Multivariable Hypersonic Variable Configuration Aircraft Model and Its Design and Installation Methods

Abstract

The present invention belongs to the cross - technical field of wind tunnel tests and flight control, and discloses a multi - variable hypersonic variable - configuration aircraft model and its design and installation methods. The design method includes determining the overall design requirements; determining the components; selecting a hypersonic wind tunnel; designing each subsystem of the model; ground installation; and ground simulation. The model includes a model forebody and a model aft - body connected in sequence from front to back; a variable - center - of - mass mechanism is arranged in the inner cavity of the model forebody; on the central axis of the inner cavity of the model aft - body, a balance and a dynamic support mechanism are arranged in sequence from front to back; a variable - wing mechanism is arranged on the wall surface of the front section of the inner cavity of the model aft - body, and a servo system is arranged on the wall surface of the rear section. The installation method first installs the variable - center - of - mass mechanism, the variable - wing mechanism, and the servo system in sequence, then installs the dynamic support device and the balance on the ventral strut of the angle - of - attack mechanism of the hypersonic wind tunnel, and finally combines the model forebody and the model aft - body and conducts center - of - mass adjustment and wire connection. The present invention can be used for performance evaluation and has engineering practical value.

Description

Technical Field

[0001] The present invention belongs to the cross technical field of wind tunnel tests and flight control, and particularly relates to a multi-variable hypersonic variable configuration aircraft model and its design and installation methods. Background Art

[0002] At present, the aerodynamic characteristics evaluation of hypersonic aircraft mainly relies on conventional hypersonic wind tunnel steady tests. By measuring the aerodynamic forces and aerodynamic moments of static models under different Mach numbers, angles of attack, sideslip angles, and rudder deflection angles, an aerodynamic database and a dynamic model of hypersonic aircraft are established. The design and evaluation of the flight control law of hypersonic aircraft mainly carry out simulation analysis based on the dynamic model. However, the dynamic model does not consider the influence of the dynamic response and unsteady flow phenomena during the movement of hypersonic aircraft and the deflection of control surfaces. This simplification may be feasible for conventional hypersonic aircraft, but for hypersonic variable configuration aircraft with complex multi-variable control in the near space, due to the high non-linear coupling characteristics between aerodynamics and motion, there will be large errors in establishing an aerodynamic model based on the conventional static wind tunnel test technology of conventional hypersonic wind tunnel steady tests and conducting flight performance and control law evaluations.

[0003] The virtual flight test of a model in a wind tunnel is to support the test model in the uniform flow field of the wind tunnel in a certain way, enabling the model to obtain one or more degrees of freedom. When the wind tunnel is started, the model can freely move in these degrees of freedom directions according to the aerodynamic forces and moments it receives, as well as the control forces and moments brought about by the deflection of control surfaces. At the same time, the aerodynamic and motion parameters of the aircraft are measured to test the response and control characteristics of the aircraft, so as to achieve the purpose of integrated evaluation of the flight and control performance of the aircraft in terms of aerodynamics and motion.

[0004] Hypersonic variable configuration aircraft need to fly in a relatively large speed range, and the requirements for the aerodynamic layout vary greatly in different speed domain environments. A single and fixed shape is difficult to meet the aerodynamic performance requirements of multiple design points in a wide speed range. Therefore, when designing a hypersonic variable configuration aircraft, it is necessary to include changes in the center of mass and wing surfaces, etc.

[0005] For hypersonic variable configuration aircraft with complex multi-variable control in the near space, it is an urgent technical problem to carry out the verification of flight performance and control performance based on the virtual flight test of a model in a wind tunnel, and to establish a multi-variable hypersonic variable configuration aircraft model and its design and installation methods. Summary of the Invention

[0006] One technical problem to be solved by the present invention is to provide a design method for a multi-variable hypersonic variable configuration aircraft model. Another technical problem to be solved by the present invention is to provide a multi-variable hypersonic variable configuration aircraft model. Still another technical problem to be solved by the present invention is to provide an installation method for a multi-variable hypersonic variable configuration aircraft model, so as to overcome the defects of the prior art.

