DE102005059679A1 - Rotary circular aerofoil flying unit has a single rotary circular aerofoil with air channeling ribs for guiding compressed air to a nozzle outlet on the underside of the aerofoil wing section, with a radial airflow being generated - Google Patents

Abstract

Flying device comprises a rotary circular aerofoil that has air channeling ribs (2) and an aircraft wing cross-section (1Q). The circular aerofoil with its air channeling ribs forms a gyroscopic compressor. The generated air flow (3) is supplied radially to the aerofoil over the whole 360[deg] surface. The generated radial air flow does not cause rotor surface loading as with helicopters. Thus a number of circular aerofoils can be arranged on top of each other to generate a very large lift force.

Description

The invention relates to an aircraft 1 to 4 with annular wings ( 1 ), either with air vanes ( 2 ) or the action of separate air vanes ( 2 ) and their cross-sectional profile ( 1 _Q ) corresponds to an aircraft wing.

Wings ( 1 ) and scoop ( 2 ) generate by common rotation or by blade rotation about the vertical axis - according to the principle of a radial centrifugal compressor - an air flow ( 3 ).

It is the entire annular wing profile ( 1 _Q ) flows around. Buoyancy force F _A is generated on the basis of the usual lift determination on aircraft wings on the basis of performance parameters of the wing cross-sectional profile and the air flow. Suction on the wing upper side and overpressure on the wing underside generate buoyancy force F _A.

Further important influencing factors for the buoyancy F _A are the size of the wing cross-section ( 1 _Q ), the wing angle α and the rotational speed of the air flow.

The vertically aspirated and radially accelerated air flow ( 3 ) does not act as a rotor cradle load as with conventional helicopters. Therefore, a number of ring wings ( 1 ₁ ... 1 _n ) be arranged one above the other and thereby the buoyancy (F _{A 1} ... F _{A n} ) are multiplied per rotor circuit area.

The Trim in any flight situation can by means of speed change opposite rotating ring wing or blades and be secured by segmental deflection of the radial air flow.

Collision of the rotating round vanes or vanes with obstacles is avoided by the reaction force F _{Re of} the radial air flow and by the projection of the non-rotating vanes.

The known from conventional helicopters central drive can be used for ring-wing rotors. For counter rotating blades ( 2 ) neutralizes the torque on the vertical drive shaft, so that the tail rotor can be omitted.

Of the also usable torque-free jet drive allows synchronous rotation the ring wing.

low Constructed through small rotor circle area, high payload by stacking the Wing / rotors and low risk of collision besides cheaper Production and safe operation the transport and lifting of loads and people in cramped conditions.

An embodiment of the invention is based on 1 and 2 explained.

It demonstrate:

1 the side view of a ring wing rotor system.

2 the top view of an annular wing rotor system.

The rotating ring wings ( 1 ) with their air guide vanes ( 2 ) form a radial centrifugal compressor ( 1 and 2 ), which deflects the vertically drawn air and generates the radial air flow.

The airflow ( 3 ) is the cross-sectional profile ( 1 _Q ) is supplied radially in the 360 ° range and generates buoyancy force F _A as on an aircraft wing.

According to the calculation principles of the usual lift detections on aircraft wings on the basis of performance parameters of the wing wing profile, the wing size, the air flow, the Flügelanstellwinkels and the distance between superimposed annular wings creates suction on the wing top and pressure on the wing bottom, it buoyancy force F _{A is} generated.

in the described example, the rotation by torque-free Jet drive causes.

At least one compressed air nozzle ( 4 ) is per rotating blades ( 2 ) are arranged tangentially on the outer diameter.

Compressed air ( 5 ) is transmitted from outboard by line ( 6 ) Pipe ( 7 . 8th ) and nozzle ( 4 ) and generated by compressed air jet ( 9 ) the rotation of the annular wings ( 1 ).

With line ( 6 ) are also supplied with resources, control and regulation.

The trim in all flight situations is ensured by speed variation of the same or opposite rotors and by deflection of the radial air flow by means of segmental shaped screens ( 10 ), which are arranged outside the ring wing und and whose position is adjustable.

The composition in the sense of a Fesselfluggerätes allows reduced dead weight, low Dimensions, easy and safe operation with redundant units on the ground and above all higher payload. Practical designs and equipment allow for special and universal uses.

trimming and control can automatically or manually led by the support vehicle become.

It KFK / GFK construction is provided.

Another embodiment of the invention will be described 3 and 4 explained.

It demonstrate:

3 the side view of a ring wing system with additional lift-generating, flow-directing and driving components.

4 the top view of the same system.

The radial centrifugal compressor is in the embodiment according to 3 and 4 supplemented by a non-rotating ring wing ( 5 ) without air guiding ribs ( 3 . 4 ), which between the rotating ring wings ( 1 . 2 ) is posted.

In addition, above the ring wing ( 1 ) a non-rotating ring wing ( 6 ) whose top is that of an aircraft wing ( 6 ) corresponds.

The canopy ( 7 ) is also designed as a non-rotating ring wing top without ribs.

In the direction of flight in front of the ring wing device is a windscreen ( 12 ), which releases wind-guiding openings for the airstream supply to the concave air guide vane sides ( 2 . 4 ) and the one wind deflector forms at the convex air guide vane sides ( 3 . 4 ). This will cause the rotation of the blades ( 3 . 4 ) and buoyancy F _{A supported} by wind.

The compressed gas drive provided here consists of one outside the round wing ( 1 to 7 ) guided pressure line ( 8th ) and exhaust nozzles ( 9 ) for compressed gas ( 11 ) with beam direction on peripheral blades ( 10 ) on the blades ( 3 . 4 ).

