US20130228655A1 - Method and device for fitting out an aircraft nose compartment in an avionics bay - Google Patents
Method and device for fitting out an aircraft nose compartment in an avionics bay Download PDFInfo
- Publication number
- US20130228655A1 US20130228655A1 US13/750,115 US201313750115A US2013228655A1 US 20130228655 A1 US20130228655 A1 US 20130228655A1 US 201313750115 A US201313750115 A US 201313750115A US 2013228655 A1 US2013228655 A1 US 2013228655A1
- Authority
- US
- United States
- Prior art keywords
- flap
- aerodynamic body
- ancillary flap
- ancillary
- accordance
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
Links
- 230000008878 coupling Effects 0.000 description 5
- 238000010168 coupling process Methods 0.000 description 5
- 238000005859 coupling reaction Methods 0.000 description 5
- 230000005540 biological transmission Effects 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000002349 favourable effect Effects 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 230000001154 acute effect Effects 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D11/00—Passenger or crew accommodation; Flight-deck installations not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/18—Floors
- B64C1/20—Floors specially adapted for freight
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/22—Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing
- B64C9/24—Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing by single flap
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Definitions
- the invention concerns an aerodynamic body with an ancillary flap.
- a drive and guide device for a flap arranged on an aeroplane wing, in particular for a trailing edge flap or a landing flap is of known art.
- the drive and guide device comprises a carriage, on which the flap is held such that it can move, and which can be traversed on a support and guide rail.
- EP 1 312 545 B1 describes an aerodynamic profile with an adjustable flap, which has a front profile region, and also a rear profile region located in the wake flow, and which is bounded by a covering skin on the pressure surface and also the suction surface.
- the pressure surface and suction surface covering skins merge together in the rear profile region into a profile trailing edge.
- the object of the invention is to create an aerodynamic body with an ancillary flap, in which the ancillary flap is particularly favourably arranged aerodynamically and can be actuated in a reliable manner.
- the aerodynamic body in accordance with the invention has at least one ancillary flap arranged on the aerodynamic body such that it can be moved with the aid of a guide mechanism, and a drive device for purposes of actuating the ancillary flap.
- the drive mechanism has a pivotal articulation, by means of which the ancillary flap is articulated on the aerodynamic lifting body such that it can be extended.
- the pivotal articulation of the drive mechanism is arranged in a rear region of the ancillary flap, as viewed in the flow direction.
- the rear region can be the chordwise area of the ancillary flap extending at maximum 20% or preferably 10% of the maximum chord length of the ancillary flap from the leading edge of the ancillary flap.
- the extendable ancillary flap serves the purpose of modifying the lift coefficient of the aerodynamic body under certain cruise conditions.
- the ancillary flap with its articulation on the aerodynamic lifting body in its rear region, acts such that with an airflow in the flow direction a stagnation pressure already occurs ahead of the ancillary flap when the ancillary flap is slightly extended, which contributes to the further extension of the ancillary flap.
- one surface of the ancillary flap which when the ancillary flap is retracted is facing towards an inner surface of the aerodynamic lifting body, is exposed when the ancillary flap is extended to the airflow in the flow direction such that the stagnation pressure forms on this surface of the ancillary flap.
- the guide mechanism can be arranged completely within the aerodynamic body, which is particularly favourable in aerodynamic terms.
- the flow direction corresponds to the direction along which the airflow in the assumed flight state, that is to say, e.g. in cruise flight, flows past the aerodynamic body.
- the guide mechanism serves the purpose of guiding and/or mounting the ancillary flap on the aerodynamic body.
- a trailing edge of the ancillary flap is located particularly far to the rear with reference to the aerodynamic lifting body, which has a favourable effect on the lift and the maximum lift when the ancillary flap is extended.
- this serves as a fairing for the aerodynamic lifting body, as a result of which a separate fairing can be dispensed with.
- This leads to a reduction of the air resistance when the ancillary flap is retracted, for example during cruise flight, which leads to a reduction in the fuel consumption, as a result of which the range of the aeroplane increases.
- the lack of the separate fairing leads to a weight saving, which once again reduces the fuel consumption. Maintainability and manufacturing costs are likewise influenced in a positive manner.
- the aerodynamic body can be a main wing surface of a wing, which in addition to the main wing surface and the ancillary flap can also comprise leading edge slats or further flaps.
- the aerodynamic lifting body is, for example, a leading edge slat of the wing, or one of the flaps of the wing, which are arranged on the main wing surface such that they can be moved.
- the flap on which the ancillary flap is articulated can, for example, be a control flap, and in particular a spoiler, or a high-lift flap, and in particular a trailing edge flap.
- the ancillary flap can also be embodied as a mini trailing edge flap.
- mini trailing edge flap can be embodied such that its chord amounts to 0.3 to 7% of the wing chord of the main wing surface, if the mini trailing edge flap is arranged on the main wing surface, or such that its chord amounts to 0.3 to 7% of the chord of the flap, if the mini trailing edge flap is arranged on a flap.
- the aerodynamic lifting body has a pressure surface and a suction surface. During cruise flight the pressure surface is located on the underside of the aerodynamic lifting body.
- the ancillary flap is preferably arranged on the lower surface of the aerodynamic lifting body. Alternatively the ancillary flap can also be arranged on an upper surface of the aerodynamic lifting body.
- the aerodynamic lifting body has an extension aid, which is designed and arranged such that with its help at least in the retracted state of the ancillary flap a force can be exerted onto the ancillary flap in the extension direction, and thus the ancillary flap can at least partially be extended.
- the ancillary flap can, for example, be extended just to the point at which the airflow in the flow direction can build up the stagnation pressure ahead of the ancillary flap.
- the extension aid comprises, for example, an energy store, which receives and stores energy as the ancillary flap is retracted, and which subsequently uses this stored energy for purposes of extending the ancillary flap at least partially.
- the energy store comprises, for example, an elastic element, in particular a spring, which in the retracted state is supported on the one hand on the ancillary flap, and on the other hand on the aerodynamic lifting body.
- the guide mechanism has a cable, which on the one hand is coupled with the drive device, and on the other hand, with the ancillary flap.
- the cable line can, for example, be a Bowden cable line. This enables an optimal transmission of force from the drive device onto the ancillary flap in a simple manner.
- the cable line is, for example, of an elastic design.
- an axial section of the cable line can take the form of an extensible element. This contributes to the fact that any vibrations occurring on the ancillary flap are not transmitted to the drive device, and that despite any production tolerances occurring the ancillary flap can be fully retracted.
- the cable line can, as viewed in the chordwise direction, be arranged downstream or behind the elastic element and the pivotal articulation. Alternatively the cable line can also be arranged between the elastic element and the pivotal articulation.
- the guide mechanism comprises a connecting lever, and a second and a third pivotal articulation.
- the second pivotal articulation is arranged on the ancillary flap, at some distance from the trailing edge of the ancillary flap, and from a leading edge of the ancillary flap.
- the connecting lever In a first end region of the connecting lever the connecting lever is articulated on the ancillary flap by means of a second pivotal articulation.
- On a second end region located opposite to the first end region the connecting lever is articulated on the aerodynamic lifting body by means of a third pivotal articulation.
- the pivotal articulation, or the third pivotal articulation is arranged on the aerodynamic lifting body such that it can be moved in the chordwise direction.