[0007] The design method for a multi-variable hypersonic variable configuration aircraft model of the present invention includes the following steps:

[0008] S10. Determine the overall design requirements;

[0009] It is required that the hypersonic variable configuration aircraft model simulates the geometric shape, mass, moment of inertia, center of mass change, wing surface change and rudder deflection angle change of a real aircraft, and measures the aerodynamic force and moment of 6 components at the same time.

[0010] S20. Determine the components;

[0011] Install a variable center of mass mechanism, a variable wing surface mechanism, a servo system and a balance in the inner cavity of the hypersonic variable configuration aircraft model, and support it by connecting the ventral strut through a dynamic support mechanism located in the inner cavity of the hypersonic variable configuration aircraft model, and conduct wired control through a virtual flight control system installed in the control computer of the hypersonic wind tunnel control room.

[0012] S30. Select a hypersonic wind tunnel;

[0013] Conduct overall structural design. On the basis of the overall structural design, minimize the design of the variable center of mass mechanism, the variable wing surface mechanism, the dynamic support mechanism, the servo system, the balance and the ventral strut, determine the space occupied by each component, estimate the maximum projected area of the hypersonic variable configuration aircraft model, and select a hypersonic wind tunnel for virtual flight tests of the hypersonic variable configuration aircraft model according to the blockage degree requirements of the hypersonic wind tunnel.

[0014] S40. Design each subsystem of the model;

[0015] According to the requirements of S10~S30, design the hypersonic variable configuration aircraft model in detail; according to the functions, assemble the components into each subsystem of the hypersonic variable configuration aircraft model; the specific design requirements of each subsystem of the hypersonic variable configuration aircraft model are as follows:

[0016] S401. Overall requirements;

[0017] The hypersonic variable configuration aircraft model is similar in geometry to the hypersonic variable configuration aircraft. According to the blockage requirements of the hypersonic wind tunnel, the model geometry scale is specifically determined. According to the model geometry scale, the hypersonic variable configuration aircraft model is set up in detail, and the mass and moment of inertia characteristics of the real aircraft are required to be simulated.

[0018] S402. Support device;

[0019] The support device includes a dynamic support mechanism, a belly support plate and an angle encoder. The dynamic support mechanism has a two-degree-of-freedom motion mechanism for performing a single-degree-of-freedom test or a two-degree-of-freedom coupled test. The angle encoder is used to measure the posture of the test model.

[0020] S403. Measuring device;

[0021] Balances are used to measure aerodynamic forces and moments;

[0022] S404. Sports device;

[0023] The motion device includes a variable center of mass mechanism, a variable wing mechanism and a steering gear system;

[0024] The variable center of mass mechanism is used to adjust and feedback the center of mass position; the variable wing mechanism is used to adjust and feedback the wing sweep angle; the steering gear system is used to adjust and feedback the rudder deflection angle;

[0025] S405. Control device;

[0026] The control device includes a control computer and a virtual flight control system installed in the control computer, and a virtual flight test control sequence of a hypersonic variable configuration aircraft model pre-set in the virtual flight control system;

[0027] S50. Ground installation;

[0028] Process, install and repair the hypersonic variable configuration aircraft model, conduct ground installation inspection and repeated iterations until it is determined that all subsystems of the supersonic variable configuration aircraft model operate normally and can meet the requirements of the virtual flight test of the hypersonic variable configuration aircraft model;

[0029] S60. Ground simulation;

[0030] According to the requirements of the virtual flight test of the hypersonic variable configuration aircraft model, the test plan is planned, the control law program is compiled, the control timing is set, and simulation is carried out according to the control timing and iterated repeatedly until it is determined that the supersonic variable configuration aircraft model can achieve the control timing and the design of the hypersonic variable configuration aircraft model is completed.

