Variable camber wing trailing edge structure

Abstract

The application provides a variable camber wing trailing edge structure, which is composed of a flexible skin, a variable structure and a driving system; the driving system is composed of a driving steering gear, a steering disc, a screw, a bolt, a nut and a variable cross-section eccentric lever; the variable structure is composed of a corrugated lattice structure rudder surface and filled foam; the flexible skin is a composite material flexible skin; and the flexible skin and the variable structure are connected in a manner of glue joint, so that the application can realize smooth and continuous variable camber of the wing.

Description

Technical Field

[0001] This invention provides a variable camber wing trailing edge structure, belonging to the field of deformable wing technology. Background Technology

[0002] With the continuous development of morphing technology, various morphing schemes have been developed for different parts of the aircraft, mainly including: variable camber wing morphing, variable span wing morphing, and variable sweep wing morphing, among which variable camber wing morphing is currently one of the research hotspots. For fixed-wing aircraft, a reasonable wing camber can effectively improve the aerodynamic performance. In traditional aircraft, the control surfaces and fuselage are connected by hinges. When the control surfaces deflect vertically, gaps are generated at the connection, causing discontinuities on the wing surface, which will affect the aerodynamic efficiency of the aircraft to a certain extent. This invention provides a variable camber wing trailing edge structure. The variable camber wing trailing edge structure can achieve smooth and continuous camber of the wing, which can improve the aerodynamic efficiency of the aircraft, reduce fuel consumption, reduce noise during takeoff and landing, and improve the stealth performance of military aircraft. Summary of the Invention

[0003] 1. Purpose: This invention provides a variable camber wing trailing edge structure that enables smooth and continuous camber changes in the wing without any local or overall instability on the wing surface during the camber change process.

[0004] 2. Technical Solution: This invention discloses a variable camber wing trailing edge structure, comprising a flexible skin, a corrugated dot matrix control surface, a drive servo, a variable cross-section eccentric lever, a servo disk, screws, bolts, and nuts. There are four drive servos, four servo disks, four screws, and four variable cross-section eccentric levers. The end of the variable cross-section eccentric lever near the drive servo is a 2mm thick disc with four holes evenly spaced along its circumference. The radius and hole size of the 2mm thick disc are the same as the size of the drive servo disk and the hole size on the drive servo disk. The cross-sectional area of ​​the variable cross-section eccentric lever decreases near the trailing edge. One end of the eccentric lever is connected to the drive servo disk using bolts and nuts, and the other end of the variable cross-section eccentric lever is tightly attached to the variable cross-section eccentric lever near the trailing edge. The rudder disc and drive servo are connected by screws to the rear wall of the eccentric lever groove. The corrugated dot matrix structure rudder surface has servo grooves and variable cross-section eccentric lever grooves. The drive servo and eccentric lever are fixed in the servo grooves and variable cross-section eccentric lever grooves of the corrugated dot matrix structure rudder surface. The drive servo and variable cross-section eccentric lever are placed symmetrically in pairs. The two drive servos on the same side of the symmetry plane have the same rotational angular velocity in magnitude and direction. The drive servos on opposite sides of the symmetry plane have the same rotational angular velocity in magnitude but opposite directions. The end of the variable cross-section eccentric lever with the smaller cross-sectional area is located on the side closer to the symmetry plane. Foam is evenly filled in the gaps of the corrugated dot matrix structure with a filling thickness of 2mm, the same as the thickness of the corrugated dot matrix structure. The flexible skin is connected to the corrugated dot matrix structure rudder surface and the foam filling by adhesive bonding. A variable camber wing trailing edge structure drives the variable cross-section eccentric lever to rotate through the rotation of the drive servo. The variable cross-section eccentric lever causes the rudder surface to deflect or deflect downwards. During the deflection or deflection of the rudder surface, the wing surface remains smooth and continuous without instability.

[0005] The filling foam of this invention is made of polyurethane.

[0006] The flexible skin of this invention is a flexible composite material skin.

[0007] The corrugated dot matrix structure rudder surface of this invention is made of 3D-printed black nylon PA12.

[0008] The variable cross-section eccentric lever of this invention is made of 3D-printed aluminum alloy.

[0009] The steering wheel, nut, bolt, and screw of this invention are all made of aluminum alloy. Attached Figure Description

[0010] Figure 1 This is a schematic diagram of the variable camber wing.

[0011] Figure 2 This is a schematic diagram of the overall side view of a variable camber wing.

[0012] Figure 3 This is a schematic diagram of the overall trailing edge structure of a variable camber wing.

[0013] Figure 4 This is a schematic side view of the overall trailing edge structure of a variable camber wing.

[0014] Figure 5 This is a schematic diagram of the trailing edge structure of a variable camber wing without a flexible skin.

[0015] Figure 6 This is a schematic diagram of a flexible skin.

[0016] Figure 7 This is a schematic diagram of the corrugated dot matrix structure rudder surface and the foam filling.

[0017] Figure 8 This is a schematic diagram showing the connection between the drive servo motor and the eccentric lever.

[0018] Figure 9 This is a diagram showing the connection between the drive servo motor and the servo disc.

[0019] Figure 2 Chinese: 1. Drive servo motor

[0020] Figure 4 2. Nut; 14. Rear wall of the variable cross-section eccentric lever groove near the rear edge.

