A deformation method for an asymmetrically deformable aircraft used in wind tunnel tests

Abstract

A deformation method for an asymmetrically deformable aircraft used in wind tunnel tests, which employs an asymmetrically deformable aircraft; the structure of the asymmetrically deformable aircraft includes: the front section of the aircraft, the rear section of the aircraft, tightening screws, a balance, a lead screw bearing, a lead screw, a motor, a left wing slider, a left wing connecting rod, a left wing, a right wing connecting rod, a right wing, and a right wing slider; the deformation method includes: driving the lead screw to rotate by the motor, causing the left wing slider and the right wing slider to move towards or away from each other on the lead screw, driving the corresponding left wing connecting rod and right wing connecting rod to move, and further driving the corresponding left wing and right wing to simultaneously extend or retract from both sides of the main body of the aircraft structure; the pitches of the lead screw at the installation positions corresponding to the left wing slider and the right wing slider are different, so that the extending or retracting speeds of the left wing and the right wing are different, realizing asymmetric deformation.

Description

Technical Field

[0001] The present invention relates to a deformation method for an asymmetrically deformable aircraft used in wind tunnel tests, belonging to the field of folding wings of deformable aircraft. Background Art

[0002] Traditional fixed-configuration aircraft are usually designed at a fixed design point and can only maintain high-performance flight in a certain flight profile. However, beyond the design point, the flight performance drops sharply, and there may even be a risk of aircraft out of control. Deformable aircraft integrate the aerodynamic shape characteristics of different configuration aircraft and actively change the aerodynamic shape according to the changes in the flight environment, greatly improving the full-mission flight ability and achieving the best flight performance under different flow states. The development of deformable aircraft has become an important way to break through the performance of future aircraft and has also attracted the attention of many scholars at home and abroad.

[0003] Generally, deformable aircraft have a symmetric wing structure and are mainly used to change the magnitude of the aerodynamic force acting on the aircraft. The telescopic wing deformation of asymmetric aircraft is a special mode of deformable aircraft. Through the asymmetric deformation of the wing, it can not only change the magnitude of the aerodynamic force acting on the aircraft, but also change the direction of the force, thereby generating a control moment that affects the roll channel and greatly improving the control effect of the aircraft. At present, the research on asymmetric deformable aircraft is not deep enough, mainly focusing on three major directions: the modeling of asymmetric aircraft, the control method of asymmetric aircraft deformation, and the computer simulation calculation of the aerodynamic characteristics of asymmetric aircraft. Since the aircraft needs to undergo large-scale shape changes, on the one hand, the aircraft will inevitably have local structures such as discontinuous external surfaces and connecting gaps, and on the other hand, the flow field state will change accordingly. The existence of the above phenomena makes the aerodynamic characteristics and environmental loads of deformable aircraft very complex. As a basic research method in aerodynamics, wind tunnel tests can accurately measure the unsteady aerodynamic characteristics generated by the deformation of the aircraft and are of great significance for the research of asymmetric aircraft. Due to the large wing surface of the aircraft, the aerodynamic characteristics of the aircraft are very sensitive to the change of the wing surface deformation amount, and the deformation scale of the wing surface directly affects the test measurement results. Therefore, under the conditions of wind tunnel tests, how to achieve precise control of the wing surface has become an engineering problem to be solved urgently. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to overcome the deficiencies of the prior art and solve the problem of asymmetric deformation of the aircraft.

[0005] The object of the present invention is achieved by the following technical solutions:

[0006] A deformation method for an asymmetrically deformable aircraft used in wind tunnel tests, using an asymmetrically deformable aircraft;

[0007] The structure of the asymmetric deformation aircraft includes: the front section of the aircraft, the rear section of the aircraft, tightening screws, a balance, a lead screw bearing, a lead screw, a motor, a left-wing slider, a left-wing connecting rod, a left wing, a right-wing connecting rod, a right wing, and a right-wing slider;

[0008] The front section and the rear section of the aircraft are connected to form the main body of the aircraft structure;

[0009] The tightening screws are connected to the balance, and the nut parts of the tightening screws are fitted with the rear section of the aircraft, so that the balance is connected to the rear section of the aircraft; the balance is used for aerodynamic force measurement;

[0010] One end of the lead screw is fitted with the output end of the motor, and the other end is fitted with the lead screw bearing. The left-wing slider and the right-wing slider are installed on the lead screw. The pitches at the installation positions of the left-wing slider and the right-wing slider on the lead screw are different and the thread directions are opposite;

