A large-angle continuous variable camber aileron based on a compliant variant structure

Abstract

This invention belongs to the field of flexible aileron structure design technology, specifically relating to a large-angle continuous variable camber aileron based on a compliant variant structure, comprising: an inner wing rear spars, an inner wing middle spars, an inner wing upper skin, an inner wing lower skin, an aileron drive device, an upper aileron skin, a lower aileron skin, an L-shaped hinge, and a corrugated plate; the inner wing rear spars and the inner wing middle spars are respectively vertically fixed between the inner wing upper skin and the inner wing lower skin by bolts; one end of the aileron drive device is fixed to the inner wing middle spars by bolts; the rear end of the upper aileron skin is fixedly connected to the upper surface of the inner wing rear spars, the tip of the upper aileron skin is fixedly connected to the tip of the lower aileron skin, and the rear end of the lower aileron skin is fixedly connected to the lower surface of the inner wing rear spars by a corrugated plate; the L-shaped hinge includes two hinged hinges; the horizontal hinge is fixedly connected to the inner surface of the lower aileron skin, and the other end of the aileron drive device passes through a reserved hole in the inner wing rear spars and is fixed to the vertical hinge.

Description

Technical Field

[0001] This invention belongs to the field of flexible aileron structure design technology, specifically relating to a large-angle continuous variable camber aileron based on a compliant variant structure. Background Technology

[0002] The aileron is one of the main control surfaces of an aircraft. By controlling the differential deflection of the left and right ailerons, the resulting rolling moment enables the aircraft to perform roll maneuvers. Variable-camber ailerons can provide higher handling efficiency and reduce drag. In the design of next-generation fighter jets, high maneuverability is an important indicator. Therefore, the ability to design ailerons with large-angle continuous variable camber is key to designing a next-generation fighter jet with high maneuverability.

[0003] Aileron camber devices have been widely used in various aircraft. Representative international research includes NASA's (USA) research on "continuously camberable trailing edge flaps" with support from the Aeronautical Science Foundation. Preliminary results show that continuously camberable trailing edge flaps achieve drag reduction of 6.31% and increase lift-to-drag ratio by 4.85%. Yokozeki and Sugiura designed a wave-structured wing trailing edge to achieve wing trailing edge camber. Domestically, Chen Qian and Yin Weilong, among others, have primarily focused on the aerodynamic performance of airfoil trailing edge camber.

[0004] Previous aileron camber designs mostly used drive methods such as cable, aerodynamic tendons, and shape memory alloys, which resulted in small deformation angles and slow deformation speeds, making it difficult to meet the high maneuverability characteristics of the new generation of fighter jets. Summary of the Invention

[0005] The purpose of this invention is to address the technical challenges of small deformation angles and slow deformation speeds in conventional variable-camber ailerons by proposing a large-angle continuous variable-camber aileron based on a compliant morphological structure. This invention, based on a compliant morphological structure / mechanism, achieves continuous variable-camber aileron design by incorporating a hinge connecting an electric push rod to the lower skin, a corrugated plate between the lower skin and the rear spars of the inner wing section, and filling the lower skin and the space between the upper and lower skins with zero Poisson's ratio honeycomb. This results in continuous variable-camber skin design and high load-bearing capacity, realizing the structural mechanism design of a large-angle continuous variable-camber aileron.

[0006] The technical solution of this invention:

[0007] A large-angle continuous variable camber aileron based on a compliant variant structure includes: an inner wing rear spars, an inner wing middle spars, an inner wing upper skin, an inner wing lower skin, an aileron drive unit, an upper aileron skin, a lower aileron skin, an L-shaped hinge, and a corrugated plate.

[0008] The rear spar and the middle spar of the inner wing section are respectively vertically fixed between the upper skin and the lower skin of the inner wing section by bolts.

[0009] One end of the aileron drive device is fixed to the center beam of the inner section of the wing by bolts;

[0010] The rear end of the upper aileron skin is fixedly connected to the upper surface of the inner section of the wing's rear spars, the tip of the upper aileron skin is fixedly connected to the tip of the lower aileron skin, and the rear end of the lower aileron skin is fixedly connected to the lower surface of the inner section of the wing's rear spars via a corrugated plate.

[0011] The L-shaped hinge includes a horizontal hinge and a vertical hinge that are hinged to each other; the horizontal hinge is fixedly connected to the inner surface of the lower skin of the aileron, and the other end of the aileron drive device passes through a reserved hole in the rear spar of the inner section of the wing and is fixedly connected to the vertical hinge.

[0012] Furthermore, the aileron also includes a corrugated plate support honeycomb; the corrugated plate support honeycomb is bonded between the corrugated plate and the inner surface of the aileron's upper skin.

[0013] Furthermore, the cell walls of each cell in the corrugated plate-supported honeycomb are perpendicular to the upper skin.