- FIG. 1 shows a cross-section through a rear region of a first example of embodiment of the aerodynamic body in accordance with the invention with a retracted ancillary flap
- FIG. 2 shows a cross-section through a rear region of a second example of embodiment of the aerodynamic body in accordance with the invention with a retracted ancillary flap
- FIG. 3 shows the second example of embodiment of the aerodynamic body in accordance with the invention in the representation of FIG. 2 with a partially extended ancillary flap
- FIG. 4 shows a cross-section through a rear region of a third example of embodiment of the aerodynamic body in accordance with the invention
- FIG. 5 shows the third example of embodiment of the aerodynamic body in accordance with the invention in the representation of FIG. 4 with a partially extended ancillary flap
- FIG. 6 shows the third example of embodiment of the aerodynamic body in accordance with the invention in the representation of FIG. 4 with a fully extended ancillary flap
- FIG. 7 shows a cross-section through a rear region of a fourth example of embodiment of the aerodynamic body in accordance with the invention with a partially extended ancillary flap
- FIG. 8 shows a cross-section through a rear region of a fifth example of embodiment of the aerodynamic body in accordance with the invention with a partially extended ancillary flap.
- FIG. 9 shows a cross-section through a sixth example of an embodiment of the aerodynamic body.
- FIG. 10 shows the sixth example of the aerodynamic body as per FIG. 9 , wherein the pivotal articulation is displaced further forwards in the chordwise direction TR of the aerodynamic body, in the direction away from the trailing edge of the main wing surface.
- FIG. 1 shows a cross-section through a rear region, as viewed in the chordwise direction TR, of an aerodynamic body in the form of a main wing surface 12 .
- the aerodynamic body can be a main wing 12 of a wing 10 , in particular of a passenger or freight aeroplane.
- the aerodynamic body can be a leading edge slat of the wing 10 , or a flap of the wing 10 , which is arranged on the main wing surface 12 of the wing 10 , for example, a trailing edge flap, or a control flap such as a spoiler.
- An optionally provided trailing edge 18 of the main wing surface 12 is just partially represented and indicated as a dashed line.
- the upper surface of the aerodynamic body or main wing 12 facing a suction surface 81 facing a suction area generated by the flow around the aerodynamic body, and the lower surface facing a pressure surface S 2 , can converge at an acute angle at the trailing edge 18 of the aerodynamic body with the suction surface S 1 .
- the suction surface S 1 and the pressure surface S 2 ensue from the flow around the aerodynamic body 10 , by virtue of a flow incident onto the latter with a flow direction S in accordance with its intended purpose.
- the main wing or the adjustable flap has a first or upper side and a first or upper aerodynamic surface and has a second or lower side and second or lower aerodynamic surface, which is lying or is directed in opposite to the first aerodynamic surface.
- the ancillary flap 14 is coupled to the main wing or the flap, respectively, such that it is located at a second or lower side of the wing or the flap.
- the second or lower side of the ancillary flap 14 is completing the second surface of the main wing or the flap, respectively, when the ancillary flap 14 is in its retracted position so that, in this state, the second or lower side of the ancillary flap 14 is aerodynamically a part of the second surface of the main wing or the flap.
- the guide mechanism 25 comprises a pivotal articulation 16 , by means of which the ancillary flap 14 is articulated on the main wing surface 12 , and in fact in a rear region of the ancillary flap 14 as viewed in the flow direction.
- the pivotal articulation 16 can in particular be stationary fixed position on the ancillary flap 14 and the aerodynamic body, respectively.
- the ancillary flap 14 in its front region, in particular at its leading edge 31 , is coupled with a drive device 24 for purposes of actuating the ancillary flap 14 .
- the drive device 24 enables the ancillary flap 14 to be extended downwards in the direction of the pressure surface S 2 . As soon as the ancillary flap is slightly extended, with an airflow in the flow direction a stagnation pressure occurs ahead of the ancillary flap, which contributes to the further extension of the ancillary flap 14 .
- the length of the ancillary flap 14 can correspond, for example, to between 0.2 and 50 percent of the length of the aerodynamic body in the chordwise direction TR.
- the ancillary flap 14 can be realized as mini flap with a maximum chord length or a mean chord length between 0.2 percent and 5 percent of the mean chord length of the main wing or the flap, respectively, in the spanwise area of the ancillary flap 14 .
- the ancillary flap 14 can be realized as control flap or adjustable flap, being coupled to a main wing or another flap and in particular a high lift flap.
- FIG. 1 the ancillary flap 14 is located in the retracted state.
- the ancillary flap 14 is located in all its positions relative to the of the main wing or the flap, respectively, at the lower surface of the of the main wing or the flap, respectively.
- FIG. 2 shows a cross-section through a second example of embodiment of the aerodynamic lifting body.
- the wing 10 has the main wing surface 12 and the ancillary flap 14 .
- the main wing surface 12 is, for example, the aerodynamic body.
- the ancillary flap 14 in its rear region, as viewed in the flow direction, in particular at its trailing edge 29 , is articulated on the main wing surface 12 by means of the pivotal articulation 16 . If the wing 10 has a trailing edge flap (not represented), the ancillary flap 14 can also be articulated on the trailing edge flap.
- the guide mechanism 25 has a pivotal articulation 16 , a second pivotal articulation 27 , a third pivotal articulation 21 , and a connecting lever 23 .
- the connecting lever 23 can also be denoted as a regulating rod.
- the ancillary flap 14 is articulated at some distance from its leading edge 31 , by means of the second pivotal articulation 27 on the connecting lever 23 , in particular on a first end region of the connecting lever 23 .
- On a second end region of the connecting lever 23 the latter is articulated, by means of the third pivotal articulation 21 , on a slide 19 .
- the slide 19 is guided by a guide device, in particular a guide rail 17 , being mounted to or arranged at the aerodynamic body such that it can be moved in the chordwise direction TR of the aerodynamic body.
- the drive device 24 enables the slide 19 to move in the chordwise direction TR with the aid of a stroke rod 15 .
- the connecting lever 23 and a straight line through the pivotal articulation 16 and the second pivotal articulation 29 , 27 subtend a transmission angle ⁇ , which is preferably greater than 5 degrees, in order that the guide mechanism 25 is not operating in its dead-centre position.
- the length of the connecting lever 23 corresponds, for example, to between 1 ⁇ 4 and 3 ⁇ 4 of the length of the ancillary flap 14 .
- FIG. 3 shows the second example of embodiment of the aerodynamic body as per FIG. 2 , wherein the slide 19 is displaced in the chordwise direction TR of the aerodynamic body 10 further rearwards in the direction towards the trailing edge 18 of the main wing surface 12 .
- FIG. 4 shows a cross-section through a third example of embodiment of the aerodynamic body.
- the wing 10 has the main wing surface 12 and the ancillary flap 14 , wherein the main wing surface 12 represents the aerodynamic body.
- the ancillary flap 14 in its rear region, as viewed in the flow direction, in particular at its trailing edge 29 , is articulated on the main wing surface 12 by means of the pivotal articulation 16 . If the wing 10 has a trailing edge flap, the ancillary flap 14 can thus also be articulated on the trailing edge flap.
- the ancillary flap 14 is attached to a cable line 26 at a coupling location at some distance from its leading edge 31 .
- the cable line 26 is designed such that it can extend and/or the cable line 26 comprises an axial section, which is replaced by an extensible element 30 .
- the cable line 26 can be designed as a Bowden cable line.
- the cable line 26 is coupled with the drive device 24 , with the aid of which the cable line 26 can be subjected to a tensile force, or with the aid of which the tensile force can be removed.
- the ancillary flap 14 is coupled with an extension aid.
- the extension aid enables the ancillary flap 14 to extend from its retracted setting.
