A folding fairing at the root of the trailing edge of a variable-sweep wing

Abstract

The present invention provides a folding fairing at the root of the trailing edge of a variable-sweep wing, which belongs to the field of fixed-wing aircraft. It includes a fuselage part, a wing part, and an actuating part. The fuselage part is an absolutely fixed part in the entire system, and is responsible for connecting the mechanism of the actuating part; the actuating part is the active part of the system, and the system is driven to operate by the rotating shaft in the actuating part; the wing part is the transmission part in the system, and the rotation of the rotating shaft of the actuating part drives the entire wing part to rotate. Compared with the traditional variable-sweep wing system, the advantage of this sliding and retracting fairing is that it can maintain a good aerodynamic shape before and after the variable sweep, and it occupies a small volume after folding, has low complexity, and the system has high robustness during movement.

Description

Technical Field

[0001] The invention relates to the field of fixed-wing aircraft, and is mainly applied to an aircraft variant system of a fixed-wing aircraft during flight. Background Art

[0002] The morphing aircraft is a multi-purpose aircraft for the future. It is a new concept aircraft that can actively change its aerodynamic shape to adapt to different human environments according to different flight environments, flight profiles and other requirements. The variable-sweep wing aircraft is one of the morphing aircraft.

[0003] Hypersonic fixed-wing aircraft typically employ large sweep angles and low aspect ratios to reduce shock wave drag. However, these wings generate low lift and high induced drag at subsonic speeds, resulting in inefficient airfoil. Therefore, from an aerodynamic perspective, to simultaneously meet the requirements of supersonic flight, subsonic flight, subsonic cruise, and short takeoff and landing (STL), it is best to have variable wing sweep, using varying sweep angles to accommodate varying flight conditions. Summary of the Invention

[0004] The purpose of the present invention is to address the shortcomings of variable-sweep wing aircraft, such as complex structure and control system, heavy weight and large volume, and to provide a sliding link mechanism to solve the problem of changing the sweep angle of the aircraft during flight, so as to reduce the complexity, weight and volume of traditional variable-sweep wing aircraft.

[0005] The technical solution of the present invention:

[0006] A variable-sweep wing trailing edge root folding fairing comprises a fuselage portion, a wing portion, and an actuating portion.

[0007] The fuselage part is the absolutely fixed part in the entire system and is responsible for connecting the mechanism of the actuating part; the actuating part is the active part of the system, and the system is driven to operate through the rotating shaft in the actuating part; the wing part is the transmission part in the system, and the rotation of the rotating shaft of the actuating part drives the rotation of the entire wing part.

[0008] The actuating part includes a pushing slide block, a connecting rod, a fuselage slide rail, a rotating shaft, a sealing plate, a connecting lug and a retractable fairing.

[0009] When the front wing is in the variable sweep angle state, the main wing, the 1st retractable fairing and the 2nd retractable fairing are arranged in sequence close to one side of the fuselage slide rail; the rotating shaft is fixed to the main wing, and the main wing is fixed to the No. 1 cover plate; the No. 1 ear piece and the No. 2 ear piece are both fixed on the side of the 1st retractable fairing close to the main wing, and the push slider is fixed on the 1st retractable fairing close to the side of the fuselage slide rail; the two ends of the No. 1 connecting rod are respectively rotatably connected to the No. 1 ear piece and the No. 1 cover plate; the No. 2 cover plate is fixed on the side of the 2nd retractable fairing close to the 1st retractable fairing; the two ends of the main connecting rod are respectively rotatably connected to the No. 1 cover plate and the No. 2 cover plate; the two ends of the No. 2 connecting rod are respectively rotatably connected to the No. 1 cover plate and the No. 2 cover plate; a slide rail is set on the No. 3 cover plate, and the lower end of the No. 3 cover plate can move horizontally on the fuselage slide rail.

[0010] Beneficial effects of the present invention: Compared with the traditional variable sweep wing system, the advantage of this sliding retractable fairing is that it can maintain a good aerodynamic shape before and after the variable sweep, and it occupies a small volume after folding, has low complexity, and the system is highly robust during movement. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 The front wing is in the state of variable sweep angle.

[0012] Figure 2 The wing is in a state with a variable sweep angle of 37 degrees.

[0013] Figure 3 Divide the system into areas.

[0014] Figure 4 It is the distribution of transmission area mechanism.

[0015] Figure 5 Rotate the shaft 15 degrees counterclockwise.

[0016] Figure 6 Rotate the shaft counterclockwise to the limit of 37 degrees.

[0017] Figure 7 It is the No. 1 cover.

[0018] Figure 8 For the connecting rod.

[0019] Figure 9 It is the No. 2 cover plate.

[0020] Figure 10 It is ear piece No. 2.

[0021] Figure 11 It is the No. 3 closing board.

[0022] Figure 12 It is a 2-stage retractable fairing.

[0023] Figure 13 It is a 1-section retractable fairing.

