Higher-order non-singularity Terminal sliding-mode control method of high supersonic speed aircraft

A hypersonic speed and control method technology, applied in the field of aircraft control, can solve the problems of terminal sliding mode singularity and chattering problems in sliding mode control, etc., and achieve the effects of good tracking, good robustness and fast response speed

Active Publication Date: 2019-03-05
CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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Problems solved by technology

[0004] Chinese patent CN105653827 adopts the terminal sliding mode design method to design the controller of the hypersonic vehicle. The sliding mode surface is nonlinear, which makes the response speed of the system fast, but there is a singular problem in the terminal sliding mode
[0005] Chinese patents CN102880053 and CN102880056 both use the sliding mode design method to design the controller of the hypersonic vehicle, but there is chattering problem in the sliding mode control

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  • Higher-order non-singularity Terminal sliding-mode control method of high supersonic speed aircraft
  • Higher-order non-singularity Terminal sliding-mode control method of high supersonic speed aircraft
  • Higher-order non-singularity Terminal sliding-mode control method of high supersonic speed aircraft

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Embodiment Construction

[0108] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments.

[0109] Figure 1~8 Explanation of labels, symbols and lines in: Figure 4-Figure 8 The abscissa in represents the simulation time in seconds; Figure 4 The vertical axis in represents the speed, the unit is m / s; Figure 5 The ordinate in represents the height in meters; Image 6 The ordinate in represents the track angle , the unit is rad; Figure 7 The middle ordinate represents the angle of attack , the unit is rad; Figure 8 The ordinate in represents the pitch angular velocity , the unit is rad / s.

[0110] figure 1 It is the geometric outline drawing of the hypersonic vehicle (a top view and b side view);

[0111] figure 2 It is a schematic diagram of the high-order non-singular Terminal sliding mode control of the hypersonic speed of the present invention;

[0112] figure 2 As shown, the control schematic diagram mainly in...

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Abstract

The invention discloses a higher-order non-singularity Terminal sliding-mode control method of a high supersonic speed aircraft. A nonlinear model of the high supersonic speed aircraft is processed ina feedback linear method, and modeling errors and outside disturbance of a system are compensated via an RBF neural network control strategy. On the basis of the linearized vertical model, a novel neural network sliding-mode controller is in a nominal cruse flight condition based on a sliding mode surface of a regression structure, and an instruction signal and elevator deflection signal set by an engine throttle valve of the high supersonic speed aircraft are controlled to control the speed and height of the aircraft. The controller is highly robust for uncertainty of aerodynamic nonlinearity, pneumatic interference and system parameters. According to a simulation result, the instruction signal can be tracked effectively, and the response speed is higher.

Description

technical field [0001] The invention belongs to the technical field of aircraft control. Specifically, it relates to a high-order non-singular terminal sliding mode control method for a hypersonic vehicle. Background technique [0002] Hypersonic vehicle has the advantages of both aircraft and spacecraft, and integrates many cutting-edge aerospace technologies of human beings. It is an important direction for the development of future aircraft. Scholars at home and abroad have paid extensive attention to it. The key technologies of hypersonic vehicles include propulsion technology, aircraft integrated design technology, hypersonic aerodynamic / thermodynamic technology, structural material technology and flight control technology, etc. Flight control is one of the core issues of hypersonic flight technology, and it is also one of the current research hotspots in the control field. Affected by flight altitude and high Mach number design and flight conditions, hypersonic vehi...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 梁捷李树民梁频
Owner CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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