[0031] The multivariable hypersonic variable configuration aircraft model of the present invention comprises a model front body and a model rear body connected sequentially from front to rear;

[0032] Inside the inner cavity of the model forebody, a center-of-mass changing mechanism is provided. The center-of-mass changing mechanism drives a mass slider to move through a control motor to adjust the position of the center of mass. A laser rangefinder is used to measure the moving distance of the mass slider and feedback the position of the center of mass.

[0033] On the central axis of the inner cavity of the model afterbody, a balance and a dynamic support mechanism are arranged in sequence from front to back. The balance is a rod-type six-component measuring balance for measuring six-component aerodynamic forces and moments. The front section of the dynamic support mechanism is connected to the conical section of the balance through a two-degree-of-freedom mechanical bearing, and the lower part of the rear section of the dynamic support mechanism is connected to the ventral strut. The two-degree-of-freedom mechanical bearing of the dynamic support mechanism conducts single-degree-of-freedom tests by locking one degree of freedom and releasing the other, and conducts coupling tests by releasing both degrees of freedom simultaneously.

[0034] In the front section of the inner cavity of the model afterbody, on the wall surface close to the wing surface, a variable wing surface mechanism is provided. The variable wing surface mechanism drives a transmission device to move through a control motor to adjust the position of the wing surface, ensuring that the wing surface moves within the range of 0° to 20° sweep angle. An angular encoder records and feedbacks the sweep angle of the wing surface.

[0035] In the rear section of the inner cavity of the model afterbody, on the wall surface close to the rudder surface, a servo system is provided. The servo system drives a transmission device to move through a control motor to adjust the deflection angle of the rudder surface, ensuring that the rudder surface moves within the range of -30° to 30° rudder deflection angle. An angular encoder records and feedbacks the rudder deflection angle.

[0036] The drive and feedback data lines of the center-of-mass changing mechanism, the variable wing surface mechanism, and the servo system are connected to the virtual flight control system interface board of the control computer.

[0037] The installation method of the multi-variable hypersonic variable configuration aircraft model of the present invention includes the following processes:

[0038] Install the center-of-mass changing mechanism on the central axis of the inner cavity of the model forebody; install the variable wing surface mechanism on the wall surface close to the wing surface in the front section of the inner cavity of the model afterbody; install the servo system on the wall surface close to the rudder surface in the rear section of the inner cavity of the model afterbody.

[0039] Install the dynamic support mechanism on the ventral strut of the angle-of-attack mechanism of the hypersonic wind tunnel. The front section of the dynamic support mechanism is connected to the conical section of the balance through a two-degree-of-freedom mechanical bearing.

[0040] Install the balance on the installation surface of the model afterbody by tightening it with a front-end nut.

[0041] Install the model forebody on the model afterbody.

[0042] Fine-tune the position of the center of mass of the test model by adding mass blocks so that the center of mass of the hypersonic variable configuration aircraft model coincides with the center of rotation of the dynamic support mechanism.

[0043] Connect the drive and feedback data lines of the variable center-of-mass mechanism, variable wing surface mechanism, and servo system to the virtual flight control system interface board of the control computer;

[0044] Plan the test plan according to the test requirements, set the control timing, and conduct simulation on the main control computer; download the designed control timing and control law into the real-time simulator, and complete the wind tunnel test and data acquisition according to the set timing.

[0045] The multi-variable hypersonic variable configuration aircraft model of the present invention and its design and installation method realize the coupling simulation of the aerodynamics, motion, and control of the hypersonic variable configuration aircraft, avoiding the problems of unrealistic pure digital simulation models and high costs, high risks, and long cycles of real flight tests. It can be used to evaluate the flight performance and control performance of a new type of hypersonic variable configuration aircraft with multi-variable complex control, and has engineering practical value. Description of the Drawings

[0046] Figure 1 It is a flowchart of the design method of the multi-variable hypersonic variable configuration aircraft model of the present invention;

[0047] Figure 2 It is a structural schematic diagram of the multi-variable hypersonic variable configuration aircraft model of the embodiment.

