Semi-active controlled variable-geometry winglets for gust load alleviation and method

Abstract

The present invention discloses a semi-active control variable-angled winglet for gust load alleviation and a method thereof. The winglet includes a connection structure, a limiting mechanism, a locking mechanism, a reset mechanism, and a winglet body. The connection structure is used to connect the main wing and the winglet body, enabling the winglet body to rotate around the rotation axis. The limiting mechanism is used to limit the rotation range of the winglet body. The reset structure pulls the connection structure not in the initial position back to the initial position and cooperates with the locking mechanism to fix the connection structure at the initial position. The present invention uses a cam to push the driving rod to lock the position of the winglet body and a shape memory alloy spring to control the reset of the winglet body, which can quickly respond to external gust excitations. At the same time, a linkage mechanism is adopted, which has good stability and effectively reduces the weight. While meeting the basic performance requirements of the wing structure, through passive gust alleviation technology, the wing has a good gust alleviation effect.

Description

Technical Field

[0001] The present invention belongs to the field of aircraft design, and particularly relates to a semi-active control variable-angled winglet for gust load alleviation and a method therefor. Background Art

[0002] Most modern aircraft adopt lightweight materials to reduce the structural weight of the wing and increase the aspect ratio to improve the economy of the aircraft. However, this also leads to a series of adverse aeroelastic problems due to the increased elasticity of the wing structure.

[0003] Aircraft inevitably encounter gusts during flight. Gusts are characterized by rapid transient changes and short time scales, which can cause additional aerodynamic forces on the airframe, resulting in changes in the attitude and flight path of the aircraft and vibrations of the airframe. In particular, the overload caused by vertical gusts has a more obvious impact, making it difficult to control the aircraft, reducing the comfort of pilots and passengers, and at the same time shortening the fatigue life of the aircraft structure and even leading to aircraft accidents. With the continuous increase in the flexibility of modern large aircraft, the harm caused by gust loads has increased sharply, making the research on gust load suppression a new trend.

[0004] Due to the characteristics of rapid transient changes and short time scales of gusts, high requirements are also put forward for gust alleviation technology: rapid response and fast gust alleviation speed. In terms of gust alleviation technology, most large aircraft adopt active control technology to suppress gust alleviation. The active control of the control surfaces of the aircraft, such as flaps and ailerons, can be used for active gust alleviation. By deflecting the control surfaces, an additional pitching moment is generated on the aircraft, and the longitudinal movement of the aircraft is controlled by changing the pitching attitude. However, this method will cause a high delay and has a poor gust suppression effect. At the same time, due to the generally large aspect ratio of large aircraft, large bending and torsional deformations will occur under the action of aerodynamic loads, which puts forward high requirements for the structural strength and stiffness of the wing itself and also makes the structural weight of the wing itself relatively large. Therefore, gust alleviation can be achieved through targeted structural design, such as passive alleviation using variable wings, winglets, etc. Since the research on gust load alleviation mainly focuses on active control, the research on passive or semi-active control is not sufficient, especially the lack of relevant structural design, aeroelastic models, control theories, and relevant experimental verifications. Therefore, relevant conceptual design and structural implementation are particularly important. Summary of the Invention

[0005] In order to overcome the problem that there are many deficiencies in the traditional active control gust alleviation technology for high aspect ratio aircraft, the present invention proposes a semi-active control variable angle winglet and method for gust load alleviation. While meeting the basic performance requirements of the wing structure, through passive gust alleviation technology, the wing has a good gust alleviation effect. The method of using a cam to push the drive rod to lock the position of the winglet body and a shape memory alloy spring to control the reset of the winglet body can quickly respond to external gust excitation. At the same time, a basic link mechanism is adopted, which has a simple structure, good stability, and can effectively reduce the structural weight.

[0006] To achieve the above object, the present invention adopts the following technical solutions:

[0007] A semi-active control variable angle winglet for gust load alleviation, comprising a connection structure A, a limit mechanism B, a locking mechanism C, a reset mechanism D, and a winglet body E; the connection structure A is used to connect the main wing F and the winglet body E, so that the winglet body E can rotate around the rotation axis; the limit mechanism B is used to limit the rotation range of the winglet body E; the reset structure D pulls the connection structure A that is not in the initial position back to the initial position and cooperates with the locking mechanism C to fix the connection structure A at the initial position.

[0008] Preferably, the connection structure A includes a fixed connection component 1-1 and a rotary connection component 1-2. The fixed connection component 1-1 is fixedly installed on the main wing F and has an opening at the end; the rotary connection component 1-2 is fixedly installed on the winglet body E and has an opening at the end, and is coaxially connected with the end of the fixed connection component 1-1; two rotating bearings are respectively installed in the end openings of the fixed connection component 1-1 and the rotary connection component 1-2, and the rotary connection component 1-2 can rotate around the rotating bearings.

