CN115871915A - Large-angle continuous variable camber aileron based on compliant variant structure - Google Patents
Large-angle continuous variable camber aileron based on compliant variant structure Download PDFInfo
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- CN115871915A CN115871915A CN202211703414.1A CN202211703414A CN115871915A CN 115871915 A CN115871915 A CN 115871915A CN 202211703414 A CN202211703414 A CN 202211703414A CN 115871915 A CN115871915 A CN 115871915A
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Abstract
The invention belongs to the technical field of flexible aileron structure design, and particularly relates to a large-angle continuous variable camber aileron based on a compliant variant structure, which comprises the following components: the aircraft comprises an inner wing section back beam, an inner wing section middle beam, an inner wing section upper skin, an inner wing section lower skin, an aileron driving device, an aileron upper skin, an aileron lower skin, an L-shaped hinge and a corrugated plate; the rear beam of the inner section of the wing and the middle beam of the inner section of the wing are respectively and vertically fixed between the upper skin of the inner section of the wing and the lower skin of the inner section of the wing through bolts; one end of the aileron driving device is fixed on a middle beam of the inner section of the wing through a bolt; the rear end of the upper aileron skin is fixedly connected with the upper surface of the rear beam at the inner section of the wing, the tip of the upper aileron skin is fixedly connected with the tip of the lower aileron skin, and the rear end of the lower aileron skin is fixedly connected with the lower surface of the rear beam at the inner section of the wing through a corrugated plate; the L-shaped hinge comprises two hinged hinges; the horizontal hinge is fixedly connected with the inner surface of the lower skin of the aileron, and the other end of the aileron driving device penetrates through a preformed hole of a rear beam at the inner section of the wing to be fixed with the vertical hinge.
Description
Technical Field
The invention belongs to the technical field of flexible aileron structure design, and particularly relates to a large-angle continuous variable camber aileron based on a compliant variant structure.
Background
The ailerons are one of the main control surfaces of the airplane, the airplane can make roll maneuver by controlling the roll torque generated by the differential deflection of the left and right ailerons, and the ailerons with variable camber can provide higher control efficiency and reduce the action of resistance. In the design of the new generation of fighter plane, high maneuverability is an important index, so whether the aileron with large angle and continuous variable camber can be designed is the key for designing the new generation of fighter plane with high maneuverability.
The aileron bending device has been widely applied to various airplanes, and is more representative in foreign research, and the research result of the preliminary research on the continuously bendable trailing edge flap shows that the continuously bendable trailing edge flap achieves the resistance reduction of 6.31 percent and the lift-drag ratio is improved by 4.85 percent under the support of the national aeronautics and astronautics administration (NASA) in the aerospace funding organization. Yokozeki and Sugiura design the trailing edge of the wavy structure airfoil to achieve the purpose of camber change of the trailing edge of the airfoil. In China, the research on the aerodynamic performance of the old coin, the Yi-Wei-Long and the like is mainly carried out aiming at the camber of the trailing edge of the wing profile.
The previous aileron bending design mostly adopts drive modes such as stay wires, pneumatic tendons, shape memory alloy and the like, has small deformation angle and slow deformation speed, and is difficult to meet the characteristics of high maneuverability of a new generation of fighter.
Disclosure of Invention
The purpose of the invention is as follows: in order to solve the technical difficulties of small deformation angle and slow deformation speed of the conventional variable-camber aileron, the large-angle continuous variable-camber aileron based on the compliant variant structure is provided. According to the large-angle continuous variable camber aileron based on the compliant variant structure/mechanism, the connection hinge of the electric push rod and the lower skin is designed, the corrugated plates between the lower skin and the rear beam at the inner section of the wing are combined, and the zero Poisson ratio honeycombs are filled between the lower skin and the upper skin and between the lower skin, so that the continuous variable camber and high bearing capacity of the skin are realized, and the structural mechanism design of the large-angle continuous variable camber aileron is realized.
