Multivariable complex control test method for hypersonic wind tunnel variable configuration aircraft model

Abstract

The invention belongs to the technical field of wind tunnel test and flight control crossing, and discloses a multivariable complex control test method for a hypersonic wind tunnel variable configuration aircraft model. The test method comprises the following steps: starting the hypersonic wind tunnel; presetting a rudder deflection angle; the dynamic supporting mechanism is unlocked; changing an attack angle instruction, and controlling the model attitude to be stable for the first time; changing an airfoil sweepback instruction, and controlling the attitude of the model to be stable for the second time; changing a mass center position and an attack angle instruction, and controlling the attitude of the model to be stable for the third time; locking the dynamic supporting mechanism; and closing the hypersonic wind tunnel. According to the multivariable complex control test method for the hypersonic speed wind tunnel variable configuration aircraft model, wind tunnel virtual flight multivariable complex time sequence control of the hypersonic speed wind tunnel variable configuration aircraft is realized, and then pneumatic, motion and control coupling simulation of the test model is completed; the method can be used for carrying out flight performance and control performance evaluation on a novel hypersonic speed variable configuration aircraft with multivariable complex control, 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 in particular relates to a multivariable complex control test method for a hypersonic wind tunnel variable configuration aircraft model. 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. Hypersonic variable configuration aircraft need to include changes in center of mass and wing surface, etc. Therefore, in the process of changing the configuration of hypersonic variable configuration aircraft, more complex nonlinear coupling phenomena will appear, affecting flight stability. It is necessary to carry out model wind tunnel virtual flight tests to evaluate the flight performance and control performance of hypersonic variable configuration aircraft in the process of changing the configuration.

[0005] For hypersonic variable configuration aircraft with multi-variable complex control in near-space, it is a technical problem that needs to be solved urgently to carry out flight performance and control performance verification based on model wind tunnel virtual flight tests and to establish a multi-variable complex control test method for hypersonic wind tunnel variable configuration aircraft models. Summary of the invention

[0006] The technical problem to be solved by the present invention is to provide a multivariable complex control test method for a hypersonic wind tunnel variable configuration aircraft model to overcome the defects of the prior art.

[0007] The invention discloses a multivariable complex control test method for a hypersonic wind tunnel variable configuration aircraft model. The hypersonic wind tunnel variable configuration aircraft model used comprises a variable center of mass mechanism, a variable wing mechanism, a steering gear system and a balance. The variable center of mass mechanism, the variable wing mechanism and the steering gear system are driven by a servo motor, and the balance is a six-component balance. The hypersonic wind tunnel variable configuration aircraft model is connected to a belly support plate through a dynamic support mechanism located in the inner cavity of the hypersonic variable configuration aircraft model for belly support. The dynamic support mechanism has two degrees of freedom and is used for performing a single-degree-of-freedom virtual flight test or a two-degree-of-freedom coupled virtual flight test. The drive and feedback data lines of the variable center of mass mechanism, the variable wing mechanism and the steering gear system are connected to a control computer, and a virtual flight control system is arranged in the control computer. The test method comprises the following steps: S10. Start the hypersonic wind tunnel; At time T0, the control computer is powered on, the virtual flight control system is initialized, the servo motors of the variable center of mass mechanism, variable wing mechanism, and steering gear system maintain their initial positions, and the hypersonic wind tunnel is started at the same time; S20. Setting the rudder deflection angle of the hypersonic wind tunnel variable configuration aircraft model; Before the hypersonic wind tunnel flow field is established, the rudder deflection angle is generally set to zero to reduce the impact of the flow field establishment on the rudder deflection angle. After the hypersonic wind tunnel flow field is established, the virtual flight control system gives a rudder deflection angle command for the preset angle of attack trim position, and the servo motor of the servo system drives the servo to deflect into place. S30. Dynamic support mechanism unlocked; At time T1, the dynamic support mechanism is unlocked, and the virtual flight control system starts the attitude control loop of the hypersonic wind tunnel variable configuration aircraft model after setting a delay of 300ms, while tracking the preset hypersonic wind tunnel variable configuration aircraft model attack angle command; S40. Controlled the attitude stability of a hypersonic wind tunnel variable configuration aircraft model for the first time; After the hypersonic wind tunnel variable configuration aircraft model flew in the hypersonic wind tunnel for 10 seconds, its attitude stabilized. At time T2, the variable wing surface and variable center of mass virtual flight test process preset by the virtual flight control system began; S50. Change the wing sweep angle of the hypersonic wind tunnel variable configuration aircraft model; The virtual flight control system gives instructions for changing the wing sweep angle of the hypersonic wind tunnel variable configuration aircraft model within T2 to T2+3s; within T2 to T2+13s, the center of mass remains unchanged, simulating the process of changing the wing sweep angle of the hypersonic variable configuration aircraft during flight, and at the same time, the model's attitude is stabilized for the second time; S60. Change the center of mass position of the hypersonic wind tunnel variable configuration aircraft model; The virtual flight control system gives instructions for changing the center of mass during T2+13s to T2+16s, simulating the process of changing the center of mass of a hypersonic wind tunnel variable configuration aircraft during flight. During T2+13s to T4, the wing sweep angle is maintained unchanged, simulating the process of changing the center of mass of a hypersonic variable configuration aircraft during flight, and the angle of attack instructions are changed at the same time, and the attitude of the model is controlled to be stable for the third time. S70. Locking dynamic support mechanism; At time T4, the dynamic support mechanism is locked, and the virtual flight control system gives a command to return the rudder angle to zero; at time T4+1s, the rudder angle of the hypersonic wind tunnel variable configuration aircraft model returns to zero; S80. Close the hypersonic wind tunnel; Shut down the hypersonic wind tunnel; at T5, shut down the virtual flight control system, power off the control computer, and the test is completed.

