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Near-space aircraft control system

A near-space vehicle and control system technology, applied in the general control system, control/regulation system, adaptive control, etc., to achieve the effects of increasing robustness, good tracking performance and robust performance, and ensuring global stability

Active Publication Date: 2018-04-20
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0010] Purpose of the invention: In order to overcome the deficiencies of the existing technologies, the present invention provides an adaptive integral sliding mode control system for near-space aircraft based on a disturbance observer, which can effectively solve the problem of how to fly near-space aircraft when there is interference and parameters are uncertain. problem of control

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[0031] specific implementation plan

[0032] The technical solutions of the present invention will be described in detail below in conjunction with the accompanying drawings, and the contents mentioned in the implementation modes are not intended to limit the present invention.

[0033] According to the characteristics of the near-space aircraft, the present invention designs a near-space aircraft adaptive integral sliding mode control system based on the disturbance observer through the state feedback output tracking model reference adaptive control system design method, which is used to generate the control of the near-space aircraft Input u, so that the pitch angle θ of the near-space vehicle can quickly and stably track the command signal θ cmd , so as to solve the flight control problem of variable-wing aircraft in near-space with uncertain parameters and constant parameters in the process of winglet switching.

[0034] Such as figure 1 , the control system of the near-...

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Abstract

The invention discloses a near-space aircraft control system, which belongs to the technical field of aviation aerospace propulsion control. The near-space aircraft control system aims at the attitudestable tracking control problem of a near-space aircraft, and considers the problems of unknown interference and parameter uncertainty. According to the near-space aircraft control system, firstly, an estimated value of an interference observer for interfering the outside world, then the parameter uncertainty of the aircraft is analyzed, and a self-adaptive estimated value of the aircraft parameters is obtained; secondly, an integral sliding mode surface is selected thus a self-adaptive integral sliding mode controller is designed for tracking control of an inner ring attitude angle of the near-space aircraft; and finally, the stability of the controller is proofed by utilizing a Lyapunov stability theory. The near-space aircraft control system can ensure the global stability of a closed-loop system, and enable the system to have good tracking performance and robust performance.

Description

technical field [0001] The invention relates to an aerospace propulsion control system, in particular to a near-space vehicle control system. 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 stability of the flight control system, higher requireme...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/02
CPCG05B13/042
Inventor 杨政蒋烁莹余朝军甄子洋
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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