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Intelligent nonlinear control system for hypersonic morphing aircraft

A nonlinear control and hypersonic technology, which is applied in general control systems, control/regulation systems, instruments, etc., can solve problems such as uncertain flight control of variable-wing hypersonic aircraft with strong nonlinear characteristics

Inactive Publication Date: 2016-08-10
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0009] The technical problem to be solved by the present invention is to overcome the deficiencies in the prior art and provide an intelligent nonlinear control system for variable-wing hypersonic aircraft, which can effectively solve the problem of variable-wing hypersonic aircraft under strong nonlinear characteristics and uncertain external disturbances. flight control problem

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  • Intelligent nonlinear control system for hypersonic morphing aircraft
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  • Intelligent nonlinear control system for hypersonic morphing aircraft

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Embodiment Construction

[0037] The technical scheme of the present invention is described in detail below in conjunction with accompanying drawing:

[0038] The train of thought of the present invention is aimed at the characteristic of variable-wing hypersonic vehicle, designs a kind of intelligent nonlinear control system of variable-wing hypersonic vehicle through Backstepping control system design method and combined with neural network, in order to solve the problem of variable-wing hypersonic vehicle Flight control problems under strong nonlinear characteristics and uncertain external disturbances.

[0039] The backstepping control system design method is to use some states in the hypersonic vehicle model as virtual control inputs for other states, and compensate the effects of various uncertain factors while designing the control inputs. The husband function designs the control law from front to back to ensure the global stability of the system. This method is suitable for online control and ...

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Abstract

The invention discloses an intelligent nonlinear control system for a hypersonic morphing aircraft and belongs to the aviation aerospace propulsion control technical field. According to the intelligent nonlinear control system of the invention, according to problems in outer-loop stable tracking control of the hypersonic morphing aircraft, with influence on modeling caused by a morphing structure and influence on tracking control performance caused by model parameter uncertainty and external unknown interference considered, the control system is divided into three sub systems according to the state variable characteristics of the aircraft; control signals are obtained sequentially through using a backstepping method; approximation is performed on the unknown interference through adopting an RBF neural network, so that the robustness of the controller can be ensured; and according to the problems of difficulty in the derivation of virtual control signals and differential expansion, dynamic surface control thinking is introduced to make improvement. With the above technical schemes of the invention adopted, the global stability of the closed-loop system can be guaranteed, and the system has high tracking performance and robust performance.

Description

technical field [0001] The invention relates to an aircraft control system, in particular to an intelligent nonlinear control system for a variable-wing hypersonic aircraft, which belongs to the technical field of aerospace propulsion control. Background technique [0002] The propulsion power used by the hypersonic vehicle is a supersonic combustion ramjet engine that does not need its own oxidant, and the aerodynamic layout is an integrated body / engine design. There is a strong coupling between the elastic body of the hypersonic vehicle and the flight propulsion system, the nonlinear characteristics of the vehicle model are very serious, the flight process has rapid time-varying characteristics, the aerodynamic characteristics of the hypersonic vehicle change drastically, and various uncertainties are serious , the traditional classical control methods cannot well meet the performance requirements of flight control system stability and strong robustness. Therefore, to ens...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B17/02
CPCG05B17/02
Inventor 甄子洋江驹吴雨珊杨政
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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