The technical scheme of the invention is as follows:
a compliant variant structure-based wide-angle continuously variable camber aileron comprising: the aircraft comprises an inner wing section rear beam, an inner wing section middle beam, an inner wing section upper skin, an inner wing section lower skin, an aileron driving device, an aileron upper skin, an aileron lower skin, an L-shaped hinge and a corrugated plate;
the rear beam of the inner section of the wing and the middle beam of the inner section of the wing are respectively and vertically fixed between the upper skin of the inner section of the wing and the lower skin of the inner section of the wing through bolts;
one end of the aileron driving device is fixed on a middle beam of the inner section of the wing through a bolt;
the rear end of the upper aileron skin is fixedly connected with the upper surface of the rear beam at the inner section of the wing, the tip of the upper aileron skin is fixedly connected with the tip of the lower aileron skin, and the rear end of the lower aileron skin is fixedly connected with the lower surface of the rear beam at the inner section of the wing through a corrugated plate;
the L-shaped hinge comprises a horizontal hinge and a vertical hinge which are hinged with each other; the horizontal hinge is fixedly connected with the inner surface of the lower skin of the aileron, and the other end of the aileron driving device penetrates through a preformed hole of a rear beam at the inner section of the wing to be fixedly connected with the vertical hinge.
Further, the aileron further comprises: corrugated plate support honeycombs; the corrugated plate supporting honeycombs are bonded between the corrugated plate and the inner surface of the upper skin of the aileron.
Further, each cell wall of the corrugated plate supporting cell is perpendicular to the upper skin.
Further, the flap further comprises: a skin support hinge; the skin supporting hinge comprises an upper hinge, a lower hinge and a middle hinge; the upper hinge is fixedly connected with the inner surface of the upper skin of the aileron, the lower hinge is fixedly connected with the inner surface of the lower skin of the aileron, and two ends of the middle hinge are respectively hinged with the upper hinge and the lower hinge.
Furthermore, the plane of the middle hinge is perpendicular to the span direction of the auxiliary wing.
Further, the aileron driving device is a linear driving device, and the driving end movement direction of the linear driving device is parallel to the unfolding direction and perpendicular to the vertical hinge of the L-shaped hinge.
Further, a zero-Poisson's ratio honeycomb is filled between the upper skin and the lower skin of the aileron, and the zero-Poisson's ratio honeycomb is positioned between the skin support hinge and the tip ends of the upper skin and the lower skin. After the zero Poisson ratio honeycomb is subjected to spanwise deformation caused by deflection of the aileron, the chord direction of the zero Poisson ratio honeycomb cannot deform, and the appearance of the aileron is maintained.
Furthermore, the skin supporting hinges are provided with a plurality of groups and are uniformly distributed between the honeycomb with zero Poisson's ratio and the corrugated plate supporting honeycomb.
Further, the linear driving device includes: hydraulic actuator, electric push rod actuator, rack and pinion.
The invention has the beneficial effects that:
the invention discloses a large-angle continuous variable-camber aileron based on a flexible variant structure, which utilizes an electric push rod to drive a hinge and adopts a corrugated plate to perform degeneration compensation, designs an aileron structure capable of being flexibly deformed at a large angle, and can provide higher control efficiency and reduce flight resistance.
Drawings
FIG. 1 is a schematic view of an assembly of a driving device, an upper skin, a lower skin and a supporting plate of a large-angle continuous variable camber aileron structure based on a compliant variant structure;
FIG. 2 is a schematic view of a large angle continuous variable camber aileron structure based on a compliant variant structure;
FIG. 3 is a partial side view of a wide angle continuously variable camber aileron drive and skin support hinge based on a compliant variant construction;
description of reference numerals:
101 aileron driving device transfer hinges, 102 aileron trailing edge zero poisson ratio honeycombs, 103 aileron lower skins, 104 aileron upper skins, 105 skin support hinges, 106 corrugated plates, 107 corrugated plate support honeycombs, 201 wing inner section upper skins, 202 wing inner section lower skins, 203 wing inner section middle beams, 204 wing inner section rear beams, 205 aileron driving devices.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The embodiment of the invention provides a large-angle continuous variable camber aileron based on a compliant variant structure, and as shown in figure 1, the large-angle continuous variable camber aileron based on the compliant variant structure comprises: an outer wing component and an inner aileron component.