[0021] Figure 6 3. Flexible skin

[0022] Figure 7 In the middle: 4. Variable cross-section bias lever groove, 5. Servo gear groove, 6. Foam filling, 7. Corrugated dot matrix structure rudder surface, 8. Corrugated dot matrix structure

[0023] Figure 8 In the middle: 9. Bolt, 10. Variable cross-section eccentric lever, 13. Disc

[0024] Figure 9 Chinese: 11. Steering wheel, 12. Screw Detailed Implementation

[0025] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0026] This invention discloses a trailing edge structure for a variable camber wing. The structure comprises a flexible skin 3, a corrugated dot matrix control surface 7, a drive servo 1, a variable cross-section eccentric lever 10, a servo disc 11, screws 12, bolts 9, and nuts 2. There are four drive servos 1, four servo discs 11, four screws 12, and four variable cross-section eccentric levers 10. The end of the variable cross-section eccentric lever 10 closest to the drive servo 1 is a 2mm thick disc 13 with four evenly spaced holes along its circumference. The radius and hole size of the 2mm thick disc 13 are the same as the dimensions of the servo disc 11 and the hole size on the servo disc 11. Near the trailing edge, the cross-sectional area of ​​the variable cross-section eccentric lever decreases. One end of the eccentric lever is connected to the drive servo 1's servo disk 11 using bolts 9 and nuts 2. The other end of the variable cross-section eccentric lever 10 is tightly attached to the rear wall 14 of the variable cross-section eccentric lever groove near the trailing edge. The servo disk 11 and the drive servo 1 are connected by screws 12. The corrugated dot matrix structure servo surface 7 has servo grooves 5 and variable cross-section eccentric lever grooves 4 inside. The drive servo 1 and the variable cross-section eccentric lever 10 are fixed in the servo grooves 5 and eccentric lever grooves 4 of the corrugated dot matrix structure servo surface 7. The drive servo 1 and the variable cross-section eccentric lever 10 are placed symmetrically in pairs. The two drive servos located on the same side of the symmetry plane have the same angular velocity in the same direction. The drive servos located on opposite sides of the symmetry plane have the same angular velocity in the same direction but opposite directions. The end of the variable cross-section eccentric lever 10 with the smaller cross-sectional area is located on the side closer to the symmetry plane. Foam 6 is uniformly filled into the gaps of the corrugated dot matrix structure 8. The filling thickness of foam 6 is the same as the thickness of corrugated dot matrix structure 8, both being 2mm. The flexible skin 3 is bonded to the corrugated dot matrix control surface 7 and the foam 6 by adhesive bonding. A variable camber wing trailing edge structure drives the servo motor 1 to rotate, which in turn drives the variable cross-section eccentric lever 10 to rotate. The variable cross-section eccentric lever 10 causes the control surface to deflect or deflect downwards. During the deflection or deflection of the control surface, the wing surface remains smooth and continuous, without any instability.

Claims

1. A trailing edge structure for a variable camber wing, characterized in that: Includes flexible skin, corrugated dot matrix control surfaces, drive servo motor, variable cross-section eccentric lever, rudder disk, filler foam, screws, bolts and nuts; The drive servo motor, servo disc, and variable cross-section eccentric lever are all provided with 4 units; The corrugated dot matrix structure rudder surface is provided with a rudder slot and a variable cross-section eccentric lever slot inside, and the drive rudder and the variable cross-section eccentric lever are fixed in the rudder slot and the variable cross-section eccentric lever slot of the corrugated dot matrix structure rudder surface. The four drive servos and the four variable cross-section eccentric levers are arranged symmetrically in pairs with respect to the plane of symmetry; Two drive servos located on the same side of the plane of symmetry have the same angular velocity and the same direction. The drive servos located on both sides of the plane of symmetry have the same angular velocity but opposite directions; The end of the variable cross-section eccentric lever with the smaller cross-sectional area is located on the side closer to the plane of symmetry. The cross-sectional area of ​​the variable cross-section eccentric lever becomes smaller near the trailing edge. One end of the variable cross-section eccentric lever is connected to the drive servo disk, and the other end of the variable cross-section eccentric lever is in close contact with the rear wall of the variable cross-section eccentric lever groove near the trailing edge. The filling foam is evenly filled into the gaps of the corrugated dot matrix structure, and the filling thickness of the filling foam is the same as the thickness of the corrugated dot matrix structure. The flexible skin, corrugated dot matrix rudder surface, and filling foam are connected by adhesive bonding. By driving the servo motor to rotate, the variable cross-section eccentric lever is driven to rotate. The variable cross-section eccentric lever causes the control surface to deflect upwards or downwards. During the deflection or downward deflection of the control surface, the wing surface remains smooth and continuous without any instability.

2. The trailing edge structure of a variable camber wing according to claim 1, characterized in that: A disc is provided at the end of the variable cross-section eccentric lever near the drive servo motor; Four holes are evenly distributed along the circumference of the disk; The radius and the size of the opening of the disk are the same as the size of the drive servo shroud and the size of the opening on the drive servo shroud; The variable cross-section eccentric lever is connected to the rudder by bolts and nuts.

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