[0048] In the figure, 1. Model forebody; 2. Model afterbody; 3. Variable center-of-mass mechanism; 4. Variable wing surface mechanism; 5. Dynamic support mechanism; 6. Servo system; 7. Balance; 8. Belly strut; 9. Angle encoder; 10. Control computer. Detailed Description of the Invention

[0049] The present invention will be described in detail below with reference to the drawings and embodiments.

[0050] Embodiment: The test wind tunnel in this embodiment is a large-caliber conventional hypersonic wind tunnel. The hypersonic variable configuration aircraft model is 2000 mm long and 411 mm high, the test Mach number is Mach 7, the total incoming flow temperature is 600 K, and the total incoming flow pressure is 1.2 MPa.

[0051] As Figure 1 shown, the design method of the multi-variable hypersonic variable configuration aircraft model in this embodiment includes the following steps:

[0052] S10. Determine the overall design requirements;

[0053] It is required that the hypersonic variable configuration aircraft model simulates the geometric shape, mass, moment of inertia, center-of-mass change, wing surface change, and rudder deflection angle change of a real aircraft, and measures the aerodynamic force and moment of 6 components at the same time;

[0054] S20. Determine the components;

[0055] Install a variable center of mass mechanism 3, a variable wing surface mechanism 4, a servo system 6 and a balance 7 inside the cavity of the hypersonic variable configuration aircraft model. Support it by connecting the ventral strut 8 through the dynamic support mechanism 5 located inside the cavity of the hypersonic variable configuration aircraft model, and conduct wired control through the virtual flight control system installed in the control computer 10 located in the hypersonic wind tunnel control room;

[0056] S30. Select a hypersonic wind tunnel;

[0057] Conduct overall structural design. On the basis of the overall structural design, minimize the design of the variable center of mass mechanism 3, the variable wing surface mechanism 4, the dynamic support mechanism 5, the servo system 6, the balance 7 and the ventral strut 8, determine the space occupied by each component, estimate the maximum projected area of the hypersonic variable configuration aircraft model, and select a hypersonic wind tunnel for the virtual flight test of the hypersonic variable configuration aircraft model according to the blockage ratio requirements of the hypersonic wind tunnel;

[0058] S40. Design each subsystem of the model;

[0059] According to the requirements of S10~S30, detail the design of the hypersonic variable configuration aircraft model; according to the functions, assemble the components into each subsystem of the hypersonic variable configuration aircraft model; the specific design requirements of each subsystem of the hypersonic variable configuration aircraft model are as follows:

[0060] S401. General requirements;

[0061] The hypersonic variable configuration aircraft model is geometrically similar to the hypersonic variable configuration aircraft. According to the blockage ratio requirements of the hypersonic wind tunnel, specifically determine the model geometric scale ratio, and carry out detailed settings of the hypersonic variable configuration aircraft model according to the model geometric scale ratio, requiring to simulate the mass and moment of inertia characteristics of the real aircraft;

[0062] S402. Support device;

[0063] The support device includes a dynamic support mechanism 5, a ventral strut 8 and an angle encoder 9. The dynamic support mechanism 5 has a two-degree-of-freedom motion mechanism to conduct single-degree-of-freedom tests or two-degree-of-freedom coupling tests, and the angle encoder 9 is used to measure the attitude of the test model;

[0064] S403. Measuring device;

[0065] The balance 7 is used to measure aerodynamic forces and moments;

[0066] S404. Motion device;

[0067] The motion device includes a variable center of mass mechanism 3, a variable wing surface mechanism 4 and a servo system 6;

[0068] The variable center-of-mass mechanism 3 is used to adjust and feedback the center-of-mass position; the variable wing surface mechanism 4 is used to adjust and feedback the wing surface sweep angle; the servo system 6 is used to adjust and feedback the rudder deflection angle;

[0069] S405. Control device;

[0070] The control device includes a control computer 10 and a virtual flight control system installed in the control computer 10, as well as the virtual flight test control timing sequence preset in the virtual flight control system for the hypersonic variable configuration aircraft model;

[0071] S50. Ground installation;

[0072] Machine, install and repair the hypersonic variable configuration aircraft model, conduct ground installation inspection and repeated iteration until it is determined that each subsystem of the supersonic variable configuration aircraft model operates normally and can meet the requirements of the virtual flight test of the hypersonic variable configuration aircraft model;

[0073] S60. Ground simulation;

[0074] Plan the test plan for the virtual flight test requirements of the hypersonic variable configuration aircraft model, compile the control law program, set the control timing sequence, carry out simulation according to the control timing sequence and repeat iteration until it is determined that the supersonic variable configuration aircraft model can achieve the control timing sequence and complete the design of the hypersonic variable configuration aircraft model.

