Control device and control method of multivariable hypersonic variable configuration aircraft model

Abstract

The invention belongs to the technical field of wind tunnel test and flight control crossing, and discloses a control device and a control method of a multivariable hypersonic variable configuration aircraft model. The control device comprises a main control computer; the main control computer is used for project management and development, data storage and display, flight and control simulation; the system also comprises a real-time simulation machine which is used for simulating the real-time environment of the flight control system, and completing the data collection of the sensor, and the generation and transmission of a control instruction. The control method comprises the steps of establishing a digital simulation model; verifying the digital simulation model; compiling a control law program and testing; performing a virtual flight test; and analyzing and processing data. According to the control device and the control method of the multivariable hypersonic-speed variable-configuration aircraft model, simulation of a multivariable hypersonic-speed variable-configuration aircraft digital model and a control law is realized, and a control algorithm operated in a real-time simulation machine can be used for carrying out a wind tunnel pneumatic, motion and control coupling virtual flight test; the engineering practical value is realized.

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 control device and a control method for a multivariable hypersonic 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 complex multi-variable controls 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 control device and control method for the multi-variable hypersonic variable configuration aircraft model. Summary of the invention

[0006] One technical problem to be solved by the present invention is to provide a control device for a multivariable hypersonic variable configuration aircraft model. Another technical problem to be solved by the present invention is to provide a control method for a multivariable hypersonic variable configuration aircraft model to overcome the defects of the prior art.

[0007] The control device of the multivariable hypersonic variable configuration aircraft model of the present invention comprises a variable center of mass mechanism, a variable wing mechanism, a steering gear system and a balance, and the belly support is performed by connecting the belly support plate through a dynamic support mechanism located in the inner cavity of the hypersonic variable configuration aircraft model; 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 control device of the multivariable hypersonic variable configuration aircraft model includes a main control computer, which is used for project management and development, data storage and display, flight and control simulation; virtual flight simulation software is installed in the main control computer, and the functions of the virtual flight simulation software include project management, program writing, code generation, data monitoring and display, data storage and analysis, and real-time control of the operation process; The control device of the multivariable hypersonic variable configuration aircraft model also includes a real-time simulator, which is used to simulate the real-time environment of the multivariable hypersonic variable configuration aircraft flight control system, complete the collection of sensor data, and generate and send control instructions; the real-time simulator integrates a CPU and memory card, output card, input card and board interfaces corresponding to the variable center of mass mechanism, variable wing mechanism, dynamic support mechanism, and servo system.

[0008] The control method of the multivariable hypersonic variable configuration aircraft model of the present invention comprises the following steps: S10. Establishing a digital simulation model; A digital simulation model of the test model is established on a main control computer according to a multivariable hypersonic variable configuration aircraft aerodynamic database; S20. Verify the digital simulation model; Given input data in the digital simulation model, verify whether the response data of the digital simulation model conforms to the rules of the aerodynamic database, and verify whether the simulation capability of the virtual flight test can cover the simulation requirements of the model response process; S30. Write control law program and test; Write control law programs, embed them into digital simulation models and conduct simulation verification to test the flight performance and control performance of multivariable hypersonic variable configuration aircraft models; S40. Conduct virtual flight test; The control law program is uploaded to the real-time simulator to conduct a virtual flight test. During the virtual flight test, the sensor data measured on the multivariable hypersonic variable configuration aircraft model is collected through the interface board, the state of the multivariable hypersonic variable configuration aircraft model is controlled in real time, and the response of the multivariable hypersonic variable configuration aircraft model is recorded. S50.Data analysis and processing; After the virtual flight test is completed, the test data is analyzed and processed to obtain the flight performance and control performance of the aircraft.

[0009] The control device and control method of the multivariable hypersonic variable configuration aircraft model of the present invention realize the simulation of the digital model and control law of the multivariable hypersonic variable configuration aircraft. The control algorithm running in the real-time simulator can carry out wind tunnel aerodynamic, motion and control coupled virtual flight tests, avoiding the problems of the unreality of pure digital simulation models and the high cost, high risk and long cycle of real flight tests. It 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

[0010] Figure 1 It is a schematic diagram of the control device structure of the multivariable hypersonic variable configuration aircraft model of the present invention. DETAILED DESCRIPTION

[0011] The present invention is described in detail below with reference to the accompanying drawings and embodiments.