- the extension aid comprises for example, an energy store, in particular an elastic element 20 , which is supported on the one hand on the retracted ancillary flap 14 , and on the other hand on a spring mounting 22 , which is securely connected with the main wing surface 12 .
- the elastic element 20 comprises a spring, which in the retracted setting is pre-stressed between the ancillary flap 14 , and the spring mounting 22 , and which subjects the ancillary flap 14 to a force in the extension direction.
- the extension aid can have an eccentric, with the aid of which the ancillary flap 14 can be moved out of its retracted state.
- the chordwise direction TR of the aerodynamic body 10 are arranged, starting from the trailing edge 18 of the aerodynamic body 10 , firstly the pivotal articulation 16 , then the extension aid, and then the coupling location for the cable line 26 .
- FIG. 5 shows the third example of embodiment of the aerodynamic body as per FIG. 4 , with a partially extended ancillary flap 14 .
- the ancillary flap 14 subtends the extension angle ⁇ , which in the partially extended setting is, for example, 30 degrees. In such a partially extended setting the extension aid no longer acts on the ancillary flap 14 .
- the stagnation pressure is utilised in this example of embodiment; this builds during the flight of the aeroplane as a result of the airflow that flows past the lower surface of the aerodynamic body, namely the pressure surface S 2 , and extends the ancillary flap 14 further.
- the extension angle ⁇ is a function of an effective length of the cable line 26 .
- the effective length corresponds to the length that the cable line 26 has between the ancillary flap 14 , and the drive device 24 .
- FIG. 6 shows the third example of embodiment of the aerodynamic body as per FIGS. 4 and 5 , wherein the ancillary flap 14 is located in the fully extended state.
- the extension angle ⁇ is approximately equal to 90 degrees.
- the extension angle ⁇ can also be more or less than 90 degrees.
- the cable line 26 is subjected to a tensile force with the aid of the drive device 24 , at least until the ancillary flap 14 pre-stresses the elastic element 20 , in order that a renewed extension of the ancillary flap 14 is reliably possible.
- FIG. 7 shows a cross-section through a fourth example of embodiment of the aerodynamic body, which, for example, is once again designed as a main wing surface 12 of the wing 10 .
- the ancillary flap 14 in its rear region, in particular at its trailing edge 29 , is articulated on the main wing surface 12 by means of the pivotal articulation 16 .
- the rear region of the ancillary flap 14 can in particular be a region extending at maximum 20% and preferably 10% of the maximum chord length of the ancillary flap 14 from the leading edge of the same. If the wing 10 has a trailing edge flap, the ancillary flap 14 can thus also be articulated on the trailing edge flap, which then represents the aerodynamic body.
- the ancillary flap 14 is attached to the cable line 26 at some distance from its leading edge 31 .
- the cable line 26 is designed such that it can extend, and does not comprise an extensible element 30 .
- the cable line 26 is coupled with the drive device 24 , with the aid of which the cable line 26 can be subjected to a tensile force, or with the aid of which the tensile force can be removed.
- the extension aid enables the ancillary flap 14 to extend from its retracted setting.
- the extension aid comprises for example, an energy store, in particular the elastic element 20 , which is supported on the one hand on the retracted ancillary flap 14 , and on the other hand on the spring mounting 22 .
- the elastic element 20 comprises a spring, which in the retracted setting is pre-stressed between the ancillary flap 14 and the spring mounting 22 , and which subjects the ancillary flap 14 to a force in the extension direction.
- the extension aid can have an eccentric. In the chordwise direction TR of the aerodynamic body 10 are arranged, starting from the trailing edge 18 of the main wing surface 12 , firstly the pivotal articulation 16 , then the extension aid, and then the coupling location for the cable line 26 .
- FIG. 8 shows a cross-section through a fifth example of embodiment of the aerodynamic body, which, for example, is once again designed as a main wing surface 12 of the wing 10 .
- the ancillary flap 14 in its rear region, as viewed in the flow direction, in particular at its trailing edge 29 , is articulated by means of the pivotal articulation 16 on the main wing surface 12 . If the wing 10 has a trailing edge flap, the ancillary flap 14 can thus also be articulated on the trailing edge flap.
- the ancillary flap 14 is attached to the cable line 26 at some distance from its leading edge 31 .
- the cable line 26 is designed such that it can extend and comprises the extensible element 30 .
- the cable line 26 is coupled with the drive device 24 , with the aid of which the cable line 26 can be subjected to a tensile force, or with the aid of which the tensile force can be removed.
- the cable line 26 can also be designed as a Bowden cable line.
- the extension aid enables the ancillary flap 14 to extend from its retracted setting.
- the extension aid comprises for example, an energy store, in particular the elastic element 20 , which is supported on the one hand on the retracted ancillary flap 14 , and on the other hand on the spring mounting 22 .
- the elastic element 20 comprises a spring, which in the retracted setting is pre-stressed between the ancillary flap 14 and the spring mounting 22 , and which subjects the ancillary flap 14 to a force in the extension direction.
- the extension aid can comprise an eccentric. In the chordwise direction TR are arranged, starting from the trailing edge 18 of the aerodynamic body, firstly the pivotal articulation 16 , then the coupling location for the cable line 26 , and then the extension aid.
- FIG. 9 shows a cross-section through a sixth example of embodiment of the aerodynamic body.
- the wing 10 has the main wing surface 12 and the ancillary flap 14 .
- the main wing surface 12 is, for example, the aerodynamic body.
- the ancillary flap 14 in its rear region, as viewed in the flow direction, in particular at its trailing edge 29 , is articulated by means of the pivotal articulation 16 on the main wing surface 12 . If the wing 10 has a trailing edge flap, the ancillary flap 14 can thus also be articulated on the trailing edge flap, which then represents the aerodynamic body.
- the guide mechanism 25 has a pivotal articulation 16 , the second pivotal articulation 27 , the third pivotal articulation 21 , and the connecting lever 23 .
- the ancillary flap 14 is articulated on the connecting lever 23 , at some distance from its leading edge 31 , by means of the second pivotal articulation 27 , in particular it is articulated on a first end region of the connecting lever 23 .
- the latter is articulated on the main wing surface 12 , by means of the third pivotal articulation 21 .
- the pivotal articulation 16 is arranged on the main wing surface 12 such that it can be moved in the chordwise direction TR.
- the drive device 24 enables the pivotal articulation 16 to be moved in the chordwise direction TR with the aid of the stroke rod 15 .
- the connecting lever 23 and a straight line through the pivotal articulation 16 and the second pivotal articulation 27 subtend a transmission angle ⁇ , which is preferably greater than 5 degrees, in order that the guide mechanism 25 is not operating in its dead-centre position.
- the length of the connecting lever 23 corresponds, for example, to between 1 ⁇ 4 and 3 ⁇ 4 of the length of the ancillary flap 14 .
- FIG. 10 shows the sixth example of embodiment of the aerodynamic body as per FIG. 9 , wherein the pivotal articulation 16 is displaced further forwards in the chordwise direction TR of the aerodynamic body 10 , in the direction away from the trailing edge 18 of the main wing surface 12 .
- extension aid can be driven electrically or hydraulically, and can be electronically controlled.
Abstract
Description
- This application is a continuation of and claims priority to PCT Application No. PCT/EP2011/003741, filed Jul. 26, 2011, which claims the benefit of the filing date of German Patent Application No. DE 10 2010 032 225.3 filed Jul. 26, 2010 and of U.S. Provisional Patent Application No. 61/367,504 filed Jul. 26, 2010, the disclosures of which applications are hereby incorporated herein by reference.
- The invention concerns an aerodynamic body with an ancillary flap.
