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

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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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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