[0075] As Figure 2 shown, the multivariable hypersonic variable configuration aircraft model of this embodiment includes a model forebody 1 and a model aft body 2 connected in sequence from front to back;

[0076] In the inner cavity of the model forebody 1, a variable center-of-mass mechanism 3 is arranged. The variable center-of-mass mechanism 3 drives the mass slider to move through a control motor to adjust the center-of-mass position; a laser rangefinder is used to measure the movement distance of the mass slider and feedback the center-of-mass position;

[0077] On the central axis of the inner cavity of the model aft body 2, a balance 7 and a dynamic support mechanism 5 are arranged in sequence from front to back; the balance 7 is a rod-type six-component measuring balance for measuring six-component aerodynamic forces and moments; the front section of the dynamic support mechanism 5 is connected to the tapered section of the balance 7 through a two-degree-of-freedom mechanical bearing, and the rear section of the dynamic support mechanism 5 is connected to the ventral support plate 8 below; the two-degree-of-freedom mechanical bearing of the dynamic support mechanism 5 conducts single-degree-of-freedom tests by locking one degree of freedom and releasing the other degree of freedom, and conducts coupling tests by releasing both degrees of freedom simultaneously;

[0078] In the front section of the inner cavity of the model aft body 2, on the wall surface close to the wing surface, a variable wing surface mechanism 4 is arranged. The variable wing surface mechanism 4 drives the transmission device to move through a control motor to adjust the wing surface position, ensuring that the wing surface moves within the range of 0° to 20° sweep angle, and records and feedbacks the wing surface sweep angle through an angular encoder;

[0079] A servo system 6 is provided on the wall surface near the rudder surface in the rear section of the inner cavity of the model rear body 2. The servo system 6 drives the transmission device to move through the control motor, adjusts the rudder angle, ensures that the rudder surface moves within the range of -30° to 30° rudder deflection angle, and records and feedbacks the rudder deflection angle through an angle encoder.

[0080] The drive and feedback data lines of the variable center-of-mass mechanism 3, the variable wing surface mechanism 4, and the servo system 6 are connected to the virtual flight control system interface board of the control computer 10.

[0081] The installation method of the multi-variable hypersonic variable configuration aircraft model in this embodiment includes the following processes:

[0082] Install the variable center-of-mass mechanism 3 on the central axis of the inner cavity of the model front body 1; install the variable wing surface mechanism 4 on the wall surface near the wing surface in the front section of the inner cavity of the model rear body 2; install the servo system 6 on the wall surface near the rudder surface in the rear section of the inner cavity of the model rear body 2;

[0083] Install the dynamic support mechanism 5 on the ventral strut 8 of the hypersonic wind tunnel angle-of-attack mechanism. The front section of the dynamic support mechanism 5 is connected to the conical section of the balance 7 through a two-degree-of-freedom mechanical bearing;

[0084] Install the balance 7 on the mounting surface of the model rear body 2 by tightening with a front-end nut;

[0085] Install the model front body 1 on the model rear body 2;

[0086] Fine-tune the center-of-mass position of the test model by adding mass blocks so that the center of mass of the hypersonic variable configuration aircraft model coincides with the rotation center of the dynamic support mechanism 5;

[0087] Connect the drive and feedback data lines of the variable center-of-mass mechanism 3, the variable wing surface mechanism 4, and the servo system 6 to the virtual flight control system interface board of the control computer 10;

[0088] Plan the test plan according to the test requirements, set the control timing, and carry out simulation on the main control computer; download the designed control timing and control law to the real-time simulator, and complete the wind tunnel test and data acquisition according to the set timing.

