A novel deformable aircraft structure

Abstract

The present invention discloses a novel deformable aircraft structure, which includes an aircraft model, a left aircraft wing, a right aircraft wing, a measurement system and a transmission system; the measurement system and the transmission system are installed in the inner cavity of the aircraft model, and the left aircraft wing and the right aircraft wing are respectively located on the left and right sides of the aircraft model; the transmission system includes a motor, and a slider, an XOZ plane connecting rod, an angle conversion block and an XOY plane connecting rod connected in sequence, and the XOY plane connecting rod is connected to the left aircraft wing or the right aircraft wing; the motor drives the slider to move along the X axis, drives the angle conversion block to move in the XOZ plane through the XOZ plane connecting rod, and the movement of the angle conversion block in the XOZ plane is converted into the movement of the left aircraft wing or the right aircraft wing in the XOY plane through the XOY plane connecting rod. The present invention can realize the up-and-down rotation of the aircraft wing, and has a compact structure, good synchronism, no jamming action delay, and is convenient for processing and installation, and is suitable for the special test requirements of wind tunnel tests.

Description

Technical Field

[0001] The present invention belongs to the field of folding wings of aircraft, and particularly relates to a small deformable aircraft structure that can be used for wind tunnel tests. Background Art

[0002] With the increasing complexity of the war environment, traditional aircraft have exposed many defects due to their almost unchanged geometric shape. For example, the ability of aircraft to change the attacking target is poor, and it is difficult to perform certain maneuvers at the end of the attack. In order to meet specific flight tasks completed under specific airflows and specific environments, the theory of deformable aircraft has become a hot topic in the field of aerospace. Variant aircraft improve the comprehensive flight performance through the adaptive change of the wing aerodynamic shape during flight, enabling the aerodynamic performance of the aircraft to reach the best state under different flight conditions.

[0003] Flapping-wing aircraft have both the characteristics of concealment and mobility, which conform to the concept of covert reconnaissance and precision strike in modern warfare and have good prospects for military applications. For example, Zhu Mingkang et al. designed a large-size flapping-wing structure in "Structural Analysis and Simulation Analysis of a Two-End Three-Degree-of-Freedom Bird-Imitating Flapping-Wing Aircraft" and carried out numerical simulation analysis; Liu Xubo et al. designed a flexible wing structure in "Research on the Aerodynamic Characteristics of Flexible Wings of Flapping-Wing Aircraft" with reference to the flight state of pigeons and numerically calculated the flow field state by means of fluid-structure interaction; Lin Zhenwei et al. designed a bionic double-segment wing flapping-wing aircraft with adjustable angle of attack based on mechanical design, bionics principles and aerodynamics principles. At present, the research on flapping-wing aircraft at home and abroad mainly focuses on wing surface structure simulation and numerical simulation, and there is relatively little research on aircraft structures applied to ground wind tunnel tests. Conventional flapping-wing aircraft have complex structures, large sizes and low structural strengths. However, in wind tunnel tests, the size of the wind tunnel is limited and there is a large aerodynamic load, so conventional flapping-wing aircraft cannot be directly applied to wind tunnel tests. Summary of the Invention

[0004] The object of the present invention is to overcome the above-mentioned defects and provide a novel deformable aircraft structure, which includes an aircraft model, a left aircraft wing, a right aircraft wing, a measurement system and a transmission system; the measurement system and the transmission system are installed in the inner cavity of the aircraft model, and the left aircraft wing and the right aircraft wing are respectively located on the left and right sides of the aircraft model; the transmission system includes a motor, and a slider, an XOZ plane connecting rod, an angle conversion block and an XOY plane connecting rod connected in sequence, and the XOY plane connecting rod is connected to the left aircraft wing or the right aircraft wing; the motor drives the slider to move along the X-axis, drives the angle conversion block to move in the XOZ plane through the XOZ plane connecting rod, and the movement of the angle conversion block in the XOZ plane is converted into the movement of the left aircraft wing or the right aircraft wing in the XOY plane through the XOY plane connecting rod. The present invention can realize the up-and-down rotation of the aircraft wing, and has a compact structure, good synchronization, no jamming action delay, and is convenient for processing and installation, and is suitable for the special test requirements of wind tunnel tests.

