly increased, extending from a first location near the wing tip to a second location between the first location and the blade root, said second location being variable in the longitudinal direction of the wing by adjusting the activation means, characterized in that the buoyancy control means comprise at least, a flexible flap and / or rigid flap, and / or, a plurality of small rigid and / or flexible flaps are formed, and that the activation means consists of at least one fluid-fillable tube, which in particular is foldable and when filling, preferably only 2-dimensiional verfo and in that the activation device system consists of at least one hose which can be filled with fluid, a line system, at least one pressure accumulator and at least one control valve, wherein the at least one flap or at least one plurality of small flaps is arranged in the longitudinal direction of the sheet and by means of a or more activation means is adjustable so that the buoyancy changing position of the flap or the plurality of small flaps in the longitudinal direction of the flap or the plurality of small flaps, quickly and / or gradually change.

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