[0012] Embodiment: The control device of the multivariable hypersonic variable configuration aircraft model of this embodiment includes a variable center of mass mechanism, a variable wing mechanism, a steering gear system and a balance, and the belly support is connected to the belly support plate through a dynamic support mechanism located in the inner cavity of the hypersonic variable configuration aircraft model; the dynamic support mechanism has two degrees of freedom and is used to perform a single-degree-of-freedom virtual flight test or a two-degree-of-freedom coupled virtual flight test; The control device of the multivariable hypersonic variable configuration aircraft model includes a main control computer, which is used for project management and development, data storage and display, flight and control simulation; virtual flight simulation software is installed in the main control computer, and the functions of the virtual flight simulation software include project management, program writing, code generation, data monitoring and display, data storage and analysis, and real-time control of the operation process; The control device of the multivariable hypersonic variable configuration aircraft model also includes a real-time simulator, which is used to simulate the real-time environment of the multivariable hypersonic variable configuration aircraft flight control system, complete the collection of sensor data, and generate and send control instructions; the real-time simulator integrates a CPU and memory card, output card, input card and board interfaces corresponding to the variable center of mass mechanism, variable wing mechanism, dynamic support mechanism, and servo system.

[0013] like Figure 1 As shown, the control method of the multivariable hypersonic variable configuration aircraft model of this embodiment includes the following steps: S10. Establishing a digital simulation model; A digital simulation model of the test model is established on a main control computer according to a multivariable hypersonic variable configuration aircraft aerodynamic database; S20. Verify the digital simulation model; Given input data in the digital simulation model, verify whether the response data of the digital simulation model conforms to the rules of the aerodynamic database, and verify whether the simulation capability of the virtual flight test can cover the simulation requirements of the model response process; S30. Write control law program and test; Write control law programs, embed them into digital simulation models and conduct simulation verification to test the flight performance and control performance of multivariable hypersonic variable configuration aircraft models; S40. Conduct virtual flight test; The control law program is uploaded to the real-time simulator to conduct a virtual flight test. During the virtual flight test, the sensor data measured on the multivariable hypersonic variable configuration aircraft model is collected through the interface board, the state of the multivariable hypersonic variable configuration aircraft model is controlled in real time, and the response of the multivariable hypersonic variable configuration aircraft model is recorded. S50.Data analysis and processing; After the virtual flight test is completed, the test data is analyzed and processed to obtain the flight performance and control performance of the aircraft.

[0014] 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 control device for a multivariable hypersonic variable configuration aircraft model, characterized in that: The multivariable hypersonic variable configuration aircraft model includes a variable center of mass mechanism, a variable wing mechanism, a steering gear system and a balance, and 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 single-degree-of-freedom virtual flight tests or two-degree-of-freedom coupled virtual flight tests; The control device of the multivariable hypersonic variable configuration aircraft model includes a main control computer, which is used for project management and development, data storage and display, flight and control simulation; virtual flight simulation software is installed in the main control computer, and the functions of the virtual flight simulation software include project management, program writing, code generation, data monitoring and display, data storage and analysis, and real-time control of the operation process; The control device of the multivariable hypersonic variable configuration aircraft model also includes a real-time simulator, which is used to simulate the real-time environment of the multivariable hypersonic variable configuration aircraft flight control system, complete the collection of sensor data, and generate and send control instructions; the real-time simulator integrates a CPU and memory card, output card, input card and board interfaces corresponding to the variable center of mass mechanism, variable wing mechanism, dynamic support mechanism, and servo system.

2. A control method for a multivariable hypersonic variable configuration aircraft model, characterized in that: The control method comprises the following steps: S10. Establishing a digital simulation model; A digital simulation model of the test model is established on a main control computer according to a multivariable hypersonic variable configuration aircraft aerodynamic database; S20. Verify the digital simulation model; Given input data in the digital simulation model, verify whether the response data of the digital simulation model conforms to the rules of the aerodynamic database, and verify whether the simulation capability of the virtual flight test can cover the simulation requirements of the model response process; S30. Write control law program and test; Write control law programs, embed them into digital simulation models and conduct simulation verification to test the flight performance and control performance of multivariable hypersonic variable configuration aircraft models; S40. Conduct virtual flight test; The control law program is uploaded to the real-time simulator to conduct a virtual flight test. During the virtual flight test, the sensor data measured on the multivariable hypersonic variable configuration aircraft model is collected through the interface board, the state of the multivariable hypersonic variable configuration aircraft model is controlled in real time, and the response of the multivariable hypersonic variable configuration aircraft model is recorded. S50.Data analysis and processing; After the virtual flight test is completed, the test data is analyzed and processed to obtain the flight performance and control performance of the aircraft.

Images