[0005] To achieve the above-mentioned invention object, the present invention provides the following technical solutions:

[0006] A novel deformable aircraft structure, which includes an aircraft model, a left aircraft wing, a right aircraft wing, a measurement system and a transmission system;

[0007] The measurement system and the transmission system are installed in the inner cavity of the aircraft model, and the left aircraft wing and the right aircraft wing are respectively located on the left and right sides of the aircraft model;

[0008] Let the geometric center of the aircraft model be the origin O, the head of the aircraft model faces the positive direction of the X-axis, the upper part of the aircraft model is the positive direction of the Y-axis, and the Z-axis is determined according to the right-hand rule;

[0009] The transmission system includes a motor, and a slider, an XOZ plane connecting rod, an angle conversion block and an XOY plane connecting rod connected in sequence, and the XOY plane connecting rod is connected to the left aircraft wing or the right aircraft wing; the motor drives the slider to move along the X-axis, drives the angle conversion block to move in the XOZ plane through the XOZ plane connecting rod, and the movement of the angle conversion block in the XOZ plane is converted into the movement of the left aircraft wing or the right aircraft wing in the XOY plane through the XOY plane connecting rod.

[0010] Further, both the left aircraft wing and the right aircraft wing include a wing main body and a bending connecting rod; one end of the bending connecting rod is fixed to the inner side of the wing main body, and the other end is hinged to the XOY plane connecting rod.

[0011] Further, the wing main bodies of both the left aircraft wing and the right aircraft wing are right-angled triangles, the inner sides of the wing main bodies correspond to the hypotenuses of the right-angled triangles, and the inner sides of the wing main bodies are not parallel to the X-axis.

[0012] Further, the bent link includes a first link parallel to the wing surface of the left wing or the right wing of the aircraft, and a second link not parallel to the wing surface of the left wing or the right wing of the aircraft. One end of the first link is fixed to the inner side of the wing body, the other end of the first link is connected to one end of the second link, and the other end of the second link is hinged to the XOY plane link.

[0013] The left wing and the right wing of the aircraft also respectively include wing bearings. The connection between the other end of the first link and one end of the second link is rotatably connected to the aircraft model through the wing bearings, and the wing bearings are parallel to the inner side of the wing body.

[0014] Further, one end of the angle conversion block has a first groove opened in the XOZ plane, and the other end has a second groove opened in the XOY plane. The angle conversion block is connected to the XOZ plane link through the first groove and connected to the XOY plane link through the second groove.

[0015] Further, the transmission system also includes an angle conversion block track. The angle conversion block track is parallel to the XOZ plane and perpendicular to the inner side of the wing body of the left wing or the right wing of the aircraft. The angle conversion block is installed in the angle conversion block track, and the angle conversion block track enables the angle conversion block to move only in the direction perpendicular to the inner side of the wing body in the XOZ plane.

[0016] Further, the transmission system also includes a motor lead screw. The rotation of the motor is converted into the movement of the slider along the X-axis through the motor lead screw.

[0017] Further, the aircraft model includes a front section of the aircraft, a rear section of the aircraft, a transmission system seal cover, and a measurement system seal cover.

[0018] The front section of the aircraft is connected to the rear section of the aircraft. The rear section of the aircraft is provided with a measurement system installation cavity and a transmission system installation cavity that are distributed up and down and are independent of each other. The measurement system and the transmission system are respectively installed in the measurement system installation cavity and the transmission system installation cavity. The measurement system seal cover and the transmission system seal cover are installed at the rear end of the rear section of the aircraft, and are respectively used to seal the measurement system installation cavity and the transmission system installation cavity. The left wing and the right wing of the aircraft are respectively located on the left and right sides of the rear section of the aircraft.

[0019] Further, the measurement system installation cavity and the transmission system installation cavity are made independent of each other through a partition.

[0020] The measurement system includes a measurement balance. A conical groove for installing the measurement balance is provided in the measurement system installation cavity.

[0021] The measurement system seal cover is provided with through holes for passing the balance wire and the motor control wire.

[0022] The transmission system installation cavity is provided with a groove along the X direction, and the slider is provided with a protrusion. The protrusion provided on the slider cooperates with the groove to realize the movement limit of the slider along the X-axis.

[0023] Furthermore, the aircraft model further includes a wing bearing seal cover.

[0024] Both the left wing and the right wing of the aircraft include a wing main body and a bent connecting rod. One end of the bent connecting rod is fixed to the inner side of the wing main body, and the other end is hinged to the XOY plane connecting rod. The bent connecting rod is rotatably connected to the aircraft model through a wing bearing.

[0025] The wing bearing seal cover is installed at the rear end of the rear section of the aircraft, and the inner side surface of the wing bearing seal cover cooperates with the wing bearing.