[0008] The multivariable complex control test method for a hypersonic wind tunnel variable configuration aircraft model of the present invention realizes the multivariable complex timing control of the wind tunnel virtual flight of the hypersonic variable configuration aircraft, and further completes the aerodynamic, motion and control coupling simulation of the test model, avoiding the problems of the unreality of a pure digital simulation model and the high cost, high risk and long cycle of a real flight test. It can be used to carry out wind tunnel virtual flight test verification of a new type of hypersonic variable configuration aircraft with multivariable complex control, and has practical engineering value. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] Figure 1 The present invention is a flow chart of a multivariable complex control test method for a hypersonic wind tunnel variable configuration aircraft model. DETAILED DESCRIPTION

[0010] The present invention is described in detail below with reference to the accompanying drawings and embodiments.

[0011] Embodiment: The test wind tunnel of this embodiment is a large-caliber conventional hypersonic wind tunnel, the hypersonic variable configuration aircraft model is 2000mm long and 411mm 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 1.2MPa. The initial angle of attack of this embodiment is 3°, the final angle of attack is 5°; the preset rudder deflection angle is 5°, the maximum sweep angle of the wing surface is 18°, and the variable center of mass mode is that the center of mass moves from front to back.

[0012] like Figure 1As shown, the hypersonic wind tunnel variable configuration aircraft model multivariable complex control test method of this embodiment, the hypersonic wind tunnel variable configuration aircraft model used includes a variable center of mass mechanism, a variable wing mechanism, a steering gear system and a balance, the variable center of mass mechanism, the variable wing mechanism, and the steering gear system are driven by a servo motor, and the balance is a six-component balance; the hypersonic wind tunnel variable configuration aircraft model is connected to the belly support plate through a dynamic support mechanism located in the inner cavity of the hypersonic variable configuration aircraft model for belly support; the dynamic support mechanism has two degrees of freedom and is used for single-degree-of-freedom virtual flight test or two-degree-of-freedom coupled virtual flight test; the drive and feedback data lines of the variable center of mass mechanism, the variable wing mechanism, and the steering gear system are connected to the control computer, and a virtual flight control system is set in the control computer; the test method includes the following steps: S10. Start the hypersonic wind tunnel; At time T0, the control computer is powered on, the virtual flight control system is initialized, the servo motors of the variable center of mass mechanism, variable wing mechanism, and steering gear system maintain their initial positions, and the hypersonic wind tunnel is started at the same time; S20. Setting the rudder deflection angle of the hypersonic wind tunnel variable configuration aircraft model; Before the hypersonic wind tunnel flow field is established, the rudder deflection angle is generally set to zero to reduce the impact of the flow field establishment on the rudder deflection angle. After the hypersonic wind tunnel flow field is established, the virtual flight control system gives a rudder deflection angle command for the preset angle of attack trim position, and the servo motor of the servo system drives the servo to deflect into place. S30. Dynamic support mechanism unlocked; At time T1, the dynamic support mechanism is unlocked, and the virtual flight control system starts the attitude control loop of the hypersonic wind tunnel variable configuration aircraft model after setting a delay of 300ms, while tracking the preset hypersonic wind tunnel variable configuration aircraft model attack angle command; S40. Controlled the attitude stability of a hypersonic wind tunnel variable configuration aircraft model for the first time; After the hypersonic wind tunnel variable configuration aircraft model flew in the hypersonic wind tunnel for 10 seconds, its attitude stabilized. At time T2, the variable wing surface and variable center of mass virtual flight test process preset by the virtual flight control system began; S50. Change the wing sweep angle of the hypersonic wind tunnel variable configuration aircraft model; The virtual flight control system gives instructions for changing the wing sweep angle of the hypersonic wind tunnel variable configuration aircraft model within T2 to T2+3s; within T2 to T2+13s, the center of mass remains unchanged, simulating the process of changing the wing sweep angle of the hypersonic variable configuration aircraft during flight, and at the same time, the model's attitude is stabilized for the second time; S60. Change the center of mass position of the hypersonic wind tunnel variable configuration aircraft model; The virtual flight control system gives instructions for changing the center of mass during T2+13s to T2+16s, simulating the process of changing the center of mass of a hypersonic wind tunnel variable configuration aircraft during flight. During T2+13s to T4, the wing sweep angle is maintained unchanged, simulating the process of changing the center of mass of a hypersonic variable configuration aircraft during flight, and the angle of attack instructions are changed at the same time, and the attitude of the model is controlled to be stable for the third time. S70. Locking dynamic support mechanism; At time T4, the dynamic support mechanism is locked, and the virtual flight control system gives a command to return the rudder angle to zero; at time T4+1s, the rudder angle of the hypersonic wind tunnel variable configuration aircraft model returns to zero; S80. Close the hypersonic wind tunnel; Shut down the hypersonic wind tunnel; at T5, shut down the virtual flight control system, power off the control computer, and the test is completed.