[0011] One end of the left-wing connecting rod is connected to the left-wing slider, and the other end is connected to the left wing;

[0012] One end of the right-wing connecting rod is connected to the right-wing slider, and the other end is connected to the right wing;

[0013] The deformation method includes: using the motor to drive the lead screw to rotate, so that the left-wing slider and the right-wing slider move towards or away from each other on the lead screw, driving the corresponding left-wing connecting rod and right-wing connecting rod to move, and further driving the corresponding left wing and right wing to extend or retract simultaneously from both sides of the main body of the aircraft structure;

[0014] The pitches at the installation positions of the left-wing slider and the right-wing slider on the lead screw are different, so that the extending or retracting speeds of the left wing and the right wing are different, realizing asymmetric deformation.

[0015] Preferably, the asymmetric deformation aircraft further includes a pressing gasket, a heat insulation gasket, and a heat insulation cone sleeve;

[0016] The pressing gasket is installed between the tightening screw and the rear section of the aircraft; the heat insulation gasket is installed between the pressing gasket and the rear section of the aircraft;

[0017] For the heat insulation cone sleeve, the outer conical surface is fitted with the rear section of the aircraft, and the inner conical surface is fitted with the outer conical surface of the head of the balance.

[0018] Preferably, the asymmetric deformation aircraft further includes a motor heat insulation sleeve, the outer diameter surface of the motor heat insulation sleeve is fitted with the rear section of the aircraft, and the inner diameter surface is fitted with the motor.

[0019] Preferably, the asymmetric deformation aircraft further includes a sealing cover for the balance measurement system and a sealing cover for the wing surface drive system;

[0020] The sealing cover for the balance measurement system and the sealing cover for the wing surface drive system are both installed at the tail of the aircraft structure main body;

[0021] The sealing cover of the balance measurement system is used to reduce the influence of hot air flow on the balance measurement;

[0022] The sealing cover of the wing surface drive system is used to prevent the impurities in the flow field from affecting the extension or retraction of the left wing and the right wing.

[0023] Preferably, the asymmetric deformation aircraft further includes a motor flange, which is installed between the rear section of the aircraft and the motor to fix the motor.

[0024] Preferably, the rear section of the aircraft is a cavity and is provided with a partition, which divides the cavity into a wing surface drive system cavity chamber and a balance measurement system cavity chamber.

[0025] Preferably, the tightening screw and the balance are both located in the balance measurement system cavity chamber.

[0026] Preferably, the lead screw bearing, the lead screw, the motor, the left wing slider, the left wing connecting rod, the right wing connecting rod, and the right wing slider are all located in the wing surface drive system cavity chamber.

[0027] Preferably, a slider track is provided in the wing surface drive system cavity chamber, and the left wing slider and the right wing slider slide along the direction of the slider track.

[0028] Preferably, the method for determining the wing surface movement distance is as follows:

[0029] ΔL = d·sin(α'1 + α'2) - d·sin(α1 + α2)

[0030]

[0031]

[0032]

[0033]

[0034] In the formula, a is the distance from the wing-body rotation axis to the wing connecting rod rotation axis; b is the Z-direction distance from the wing-body rotation axis to the slider connecting rod rotation axis; c is the X-direction distance from the wing-body rotation axis to the slider connecting rod rotation axis; d is the distance from the connecting rod slider connecting rod rotation axis to the wing connecting rod rotation axis; n is the motor speed; t is the motor operation time; h is the lead screw pitch. The coordinate system adopts the front-up-right coordinate system, the coordinate origin is located at the vertex of the aircraft head, the X-axis points to the front of the aircraft, the Y-axis is perpendicular to the X-axis and upward in the longitudinal symmetry plane, and the Z-axis is determined according to the right-hand rule.