- From DE 41 07 556 C1 a drive and guide device for a flap arranged on an aeroplane wing, in particular for a trailing edge flap or a landing flap, is of known art. The drive and guide device comprises a carriage, on which the flap is held such that it can move, and which can be traversed on a support and guide rail.
-
EP 1 312 545 B1 describes an aerodynamic profile with an adjustable flap, which has a front profile region, and also a rear profile region located in the wake flow, and which is bounded by a covering skin on the pressure surface and also the suction surface. The pressure surface and suction surface covering skins merge together in the rear profile region into a profile trailing edge. - The object of the invention is to create an aerodynamic body with an ancillary flap, in which the ancillary flap is particularly favourably arranged aerodynamically and can be actuated in a reliable manner.
- This object is achieved with the features of
Claim 1. Further forms of embodiment are specified in the dependent claims. - The aerodynamic body in accordance with the invention has at least one ancillary flap arranged on the aerodynamic body such that it can be moved with the aid of a guide mechanism, and a drive device for purposes of actuating the ancillary flap. The drive mechanism has a pivotal articulation, by means of which the ancillary flap is articulated on the aerodynamic lifting body such that it can be extended. Here provision is made that the pivotal articulation of the drive mechanism is arranged in a rear region of the ancillary flap, as viewed in the flow direction. The rear region can be the chordwise area of the ancillary flap extending at maximum 20% or preferably 10% of the maximum chord length of the ancillary flap from the leading edge of the ancillary flap.
- The extendable ancillary flap serves the purpose of modifying the lift coefficient of the aerodynamic body under certain cruise conditions. The ancillary flap, with its articulation on the aerodynamic lifting body in its rear region, acts such that with an airflow in the flow direction a stagnation pressure already occurs ahead of the ancillary flap when the ancillary flap is slightly extended, which contributes to the further extension of the ancillary flap. Thus one surface of the ancillary flap, which when the ancillary flap is retracted is facing towards an inner surface of the aerodynamic lifting body, is exposed when the ancillary flap is extended to the airflow in the flow direction such that the stagnation pressure forms on this surface of the ancillary flap.
- This enables the drive device for purposes of actuating the ancillary flap to be of a relatively simple design. This can contribute to the production of the drive device in a light and space-saving manner, and/or to the ability to open the ancillary flap reliably. Furthermore, by this means the guide mechanism can be arranged completely within the aerodynamic body, which is particularly favourable in aerodynamic terms. The flow direction corresponds to the direction along which the airflow in the assumed flight state, that is to say, e.g. in cruise flight, flows past the aerodynamic body. The guide mechanism serves the purpose of guiding and/or mounting the ancillary flap on the aerodynamic body.
- Furthermore as a result of the coupling of the ancillary flap in its rear region in the chordwise direction of the aerodynamic body, a trailing edge of the ancillary flap, as viewed in the flow direction, is located particularly far to the rear with reference to the aerodynamic lifting body, which has a favourable effect on the lift and the maximum lift when the ancillary flap is extended. When the ancillary flap is retracted this serves as a fairing for the aerodynamic lifting body, as a result of which a separate fairing can be dispensed with. This leads to a reduction of the air resistance when the ancillary flap is retracted, for example during cruise flight, which leads to a reduction in the fuel consumption, as a result of which the range of the aeroplane increases. Furthermore, the lack of the separate fairing leads to a weight saving, which once again reduces the fuel consumption. Maintainability and manufacturing costs are likewise influenced in a positive manner.
- The aerodynamic body can be a main wing surface of a wing, which in addition to the main wing surface and the ancillary flap can also comprise leading edge slats or further flaps. Alternatively, the aerodynamic lifting body is, for example, a leading edge slat of the wing, or one of the flaps of the wing, which are arranged on the main wing surface such that they can be moved. The flap on which the ancillary flap is articulated, can, for example, be a control flap, and in particular a spoiler, or a high-lift flap, and in particular a trailing edge flap. In this context the ancillary flap can also be embodied as a mini trailing edge flap. Here the mini trailing edge flap can be embodied such that its chord amounts to 0.3 to 7% of the wing chord of the main wing surface, if the mini trailing edge flap is arranged on the main wing surface, or such that its chord amounts to 0.3 to 7% of the chord of the flap, if the mini trailing edge flap is arranged on a flap.
- The aerodynamic lifting body has a pressure surface and a suction surface. During cruise flight the pressure surface is located on the underside of the aerodynamic lifting body. The ancillary flap is preferably arranged on the lower surface of the aerodynamic lifting body. Alternatively the ancillary flap can also be arranged on an upper surface of the aerodynamic lifting body.
- In accordance with one example of embodiment the aerodynamic lifting body has an extension aid, which is designed and arranged such that with its help at least in the retracted state of the ancillary flap a force can be exerted onto the ancillary flap in the extension direction, and thus the ancillary flap can at least partially be extended. Here with the help of the extension aid the ancillary flap can, for example, be extended just to the point at which the airflow in the flow direction can build up the stagnation pressure ahead of the ancillary flap. In this context the extension aid comprises, for example, an energy store, which receives and stores energy as the ancillary flap is retracted, and which subsequently uses this stored energy for purposes of extending the ancillary flap at least partially. The energy store comprises, for example, an elastic element, in particular a spring, which in the retracted state is supported on the one hand on the ancillary flap, and on the other hand on the aerodynamic lifting body.
- In accordance with a further example of embodiment the guide mechanism has a cable, which on the one hand is coupled with the drive device, and on the other hand, with the ancillary flap. With the aid of the drive device and the cable line a force can be exerted on the ancillary flap in the retraction direction. The cable line can, for example, be a Bowden cable line. This enables an optimal transmission of force from the drive device onto the ancillary flap in a simple manner. The cable line is, for example, of an elastic design. Alternatively, an axial section of the cable line can take the form of an extensible element. This contributes to the fact that any vibrations occurring on the ancillary flap are not transmitted to the drive device, and that despite any production tolerances occurring the ancillary flap can be fully retracted.
- Starting from a trailing edge of the aerodynamic body with the ancillary flap retracted, the cable line can, as viewed in the chordwise direction, be arranged downstream or behind the elastic element and the pivotal articulation. Alternatively the cable line can also be arranged between the elastic element and the pivotal articulation.
- In an alternative example of embodiment the guide mechanism comprises a connecting lever, and a second and a third pivotal articulation. The second pivotal articulation is arranged on the ancillary flap, at some distance from the trailing edge of the ancillary flap, and from a leading edge of the ancillary flap. In a first end region of the connecting lever the connecting lever is articulated on the ancillary flap by means of a second pivotal articulation. On a second end region located opposite to the first end region the connecting lever is articulated on the aerodynamic lifting body by means of a third pivotal articulation. The pivotal articulation, or the third pivotal articulation, is arranged on the aerodynamic lifting body such that it can be moved in the chordwise direction.