[0026] Compared with the prior art, the present invention has at least one of the following beneficial effects:

[0027] (1) The present invention provides a novel deformable aircraft structure, which innovatively designs a transmission system to convert the displacement in the XOZ plane into the displacement in the XOY plane, thereby realizing the up-and-down rotation of the aircraft wing surface. Moreover, the structure is compact, has good synchronism, no jamming action delay, is convenient for processing and installation, meets the special test requirements of wind tunnel tests, and improves the comprehensive flight performance.

[0028] (2) The present invention provides a novel deformable aircraft structure, which designs the structure of the wing, enabling the transmission system to drive the movement of the wing more effectively and stably when connected to the wing.

[0029] (3) The present invention provides a novel deformable aircraft structure, which particularly designs the structure of the angle conversion block and further limits its movement direction, thereby solving the problem of non-parallelism between the rudder shaft and the motor shaft and realizing the transmission in different movement directions.

[0030] (4) The present invention provides a novel deformable aircraft structure, which restricts the freedom degrees of specific components in the transmission system through the design of grooves or tracks, making the transmission process more efficient and controllable.

[0031] (5) The internal design of the aircraft structure of the present invention is provided with a limit groove, which can ensure that the starting and ending positions of the wing surface relative to the aircraft are fixed, thereby ensuring a similar motion state to that of the actual aircraft and making the wind tunnel test results more accurate.

[0032] (6) The present invention arranges the measurement system and the transmission system vertically and independently, enabling the measurement of the aerodynamic force of the deformable aircraft under wind tunnel conditions and avoiding interference between the measurement system and the transmission system.

[0033] (7) The present invention designs a series of sealing covers to isolate the measurement system and the transmission system from the outside world, avoiding the influence of external factors such as heat and impurities on the operation and measurement of the system. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 It is a schematic structural diagram of a novel deformable aircraft of the present invention;

[0035] Figure 2 It is a schematic diagram of the transmission system of the present invention;

[0036] Figure 3 It is a schematic diagram of the motor-slider-XOZ plane connecting rod-angle conversion block transmission chain of the present invention; where (a) is a certain state; (b) is the state after the slider moves leftward;

[0037] Figure 4 It is a schematic diagram of the angle conversion block-XOY plane connecting rod-wing transmission chain of the present invention; where (a) is a certain state; (b) is the state after the angle conversion block moves leftward;

[0038] Figure 5 It is a schematic structural diagram of the left wing of the aircraft of the present invention; where (a) is a schematic diagram of the XOZ plane; (b) is a schematic diagram of the XOY plane;

[0039] Figure 6 It is a schematic structural diagram of the left wing bearing sealing cover of the present invention, where (a) is a left view; (b) is a front view;

[0040] Figure 7 It is a schematic structural diagram of the rear section of the aircraft of the present invention; where (a) is a front view, (b) is a top view, and (c) is a cross-sectional view of (a) in the A-A direction;

[0041] Figure 8 It is a schematic structural diagram of the angle conversion block of the present invention; where (a) is a schematic diagram of the XOZ plane; (b) is a schematic diagram of the XOY plane;

[0042] Figure 9 It is a schematic diagram of the angle conversion block track of the present invention;

[0043] Figure 10 It is a schematic structural diagram of the slider of the present invention, where (a) is a front view; (b) is a cross-sectional view of (a) in the A-A direction;

[0044] Figure 11 It is a schematic structural diagram of the motor flange of the present invention. DETAILED DESCRIPTION OF THE INVENTION

[0045] The following is a detailed description of the present invention, and the features and advantages of the present invention will become clearer and more definite with these descriptions.

[0046] As used herein, the term "exemplary" means "serving as an example, embodiment, or illustration". Any embodiment described as "exemplary" herein need not be construed as superior or better than other embodiments. Although various aspects of the embodiments are shown in the drawings, the drawings are not necessarily drawn to scale unless otherwise specified.

[0047] In ground wind tunnel tests, it is necessary to perform adaptive scaling on the aircraft, and it is also necessary to optimize the transmission system structure and layout of the scaled deformable aircraft. Therefore, a deformable aircraft structure applied to wind tunnel tests is designed, which can not only realize the up and down flapping of the aircraft wing surface, but also has high mechanical strength, and at the same time has a compact structure, good synchronization and no jamming action delay.