[0035] The present invention has the following beneficial effects compared with the prior art:

[0036] (1) The wing surface deformation method of the present invention analyzes the relative relationship between the wing surface movement and the lead screw movement, constructs a digital model of wing surface deformation, and realizes the precise control of the wing surface movement;

[0037] (2) The double-wing surface control method of the present invention uses time as the reference coordinate system to create the double-wing surface motion equation in the same time dimension, so as to accurately obtain the relative relationship of the double-wing surface and provide theoretical support for the wing surface deformation scale under test conditions;

[0038] (3) For the wing surface transmission mechanism of the present invention, a servo motor is designed as the driving energy source to convert the rotational motion of the motor into the rotational motion of the wing surface. At the same time, the internal transmission components of the mechanism are all designed as rigid structures, which on the one hand ensures the structural strength of the transmission mechanism, and on the other hand avoids the occurrence of motion slipping and ensures the motion accuracy of the wing surface. Description of the Drawings

[0039] Figure 1 is a schematic diagram of the external structure of an embodiment of the present invention;

[0040] Figure 2 is a schematic diagram of the internal structure of an embodiment of the present invention;

[0041] Figure 3 is a schematic diagram of the rear section of the aircraft of an embodiment of the present invention;

[0042] Figure 4 is a schematic diagram of the connection of the motor, motor heat insulation sleeve, lead screw, left wing slider, right wing slider, and lead screw bearing of an embodiment of the present invention;

[0043] Figure 5 is a schematic diagram of the structure of the left wing slider of an embodiment of the present invention;

[0044] Figure 6 is a schematic diagram of the structure of the motor flange of an embodiment of the present invention;

[0045] Figure 7 is a schematic diagram of the control parameters of the wing surface motion of an embodiment of the present invention. Detailed Embodiments

[0046] To make the objectives, technical solutions, and advantages of the present invention clearer, the embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0047] A deformation method for an aircraft structure capable of achieving asymmetric telescoping of wing surfaces. The aircraft structure includes: the front section 1 of the aircraft; the rear section 2 of the aircraft, which has a cavity inside to accommodate the balance measurement system and the wing surface drive system; the balance measurement system seal cover 3, which on the one hand avoids the interference of wing surface drive on the test system, and on the other hand reduces the influence of external heat and impurities on the measurement system; the wing surface drive system seal cover 4, which avoids the entry of flow field impurities into the system, thereby reducing the probability of wing surface movement jamming. The internal structure includes: the tightening screw 5, which fixes the balance to the rear section of the aircraft; the pressing gasket 6; the heat insulation gasket 7; the heat insulation cone sleeve 8; the balance 9, which realizes the measurement of the aircraft's aerodynamic coefficient; the lead screw bearing 10, which realizes the fixation of the lead screw; the lead screw 11, whose front and rear sections are designed with different pitches and are respectively matched with the left / right wing sliders to convert the rotational motion into a linear motion; the motor flange 12, which fixes the motor to the rear section of the aircraft; the motor heat insulation sleeve 13; the motor 14, which provides power; the left wing slider 17; the left wing connecting rod 16; the left wing 15; the right wing connecting rod 18; the right wing 19; the right wing slider 20.

[0048] Among them, the tightening screw, the pressing gasket, the heat insulation gasket, the heat insulation cone sleeve, the balance and the balance measurement system seal cover together constitute the balance measurement system. During the installation process, first, the outer conical surface of the heat insulation cone sleeve is matched with the conical groove on the rear section of the aircraft, and the inner conical surface is matched with the outer conical surface of the balance head. One end of the tightening screw is matched with the balance through threads, and the nut part at the other end is limited by the rear section of the aircraft. A heat insulation gasket and a tightening gasket are placed between the tightening screw and the rear section of the aircraft.

[0049] Among them, the motor, the motor heat insulation sleeve, the motor flange, the lead screw, the lead screw bearing, the left wing slider, the left wing connecting rod, the left wing, the right wing connecting rod, the right wing, the right wing slider and the wing surface drive system seal cover together constitute the wing surface drive system. During the installation process, the outer diameter surface of the motor heat insulation sleeve is matched with the rear section of the aircraft, and the inner diameter surface is matched with the motor. The motor flange cover is fixed to the motor by screws. The output end of the motor is connected to the lead screw by a pin. The front section of the lead screw is matched with the left wing slider through threads. One end of the left wing connecting rod is connected to the left wing slider and the other end is connected to the left wing; the rear section of the lead screw is matched with the right wing slider through threads. One end of the right wing connecting rod is connected to the right wing slider and the other end is connected to the right wing.

[0050] In the wing surface drive system, the lead screw is simultaneously matched with the left / right wing sliders, thus solving the problem of synchronous start and stop of the asymmetric movement of the left and right wing surfaces. The spiral directions of the threads of the front and rear sections of the lead screw are opposite, so that the left wing slider moves towards the tail of the model and the right wing slider moves towards the head of the model. At the same time, the corresponding pitches are different, the pitch of the front section is larger and the pitch of the rear section is smaller. Therefore, the movement speed of the right wing is greater than that of the left wing, and finally the asymmetric deformation of the aircraft is realized.