[0013] 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 multivariable complex control test method for a hypersonic wind tunnel variable configuration aircraft model, characterized in that: The hypersonic wind tunnel variable configuration aircraft model comprises a variable center of mass mechanism, a variable wing mechanism, a steering gear system and a balance, wherein the variable center of mass mechanism, the variable wing mechanism and the steering gear system are driven by a servo motor, and the balance is a six-component balance; the hypersonic wind tunnel variable configuration aircraft model is connected to a belly support plate through a dynamic support mechanism located in the inner cavity of the hypersonic variable configuration aircraft model for belly support; the dynamic support mechanism has two degrees of freedom and is used for performing a single-degree-of-freedom virtual flight test or a two-degree-of-freedom coupled virtual flight test; the drive and feedback data lines of the variable center of mass mechanism, the variable wing mechanism and the steering gear system are connected to a control computer, and a virtual flight control system is set in the control computer; the test method comprises the following steps: S10. Start the hypersonic wind tunnel; At time T0, the control computer is powered on, the virtual flight control system is initialized, the servo motors of the variable center of mass mechanism, variable wing mechanism, and steering gear system maintain their initial positions, and the hypersonic wind tunnel is started at the same time; S20. Setting the rudder deflection angle of the hypersonic wind tunnel variable configuration aircraft model; Before the hypersonic wind tunnel flow field is established, the rudder deflection angle is generally set to zero to reduce the impact of the flow field establishment on the rudder deflection angle. After the hypersonic wind tunnel flow field is established, the virtual flight control system gives a rudder deflection angle command for the preset angle of attack trim position, and the servo motor of the servo system drives the servo to deflect into place. S30. Dynamic support mechanism unlocked; At time T1, the dynamic support mechanism is unlocked, and the virtual flight control system starts the attitude control loop of the hypersonic wind tunnel variable configuration aircraft model after setting a delay of 300ms, while tracking the preset hypersonic wind tunnel variable configuration aircraft model attack angle instruction; S40. Controlled the attitude stability of a hypersonic wind tunnel variable configuration aircraft model for the first time; After the hypersonic wind tunnel variable configuration aircraft model flew in the hypersonic wind tunnel for 10 seconds, its attitude stabilized. At time T2, the variable wing surface and variable center of mass virtual flight test process preset by the virtual flight control system began; S50. Change the wing sweep angle of the hypersonic wind tunnel variable configuration aircraft model; The virtual flight control system gives instructions for changing the wing sweep angle of the hypersonic wind tunnel variable configuration aircraft model within T2 to T2+3s; within T2 to T2+13s, the center of mass is kept unchanged to simulate the process of changing the wing sweep angle of the hypersonic variable configuration aircraft during flight, and the attitude of the model is controlled to be stable for the second time; S60. Change the center of mass position of the hypersonic wind tunnel variable configuration aircraft model; The virtual flight control system gives instructions for changing the center of mass during T2+13s to T2+16s, simulating the process of changing the center of mass of a hypersonic wind tunnel variable configuration aircraft during flight. During T2+13s to T4, the wing sweep angle is maintained unchanged, simulating the process of changing the center of mass of a hypersonic variable configuration aircraft during flight, and the angle of attack instructions are changed at the same time, and the attitude of the model is controlled to be stable for the third time. S70. Locking dynamic support mechanism; At time T4, the dynamic support mechanism is locked, and the virtual flight control system gives a command to return the rudder angle to zero; at time T4+1s, the rudder angle of the hypersonic wind tunnel variable configuration aircraft model returns to zero; S80. Close the hypersonic wind tunnel; Shut down the hypersonic wind tunnel; at T5, shut down the virtual flight control system, power off the control computer, and the test is completed.

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