The fixed vertical tube axis ( 13 ) carries over rolling bearings ( 14 ) the hubs ( 15 . 16 ) of the air guide vanes ( 3 . 4 ).

Adjustable air deflection screens ( 17 ) are at axis ( 13 ) stored. They support trim and propulsion through the remaining resulting radial airflow recoil.

since 1933 are hoverable and flyable rotorcraft as Gyroplane and helicopter known with diverse capabilities.

she were equipped with central drive or blade tip drive and increasingly used universally.

Lots Improvements to the current state of the art allow special Interpretations for respective applications.

Consist the risk of collision with rotor blade breakage remained as well as often disadvantageous rotor surface area load.

One Another disadvantage remained with the power rising rotor circuit area.

When solution These problems offer the invention of the annular wing rotor system at.

Thereby the risk of leaf breakage is eliminated, the rotor circuit area is reduced and the payload by superposition the ring wing higher.

Control, Control, trim and propulsion are simplified.

• – Bestellungen in der Landwirtschaft (Saat, Ernte, Berieselung).
• – Rettungsdienste der Feuerwehr, an Skipisten, am Wasser usw.
• – Überwachung im Gelände, an Grenzen und bei Waldbrandgefahr.
• – Serviceleistungen an Häusern, Brücken und Türmen.
• – Transport und Heben von Personen und Lasten.

The following uses are possible without danger:

• - Orders in agriculture (sowing, harvesting, sprinkling).
• - Rescue services of the fire department, on ski slopes, on the water, etc.
• - Surveillance in the field, at borders and forest fire danger.
• - Services on houses, bridges and towers.
• - Transport and lifting of persons and loads.

GRP / CFRP Construction and other composites provide benefits in terms of strength and costs.

Claims (16)

Aircraft consisting of at least one rotating annular wing ( 1 ), with air guiding ribs ( 2 ), and its cross-sectional area ( 1 _Q ) which corresponds to an aircraft wing; characterized in that the annular aircraft wing ( 1 ) in conjunction with the air guide ribs ( 2 ) forms a radial centrifugal compressor. The generated air flow ( 3 ) is radially the annular wing ( 1 ) is supplied in the entire 360 ° range. Aircraft according to claim 1, characterized in that the air flow ( 3 ) the wing profile ( 1 _Q ) flows around and acts according to the calculation bases of the usual buoyancy force investigations on aircraft wings. By suction on the wing top and pressure on the wing underside buoyancy force F _{A is} generated. Aircraft according to claim 1, characterized in that the angle of employment α is adapted to the requirements and, in conjunction with the rotor speed n, generates the respective required buoyancy force F _A. Aircraft according to claim 1, characterized in that a number of annular wings ( 1 ₁ ... 1 _n ) can be arranged one above the other and thereby the buoyancy force F _{A 1} ... F _An , per rotor circuit area is increased as well as by vertical air suction ( 3 ) from above, with closure of the lowest ring wing center. Aircraft according to claim 1, characterized in that the rotation of the annular wing by torque-free recoil force ( 9 ) at least one tangentially arranged in / on the wing profile jet propulsion ( 4 ) is effected. Aircraft according to claim 1, characterized in that one of conventional helicopters and gyrocopters known central drive superimposed annular wing ( 1 ₁ ... 1 _n ) can be rotated in the same direction or in opposite directions. Aircraft according to claim 1, characterized in that the annular wing ( 1 ) not rotated, but above and below the wing ( 1 ) rotating impellers ( 2 ) are positioned. The rotating paddle wheels ( 2 ) form together with wings ( 1 ) a radial centrifugal compressor. Aircraft according to claim 1, characterized in that, based on 3 and 4 at least one compressed gas nozzle ( 9 ) on the rotor circumference or in / on a non-rotating annular wing ( 5 ) is installed - with beam action in the direction of rotation on each one rotor-integrated lamellar rim ( 19 ). Aircraft according to claim 1, characterized in that the trim is ensured in all flight situations - based on 3 and 4 - By changing the speed of the counter-rotating ring wings ( 1 - 4 ) and by deflection of the radial air flow ( 3 ) by means of the umbrella segments ( 10 ), which are positioned outside the wing-⌀ adjustable. The resulting reaction force F _R prevents collisions. aircraft according to claim 1, characterized in that the rotation of the annular wing by Direct contact of its circumference with at least one friction or gear or toothed belt drive is effected. aircraft according to claim 1, characterized in that an electric motor (EP1489 722A1) between the vertical axis and the hub, or between counter-rotating ones Around wings or arranged between a fixed and a rotating round wing is and forms the frequency-controlled drive. aircraft according to claim 1, characterized in that a jet or propeller engine the Airspeed can generate. Aircraft according to claim 1, characterized in that the cabin roof ( 7 ) is designed to improve buoyancy as a ring-wing top profile and above the rotors a non-rotating wing ( 6 ) is installed, the roof shape of a wing wing top corresponds. Aircraft according to claim 1, characterized in that between right / left rotating ring wings ( 1 . 2 ) a non-rotating ring wing ( 5 ) is installed. Aircraft according to claim 1, characterized in that in the take-off or landing phase, the annular wing means provides the lift by motor drive and then, during the airspeed by jet or propeller engine, the buoyancy by self-rotating ring wing ( 1 - 4 ) arises. The ring wings have backward curved blade ribs ( 3 . 4 ) on. aircraft according to claim 1, characterized in that in front of the round wing device an appropriately shaped windshield is installed on the concave rib side the Fahrtwind zuleitet and on the convex Rib side distracts the wind.