[0009] Further preferably, a sleeve is used to separate the two rotating bearings, which can effectively prevent the relative sliding between the bearings and at the same time effectively reduce the structural mass.

[0010] Preferably, the limit mechanism B includes an upper limit baffle 2-1 and a lower limit baffle 2-2. The upper limit baffle 2-1 is fixed on the main wing F and is located above the fixed connection component 1-1 to limit the upward rotation range of the rotary connection component 1-2; the lower limit baffle 2-2 is fixed on the main wing F and is located below the fixed connection component 1-1 to limit the downward rotation range of the rotary connection component 1-2.

[0011] Preferably, the locking mechanism C includes a driving rod 3-1, a cam 3-2, a spring 3-3, and an axial fixing member 3-4. The cam 3-2 is connected to the motor and can rotate under the action of the motor. The tip part of the cam is connected to the driving rod 3-1. The axial fixing member 3-4 is fixedly connected to the main wing F and has openings at both ends. The driving rod 3-1 passes through the openings at the ends of the axial fixing member 3-4. The spring 3-3 is installed on the driving rod 3-1.

[0012] Preferably, the reset mechanism D includes a fixed initial position member 2-5 and a shape memory alloy spring 3-5. The ends of the shape memory alloy spring 3-5 are respectively connected to ropes. The ropes are respectively wound around the fixed pulleys and connected to the rotary connection member 1-2. The fixed pulleys are fixed in the bottom slots of the lower limit baffle 2-2. The fixed initial position member 2-5 is fixed on the winglet body E and has an opening at the end. The end of the driving rod 3-1 passes through the opening at the end of the fixed initial position member 2-5 to fix the winglet body E at the initial position.

[0013] For the working method of the semi-active controlled variable-angle winglet for gust load mitigation, during the flight of the main wing equipped with the semi-active controlled variable-angle winglet for gust load mitigation, when affected by external gusts, the gust monitoring sensor transmits the gust signal to the motor, and the motor drives the cam 3-2 to rotate. The cam 3-2 pushes the driving rod 3-1 to move axially. The driving rod 3-1 is pulled out from the opening at the end of the fixed initial position member 2-5. At the same time, the convex structure on the driving rod 3-1 will squeeze the spring 3-3 during the movement. The winglet body E is liberated from the locked state and rotates around the rotating shaft determined by the opening at the end of the rotary connecting rod member 1-2 under the action of the external gust, dissipating the energy of the gust. After the gust energy is dissipated, a current is applied to both ends of the shape memory alloy spring 3-5. The shape memory alloy spring 3-5 undergoes a shape memory effect under the action of the current and shortens in length. At the same time, it pulls the rope to rotate around the fixed pulley, and the other end of the rope pulls the winglet body E back to the initial position. After the winglet body E returns to the initial position, the motor drives the cam 3-2 to rotate. The driving rod 3-1 moves horizontally under the action of the spring. The end of the driving rod 3-1 passes through the opening at the end of the fixed initial position member 2-5 to fix the winglet body E at the initial position. The cam 3-2 also returns to its original position under the drive of the motor, and the power supply of the motor is cut off.

[0014] Compared with the prior art, the present invention has the following advantages:

[0015] 1) When a gust is sensed, the locking mechanism is quickly opened, and the gust aerodynamic load is used to drive the winglet, while reducing the gust response and the internal stress applied by the gust to the structure.

[0016] 2) After the gust has passed, the shape memory alloy spring is used to slowly drive the winglet to return to its original state. The recovery time is controllable. After recovery, the winglet is fixed by a locking mechanism. Once the locking mechanism is locked, the shape memory alloy can be powered off, and the system does not need to consume additional control energy, which is energy-saving, safe and reliable.

[0017] 3) The present invention adopts a connecting rod structure design, which has a simple structure and good stability, and can effectively reduce the weight of the connecting structure. Description of the Drawings

[0018] Figure 1 It is a schematic diagram of the overall structure of a semi-active control variable angle winglet for gust load mitigation.

[0019] Figure 2 It is a schematic diagram of the overall structure of other components except the wing and the winglet.

[0020] Figure 3 It is a schematic diagram of the locking mechanism of the connecting structure.

[0021] Figure 4 It is a schematic diagram of the locking mechanism and the limiting mechanism.

[0022] Figure 5 It is a schematic diagram of the locking mechanism.

[0023] Figure 6 It is a schematic diagram of the reset mechanism.