[0048] A small and novel deformable aircraft structure of the present invention converts the displacement in the X direction into the displacement in the wing pitch direction through an angle conversion block. During use, the motor drives the slider to move, and the slider then drives the angle conversion block module to move, finally realizing the up and down rotation of the aircraft wing. The aircraft of the present invention can realize the up and down rotation of the wing surface, is applicable to the ground wind tunnel, and has a simple structure and good repeatability.

[0049] Such as Figure 1 and Figure 2 , the specific structure of the aircraft of the present invention is as follows:

[0050] Such as Figure 7 , the rear section 7 of the aircraft has a cavity inside to accommodate the measurement system and the transmission system. The rear section 7 of the aircraft and the front section 8 of the aircraft are the main body of the aircraft model;

[0051] The measurement system includes a measurement balance;

[0052] The transmission system includes a motor 16, and a slider 14, an XOZ plane connecting rod 13, an angle conversion block 10, and an XOY plane connecting rod 11 connected in sequence. In a preferred embodiment, it also includes an angle conversion block track 12 or an electrode lead screw; wherein the angle conversion block 10 is as Figure 8 , for converting the displacement in the XOZ plane into the displacement in the XOY plane; the XOY plane connecting rod 11 is a connecting rod transmission mechanism in the XOY plane, one end is connected to the wing, and the other end is connected to the angle conversion block 10; the XOZ plane connecting rod 13 is a connecting rod transmission mechanism in the XOZ plane, one end is connected to the angle conversion block 10, and the other end is connected to the slider 14; the motor 16 provides power, such as Figure 10 the slider 14 is connected to the motor lead screw, and through lead screw transmission, the motor rotating pair is converted into a moving pair; such as Figure 9 , the angle conversion block track 12 defines the degree of freedom of the angle conversion block 10, so that the angle conversion block 10 can only move in a given direction; the motor 16 is fixed to the rear section 7 of the aircraft through a motor flange 15 as Figure 11 .

[0053] In a preferred embodiment, as Figure 5 , the left wing 1 of the aircraft and the right wing 6 of the aircraft have the same structure. A bent connecting rod is provided inside the wing, and a shaft hole is provided at the bent part of the bent connecting rod. The wing bearing 9 is installed in the shaft hole, and the up-and-down rotation of the wing surface around the wing bearing 9 is realized through the transmission of the bent connecting rod;

[0054] In a preferred embodiment, the measurement system sealing cover 4 provided on the rear end face of the rear section 7 of the aircraft is used to isolate the influence of external heat and impurities on the measurement system, and the transmission system sealing cover 3 is used to prevent external impurities from affecting the wing surface transmission of the aircraft. As Figure 6 , the right wing bearing sealing cover 5 and the left wing bearing sealing cover 2 are used to form a seal at the wing bearing 9.

[0055] Applying the technical solution of the present invention, as Figure 3 and Figure 4 , after the motor runs, it successively experiences a series of transmission chains of the slider 14 - XOZ plane connecting rod 13 - angle conversion block 10 - XOY plane connecting rod 11 - wing, and finally realizes the up-and-down rotation of the wing surface.

[0056] Example 1:

[0057] As Figure 1 , Figure 2 shown, the deformable aircraft structure for wind tunnel test of the present invention includes: left wing 1 of the aircraft, left wing bearing sealing cover 2, transmission system sealing cover 3, measurement system sealing cover 4, right wing bearing sealing cover 5, right wing 6 of the aircraft, rear section 7 of the aircraft, front section 8 of the aircraft, wing bearing 9, angle conversion block 10, XOY plane connecting rod 11, angle conversion block track 12, XOZ plane connecting rod 13, slider 14, motor flange 15 and motor 16.

[0058] The rear section 7 of the aircraft and the front section 8 of the aircraft form the main body structure of the deformable aircraft. The rear section 7 of the aircraft houses the measurement system and the transmission system. In order to avoid interference between the measurement system and the transmission system, a partition is also designed inside to form an independent measurement system installation cavity and transmission system installation cavity. In the transmission system installation cavity, a slider track is designed, and the groove of the slider track and the protrusion provided on the slider 14 are in clearance fit to ensure that the slider 14 has only one degree of freedom. At the same time, positioning holes corresponding to the angle conversion block track 12 are designed in the transmission system installation cavity. Through a series of positioning designs, the direction of the angle conversion block track 12 is determined, so that the angle conversion block 10 installed on the angle conversion block track 12 can move in a specified direction; in the measurement system installation cavity, a conical groove is designed to facilitate the connection and fixation of the measurement balance.