- In what follows examples of embodiment of the invention are described with the aid of the accompanying figures. In the figures:
-
FIG. 1 shows a cross-section through a rear region of a first example of embodiment of the aerodynamic body in accordance with the invention with a retracted ancillary flap, -
FIG. 2 shows a cross-section through a rear region of a second example of embodiment of the aerodynamic body in accordance with the invention with a retracted ancillary flap, -
FIG. 3 shows the second example of embodiment of the aerodynamic body in accordance with the invention in the representation ofFIG. 2 with a partially extended ancillary flap, -
FIG. 4 shows a cross-section through a rear region of a third example of embodiment of the aerodynamic body in accordance with the invention, -
FIG. 5 shows the third example of embodiment of the aerodynamic body in accordance with the invention in the representation ofFIG. 4 with a partially extended ancillary flap, -
FIG. 6 shows the third example of embodiment of the aerodynamic body in accordance with the invention in the representation ofFIG. 4 with a fully extended ancillary flap, -
FIG. 7 shows a cross-section through a rear region of a fourth example of embodiment of the aerodynamic body in accordance with the invention with a partially extended ancillary flap, -
FIG. 8 shows a cross-section through a rear region of a fifth example of embodiment of the aerodynamic body in accordance with the invention with a partially extended ancillary flap. -
FIG. 9 shows a cross-section through a sixth example of an embodiment of the aerodynamic body. -
FIG. 10 shows the sixth example of the aerodynamic body as perFIG. 9 , wherein the pivotal articulation is displaced further forwards in the chordwise direction TR of the aerodynamic body, in the direction away from the trailing edge of the main wing surface. - Elements of the same design or function are allocated the same reference symbols across the figures. For purposes of describing the aerodynamic body in accordance with the invention reference is made to the coordinate system KS registered e.g. in
FIG. 1 , with a spanwise direction SW, a chordwise direction TR, and a wing thickness direction DR of the aerodynamic body respectively. -
FIG. 1 shows a cross-section through a rear region, as viewed in the chordwise direction TR, of an aerodynamic body in the form of amain wing surface 12. The aerodynamic body can be amain wing 12 of awing 10, in particular of a passenger or freight aeroplane. Alternatively, the aerodynamic body can be a leading edge slat of thewing 10, or a flap of thewing 10, which is arranged on themain wing surface 12 of thewing 10, for example, a trailing edge flap, or a control flap such as a spoiler. An optionally provided trailingedge 18 of themain wing surface 12 is just partially represented and indicated as a dashed line. The upper surface of the aerodynamic body ormain wing 12 facing a suction surface 81 facing a suction area generated by the flow around the aerodynamic body, and the lower surface facing a pressure surface S2, can converge at an acute angle at the trailingedge 18 of the aerodynamic body with the suction surface S1. The suction surface S1 and the pressure surface S2 ensue from the flow around theaerodynamic body 10, by virtue of a flow incident onto the latter with a flow direction S in accordance with its intended purpose. - Generally, the main wing or the adjustable flap has a first or upper side and a first or upper aerodynamic surface and has a second or lower side and second or lower aerodynamic surface, which is lying or is directed in opposite to the first aerodynamic surface. The
ancillary flap 14 is coupled to the main wing or the flap, respectively, such that it is located at a second or lower side of the wing or the flap. Preferably, the second or lower side of theancillary flap 14 is completing the second surface of the main wing or the flap, respectively, when theancillary flap 14 is in its retracted position so that, in this state, the second or lower side of theancillary flap 14 is aerodynamically a part of the second surface of the main wing or the flap. - The
guide mechanism 25 comprises apivotal articulation 16, by means of which theancillary flap 14 is articulated on themain wing surface 12, and in fact in a rear region of theancillary flap 14 as viewed in the flow direction. Thepivotal articulation 16 can in particular be stationary fixed position on theancillary flap 14 and the aerodynamic body, respectively. Theancillary flap 14 in its front region, in particular at its leadingedge 31, is coupled with adrive device 24 for purposes of actuating theancillary flap 14. Thedrive device 24 enables theancillary flap 14 to be extended downwards in the direction of the pressure surface S2. As soon as the ancillary flap is slightly extended, with an airflow in the flow direction a stagnation pressure occurs ahead of the ancillary flap, which contributes to the further extension of theancillary flap 14. - The length of the
ancillary flap 14 can correspond, for example, to between 0.2 and 50 percent of the length of the aerodynamic body in the chordwise direction TR. In particular, theancillary flap 14 can be realized as mini flap with a maximum chord length or a mean chord length between 0.2 percent and 5 percent of the mean chord length of the main wing or the flap, respectively, in the spanwise area of theancillary flap 14. Alternatively, theancillary flap 14 can be realized as control flap or adjustable flap, being coupled to a main wing or another flap and in particular a high lift flap. InFIG. 1 theancillary flap 14 is located in the retracted state. In particular, theancillary flap 14 is located in all its positions relative to the of the main wing or the flap, respectively, at the lower surface of the of the main wing or the flap, respectively. -
FIG. 2 shows a cross-section through a second example of embodiment of the aerodynamic lifting body. Thewing 10 has themain wing surface 12 and theancillary flap 14. In this context themain wing surface 12 is, for example, the aerodynamic body. Theancillary flap 14, in its rear region, as viewed in the flow direction, in particular at its trailingedge 29, is articulated on themain wing surface 12 by means of thepivotal articulation 16. If thewing 10 has a trailing edge flap (not represented), theancillary flap 14 can also be articulated on the trailing edge flap. In this example of embodiment theguide mechanism 25 has apivotal articulation 16, a secondpivotal articulation 27, a thirdpivotal articulation 21, and a connectinglever 23. The connectinglever 23 can also be denoted as a regulating rod. Theancillary flap 14 is articulated at some distance from its leadingedge 31, by means of the secondpivotal articulation 27 on the connectinglever 23, in particular on a first end region of the connectinglever 23. On a second end region of the connectinglever 23 the latter is articulated, by means of the thirdpivotal articulation 21, on aslide 19. Theslide 19 is guided by a guide device, in particular aguide rail 17, being mounted to or arranged at the aerodynamic body such that it can be moved in the chordwise direction TR of the aerodynamic body. Thedrive device 24 enables theslide 19 to move in the chordwise direction TR with the aid of astroke rod 15. The connectinglever 23 and a straight line through thepivotal articulation 16 and the secondpivotal articulation guide mechanism 25 is not operating in its dead-centre position. The length of the connectinglever 23 corresponds, for example, to between ¼ and ¾ of the length of theancillary flap 14. -
FIG. 3 shows the second example of embodiment of the aerodynamic body as perFIG. 2 , wherein theslide 19 is displaced in the chordwise direction TR of theaerodynamic body 10 further rearwards in the direction towards the trailingedge 18 of themain wing surface 12. This causes theancillary flap 14 to be partially swung out. In the partially extended setting theancillary flap 14, and a lower surface of themain wing surface 12, facing the pressure surface S2, subtend an extension angle of, for example, 30 degrees. -
FIG. 4 shows a cross-section through a third example of embodiment of the aerodynamic body. Thewing 10 has themain wing surface 12 and theancillary flap 14, wherein themain wing surface 12 represents the aerodynamic body. Theancillary flap 14, in its rear region, as viewed in the flow direction, in particular at its trailingedge 29, is articulated on themain wing surface 12 by means of thepivotal articulation 16. If thewing 10 has a trailing edge flap, theancillary flap 14 can thus also be articulated on the trailing edge flap. Theancillary flap 14 is attached to acable line 26 at a coupling location at some distance from its leadingedge 31. Thecable line 26 is designed such that it can extend and/or thecable line 26 comprises an axial section, which is replaced by anextensible element 30. Alternatively thecable line 26 can be designed as a Bowden cable line. At its opposite end thecable line 26 is coupled with thedrive device 24, with the aid of which thecable line 26 can be subjected to a tensile force, or with the aid of which the tensile force can be removed. - At some distance from the trailing