[0024] Wherein: A is the connecting structure part, B is the limiting mechanism part, C is the locking mechanism part, D is the reset mechanism, 1-1 is the fixed connecting component, 1-2 is the rotating connecting component, 1-3 is the fixed component for restricting the axial movement of the bearing, 2-1 is the upper limit baffle, 2-2 is the lower limit baffle, 2-3 is the component for fixing the initial position, 3-1 is the driving rod, 3-2 is the cam, 3-3 is the spring, 3-4 is the axial fixing component, 2-5 is the component for fixing the initial position, and 3-5 is the shape memory alloy spring. Detailed Embodiment

[0025] The present invention will be further described in detail below in conjunction with the drawings and the detailed embodiment.

[0026] The following are specific embodiments of the present invention. It should be noted that the present invention is not limited to the following specific embodiments, and any equivalent transformation based on the technical solution of the present application falls within the protection scope of the present invention.

[0027] Complying with the above technical solution, as Figures 1 to 6 shown, this embodiment provides a semi-active control variable angle winglet and method for gust load mitigation, which can deform under the influence of external gusts to eliminate the influence of gusts.

[0028] As shown Figure 1 and Figure 2 in FIGS. and, a semi-active control variable-angled winglet for gust load alleviation according to the present invention includes a connection structure A, a limit mechanism B, a locking mechanism C, a reset mechanism D, and a winglet body E.

[0029] The connection structure A connects the main wing F and the winglet body E and is restricted in its rotation range by the limit mechanism B; the reset structure D pulls the connection structure A that is not in the initial position back to the initial position and cooperates with the locking mechanism C to fix the connection structure A at the initial position.

[0030] As shown Figure 3 in FIGS., the connection structure A is used to connect the main wing F and the winglet body E so that the winglet body E can rotate around the rotation axis; the connection structure A includes a fixed connection component 1-1 and a rotating connection component 1-2. The fixed connection component 1-1 is fixedly installed on the main wing F and has a circular opening at the end; the rotating connection component 1-2 is fixedly installed on the winglet body E and has an opening at the end, and is coaxially connected with the end of the fixed connection component 1-1; two rotating bearings are respectively installed in the end openings of the fixed connection component 1-1 and the rotating connection component 1-2, and the two rotating bearings are separated by a sleeve. The rotating connection component 1-2 can rotate around the rotating bearing.

[0031] As shown Figure 4 in FIGS., the limit mechanism B is used to limit the rotation range of the winglet body E; the limit mechanism B includes an upper limit baffle 2-1 and a lower limit baffle 2-2. The upper limit baffle 2-1 is fixed on the main wing F and is located above the fixed connection component 1-1 to limit the upward rotation range of the rotating connection component 1-2; the lower limit baffle 2-2 is fixed on the main wing F and is located below the fixed connection component 1-1 to limit the downward rotation range of the rotating connection component 1-2.

[0032] As shown Figure 5 in FIGS., the locking mechanism C is used to fix the winglet body E at the initial position; the locking mechanism C includes a driving rod 3-1, a cam 3-2, a spring 3-3, and an axial fixing component 3-4. The cam 3-2 is connected to a motor and can rotate under the action of the motor, and the tip part of the cam is connected to the driving rod 3-1; the axial fixing component 3-4 is fixedly connected to the main wing F and has circular openings at both ends; the driving rod 3-1 passes through the end opening of the axial fixing component 3-4; the spring 3-3 is installed on the driving rod 3-1.

[0033] As shown Figure 4 and Figure 6As shown, the reset mechanism D is used to pull the winglet body E back to the initial position, cooperate with the locking mechanism C to fix the winglet body E at the initial position; the reset mechanism D includes a fixed initial position component 2-5 and a shape memory alloy spring 3-5, and the ends of the shape memory alloy springs 3-5 are both connected to ropes; the ropes are respectively wound around the fixed pulleys and connected to the rotary connection component 1-2; the fixed pulleys are fixed in the bottom slots of the lower limit baffle 2-2. The fixed initial position component 2-5 is fixed on the winglet body E and has a circular opening at the end; the end of the driving rod 3-1 passes through the end of the fixed initial position component 2-5 to fix the winglet body E at the initial position.

[0034] The working process of the present invention is as follows:

[0035] As Figure 2 As shown, when the main wing equipped with the above semi-active control variable angle winglet for gust load mitigation encounters external gusts during flight, the gust monitoring sensor transmits the gust signal to the motor, and the motor drives the cam 3-2 to rotate. The cam 3-2 pushes the driving rod 3-1 to move axially. The driving rod 3-1 is drawn out from the end opening of the fixed initial position component 2-5. At the same time, the convex structure on the driving rod 3-1 will squeeze the spring 3-3 during the movement. The winglet body E is released from the locked state and rotates around the rotation axis determined by the opening at the end of the rotary connection rod 1-2 under the action of the external gust, dissipating the energy of the gust; after the gust energy is dissipated, an electric current is applied to both ends of the shape memory alloy spring 3-5. The shape memory alloy spring 3-5 undergoes a shape memory effect under the action of the current and its length becomes shorter. At the same time, it pulls the rope to rotate around the fixed pulley, and the other end of the rope pulls the winglet body E back to the initial position; after the winglet body E returns to the initial position, the motor drives the cam 3-2 to rotate, and the driving rod 3-1 moves horizontally under the action of the spring. The end of the driving rod 3-1 passes through the end opening of the fixed initial position component 2-5 to fix the winglet body E at the initial position. The cam 3-2 also returns to its original position driven by the motor, and the motor is powered off.