As shown in fig. 1, the wing external assembly includes an aileron lower skin 103, an aileron upper skin 104, a corrugated plate 106, a wing inner section upper skin 201, a wing inner section lower skin 202, a wing inner section center sill 203, a wing inner section rear sill 204;
the inner wing section back girder 204 and the inner wing section middle girder 203 are vertically and fixedly connected to the inner surfaces of the inner wing section upper skin 201 and the inner wing section lower skin 202 through bolts respectively;
further, one end of the aileron lower skin 103 is connected with the aileron upper skin 104, and the other end is connected with the corrugated plate 106 through a bolt;
further, one end of the upper aileron skin 104 is connected with the inner wing section back beam 204 through a bolt, and the other end is connected with the lower aileron skin 103;
as shown in fig. 2, the inner assembly of the aileron comprises an aileron trailing edge zero poisson's ratio honeycomb 102, a corrugated plate support honeycomb 107, and an aileron driving device 205;
the part of the upper aileron skin 104 directly connected with the lower aileron skin 103 is filled with and glued with the zero Poisson ratio honeycomb 102 at the trailing edge of the aileron;
furthermore, a corrugated plate supporting honeycomb 107 and a skin supporting hinge 105 are sequentially arranged between the upper skin and the lower skin of the aileron from the rear beam 204 of the inner section of the aileron to the rear edge of the aileron; one end of each corrugated plate supporting honeycomb 107 is connected with a corrugated plate, the other end of each corrugated plate supporting honeycomb 107 is connected with the inner surface of the upper skin 104 of the aileron, and the honeycomb wall of each honeycomb unit of each corrugated plate supporting honeycomb 107 is vertical to the upper skin 104;
as shown in fig. 3, the aileron drive and skin support hinge partially includes an aileron drive-type transfer hinge 101, an aileron drive 205, a skin support hinge 105;
further, one end of an aileron driving device 205 is connected to the middle part of the middle beam 203 of the inner section of the wing through a bolt and penetrates through a hole reserved in a rear beam 204 of the inner section of the wing, the other end of the aileron driving device is connected with an aileron driving device type switching hinge 101 through a bolt, the aileron driving device 205 is a linear driving device, and the motion direction of the driving end of the linear driving device is parallel to the aileron span direction and is vertical to a vertical hinge of an L-shaped hinge;
the skin support hinge 105 is in the shape of a ']', and comprises an upper hinge, a lower hinge and a middle hinge; the upper hinge is fixedly connected with the inner surface of the upper skin 104 of the aileron, the lower hinge is fixedly connected with the inner surface of the lower skin 103 of the aileron, and two ends of the middle hinge are respectively hinged with the upper hinge and the lower hinge.
In the aileron upward deviation process, the aileron driving device 205 drives the transfer hinge 101 from the wing inner section middle beam 203 to the wing inner section rear beam 204 in a linear driving mode to drive the aileron lower skin 103 to move simultaneously, so that a corrugated plate 106 which is connected with the aileron lower skin 103 and can provide deformation compensation is stretched, and the aileron upward deviation is realized.
In the downward deflection process of the aileron, the aileron driving device 205 drives the aileron lower skin 103 to move simultaneously from the wing inner section rear beam 204 to the wing inner section middle beam 203 driving type switching hinge 101 in a linear driving mode, so that a corrugated plate 106 which is connected with the aileron lower skin 103 and can provide deformation compensation is compressed, and downward deflection of the aileron is realized.
During aileron deflection, the aileron trailing edge zero poisson's ratio honeycomb 102 can provide support rigidity, maintain the relative distance between the aileron lower skin 103 and the aileron upper skin 104 unchanged during deflection, and keep the aileron shape unchanged. On the other hand, the skin support hinge 105 is hinged with the lower aileron skin 103 and the upper aileron skin 104, so that only shear force is transmitted in the deflection process, local bending moment is not generated, local bulging of the aileron skin is not generated in the deflection process, and the appearance of the skin is maintained. On the other hand, in the stretching process of the corrugated plate 106, the corrugated plate supporting honeycomb 107 stretches and supports the aileron upper skin 104, so that the aileron upper skin 104 is not bent and collapsed, and the shape of the aileron is kept unchanged.
The deflection amount of the aileron in the embodiment of the invention is related to the length of the corrugated plate 106 and the driving stroke of the aileron driving device 205, the deflection angle of the aileron can reach 30 degrees under the reasonable parameter matching, and the appearance of the skin of the aileron does not generate local bulge and bending collapse in the deflection process.
