Back-stepping robust self-adaptive dynamic surface-based near-space aircraft control system

A robust adaptive technology for near-space vehicles, applied in adaptive control, general control systems, control/regulation systems, etc., can solve problems such as computational expansion, uncertainty, and interference parameters of near-space vehicles

Inactive Publication Date: 2018-12-21
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0010] Purpose of the invention: The purpose of the present invention is to overcome the deficiencies of the prior art and provide a control system for near-space aircraft based on Back-stepping robust adaptive dynamic surface, so as to eff

Method used

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  • Back-stepping robust self-adaptive dynamic surface-based near-space aircraft control system
  • Back-stepping robust self-adaptive dynamic surface-based near-space aircraft control system
  • Back-stepping robust self-adaptive dynamic surface-based near-space aircraft control system

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Embodiment Construction

[0095] The technical solution of the present invention will be further described below in conjunction with the accompanying drawings.

[0096] Taking a certain type of near-space aircraft as an example, it adopts a wing-body fusion layout, and the outline of the body is triangular. The large-swept wing and the fuselage adopt a wing-body fusion method, and the elevator is arranged on the trailing edge of the wing. The longitudinal attitude model of the aircraft under hypersonic cruise flight conditions can be written in the following form:

[0097]

[0098]

[0099]

[0100]

[0101]

[0102]

[0103] The aerodynamic forces and moments of the aircraft are expressed as:

[0104] L=0.5ρV 2 sC L

[0105] D=0.5ρV 2 sC D

[0106] T=0.5ρV 2 sC T

[0107] m yy =0.5ρV 2 sc[C M (α)+C M (δ e )+C M (q)]

[0108] Among them, V, γ, h, α, q, β, m, I yyRespectively represent aircraft speed, flight track inclination angle, aircraft altitude, flight angle of a...

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Abstract

The invention discloses a back-stepping robust self-adaptive dynamic surface-based near-space aircraft control system. The system comprises the steps of: initially employing interpolation fitting to obtain an aerodynamic parameter of an aircraft cruising segment, and building a longitudinal uncertainty strict feedback block non-linear model of an aircraft; secondly, separately controlling speed and height according to state variable characteristic of the aircraft, sequentially solving a control signal by a back-stepping method, approaching unknown interference by employing a RBF neural network, and updating the parameter on line and in real time; and finally, adding a dynamic surface control method with regard to the problems of virtual control signal derivation difficulty and differentialexpansion. By the system, the problems of virtual control signal derivation difficulty and differential expansion are solved, and the system has favorable tracking property and robustness.

Description

technical field [0001] The invention relates to an aircraft control system, in particular to a near-space aircraft control system based on Back-stepping robust self-adaptive dynamic surface. Background technique [0002] The propulsion power used by the near-space 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 near-space 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 near-space 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 ensure the real-time performance, robustness and stabili...

Claims

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Application Information

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IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 徐文萤江驹万月丰蒋烁莹
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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