Claims

1. A semi-active controlled variable-geometry winglet for gust load alleviation, characterized in that: It includes a connection structure (A), a limiting mechanism (B), a locking mechanism (C), a reset mechanism (D) and a winglet body (E); the connection structure (A) is used to connect the main wing (F) and the winglet body (E) so that the winglet body (E) can rotate around the rotation axis; the limiting mechanism (B) is used to limit the rotation range of the winglet body (E); the reset mechanism (D) pulls the connection structure (A) that is not in the initial position back to the initial position and cooperates with the locking mechanism (C) to fix the connection structure (A) at the initial position. The locking mechanism (C) includes a driving rod (3-1), a cam (3-2), a spring (3-3) and an axially fixed component (3-4). The cam (3-2) is connected to the motor and can rotate under the action of the motor. The tip part of the cam is connected to the driving rod (3-1); the axially fixed component (3-4) is fixedly connected to the main wing (F) and has openings at both ends; the driving rod (3-1) passes through the openings at the ends of the axially fixed component (3-4). The spring (3-3) is installed on the driving rod (3-1). The reset mechanism (D) includes a fixed initial position component (2-5) and a shape memory alloy spring (3-5). The ends of the shape memory alloy spring (3-5) are respectively connected to ropes; the ropes respectively bypass the fixed pulleys and are connected to the rotary connection component (1-2); the fixed pulleys are fixed in the bottom slots of the lower limit baffle (2-2); the fixed initial position component (2-5) is fixed on the winglet body (E) and has an opening at the end; the end of the driving rod (3-1) passes through the end of the fixed initial position component (2-5) to fix the winglet body (E) at the initial position.

2. The semi-active controlled variable-geometry winglet for gust load alleviation according to claim 1, characterized in that: The connection structure (A) includes a fixed connection component (1-1) and a rotary connection component (1-2). The fixed connection component (1-1) is fixedly installed on the main wing (F) and has an opening at the end; the rotary connection component (1-2) is fixedly installed on the winglet body (E) and has an opening at the end, and is coaxially connected to the end of the fixed connection component (1-1); two rotating bearings are respectively installed in the openings at the ends of the fixed connection component (1-1) and the rotary connection component (1-2), and the rotary connection component (1-2) can rotate around the rotating bearings.

3. The semi-active controlled variable-angled winglet for gust load alleviation according to claim 2, wherein: The two rotating bearings are separated by a sleeve.

4. The semi-active controlled variable-tilt winglet for gust load alleviation according to claim 1, wherein: The limiting mechanism (B) includes an upper limit baffle (2-1) and a lower limit baffle (2-2). The upper limit baffle (2-1) is fixed on the main wing (F) and is located above the fixed connection component (1-1) to limit the upward rotation range of the rotary connection component (1-2); the lower limit baffle (2-2) is fixed on the main wing (F) and is located below the fixed connection component (1-1) to limit the downward rotation range of the rotary connection component (1-2).

5. A working method of a semi-active controlled variable-angled winglet for gust load alleviation according to any one of claims 1 to 4, characterized in that: During the flight of the main wing equipped with the semi-active controlled variable-geometry winglet for gust load alleviation, when encountering external gusts, the gust monitoring sensor transmits the gust signal to the motor. The motor drives the cam (3-2) to rotate, and the cam (3-2) pushes the driving rod (3-1) to move axially. The driving rod (3-1) is drawn out from the end opening of the fixed initial position component (2-5). At the same time, the protruding structure on the driving rod (3-1) will compress the spring (3-3) during the movement, and the winglet body (E) is liberated from the locked state and rotates around the rotation axis determined by the end opening of the rotating connection component (1-2) under the action of the external gust, dissipating the energy of the gust. After the gust energy is dissipated, a current is applied to both ends of the shape memory alloy spring (3-5). The shape memory alloy spring (3-5) undergoes a shape memory effect under the action of the current and shortens in length. At the same time, it pulls the rope to rotate around the fixed pulley, and the other end of the rope pulls the winglet body (E) back to the initial position. After the winglet body (E) returns to the initial position, the motor drives the cam (3-2) to rotate, and the driving rod (3-1) moves horizontally under the action of the spring. The end of the driving rod (3-1) passes through the end opening of the fixed initial position component (2-5) to fix the winglet body (E) at the initial position. The cam (3-2) also returns to its original position under the drive of the motor, and the motor is powered off.

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