[0059] The transmission system seal cover 3 and the measurement system seal cover 4 are installed at the tail end of the rear section 7 of the aircraft. The transmission system seal cover 3 closes the installation cavity of the deformable aircraft transmission system to prevent foreign impurities from affecting the system operation. The measurement system seal cover 4 separates the measurement system from the external environment to avoid interference from external heat, impurities and other factors on the wind tunnel measurement system. There are two small holes on the measurement system seal cover 4, through which the balance wire and the motor control wire pass respectively;

[0060] The left wing 1 and the right wing 6 of the aircraft have the same structure, including a wing main body and an angled connecting rod inside the wing main body, that is, a bent connecting rod. There is a shaft hole in the middle of the bent connecting rod, and the wing bearing 9 is installed in the shaft hole. The wing surface rotates up and down around the wing bearing 9 through the transmission of the bent connecting rod;

[0061] The left wing bearing seal cover 2 and the right wing bearing seal cover 5 are installed at the tail end of the rear section 7 of the aircraft. The inner side of the wing bearing cover cooperates with one end of the wing bearing 9, and the other end of the wing bearing 9 cooperates with the rear section 7 of the aircraft.

[0062] The motor 16, the angle conversion block track 12, and the slider 14, the XOZ plane connecting rod 13, the angle conversion block 10, and the XOY plane connecting rod 11 connected in sequence all belong to the transmission system, as Figure 8 shown. Among them, the angle conversion block 10 is used to convert the displacement in the XOZ plane into the displacement in the XOY plane. Grooves are designed on both sides of the angle conversion block. One side of the groove is parallel to the XOZ plane, and the other side of the groove is parallel to the XOY plane. The XOY plane connecting rod 11 is a connecting rod transmission mechanism in the XOY plane, one end is connected to the bent connecting rod on the wing, and the other end is connected to the angle conversion block 10; the XOZ plane connecting rod 13 is a connecting rod transmission mechanism in the XOZ plane, one end is connected to the angle conversion block 10, and the other end is connected to the slider 14; the motor 16 is used to provide power. The output end of the motor is a lead screw, and the slider 14 is connected to the motor lead screw. Through the lead screw transmission, the motor rotary pair is converted into a moving pair. The upper end of the slider 14 is designed with a groove, and the lower end is designed with a protrusion. The slider cooperates with the rear section of the aircraft, and is limited by the groove and the protrusion, ensuring only one degree of freedom in one direction; as Figure 9 shown, the angle conversion block track 12 limits the degree of freedom of the angle conversion block 10, so that the angle conversion block 10 can only move in a given direction. The given direction here is the direction in the XOZ plane and perpendicular to the inner side surface of the wing main body.

[0063] The motor 16 is fixed on the rear section 7 of the aircraft through the motor flange 15. There are screw holes in the middle of the flange plate, which can be connected to the motor 16; there are also screw holes at both ends of the flange plate, which can be connected to the rear section 7 of the aircraft.

[0064] By providing a driving power source for the motor, the present invention can achieve the rotation of the wing surface around the axis, thereby realizing the up-and-down rotation of the wing surface. At the same time, the deformable aircraft structure reserves space for the measurement system, enabling the measurement of the aerodynamic force of the deformable aircraft under wind tunnel conditions.

[0065] The present invention has been described in detail above in combination with specific embodiments and exemplary examples, but these descriptions should not be construed as limiting the present invention. Those skilled in the art understand that, without departing from the spirit and scope of the present invention, various equivalent substitutions, modifications, or improvements can be made to the technical solutions of the present invention and their implementation manners, and these all fall within the scope of the present invention. The protection scope of the present invention shall be subject to the appended claims.

[0066] 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.