[0014] Furthermore, the aileron also includes: a skin support hinge; the skin support hinge includes an upper hinge, a lower hinge, and a middle hinge; the upper hinge is fixedly connected to the inner surface of the upper skin of the aileron, the lower hinge is fixedly connected to the inner surface of the lower skin of the aileron, and the two ends of the middle hinge are respectively hinged to the upper and lower hinges.

[0015] Furthermore, the plane where the middle hinge is located is perpendicular to the span of the aileron.

[0016] Furthermore, the aileron drive device is a linear drive device, and the direction of motion of the drive end of the linear drive device is parallel to the spanwise direction and perpendicular to the vertical hinge of the L-shaped hinge.

[0017] Furthermore, a zero Poisson's ratio honeycomb is filled between the upper and lower skins of the aileron, and the zero Poisson's ratio honeycomb is located between the skin support hinge and the tips of the upper and lower skins. The zero Poisson's ratio honeycomb does not deform in the chord direction after spanwise deformation caused by aileron deflection, thus maintaining the aileron's shape.

[0018] Furthermore, the skin support hinges are in multiple sets, evenly distributed between the zero Poisson's ratio honeycomb and the corrugated plate support honeycomb.

[0019] Furthermore, the linear drive device includes: a hydraulic actuator, an electric actuator, and a gear rack.

[0020] The beneficial effects of this invention are:

[0021] The present invention, “A Large-Angle Continuous Variable Camber Aileron Based on a Compliant Variant Structure,” utilizes an electric actuator to drive the hinge and employs a corrugated plate for deformation compensation, designing an aileron structure capable of compliant deformation at large angles, which can provide higher handling efficiency and reduce flight drag. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the assembly of a drive device, upper and lower skins, and support plates for a large-angle continuous variable camber aileron structure based on a compliant variant structure.

[0023] Figure 2 A schematic diagram of a large-angle continuous variable camber aileron structure based on a compliant variant structure;

[0024] Figure 3 A partial side view of a large-angle continuous variable camber aileron drive device and skin support hinge based on a compliant variant structure;

[0025] Explanation of reference numerals in the attached figures:

[0026] 101 Aileron drive mechanism hinge, 102 Aileron trailing edge zero Poisson's ratio honeycomb, 103 Lower aileron skin, 104 Upper aileron skin, 105 Skin support hinge, 106 Corrugated plate, 107 Corrugated plate support honeycomb, 201 Upper inner wing skin, 202 Lower inner wing skin, 203 Inner wing spars, 204 Inner wing rear spars, 205 Aileron drive mechanism. Detailed Implementation

[0027] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0028] This invention proposes a large-angle continuous variable camber aileron based on a compliant variant structure, such as... Figure 1 As shown, the large-angle continuous variable camber aileron based on a compliant variant structure includes: an external wing component and an internal aileron component.

[0029] like Figure 1 As shown, the external wing components include aileron lower skin 103, aileron upper skin 104, corrugated plate 106, wing inner section upper skin 201, wing inner section lower skin 202, wing inner section center spars 203, and wing inner section rear spars 204.

[0030] The rear spar 204 and the middle spar 203 of the inner wing section are respectively vertically fixed to the inner surfaces of the upper skin 201 and the lower skin 202 of the inner wing section by bolts.

[0031] Furthermore, one end of the lower aileron skin 103 is connected to the upper aileron skin 104, and the other end is connected to the corrugated plate 106 by bolts;

[0032] Furthermore, one end of the upper aileron skin 104 is bolted to the rear spar 204 of the inner section of the wing, and the other end is connected to the lower aileron skin 103.

[0033] like Figure 2 As shown, the internal components of the aileron include a zero Poisson's ratio aileron trailing edge honeycomb 102, a corrugated plate support honeycomb 107, and an aileron drive device 205.

[0034] The portion where the upper aileron skin 104 and the lower aileron skin 103 are directly connected is filled and glued to the aileron trailing edge zero Poisson's ratio honeycomb 102;

[0035] Furthermore, a corrugated plate support honeycomb 107 and a skin support hinge 105 are arranged sequentially between the upper and lower skins of the aileron from the rear spars 204 of the inner section of the wing to the trailing edge of the aileron; one end of the corrugated plate support honeycomb 107 is connected to the corrugated plate, and the other end is connected to the inner surface of the upper skin 104 of the aileron; the honeycomb wall of each honeycomb unit of the corrugated plate support honeycomb 107 is perpendicular to the upper skin 104.

[0036] like Figure 3 As shown, the aileron drive device and skin support hinge partially include an aileron drive device type transition hinge 101, an aileron drive device 205, and a skin support hinge 105.

[0037] Furthermore, one end of the aileron drive device 205 is bolted to the middle of the inner section middle beam 203 of the wing and passes through the reserved hole in the inner section rear beam 204 of the wing, and the other end is bolted to the aileron drive device type transition hinge 101. The aileron drive device 205 is a linear drive device. The direction of movement of the drive end of the linear drive device is parallel to the spanwise direction of the aileron and perpendicular to the vertical hinge of the "L" type hinge.