edge 29 of theancillary flap 14 theancillary flap 14 is coupled with an extension aid. The extension aid enables theancillary flap 14 to extend from its retracted setting. For this purpose the extension aid comprises for example, an energy store, in particular anelastic element 20, which is supported on the one hand on the retractedancillary flap 14, and on the other hand on a spring mounting 22, which is securely connected with themain wing surface 12. In a simple variant of embodiment theelastic element 20 comprises a spring, which in the retracted setting is pre-stressed between theancillary flap 14, and the spring mounting 22, and which subjects theancillary flap 14 to a force in the extension direction. Alternatively the extension aid can have an eccentric, with the aid of which theancillary flap 14 can be moved out of its retracted state. In the chordwise direction TR of theaerodynamic body 10 are arranged, starting from the trailingedge 18 of theaerodynamic body 10, firstly thepivotal articulation 16, then the extension aid, and then the coupling location for thecable line 26. -
FIG. 5 shows the third example of embodiment of the aerodynamic body as perFIG. 4 , with a partially extendedancillary flap 14. With the lower surface of themain wing surface 12 theancillary flap 14 subtends the extension angle β, which in the partially extended setting is, for example, 30 degrees. In such a partially extended setting the extension aid no longer acts on theancillary flap 14. For purposes of the further extension of theancillary flap 14 the stagnation pressure is utilised in this example of embodiment; this builds during the flight of the aeroplane as a result of the airflow that flows past the lower surface of the aerodynamic body, namely the pressure surface S2, and extends theancillary flap 14 further. Here the extension angle β is a function of an effective length of thecable line 26. The effective length corresponds to the length that thecable line 26 has between theancillary flap 14, and thedrive device 24. -
FIG. 6 shows the third example of embodiment of the aerodynamic body as perFIGS. 4 and 5 , wherein theancillary flap 14 is located in the fully extended state. In the fully extended state the extension angle β is approximately equal to 90 degrees. In the fully extended state the extension angle β can also be more or less than 90 degrees. For purposes of retracting theancillary flap 14 thecable line 26 is subjected to a tensile force with the aid of thedrive device 24, at least until theancillary flap 14 pre-stresses theelastic element 20, in order that a renewed extension of theancillary flap 14 is reliably possible. -
FIG. 7 shows a cross-section through a fourth example of embodiment of the aerodynamic body, which, for example, is once again designed as amain wing surface 12 of thewing 10. Theancillary flap 14, in its rear region, in particular at its trailingedge 29, is articulated on themain wing surface 12 by means of thepivotal articulation 16. In this application, the rear region of theancillary flap 14 can in particular be a region extending at maximum 20% and preferably 10% of the maximum chord length of theancillary flap 14 from the leading edge of the same. If thewing 10 has a trailing edge flap, theancillary flap 14 can thus also be articulated on the trailing edge flap, which then represents the aerodynamic body. Theancillary flap 14 is attached to thecable line 26 at some distance from its leadingedge 31. Thecable line 26 is designed such that it can extend, and does not comprise anextensible element 30. At its opposite end thecable line 26 is coupled with thedrive device 24, with the aid of which thecable line 26 can be subjected to a tensile force, or with the aid of which the tensile force can be removed. - At some distance from the trailing
edge 29 of theancillary flap 14 theancillary flap 14 is coupled with the extension aid. The extension aid enables theancillary flap 14 to extend from its retracted setting. For this purpose the extension aid comprises for example, an energy store, in particular theelastic element 20, which is supported on the one hand on the retractedancillary flap 14, and on the other hand on the spring mounting 22. In a simple variant of embodiment theelastic element 20 comprises a spring, which in the retracted setting is pre-stressed between theancillary flap 14 and the spring mounting 22, and which subjects theancillary flap 14 to a force in the extension direction. Alternatively, the extension aid can have an eccentric. In the chordwise direction TR of theaerodynamic body 10 are arranged, starting from the trailingedge 18 of themain wing surface 12, firstly thepivotal articulation 16, then the extension aid, and then the coupling location for thecable line 26. -
FIG. 8 shows a cross-section through a fifth example of embodiment of the aerodynamic body, which, for example, is once again designed as amain wing surface 12 of thewing 10. Theancillary flap 14, in its rear region, as viewed in the flow direction, in particular at its trailingedge 29, is articulated by means of thepivotal articulation 16 on themain wing surface 12. If thewing 10 has a trailing edge flap, theancillary flap 14 can thus also be articulated on the trailing edge flap. Theancillary flap 14 is attached to thecable line 26 at some distance from its leadingedge 31. Thecable line 26 is designed such that it can extend and comprises theextensible element 30. At its opposite end thecable line 26 is coupled with thedrive device 24, with the aid of which thecable line 26 can be subjected to a tensile force, or with the aid of which the tensile force can be removed. Thecable line 26 can also be designed as a Bowden cable line. - At some distance from the leading
edge 31 of theancillary flap 14 theancillary flap 14 is coupled with the extension aid. The extension aid enables theancillary flap 14 to extend from its retracted setting. For this purpose the extension aid comprises for example, an energy store, in particular theelastic element 20, which is supported on the one hand on the retractedancillary flap 14, and on the other hand on the spring mounting 22. In a simple variant of embodiment theelastic element 20 comprises a spring, which in the retracted setting is pre-stressed between theancillary flap 14 and the spring mounting 22, and which subjects theancillary flap 14 to a force in the extension direction. Alternatively, the extension aid can comprise an eccentric. In the chordwise direction TR are arranged, starting from the trailingedge 18 of the aerodynamic body, firstly thepivotal articulation 16, then the coupling location for thecable line 26, and then the extension aid. -
FIG. 9 shows a cross-section through a sixth example of embodiment of the aerodynamic body. Thewing 10 has themain wing surface 12 and theancillary flap 14. In this context themain wing surface 12 is, for example, the aerodynamic body. Theancillary flap 14, in its rear region, as viewed in the flow direction, in particular at its trailingedge 29, is articulated by means of thepivotal articulation 16 on themain wing surface 12. If thewing 10 has a trailing edge flap, theancillary flap 14 can thus also be articulated on the trailing edge flap, which then represents the aerodynamic body. In this example of embodiment theguide mechanism 25 has apivotal articulation 16, the secondpivotal articulation 27, the thirdpivotal articulation 21, and the connectinglever 23. Theancillary flap 14 is articulated on the connectinglever 23, at some distance from its leadingedge 31, by means of the secondpivotal articulation 27, in particular it is articulated on a first end region of the connectinglever 23. At a second end region of the connectinglever 23 the latter is articulated on themain wing surface 12, by means of the thirdpivotal articulation 21. Thepivotal articulation 16 is arranged on themain wing surface 12 such that it can be moved in the chordwise direction TR. Thedrive device 24 enables thepivotal articulation 16 to be moved in the chordwise direction TR with the aid of thestroke rod 15. The connectinglever 23 and a straight line through thepivotal articulation 16 and the secondpivotal articulation 27 subtend a transmission angle α, which is preferably greater than 5 degrees, in order that theguide mechanism 25 is not operating in its dead-centre position. The length of the connectinglever 23 corresponds, for example, to between ¼ and ¾ of the length of theancillary flap 14. -
FIG. 10 shows the sixth example of embodiment of the aerodynamic body as perFIG. 9 , wherein thepivotal articulation 16 is displaced further forwards in the chordwise direction TR of theaerodynamic body 10, in the direction away from the trailingedge 18 of themain wing surface 12. This causes theancillary flap 14 to be partially extended. In the partially extended setting theancillary flap 14 and the lower surface of themain wing surface 12 subtend an extension angle of, for example, 30 degrees. - The invention is not limited to the examples of embodiment specified. For example, features of different examples of embodiment can be combined with one another so as to complement one another. Furthermore, the extension aid can be driven electrically or hydraulically, and can be electronically controlled.