[0089] The above embodiments only represent the typical implementation modes of the present invention, and the description is relatively specific and detailed, but it should not be understood as a limitation of the scope of the present invention patent. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present invention, several deformations and improvements can still be made, and these all belong to the protection scope of the present invention. Therefore, the protection scope of the present invention patent should be subject to the appended claims.

Claims

1. A design method for a multivariable hypersonic variable configuration aircraft model, characterized in that: The design method comprises the following steps: S10. Determine the overall design requirements; The hypersonic variable configuration aircraft model is required to simulate the actual aircraft geometry, mass, moment of inertia, center of mass change, wing surface change and rudder angle change, and measure the aerodynamic force and moment of the six components at the same time; S20. Determine the components; A variable center of mass mechanism (3), a variable wing mechanism (4), a steering gear system (6) and a balance (7) are installed in the inner cavity of the hypersonic variable configuration aircraft model, and the dynamic support mechanism (5) located in the inner cavity of the hypersonic variable configuration aircraft model is connected to the belly support plate (8) for support, and a virtual flight control system installed in a control computer (10) located in the control room of the hypersonic wind tunnel is used for wired control; S30. Select a hypersonic wind tunnel; Performing an overall structural design, and based on the overall structural design, performing a minimization design on the variable center of mass mechanism (3), the variable wing mechanism (4), the dynamic support mechanism (5), the steering gear system (6), the balance (7) and the belly support plate (8), determining the space occupied by each component, estimating the maximum projected area of ​​the hypersonic variable configuration aircraft model, and selecting a hypersonic wind tunnel for conducting a virtual flight test of the hypersonic variable configuration aircraft model according to the blockage requirements of the hypersonic wind tunnel; S40. Design each subsystem of the model; According to the requirements of S10~S30, the hypersonic variable configuration aircraft model is designed in detail; according to the function, the components are assembled into the subsystems of the hypersonic variable configuration aircraft model; the specific design requirements of each subsystem of the hypersonic variable configuration aircraft model are as follows: S401. General requirements; The hypersonic variable configuration aircraft model is similar in geometry to the hypersonic variable configuration aircraft. According to the blockage requirements of the hypersonic wind tunnel, the model geometry scale is specifically determined. According to the model geometry scale, the hypersonic variable configuration aircraft model is set up in detail, and the mass and moment of inertia characteristics of the real aircraft are required to be simulated. S402. Support device; The support device comprises a dynamic support mechanism (5), a belly support plate (8) and an angle encoder (9); the dynamic support mechanism (5) has a two-degree-of-freedom motion mechanism for performing a single-degree-of-freedom test or a two-degree-of-freedom coupled test; and the angle encoder (9) is used to measure the posture of the test model; S403. Measuring device; A balance (7) is used to measure aerodynamic forces and moments; S404. Sports device; The motion device comprises a variable center of mass mechanism (3), a variable wing surface mechanism (4) and a steering gear system (6); The variable center of mass mechanism (3) is used to adjust and provide feedback on the center of mass position; the variable wing mechanism (4) is used to adjust and provide feedback on the wing sweep angle; the steering gear system (6) is used to adjust and provide feedback on the rudder deflection angle; S405. Control device; The control device comprises a control computer (10) and a virtual flight control system installed in the control computer (10), and a virtual flight test control sequence of a hypersonic variable configuration aircraft model pre-set in the virtual flight control system; S50. Ground installation; Process, install and repair the hypersonic variable configuration aircraft model, conduct ground installation inspection and repeated iterations until it is determined that all subsystems of the supersonic variable configuration aircraft model operate normally and can meet the requirements of the virtual flight test of the hypersonic variable configuration aircraft model; S60. Ground simulation; Plan the test plan according to the requirements of the virtual flight test of the hypersonic variable configuration aircraft model, compile the control law program, set the control sequence, carry out simulation according to the control sequence and iterate repeatedly until it is determined that the supersonic variable configuration aircraft model can achieve the control sequence and complete the design of the hypersonic variable configuration aircraft model; The design method realizes the coupled simulation of aerodynamics, motion and control of hypersonic variable configuration aircraft, and is used to evaluate the flight performance and control performance of multivariable hypersonic variable configuration aircraft.

2. A multivariable hypersonic variable configuration aircraft model, which is obtained by the design method of the multivariable hypersonic variable configuration aircraft model according to claim 1, characterized in that: The hypersonic variable configuration aircraft model comprises a model front body (1) and a model rear body (2) which are sequentially connected from front to rear; A mass center changing mechanism (3) is arranged in the inner cavity of the model front body (1), and the mass center changing mechanism (3) drives the mass slider to move by operating the motor to adjust the mass center position; a laser rangefinder is used to measure the movement distance of the mass slider and to provide feedback on the mass center position; A balance (7) and a dynamic support mechanism (5) are arranged in sequence from front to back on the central axis of the inner cavity of the rear body (2) of the model; the balance (7) is a rod-type six-component measuring balance for measuring six-component aerodynamic forces and moments; the front section of the dynamic support mechanism (5) is connected to the conical section of the balance (7) via a two-degree-of-freedom mechanical bearing, and the lower section of the rear section of the dynamic support mechanism (5) is connected to the belly support plate (8); the two-degree-of-freedom mechanical bearing of the dynamic support mechanism (5) performs a single-degree-of-freedom test by locking one degree of freedom and releasing the other degree of freedom, and performs a coupling test by releasing the two degrees of freedom at the same time; A variable wing surface mechanism (4) is arranged at the front section of the inner cavity of the rear body (2) of the model and on the wall surface close to the wing surface. The variable wing surface mechanism (4) drives the transmission device to move by operating the motor to adjust the position of the wing surface, ensure that the wing surface moves within the sweep angle range of 0° to 20°, and record and feedback the sweep angle of the wing surface through an angle encoder; A steering gear system (6) is arranged at the rear section of the inner cavity of the rear body (2) of the model and on the wall surface close to the rudder surface. The steering gear system (6) drives the transmission device to move by operating the motor to adjust the rudder surface deflection angle, ensure that the rudder surface moves within the rudder deflection angle range of -30° to 30°, and record and feedback the rudder deflection angle through an angle encoder; The drive and feedback data lines of the variable center of mass mechanism (3), the variable wing surface mechanism (4), and the steering gear system (6) are connected to the virtual flight control system interface board of the control computer (10).

3. A method for installing a multivariable hypersonic variable configuration aircraft model, which is used to install the multivariable hypersonic variable configuration aircraft model according to claim 2, characterized in that: The installation method includes the following steps: A variable center of mass mechanism (3) is installed on the central axis of the inner cavity of the front body (1) of the model; a variable wing mechanism (4) is installed on the front section of the inner cavity of the rear body (2) of the model, on the wall surface close to the wing surface; and a steering gear system (6) is installed on the rear section of the inner cavity of the rear body (2), on the wall surface close to the rudder surface. A dynamic support mechanism (5) is installed on a belly support plate (8) of a hypersonic wind tunnel angle of attack mechanism, wherein a front section of the dynamic support mechanism (5) is connected to a cone section of a balance (7) via a two-degree-of-freedom mechanical bearing; Install the balance (7) on the mounting surface of the rear body (2) of the model by tightening the front nut; Mounting the model front body (1) on the model rear body (2); The center of mass position of the test model is fine-tuned by adding a mass block so that the center of mass of the hypersonic variable configuration aircraft model coincides with the center of rotation of the dynamic support mechanism (5); Connecting the drive and feedback data lines of the variable center of mass mechanism (3), the variable wing surface mechanism (4), and the steering gear system (6) to the virtual flight control system interface board of the control computer (10); Plan the test plan according to the test requirements, set the control sequence, and carry out simulation on the main control computer; download the designed control sequence and control law to the real-time simulator, and complete the wind tunnel test and data collection according to the set sequence.

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