[0024] In the figure: 1: fuselage part, 2: wing part, 3: actuating part, 4: rotating shaft, 5: ear piece No. 1, 6: main wing, 7: connecting rod No. 1, 8: closing plate No. 1, 9: ear piece No. 2, 10: 1-section retractable fairing, 11: closing plate No. 2, 12: main connecting rod, 13: pushing slide, 14: connecting rod No. 2, 15: 2-section retractable fairing, 16: closing plate No. 3, 17: fuselage slide rail. DETAILED DESCRIPTION

[0025] The present invention enables the entire wing to achieve a variable sweep angle under the coordinated action of the entire system. Figure 1 and Figure 2 shown.

[0026] The system is divided into three parts: the fuselage part, the wing part, and the actuator part. Figure 3 As shown. The fuselage part is an absolutely fixed part in the entire system and is responsible for connecting the mechanism of the actuating part; the actuating part is the active part of the system, which drives the system to operate through the rotating shaft in the actuating part; the wing part is the transmission part in the system, and the rotation of the rotating shaft of the actuating part drives the entire wing part to rotate. The actuating part is the core part of the entire invention, which includes seven mechanisms: a push slider, a connecting rod, a fuselage slide rail, a rotating shaft, a sealing plate, a connecting lug, and a retractable fairing. Figure 4 shown.

[0027] The working principle of the overall transmission part is that the rotating shaft is fixedly connected to the main wing, and the rotation of the rotating shaft drives the rotation of the main wing. The main wing is fixedly connected to the No. 1 cover plate, and the rotation of the main wing will drive the No. 1 cover plate to rotate counterclockwise. The No. 1 ear is connected to the No. 1 cover plate via the No. 1 connecting rod, and the No. 1 cover plate is connected to the No. 2 cover plate via the main connecting rod. The No. 1 cover plate rotates counterclockwise, driving the No. 1 connecting rod and the main connecting rod to rotate counterclockwise. The main connecting rod rotates counterclockwise, driving the No. 2 cover plate to rotate counterclockwise. The No. 2 cover plate is fixedly connected to the two-stage retractable fairing, so the two-stage retractable fairing also tends to rotate counterclockwise. The No. 2 cover plate is then connected to the No. 2 ear plate, and the No. 2 cover plate is pulled by the No. 2 cover plate, so the No. 2 connecting rod also tends to rotate counterclockwise. The one-stage retractable fairing also tends to rotate counterclockwise due to the coordinated drive of the No. 1 and No. 2 ears fixed to it. As the first stage retracts the fairing, it rotates counterclockwise, while the slider attached to it pushes the No. 3 cover plate. This slider slides upward along the slide rails on the No. 3 cover plate, driving the No. 3 cover plate inward along the fuselage slide rails. Ultimately, the entire system retracts into the fuselage, achieving the desired sweep angle.

[0028] The overall system rotates 15 degrees and reaches the limit of 37 degrees of structural contraction as shown below Figure 5 Figure 6 shown.

Claims

1. A variable sweep wing trailing edge root folding fairing, characterized in that: Including the fuselage part, wing part and actuation part; The fuselage is the absolutely fixed part of the entire system and is responsible for connecting the mechanism of the actuating part; the actuating part is the active part of the system, and the system is driven by the rotating shaft in the actuating part; the wing part is the transmission part of the system, and the rotation of the rotating shaft of the actuating part drives the rotation of the entire wing part; The actuating part includes a push slider, a connecting rod, a fuselage slide rail, a rotating shaft, a sealing plate, a connecting lug and a retractable fairing; the connecting rod includes a No. 1 connecting rod, a main connecting rod and a No. 2 connecting rod; the sealing plate includes a No. 1 sealing plate, a No. 2 sealing plate and a No. 3 sealing plate; the connecting lug includes a No. 1 lug and a No. 2 lug; the retractable fairing includes a 1-stage retractable fairing and a 2-stage retractable fairing; When the front wing is in the variable sweep angle state, the main wing, the 1st retractable fairing and the 2nd retractable fairing are arranged in sequence close to one side of the fuselage slide rail; the rotating shaft is fixed to the main wing, and the main wing is fixed to the No. 1 cover plate; the No. 1 ear and the No. 2 ear are both fixed on the side of the 1st retractable fairing close to the main wing, and the push slider is fixed on the 1st retractable fairing close to the side of the fuselage slide rail; the two ends of the No. 1 connecting rod are respectively rotatably connected to the No. 1 ear and the No. 1 cover plate; the No. 2 cover plate is fixed on the side of the 2nd retractable fairing close to the 1st retractable fairing; the two ends of the main connecting rod are respectively rotatably connected to the No. 1 cover plate and the No. 2 cover plate; the two ends of the No. 2 connecting rod are respectively rotatably connected to the No. 2 cover plate; a slide rail is set on the No. 3 cover plate, and the No. 1 cover plate is pushed by the push slider, and the slider slides along the slide rail on the No. 3 cover plate, and the lower end of the No. 3 cover plate can move horizontally on the fuselage slide rail.

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