[0051] During the actual operation process, it is necessary to achieve precise control of the wing surface movement. The corresponding wing surface movement distance formula is as follows:

[0052] ΔL = d·sin(α'1 + α'2) - d·sin(α1 + α2) (1)

[0053]

[0054]

[0055]

[0056]

[0057] In the formula, a is the distance from the wing-body rotating shaft to the wing-link rotating shaft; b is the Z-direction distance from the wing-body rotating shaft to the slider-link rotating shaft; c is the X-direction distance from the wing-body rotating shaft to the slider-link rotating shaft; d is the distance from the link-slider-link rotating shaft to the wing-link rotating shaft; n is the motor speed; t is the motor running time; h is the lead of the screw thread. The coordinate system adopts the front-up-right coordinate system, with the coordinate origin located at the vertex of the aircraft head, the X-axis pointing forward of the aircraft, the Y-axis perpendicular to the X-axis and upward within the longitudinal symmetry plane, and the Z-axis determined by the right-hand rule, as Figure 7 shown.

[0058] Wing surface movement process:

[0059] The motor heat insulation sleeve is integrally sleeved on the motor. The motor flange cover is connected to the motor by screws and is also fixed to the rear section of the aircraft by screws, thereby realizing the connection between the motor and the aircraft. The output end of the motor is connected to the screw by a pin. The front section of the screw is matched with the left-wing slider through threads. One end of the left-wing link is connected to the left-wing slider and the other end is connected to the left wing; the rear section of the screw is matched with the right-wing slider through threads. One end of the right-wing link is connected to the right-wing slider and the other end is connected to the right wing. The upper ends of the left wing and the right wing are connected to the rear section of the aircraft by pin shafts, and the wings can rotate freely around the aircraft. Taking the left wing surface as an example, the movement of the wing surface is described as follows: When the motor runs, it drives the screw to rotate. Due to the existence of the thread, the rotational movement of the screw is converted into the linear movement of the left-wing slider. The left-wing slider moves along the axial direction of the screw towards the warhead, thereby driving the left-wing link to move. Since the left wing is connected to the rear section of the aircraft through a rotating shaft, the left wing can only perform rotational movement. The left-wing link is a rigid body, so the link pushes the wing surface out. Due to the limit of the rotating shaft, the left wing rotates outwards, and finally the extension (rotational movement) of the wing surface is realized.

[0060] As Figure 1 、 Figure 2As shown, according to an embodiment of the present invention, an asymmetric deformable aircraft structure for wind tunnel testing includes: an aircraft front section 1, an aircraft rear section 2, a balance measurement system sealing cover 3, an airfoil transmission system sealing cover 4, a tightening screw 5, a compression gasket 6, a thermal insulation gasket 7, a thermal insulation cone sleeve 8, a balance 9, a screw bearing 10, a screw 11, a motor flange 12, a motor thermal insulation sleeve 13, a motor 14, a left wing slider 17, a left wing connecting rod 16, a left wing 15, a right wing connecting rod 19, a right wing 18, and a right wing slider 20.

[0061] The aircraft front section 1, one of the main structures of the asymmetric aircraft model, is connected to the aircraft rear section 2 by pins.

[0062] The rear section of the aircraft 2 Figure 3 As shown, one of the main structures of the asymmetric aircraft model houses the balance measurement system and the wing drive system. To prevent interference between the two systems, a partition 2-4 is designed inside. Within the wing drive system cavity, a slider track 2-1 is designed to enable the left and right wing sliders 16 and 19 to move in a specified direction. Screw bearing grooves 2-3 are also designed to facilitate the securing of the screw bearings. Within the balance measurement system cavity, a conical groove 2-2 is designed to facilitate the connection and securing of the measuring scale.

[0063] The sealing cover 3 of the balance measurement system separates the balance measurement system from the external environment and reduces the interference of thermal airflow on the wind tunnel measurement system. A circular hole is opened on the sealing cover to facilitate the extension of the support rod.

[0064] The airfoil transmission system sealing cover 4 prevents flow field impurities from entering the airfoil transmission system, thereby reducing the probability of airfoil movement jams. A circular hole is opened on the sealing cover to facilitate the extraction of motor wires.