Claims

1. A deformable aircraft structure, characterized in that, It includes an aircraft model, the left wing (1) of the aircraft, the right wing (6) of the aircraft, a measurement system and a transmission system; The measurement system and the transmission system are installed in the inner cavity of the aircraft model, and the left wing (1) and the right wing (6) of the aircraft are respectively located on the left and right sides of the aircraft model; Let the geometric center of the aircraft model be the origin O, the head of the aircraft model faces the positive direction of the X-axis, the upper part of the aircraft model is the positive direction of the Y-axis, and the Z-axis is determined according to the right-hand rule; The transmission system includes a motor (16), and a slider (14), an XOZ plane connecting rod (13), an angle conversion block (10) and an XOY plane connecting rod (11) connected in sequence. The XOY plane connecting rod (11) is connected to the left wing (1) or the right wing (6) of the aircraft; the motor (16) drives the slider (14) to move along the X-axis, drives the angle conversion block (10) to move in the XOZ plane through the XOZ plane connecting rod (13), and the movement of the angle conversion block (10) in the XOZ plane is converted into the movement of the left wing (1) or the right wing (6) of the aircraft in the XOY plane through the XOY plane connecting rod (11); The transmission system further includes an angle conversion block track (12). The angle conversion block track (12) is parallel to the XOZ plane and perpendicular to the inner side of the wing main body of the left wing (1) or the right wing (6) of the aircraft. The angle conversion block (10) is installed in the angle conversion block track (12), and the angle conversion block track (12) enables the angle conversion block (10) to move only in the direction perpendicular to the inner side of the wing main body in the XOZ plane; Both the left wing (1) and the right wing (6) of the aircraft include a wing main body and a bent connecting rod. One end of the bent connecting rod is fixed to the inner side of the wing main body, and the other end is hinged to the XOY plane connecting rod (11); the bent connecting rod is rotatably connected to the aircraft model through a wing bearing (9); One end of the angle conversion block (10) has a first groove opened in the XOZ plane, and the other end has a second groove opened in the XOY plane. The angle conversion block (10) is connected to the XOZ plane connecting rod (13) through the first groove and connected to the XOY plane connecting rod (11) through the second groove.

2. The deformable aircraft structure according to claim 1, characterized in that, The wing main bodies of the left wing (1) and the right wing (6) of the aircraft are both right-angled triangles. The inner side of the wing main body corresponds to the hypotenuse of the right-angled triangle, and the inner side of the wing main body is not parallel to the X-axis.

3. The deformable aircraft structure according to claim 1, characterized in that, The bent connecting rod includes a first connecting rod parallel to the wing surface of the left wing (1) or the right wing (6) of the aircraft, and a second connecting rod not parallel to the wing surface of the left wing (1) or the right wing (6) of the aircraft. One end of the first connecting rod is fixed to the inner side of the wing main body, the other end of the first connecting rod is connected to one end of the second connecting rod, and the other end of the second connecting rod is hinged to the XOY plane connecting rod (11); The left wing (1) and the right wing (6) of the aircraft also respectively include a wing bearing (9). The connection between the other end of the first connecting rod and one end of the second connecting rod is rotatably connected to the aircraft model through the wing bearing (9), and the wing bearing (9) is parallel to the inner side of the wing main body.

4. A deformable aircraft structure according to claim 1, characterized in that The transmission system further includes a motor lead screw, and the rotation of the motor (16) is converted into the movement of the slider (14) along the X-axis through the motor lead screw.

5. A deformable aircraft structure according to claim 1, characterized in that The aircraft model includes a front section (8) of the aircraft, a rear section (7) of the aircraft, a transmission system sealing cover (3), and a measurement system sealing cover (4); The front section (8) of the aircraft is connected to the rear section (7) of the aircraft. The rear section (7) of the aircraft is provided with a measurement system installation cavity and a transmission system installation cavity that are vertically distributed and independent of each other. The measurement system and the transmission system are respectively installed in the measurement system installation cavity and the transmission system installation cavity. The measurement system sealing cover (4) and the transmission system sealing cover (3) are installed at the rear end of the rear section (7) of the aircraft, and are respectively used to seal the measurement system installation cavity and the transmission system installation cavity; the left wing (1) and the right wing (6) of the aircraft are respectively located on the left and right sides of the rear section (7) of the aircraft.

6. A deformable aircraft structure according to claim 5, characterized in that, The measurement system installation cavity and the transmission system installation cavity are made independent of each other by a partition; The measurement system includes a measurement balance, and a conical groove for installing the measurement balance is provided in the measurement system installation cavity; The measurement system sealing cover (4) is provided with through holes for passing the balance wire and the motor control wire; A groove along the X direction is provided in the transmission system installation cavity, and a protrusion is provided on the slider (14). The protrusion provided on the slider (14) cooperates with the groove to realize the movement limit of the slider (14) along the X axis.

7. A deformable aircraft structure according to claim 1, characterized in that The aircraft model further includes a wing bearing sealing cover; The wing bearing sealing cover is installed at the rear end of the rear section (7) of the aircraft, and the inner side surface of the wing bearing sealing cover cooperates with the wing bearing (9).

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