-
-
- 10 Wing
- 12 Main wing surface
- 14 Ancillary flap
- 15 Stroke rod
- 16 Pivotal articulation
- 17 Guide rail
- 18 Main wing surface trailing edge
- 19 Slide
- 20 Elastic element
- 21 Third pivotal articulation
- 22 Spring mounting
- 23 Connecting lever
- 24 Drive device
- 25 Guide mechanism
- 26 Cable line
- 27 Second pivotal articulation
- 28 Turning roller
- 29 Ancillary flap trailing edge
- 30 Extensible element
- 31 Ancillary flap leading edge
- S1 Suction surface
- S2 Pressure surface
- TR Chordwise direction
- SR Spanwise direction
- DR Thickness direction
- α Transmission angle
- β Extension angle
Claims (14)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US14/620,021 US9878790B2 (en) | 2010-07-27 | 2015-02-11 | Method and device for fitting out an aircraft nose compartment in an avionics bay |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1056141A FR2963314B1 (en) | 2010-07-27 | 2010-07-27 | METHOD AND DEVICE FOR ARRANGING AN AIRCRAFT AVONIC TILT BEFORE AN AIRCRAFT |
FR1056141 | 2010-07-27 | ||
PCT/FR2011/051795 WO2012022891A1 (en) | 2010-07-27 | 2011-07-26 | Method and device for fitting out an aircraft nose compartment in an avionics bay |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2011/051795 Continuation WO2012022891A1 (en) | 2010-07-27 | 2011-07-26 | Method and device for fitting out an aircraft nose compartment in an avionics bay |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US14/620,021 Continuation US9878790B2 (en) | 2010-07-27 | 2015-02-11 | Method and device for fitting out an aircraft nose compartment in an avionics bay |
Publications (1)
Publication Number | Publication Date |
---|---|
US20130228655A1 true US20130228655A1 (en) | 2013-09-05 |
Family
ID=43735829
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/750,115 Abandoned US20130228655A1 (en) | 2010-07-27 | 2013-01-25 | Method and device for fitting out an aircraft nose compartment in an avionics bay |
US14/620,021 Active US9878790B2 (en) | 2010-07-27 | 2015-02-11 | Method and device for fitting out an aircraft nose compartment in an avionics bay |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US14/620,021 Active US9878790B2 (en) | 2010-07-27 | 2015-02-11 | Method and device for fitting out an aircraft nose compartment in an avionics bay |
Country Status (5)
Country | Link |
---|---|
US (2) | US20130228655A1 (en) |
EP (1) | EP2598398B1 (en) |
CN (1) | CN103079953B (en) |
FR (1) | FR2963314B1 (en) |
WO (1) | WO2012022891A1 (en) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20130214092A1 (en) * | 2010-07-26 | 2013-08-22 | Airbus Operations Gmbh | Aerodynamic body with an ancillary flap |
US20130266444A1 (en) * | 2010-07-26 | 2013-10-10 | Airbus Operations Gmbh | Aerodynamic body with an ancillary flap |
US20160298646A1 (en) * | 2015-04-08 | 2016-10-13 | General Electric Company | Gas turbine diffuser and methods of assembling the same |
US9878790B2 (en) | 2010-07-27 | 2018-01-30 | Airbus Operations (S.A.S.) | Method and device for fitting out an aircraft nose compartment in an avionics bay |
US20220212773A1 (en) * | 2021-01-06 | 2022-07-07 | The Boeing Company | Aircraft keel beam assembly |
Families Citing this family (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3035072B1 (en) * | 2015-04-20 | 2020-09-18 | Airbus Operations Sas | AIRCRAFT WITH IMPROVED UNDER CABIN SPACE ARCHITECTURE |
FR3064596A1 (en) * | 2017-03-31 | 2018-10-05 | Airbus Operations | FRONT LANDING TRAIN OF REDUCED HEIGHT AND AIRCRAFT, IN PARTICULAR FLYING WING, EQUIPPED WITH SUCH A FRONT TRAIN |
FR3082824A1 (en) * | 2018-06-20 | 2019-12-27 | Airbus Operations | TRANSVERSE CHASSIS FOR AN AVIONIC HOLDER OF AN AIRCRAFT, ASSEMBLY MODULE AND AIRCRAFT COMPRISING SAID TRANSVERSE CHASSIS |
CN109720538B (en) * | 2018-11-12 | 2023-08-01 | 中航通飞华南飞机工业有限公司 | Built-in wheel cabin structure of aircraft fuselage side |
JPWO2020183628A1 (en) * | 2019-03-13 | 2021-10-14 | 株式会社Pfu | Image processing device, image reading device, image processing method, and program |
FR3097839B1 (en) * | 2019-06-26 | 2021-07-02 | Airbus Operations Sas | PART OF AIRCRAFT INCLUDING AN INTERIOR MODULE WITH IMPROVED FIXATION |
FR3128442B1 (en) | 2021-10-21 | 2024-01-19 | Airbus Operations Sas | AIRCRAFT CARGO COMPRISING AT LEAST ONE FURNITURE ARRANGED LONGITUDINALLY AND MOVEABLE TRANSVERSALLY AND METHOD FOR ARRANGING IT |
FR3130753A1 (en) * | 2021-12-17 | 2023-06-23 | Airbus Operations (S.A.S.) | Aircraft comprising at least one system cabinet connected by at least one connecting system to a rail of a floor |
Family Cites Families (28)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1837186A (en) | 1927-11-28 | 1931-12-22 | Alfaro Heraclio | Aeroplane |
US1875593A (en) | 1930-07-31 | 1932-09-06 | Randolph F Hall | Airplane |
US2011902A (en) | 1933-01-18 | 1935-08-20 | L P R Company | Airplane |
US2147360A (en) | 1933-02-16 | 1939-02-14 | Zap Dev Corp | Airplane control apparatus |
US2043275A (en) | 1934-04-28 | 1936-06-09 | Fred E Weick | Split flap |
US2127864A (en) | 1936-02-25 | 1938-08-23 | Cie Des Avions Hanriot | Control device for the flaps of aircraft |
US2156403A (en) | 1937-03-13 | 1939-05-02 | Cie Des Avions Hanriot | Lateral control surfaces of airplanes |
US2194796A (en) | 1938-07-20 | 1940-03-26 | Zap Dev Corp | Airplane control surfaces |
US2218822A (en) | 1938-07-20 | 1940-10-22 | Zap Dev Corp | Control surface for airplanes |
US2791385A (en) | 1952-03-10 | 1957-05-07 | Lockheed Aircraft Corp | Landing drag flap and lift spoiler |
US4089040A (en) * | 1976-01-28 | 1978-05-09 | The Boeing Company | Electrical/electronic rack and plug-in modules therefor |
US5294080A (en) | 1993-02-08 | 1994-03-15 | The United States Of America As Represented By The Administrator Of National Aeronautics And Space Administration | Lift enhancing tabs for airfoils |
US6189837B1 (en) | 1998-10-29 | 2001-02-20 | The Boeing Company | Auxiliary spoiler retract system |
FR2792285B1 (en) | 1999-04-16 | 2001-06-08 | Onera (Off Nat Aerospatiale) | AERODYNAMIC SURFACE OF AIRCRAFT WITH LEAK EDGE DEFLECTOR |
US6491261B1 (en) | 2000-04-17 | 2002-12-10 | The United States Of America As Represented By The Secretary Of The Air Force | Wing mounted aircraft yaw control device |
DE10156733B4 (en) | 2001-11-19 | 2006-04-20 | Eads Deutschland Gmbh | Aerodynamic profile with adjustable flap |