[0038] The skin support hinge 105 is "]" shaped and includes an upper hinge, a lower hinge, and a middle hinge; the upper hinge is fixedly connected to the inner surface of the upper aileron skin 104, the lower hinge is fixedly connected to the inner surface of the lower aileron skin 103, and the two ends of the middle hinge are respectively hinged to the upper and lower hinges.

[0039] During the aileron deflection process, the aileron drive device 205 drives the transition hinge 101 from the middle beam 203 of the inner wing section to the rear beam 204 of the inner wing section in a linear drive manner, which drives the lower aileron skin 103 to move simultaneously, thereby stretching the corrugated plate 106 connected to the lower aileron skin 103 and providing deformation compensation, thus realizing the aileron deflection.

[0040] During the aileron deflection process, the aileron drive device 205 drives the transition hinge 101 from the rear spar 204 of the inner wing section to the middle spar 203 of the inner wing section in a linear drive manner, thereby driving the lower aileron skin 103 to move simultaneously, thereby compressing the corrugated plate 106 connected to the lower aileron skin 103 and providing deformation compensation, thus realizing the aileron deflection.

[0041] During aileron deflection, the zero Poisson's ratio honeycomb 102 at the trailing edge of the aileron provides supporting stiffness, maintaining the relative distance between the lower aileron skin 103 and the upper aileron skin 104 unchanged during deflection, thus preserving the aileron's shape. On the other hand, the skin support hinge 105 is hinged to both the lower aileron skin 103 and the upper aileron skin 104, transmitting only shear force during deflection without generating local bending moments, thus preventing local bulging of the aileron skin and maintaining its shape. Furthermore, during the stretching of the corrugated plate 106, the corrugated plate support honeycomb 107 stretches accordingly and supports the upper aileron skin 104, preventing bending and collapse of the upper aileron skin 104 and maintaining the aileron's shape.

[0042] In this embodiment of the invention, the deflection of the aileron is related to the length of the corrugated plate 106 and the driving stroke of the aileron drive device 205. Under reasonable parameter matching, the aileron deflection angle can reach 30 degrees, and the aileron skin does not bulge or bend and collapse during the deflection process.

[0043] The above description is merely a specific embodiment of the present invention, providing a detailed description of the invention. Parts not covered herein are conventional techniques. However, the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention. The scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A large-angle continuous variable camber aileron based on a compliant variant structure, characterized in that: The aileron includes: an inner wing rear spars, an inner wing middle spars, an inner wing upper skin, an inner wing lower skin, an aileron drive unit, an upper aileron skin, a lower aileron skin, an L-shaped hinge, and a corrugated plate. The rear spar and the middle spar of the inner wing section are respectively vertically fixed between the upper skin and the lower skin of the inner wing section by bolts. The rear end of the upper aileron skin is fixedly connected to the upper surface of the inner section of the wing's rear spars, the tip of the upper aileron skin is fixedly connected to the tip of the lower aileron skin, and the rear end of the lower aileron skin is fixedly connected to the lower surface of the inner section of the wing's rear spars via a corrugated plate. The L-shaped hinge includes a horizontal hinge and a vertical hinge that are hinged to each other; the horizontal hinge is fixedly connected to the inner surface of the lower skin of the aileron; one end of the aileron drive device is fixed to the middle beam of the inner section of the wing by bolts, and the other end of the aileron drive device passes through the reserved hole of the rear beam of the inner section of the wing and is fixedly connected to the vertical hinge. The portion of the upper aileron skin directly connected to the lower aileron skin is filled and glued with zero Poisson's ratio honeycomb. Corrugated plate support honeycomb and skin support hinges are arranged sequentially between the upper and lower skins of the aileron, from the rear spars of the inner section of the wing to the trailing edge of the aileron. The corrugated plate support honeycomb is bonded between the corrugated plate and the inner surface of the upper skin of the aileron. The honeycomb wall of each honeycomb unit of the corrugated plate support honeycomb is perpendicular to the upper skin. The skin support hinge includes an upper hinge, a lower hinge, and a middle hinge. The upper hinge is fixedly connected to the inner surface of the upper skin of the aileron, the lower hinge is fixedly connected to the inner surface of the lower skin of the aileron, and the two ends of the middle hinge are hinged to the upper and lower hinges respectively.

2. The aileron according to claim 1, characterized in that: The plane of the middle hinge is perpendicular to the span of the aileron.

3. The aileron according to claim 2, characterized in that: The skin support hinges are in multiple sets, evenly distributed between the zero Poisson's ratio honeycomb and the corrugated plate support honeycomb.

4. The aileron according to claim 3, characterized in that: The aileron drive device is a linear drive device, and the direction of motion of the drive end of the linear drive device is parallel to the spanwise direction and perpendicular to the vertical hinge of the L-shaped hinge.

5. The aileron according to claim 4, characterized in that: The linear drive device includes: a hydraulic actuator, an electric actuator, and a gear rack.

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