[0065] Tighten the screw 5 , the screw thread portion cooperates with the balance 9 , and the screw nut portion cooperates with the aircraft rear section 2 , thereby achieving the connection between the balance 9 and the aircraft rear section 2 .

[0066] The compression gasket 6 is installed between the tightening screw 5 and the rear section 2 of the aircraft to increase the contact area between the tightening screw 5 and the rear section 2 of the aircraft.

[0067] The heat-insulating gasket 7 is installed between the compression gasket 6 and the rear section 2 of the aircraft to reduce heat transfer between the models and reduce the influence of temperature effects on the balance.

[0068] The outer conical surface of the heat-insulating cone sleeve 8 cooperates with the conical groove of the rear section 2 of the aircraft, and the inner conical surface cooperates with the outer conical surface of the head of the balance 9. Its main function is to reduce the heat transfer from the model to the balance and reduce the influence of the temperature effect on the balance.

[0069] The balance 9 is responsible for measuring the aerodynamic coefficients of the aircraft.

[0070] The lead screw bearing 10 fixes the lead screw 11. Since the lead screw bears an asymmetric shear force and generates a lateral torque, designing the lead screw bearing can prevent the lateral torque from being transmitted to the motor, thus avoiding damage to the motor.

[0071] One end of the lead screw 11 is fitted with the output end column section of the motor 14, and the other end is fitted with the column section of the lead screw bearing 10. The first half of the lead screw is threadedly connected to the left-wing slider 17, and the second half is threadedly connected to the right-wing slider 20. When the lead screw rotates, the thread converts the rotational motion into a linear motion. At the same time, the lead screw is designed with different pitches and different helix directions of the thread as required, so as to realize the transformation of the motion direction, motion speed, and motion range of the left / right-wing sliders, and finally realize the asymmetric motion of the wing surface.

[0072] The motor flange 12, as Figure 6 shown, fixes the motor 14 and is installed between the rear section 2 of the aircraft and the motor 14. Since the motor is placed directly in the cavity of the wing surface drive system of the rear section of the aircraft, the counterbore directions of the motor connection flange and the connection flange with the rear section are opposite.

[0073] The motor heat insulation sleeve 13 has an outer diameter surface that fits with the rear section 2 of the aircraft and an inner diameter surface that fits with the motor. Its main function is to reduce the heat transfer of the model to the motor and reduce the risk of motor failure.

[0074] The motor 14 is the driving element of the wing surface drive system; the connection of the motor, motor heat insulation sleeve, lead screw, left-wing slider, right-wing slider, and lead screw bearing is as Figure 4 shown.

[0075] The left-wing slider 17, as Figure 5 shown, fits with the front section of the lead screw 11. Through the lead screw drive, it converts the motor rotating pair into a moving pair. The lower end of the slider fits with the rear section 2 of the aircraft and is limited by a groove, ensuring only one degree of freedom in one direction. The slider is provided with a rotating shaft hole and is connected to the left-wing connecting rod 16 through a pin shaft.

[0076] The left-wing connecting rod 16 is connected to the left-wing slider 17 at one end through a pin shaft and to the left wing 15 at the other end through a pin shaft.

[0077] The left wing 17 is a deformed member for the asymmetric deformation of the aircraft.

[0078] The right-wing connecting rod 19 is connected to the right-wing slider 20 at one end through a pin shaft and to the right wing 18 at the other end through a pin shaft.

[0079] The right wing 19 is a deformed member for the asymmetric deformation of the aircraft.

[0080] The right-wing slider 20 fits with the rear section of the lead screw 11, and its motion direction is opposite to that of the left-wing slider 15.

[0081] The content not described in detail in the specification of the present invention belongs to the well-known technology of those skilled in the art.