US6843452B1 (en) | 2003-06-17 | 2005-01-18 | The Boeing Company | Variable trailing edge geometry and spanload control |
US7261257B2 (en) * | 2004-11-23 | 2007-08-28 | Helou Jr Elie | Cargo aircraft |
US7410133B2 (en) | 2005-05-31 | 2008-08-12 | The Board Of Trustees Of The Leland Stanford Junior University | Miniature trailing edge effector for aerodynamic control |
DE102005054869A1 (en) * | 2005-11-17 | 2007-05-31 | Airbus Deutschland Gmbh | Method for producing a fuselage cell of an aircraft |
FR2917377B1 (en) * | 2007-06-15 | 2009-08-07 | Airbus France Sas | DEVICE FOR ARRANGING AN AIRCRAFT FOR THE REST OF CREW MEMBERS AND AN AIRCRAFT COMPRISING IT |
US7954769B2 (en) | 2007-12-10 | 2011-06-07 | The Boeing Company | Deployable aerodynamic devices with reduced actuator loads, and related systems and methods |
FR2925462B1 (en) | 2007-12-20 | 2010-07-30 | Airbus France | STORAGE BOX FOR A FRONT TRAIN FOR AN AIRCRAFT |
DE102008011026B4 (en) * | 2008-02-25 | 2012-05-03 | Airbus Operations Gmbh | Modular device carrier |
FR2933377B1 (en) * | 2008-07-01 | 2011-04-15 | Airbus France | PLANE WITH FRONT LANDING TRAIN |
GB0902685D0 (en) | 2009-02-18 | 2009-04-01 | Airbus Uk Ltd | Aircraft wing assembly |
DE102010032225B4 (en) | 2010-07-26 | 2019-10-31 | Airbus Operations Gmbh | Aerodynamic body with additional flap |
FR2963314B1 (en) | 2010-07-27 | 2013-06-14 | Airbus Operations Sas | METHOD AND DEVICE FOR ARRANGING AN AIRCRAFT AVONIC TILT BEFORE AN AIRCRAFT |
-
2010
- 2010-07-27 FR FR1056141A patent/FR2963314B1/en active Active
-
2011
- 2011-07-26 CN CN201180042970.2A patent/CN103079953B/en active Active
- 2011-07-26 EP EP11752294.6A patent/EP2598398B1/en not_active Not-in-force
- 2011-07-26 WO PCT/FR2011/051795 patent/WO2012022891A1/en active Application Filing
-
2013
- 2013-01-25 US US13/750,115 patent/US20130228655A1/en not_active Abandoned
-
2015
- 2015-02-11 US US14/620,021 patent/US9878790B2/en active Active
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20130214092A1 (en) * | 2010-07-26 | 2013-08-22 | Airbus Operations Gmbh | Aerodynamic body with an ancillary flap |
US20130266444A1 (en) * | 2010-07-26 | 2013-10-10 | Airbus Operations Gmbh | Aerodynamic body with an ancillary flap |
US8925869B2 (en) * | 2010-07-26 | 2015-01-06 | Airbus Operations Gmbh | Aerodynamic body with an ancillary flap |
US9878790B2 (en) | 2010-07-27 | 2018-01-30 | Airbus Operations (S.A.S.) | Method and device for fitting out an aircraft nose compartment in an avionics bay |
US20160298646A1 (en) * | 2015-04-08 | 2016-10-13 | General Electric Company | Gas turbine diffuser and methods of assembling the same |
US10151325B2 (en) * | 2015-04-08 | 2018-12-11 | General Electric Company | Gas turbine diffuser strut including a trailing edge flap and methods of assembling the same |
US20220212773A1 (en) * | 2021-01-06 | 2022-07-07 | The Boeing Company | Aircraft keel beam assembly |
US11787523B2 (en) * | 2021-01-06 | 2023-10-17 | The Boeing Company | Aircraft keel beam assembly |
Also Published As
Publication number | Publication date |
---|---|
FR2963314A1 (en) | 2012-02-03 |
CN103079953B (en) | 2015-12-16 |
FR2963314B1 (en) | 2013-06-14 |
EP2598398A1 (en) | 2013-06-05 |
EP2598398B1 (en) | 2017-10-18 |
WO2012022891A1 (en) | 2012-02-23 |
US20150291281A1 (en) | 2015-10-15 |
US9878790B2 (en) | 2018-01-30 |
CN103079953A (en) | 2013-05-01 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US20130228655A1 (en) | Method and device for fitting out an aircraft nose compartment in an avionics bay | |
US8925869B2 (en) | Aerodynamic body with an ancillary flap | |
US9422050B2 (en) | Fore flap disposed on the wing of an aircraft | |
US10899431B2 (en) | System for driving and guiding of a multifunctional trailing edge control surface on an aircraft | |
EP1843942B1 (en) | Aerospace vehicle leading edge slat devices and corresponding methods | |
US8783623B2 (en) | Device for the generation of aerodynamic vortices and also a regulating flap and wing with a device for the generation of aerodynamic vortices | |
US8579230B2 (en) | Attachment pylon for aircraft turboshaft engine, comprising rear flaps with mobile incidence | |
EP3546342B1 (en) | Hinged raked wing tip | |
US6598834B2 (en) | Method for reducing fuel consumption in aircraft | |
US8651430B2 (en) | Spoiler for an aerodynamic body of an aircraft | |
US20120043428A1 (en) | High-lift flap, arrangement of a high-lift flap together with a device for influencing the flow on the same and aircraft comprising said arrangement | |
EP1398269A1 (en) | Method and apparatus for controlling airflow with a leading edge device having a flexible flow surface | |
EP3423350B1 (en) | Edge morphing arrangement for an airfoil | |
CN102015445B (en) | Lateral coupling device for holding and guiding at least one aerodynamic body in relation to the main wing of an aircraft, wing and aircraft comprising the same | |
JP2010512274A5 (en) | ||
US9688385B2 (en) | Trail-edge flap system for a wing of an aircraft | |
US20130214092A1 (en) | Aerodynamic body with an ancillary flap | |
EP1972547A1 (en) | Wing leading edge device | |
EP1695905B1 (en) | Aircraft with extendable leading edge of fuselage and wings | |
US11352122B2 (en) | Wing system for an aircraft with a flow body and a cover panel | |
US10538309B2 (en) | System for driving and guiding of a trailing edge control surface | |
EP2711290B1 (en) | Aircraft flap system and associated method | |
US20190185138A1 (en) | Cruise miniflaps for aircraft wing | |
ZA201000868B (en) | Aircraft control surfaces and mechanisms for moving same |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: AIRBUS OPERATIONS (S.A.S.), FRANCE Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:BURGUNDER, SAMUEL;GUERING, BERNARD;SIGNING DATES FROM 20130308 TO 20130315;REEL/FRAME:030459/0146 |
|
AS | Assignment |
Owner name: AIRBUS OPERATIONS (S.A.S.), FRANCE Free format text: CORRECTIVE ASSIGNMENT TO CORRECT THE ASSIGNMENT WAS INADVERTENTLY FILED IN APPLICATION SERIAL NO. 13/750,155 AND SHOULD HAVE BEEN FILED IN 13/750,115. PREVIOUSLY RECORDED ON REEL 030459 FRAME 0146. ASSIGNOR(S) HEREBY CONFIRMS THE ASSIGNMENT;ASSIGNORS:BURGUNDER, SAMUEL;GUERING, BERNARD;SIGNING DATES FROM 20130308 TO 20130315;REEL/FRAME:030498/0716 |
|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |