Multivariable hypersonic variable configuration aircraft model and design and installation method thereof

Abstract

The invention belongs to the technical field of wind tunnel test and flight control crossing, and discloses a multivariable hypersonic variable configuration aircraft model and a design and installation method thereof. The design method comprises the steps of determining total design requirements; determining components; selecting a hypersonic wind tunnel; designing subsystems of the model; mounting on the ground; and ground simulation. The model comprises a model precursor and a model afterbody which are sequentially connected from front to back; a variable-centroid mechanism is arranged in an inner cavity of the model precursor; a balance and a dynamic supporting mechanism are sequentially arranged on the central axis of the inner cavity of the model rear body from front to back; the front-section wall surface of the inner cavity of the model rear body is provided with a variable wing surface mechanism, and the rear-section wall surface is provided with a steering engine system. The mounting method comprises the following steps: firstly, sequentially mounting the variable centroid mechanism, the variable airfoil surface mechanism and the steering engine system, secondly, mounting the dynamic support device and the balance on a web support plate of the hypersonic wind tunnel attack angle mechanism, and finally, combining the model precursor and the model afterbody, and carrying out centroid adjustment and line connection. The method 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 test and flight control, and specifically relates to a multivariable hypersonic variable configuration aircraft model and a design and installation method thereof. Background Art

[0002] At present, the evaluation of aerodynamic characteristics of hypersonic vehicles is mainly based on conventional hypersonic wind tunnel steady tests. By measuring the aerodynamic force and aerodynamic moment of the static model under different Mach numbers, angles of attack, sideslip angles and rudder deflection angles, the aerodynamic database and dynamic model of hypersonic vehicles are established. The design and evaluation of the flight control law of hypersonic vehicles are mainly based on simulation analysis of dynamic models. However, the dynamic model does not take into account the dynamic response and unsteady flow phenomena of the hypersonic vehicle movement and rudder surface deflection. This simplification may be feasible for conventional hypersonic vehicles, but for hypersonic variable configuration vehicles with complex control of multivariable near-space, due to the highly nonlinear coupling characteristics between aerodynamics and motion, the conventional static wind tunnel test technology based on conventional hypersonic wind tunnel steady tests to establish an aerodynamic model and conduct flight performance and control law evaluation will produce large errors.

[0003] The model wind tunnel virtual flight test is to support the test model in the uniform flow field of the wind tunnel in some way so that the model can obtain one or more degrees of freedom. When the wind tunnel is started, it can move freely in the directions of these degrees of freedom according to the aerodynamic forces and moments it is subjected to, as well as the control forces and moments caused by the deflection of the rudder surfaces. At the same time, the aerodynamic and motion parameters of the aircraft are measured, and the response and manipulation control characteristics of the aircraft are tested, so as to achieve the purpose of integrating aerodynamics and motion to evaluate the flight and control performance of the aircraft.

[0004] Hypersonic variable configuration aircraft need to fly in a wide speed range. Different speed environments have different requirements for aerodynamic layout. A single, fixed shape is difficult to meet the aerodynamic performance requirements of multiple design points in a wide speed range. Therefore, the design of a hypersonic variable configuration aircraft needs to include changes in the center of mass and wing surface.

[0005] For hypersonic variable configuration aircraft with multi-variable complex control in near-space, it is urgent to carry out flight performance and control performance verification based on model wind tunnel virtual flight tests, 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 multivariable hypersonic variable configuration aircraft model. Another technical problem to be solved by the present invention is to provide a multivariable hypersonic variable configuration aircraft model. Still another technical problem to be solved by the present invention is to provide an installation method for a multivariable hypersonic variable configuration aircraft model to overcome the defects of the prior art.

[0007] The design method of the multivariable hypersonic variable configuration aircraft model of the present invention 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, a variable wing mechanism, a steering gear system and a balance are installed in the inner cavity of the hypersonic variable configuration aircraft model, and the belly support plate is connected to support it through a dynamic support mechanism located in the inner cavity of the hypersonic variable configuration aircraft model, and a virtual flight control system installed in a control computer in the hypersonic wind tunnel control room is used for wired control; S30. Select a hypersonic wind tunnel; Conduct overall structural design, and on the basis of the overall structural design, conduct minimization design for the variable center of mass mechanism, variable wing mechanism, dynamic support mechanism, steering gear system, balance and belly support plate, determine the space occupied by each component, estimate the maximum projected area of ​​the hypersonic variable configuration aircraft model, and select the hypersonic wind tunnel for the 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 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. S403. Measuring device; Balances are used to measure aerodynamic forces and moments; S404. Sports device; The motion device includes a variable center of mass mechanism, a variable wing mechanism and a steering gear system; 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; S405. Control device; 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; 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; 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.

[0008] 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; A mass center variable mechanism is arranged in the front inner cavity of the model, and the mass center variable mechanism 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 feedback the mass center position; On the central axis of the rear body cavity of the model, a balance and a dynamic support mechanism are arranged from front to back in sequence; the balance is a rod-type six-component measuring balance, which measures six-component aerodynamic forces and moments; the front section of the dynamic support mechanism is connected to the cone section of the balance through a two-degree-of-freedom mechanical bearing, and the lower section of the rear section of the dynamic support mechanism is connected to the belly support plate; the two-degree-of-freedom mechanical bearing of the dynamic support mechanism 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 two degrees of freedom at the same time; A variable wing mechanism is set at the front section of the rear body cavity of the model and on the wall close to the wing surface. The variable wing mechanism drives the transmission device to move through the control motor to adjust the position of the wing surface to ensure that the wing surface moves within the sweep angle range of 0°~20°, and the wing surface sweep angle is recorded and fed back through the angle encoder. A steering gear system is set at the rear section of the rear body cavity of the model, near the wall of the rudder surface. The steering gear system drives the transmission device to move through the control motor, adjusts the rudder surface deflection angle, ensures that the rudder surface moves within the range of -30°~30°, and records and feeds back the rudder deflection angle through the angle encoder; The drive and feedback data lines of the variable mass center mechanism, the variable wing surface mechanism and the steering gear system are connected with the virtual flight control system interface board of the control computer.

[0009] The installation method of the multivariable hypersonic variable configuration aircraft model of the present invention comprises the following steps: A variable center of mass mechanism is installed on the central axis of the front body cavity of the model; a variable wing surface mechanism is installed on the front section of the rear body cavity of the model, on the wall surface close to the wing surface; a steering gear system is installed on the rear section of the rear body cavity of the model, on the wall surface close to the rudder surface; A dynamic support mechanism is installed on the belly support plate of the angle of attack mechanism of the hypersonic wind tunnel, and the front section of the dynamic support mechanism is connected to the cone section of the balance through a two-degree-of-freedom mechanical bearing; Install the balance on the mounting surface of the rear body of the model by tightening the front nut; Mounting the model front body on the model rear body; 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; Connect the drive and feedback data lines of the variable center of mass mechanism, variable wing surface mechanism, and steering gear system to the virtual flight control system interface board of the control computer; 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.

[0010] The multivariable hypersonic variable configuration aircraft model of the present invention and its design and installation method realize the aerodynamic, motion and control coupled simulation of the hypersonic variable configuration aircraft, avoid the problems of the unreality of pure digital simulation models and the high cost, high risk and long cycle of real flight tests, and can be used to carry out flight performance and control performance evaluation of new hypersonic variable configuration aircraft with multivariable complex control, and has practical engineering value. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 A flow chart of a design method for a multivariable hypersonic variable configuration aircraft model of the present invention; Figure 2 It is a structural schematic diagram of a multivariable hypersonic variable configuration aircraft model of an embodiment.

[0012] In the figure, 1. model front body; 2. model rear body; 3. variable center of mass mechanism; 4. variable wing surface mechanism; 5. dynamic support mechanism; 6. servo system; 7. balance; 8. belly support plate; 9. angle encoder; 10. control computer. DETAILED DESCRIPTION

[0013] The present invention is described in detail below with reference to the accompanying drawings and embodiments.

[0014] Embodiment: The test wind tunnel of 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 temperature of the incoming flow is 600K, and the total pressure of the incoming flow is 1.2 MPa.

[0015] like Figure 1 As shown, the design method of the multivariable hypersonic variable configuration aircraft model of this embodiment includes 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 a belly support plate 8 is connected to support it through a dynamic support mechanism 5 located in the inner cavity of the hypersonic variable configuration aircraft model, 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; Perform overall structural design, and on the basis of the overall structural design, perform minimization design on the variable center of mass mechanism 3, variable wing mechanism 4, dynamic support mechanism 5, steering gear system 6, balance 7 and belly support plate 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 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 supporting device includes a dynamic supporting mechanism 5, a belly support plate 8 and an angle encoder 9. The dynamic supporting 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. The angle encoder 9 is used to measure the posture of the test model. S403. Measuring device; Balance 7 is used to measure aerodynamic forces and moments; S404. Sports device; The motion device includes a variable center of mass mechanism 3, a variable wing mechanism 4 and a steering gear system 6; The variable center of mass mechanism 3 is used to adjust and feedback the center of mass position; the variable wing mechanism 4 is used to adjust and feedback the wing sweep angle; the steering gear system 6 is used to adjust and feedback the rudder deflection angle; S405. Control device; The control device includes 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; 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.

[0016] like Figure 2 As shown, the multivariable hypersonic variable configuration aircraft model of this embodiment includes a model front body 1 and a model rear body 2 connected sequentially from front to rear; A mass center changing mechanism 3 is provided in the inner cavity of the model precursor 1. 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 feed back the mass center position; On the central axis of the inner cavity of the rear body 2 of the model, 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, which measures six-component aerodynamic forces and moments; the front section of the dynamic support mechanism 5 is connected to the cone section of the balance 7 through a two-degree-of-freedom mechanical bearing, and the lower part 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 two degrees of freedom at the same time; A variable wing 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 mechanism 4 drives the transmission device to move by operating the motor to adjust the position of the wing surface to ensure that the wing surface moves within the sweep angle range of 0° to 20°, and the sweep angle of the wing surface is recorded and fed back by the 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, near the wall of the rudder surface. The steering gear system 6 drives the transmission device to move by operating the motor, adjusts the rudder surface deflection angle, ensures that the rudder surface moves within the rudder deflection angle range of -30° to 30°, and records and feeds back 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 .

[0017] The installation method of the multivariable hypersonic variable configuration aircraft model of this embodiment includes the following steps: A variable center of mass mechanism 3 is installed on the central axis of the inner cavity of the model front body 1; a variable wing mechanism 4 is installed on the front section of the inner cavity of the model rear body 2, on the wall surface close to the wing surface; a steering gear system 6 is installed on the rear section of the inner cavity of the model rear body 2, on the wall surface close to the rudder surface; A dynamic support mechanism 5 is installed on the belly support plate 8 of the hypersonic wind tunnel angle of attack mechanism, and the front section of the dynamic support mechanism 5 is connected to the cone section of the balance 7 through a two-degree-of-freedom mechanical bearing; The balance 7 is mounted 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; Connect the drive and feedback data lines of the variable center of mass mechanism 3, the variable wing 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.

[0018] The above embodiments only express typical implementations of the present invention, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the scope of the present invention. It should be pointed out that, for those of ordinary skill in the art, several modifications and improvements can be made without departing from the concept of the present invention, and these all belong to the protection scope of the present invention. Therefore, the protection scope of the present invention's patent shall be subject to the attached 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; 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.

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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