[0082] Although the present invention has been disclosed above with the preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solution of the present invention by using the methods and technical content disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments according to the technical essence of the present invention without departing from the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A deformation method for an asymmetrically deformable aircraft used in wind tunnel tests, characterized in that, An asymmetric deformable aircraft is adopted; The asymmetric deformable aircraft includes: a front section of the aircraft, a rear section of the aircraft, a tightening screw, a balance, a lead screw bearing, a lead screw, a motor, a left-wing slider, a left-wing connecting rod, a left wing, a right-wing connecting rod, a right wing, and a right-wing slider; The front section and the rear section of the aircraft are connected to form the main body of the aircraft structure; The tightening screw is connected to the balance, and the nut part of the tightening screw cooperates with the rear section of the aircraft to connect the balance to the rear section of the aircraft; the balance is used for aerodynamic force measurement; One end of the lead screw cooperates with the output end of the motor, and the other end cooperates with the lead screw bearing. The left-wing slider and the right-wing slider are installed on the lead screw. The pitches at the installation positions of the left-wing slider and the right-wing slider on the lead screw are different and the thread directions are opposite; One end of the left-wing connecting rod is connected to the left-wing slider, and the other end is connected to the left wing; One end of the right-wing connecting rod is connected to the right-wing slider, and the other end is connected to the right wing; The deformation method includes: driving the lead screw to rotate by using the motor, so that the left-wing slider and the right-wing slider move towards or away from each other on the lead screw, driving the corresponding left-wing connecting rod and right-wing connecting rod to move, and further driving the corresponding left wing and right wing to extend or retract simultaneously from both sides of the main body of the aircraft structure; The pitches at the installation positions of the left-wing slider and the right-wing slider on the lead screw are different, so that the extending or retracting speeds of the left wing and the right wing are different, realizing asymmetric deformation.

2. The deformation method according to claim 1, characterized in that The asymmetric deformable aircraft further includes a pressing gasket, a heat-insulating gasket, and a heat-insulating cone sleeve; The pressing gasket is installed between the tightening screw and the rear section of the aircraft; the heat-insulating gasket is installed between the pressing gasket and the rear section of the aircraft; For the heat-insulating cone sleeve, the outer conical surface cooperates with the rear section of the aircraft, and the inner conical surface cooperates with the outer conical surface of the balance head.

3. The deformation method according to claim 1, characterized in that The asymmetric deformable aircraft further includes a motor heat-insulating sleeve, the outer diameter surface of the motor heat-insulating sleeve cooperates with the rear section of the aircraft, and the inner diameter surface cooperates with the motor.

4. The deformation method according to claim 1, characterized in that The asymmetric deformable aircraft further includes a sealing cover for the balance measurement system and a sealing cover for the wing surface transmission system; Both the sealing cover for the balance measurement system and the sealing cover for the wing surface transmission system are installed at the tail of the main body of the aircraft structure; The sealing cover for the balance measurement system is used to reduce the influence of hot air flow on the balance measurement; The sealing cover for the wing surface transmission system is used to prevent flow field impurities from affecting the extension or retraction of the left wing and the right wing.

5. The deformation method according to claim 1, characterized in that The asymmetric deformable aircraft further includes a motor flange, which is installed between the rear section of the aircraft and the motor to fix the motor.

6. The deformation method according to any one of claims 1 to 5, characterized in that, The rear section of the aircraft is a cavity and is provided with a partition, which divides the cavity into a wing surface transmission system cavity chamber and a balance measurement system cavity chamber.

7. The deformation method according to claim 6, characterized in that The tightening screw and the balance are both located in the balance measurement system cavity chamber.

8. The deformation method according to claim 6, characterized in that, The lead screw bearing, the lead screw, the motor, the left-wing slider, the left-wing connecting rod, the right-wing connecting rod, and the right-wing slider are all located in the wing surface transmission system cavity chamber.

9. The deformation method according to claim 6, characterized in that Slider tracks are provided in the wing surface transmission system cavity chamber, and the left-wing slider and the right-wing slider slide along the direction of the slider tracks.

10. The deformation method according to any one of claims 1 to 5, characterized in that, The method for determining the wing surface movement distance is as follows: ΔL = d·sin(α1'+α'2)-d·sin(α1+α2) Wherein, a is the distance from the wing-body rotation shaft to the wing-link rotation shaft; b is the Z-direction distance from the wing-body rotation shaft to the slider-link rotation shaft; c is the X-direction distance from the wing-body rotation shaft to the slider-link rotation shaft; d is the distance from the link-slider link rotation shaft to the wing-link rotation shaft; n is the motor speed; t is the motor operation time; h is the lead of the lead screw thread; The coordinate system adopts the front-up-right coordinate system, with the coordinate origin located at the vertex of the aircraft head, the X-axis pointing forward of the aircraft, the Y-axis being perpendicular to the X-axis and upward within the longitudinal symmetry plane, and the Z-axis determined by the right-hand rule.

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