The foregoing is merely a detailed description of the embodiments of the present invention, and some of the conventional techniques are not detailed. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (9)
1. A big-angle continuous variable camber aileron based on gentle and agreeable variant structure which characterized in that: the flap comprises: the aircraft comprises an inner wing section back beam, an inner wing section middle beam, an inner wing section upper skin, an inner wing section lower skin, an aileron driving device, an aileron upper skin, an aileron lower skin, an L-shaped hinge and a corrugated plate;
the rear beam of the inner section of the wing and the middle beam of the inner section of the wing are respectively and vertically fixed between the upper skin of the inner section of the wing and the lower skin of the inner section of the wing through bolts;
the rear end of the upper skin of the aileron is fixedly connected with the upper surface of the rear beam of the inner section of the wing, the tip of the upper skin of the aileron is fixedly connected with the tip of the lower skin of the aileron, and the rear end of the lower skin of the aileron is fixedly connected with the lower surface of the rear beam of the inner section of the wing through a corrugated plate;
the L-shaped hinge comprises a horizontal hinge and a vertical hinge which are hinged with each other; the horizontal hinge is fixedly connected with the inner surface of the lower skin of the aileron, one end of the aileron driving device is fixed on the middle beam of the inner section of the wing through a bolt, and the other end of the aileron driving device penetrates through a reserved hole of the rear beam of the inner section of the wing to be fixedly connected with the vertical hinge.
2. The aileron of claim 1, wherein: the flap further comprises: corrugated plate support honeycombs; the corrugated plate supporting honeycombs are bonded between the corrugated plate and the inner surface of the upper skin of the aileron.
3. The flap according to claim 2, wherein: each honeycomb unit cell wall of the corrugated plate supporting cell is vertical to the upper skin.
4. The flap according to claim 3, wherein: the flap further comprises: a skin support hinge; the skin supporting hinge comprises an upper hinge, a lower hinge and a middle hinge; the upper hinge is fixedly connected with the inner surface of the upper skin of the aileron, the lower hinge is fixedly connected with the inner surface of the lower skin of the aileron, and two ends of the middle hinge are respectively hinged with the upper hinge and the lower hinge.
5. The flap according to claim 4, wherein: the plane of the middle hinge is vertical to the span direction of the auxiliary wing.
6. The flap according to claim 5, wherein: the skin support hinges are provided with a plurality of groups and are uniformly distributed between the honeycomb with zero Poisson's ratio and the corrugated plate support honeycomb.
7. The flap according to claim 6, wherein: zero-Poisson ratio honeycombs are filled between the upper skin and the lower skin of the aileron and are positioned between the skin support hinge and the tips of the upper skin and the lower skin.
8. The flap according to claim 7, wherein: the aileron driving device is a linear driving device, and the driving end movement direction of the linear driving device is parallel to the unfolding direction and is perpendicular to the vertical hinge of the L-shaped hinge.
9. The aileron of claim 8, wherein: the linear driving apparatus includes: hydraulic actuator, electric push rod actuator, rack and pinion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211703414.1A CN115871915A (en) | 2022-12-29 | 2022-12-29 | Large-angle continuous variable camber aileron based on compliant variant structure |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211703414.1A CN115871915A (en) | 2022-12-29 | 2022-12-29 | Large-angle continuous variable camber aileron based on compliant variant structure |
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| CN115871915A true CN115871915A (en) | 2023-03-31 |
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| CN202211703414.1A Pending CN115871915A (en) | 2022-12-29 | 2022-12-29 | Large-angle continuous variable camber aileron based on compliant variant structure |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118723062A (en) * | 2024-07-17 | 2024-10-01 | 南京航空航天大学 | A flexible folding wingtip structure based on asymmetric stiffness |
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- 2022-12-29 CN CN202211703414.1A patent/CN115871915A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118723062A (en) * | 2024-07-17 | 2024-10-01 | 南京航空航天大学 | A flexible folding wingtip structure based on asymmetric stiffness |
| CN118723062B (en) * | 2024-07-17 | 2025-03-14 | 南京航空航天大学 | Flexible folding wing tip structure based on asymmetric rigidity |
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