Fault-tolerant control method for tiny faults of control surface of hypersonic flight vehicle with random attitude

A hypersonic, fault-tolerant control technology, applied in the field of flight control, can solve the problems of difficulty in evaluating the effect of fault-tolerant control, poor accuracy and reliability, and occupying a lot of software and hardware resources, so as to meet high reliability requirements, reduce repair costs, and eliminate The effect of software and hardware resource occupancy

Pending Publication Date: 2022-07-22
北京京航计算通讯研究所
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In view of the above analysis, the embodiment of the present invention aims to provide a micro-fault-tolerant control method for the rudder surface of a hypersonic vehicle with a random attitude, which is used to solve the problems in the prior art, such as the high cost of fault repair, the occupation of many software and hardware resources, and the problem of random Fault-tolerant control adaptability, accuracy and reliability of attitude hypersonic vehicle are poor, and fault-tolerant control effect evaluation is difficult, etc.

Method used

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  • Fault-tolerant control method for tiny faults of control surface of hypersonic flight vehicle with random attitude
  • Fault-tolerant control method for tiny faults of control surface of hypersonic flight vehicle with random attitude
  • Fault-tolerant control method for tiny faults of control surface of hypersonic flight vehicle with random attitude

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Embodiment 1

[0085] A specific embodiment of the present invention discloses a fault-tolerant control method for small rudder surface faults of a random attitude hypersonic aircraft, comprising the following steps:

[0086] S1. Carry out a random attitude hypersonic flight test, impose minor faults and disturbances on the control system model; obtain the actual PDF (Probability Density Function) of the random attitude angle;

[0087] Among them, the control system model is a non-Gaussian random distribution model introduced on the basis of the traditional hypersonic vehicle re-entry segment model, and then a random attitude hypersonic vehicle re-entry segment rudder surface-angular rate- Attitude angle control system model;

[0088] S2. Use the fuzzy observer to observe the fault to obtain the estimated fault value;

[0089] S3. Obtain the expected PDF of the random attitude angle;

[0090] S4. Design a fault-tolerant control algorithm, obtain an adaptive fault-tolerant controller based ...

Embodiment 2

[0093] Optimizing on the basis of Embodiment 1, step S1 can be further refined into the following steps:

[0094]S11. Specifically, the control system model is a non-Gaussian random distribution model introduced on the basis of the traditional hypersonic aircraft re-entry segment model, and then a random attitude hypersonic aircraft re-entry segment rudder with external faults and external disturbances is formed. The face-angular rate-attitude angle control system model, hereinafter referred to as the control system model, the nonlinear stochastic state equation of the control system model is:

[0095]

[0096]

[0097] V(t)=D(Ξx(t))

[0098] γ(ρ,u(t))=Φ 2 (C(ρ)V(t)) 2

[0099] Where t represents time, and t=0 represents the response start time; and and are the angular rate of the angle of attack, the angular rate of the roll angle and the angular rate of the sideslip angle; ρ=[ρ 1 ρ 2 ρ 3 ] T and ρ 1 , ρ 2 and ρ 3 are the angle of attack, roll angle an...

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Abstract

The invention relates to a control surface tiny fault tolerance control method for a random attitude hypersonic flight vehicle, belongs to the technical field of flight control, and solves the problems of high fault repair cost, poor fault tolerance control adaptability and reliability for the random attitude hypersonic flight vehicle, difficulty in evaluating the fault tolerance control effect and the like in the prior art. Through carrying out a random attitude hypersonic flight test, tiny faults and interferences are applied to a control system model of the random attitude hypersonic aircraft, and an actual PDF of a random attitude angle is obtained; a fuzzy observer is adopted to carry out fault observation on the control surface after the tiny fault and interference are applied so as to obtain a fault estimation value; obtaining an expected PDF of the random attitude angle; and based on the fault estimation value and a fault-tolerant control algorithm, obtaining a self-adaptive fault-tolerant controller by using the actual PDF and the expected PDF of the random attitude angle, and performing fault-tolerant control repair on the control surface fault. The fault-tolerant control of the early tiny fault of the random attitude hypersonic flight vehicle is realized.

Description

technical field [0001] The invention relates to the technical field of flight control, in particular to a fault-tolerant control method for small rudder surface faults of a random attitude hypersonic aircraft. Background technique [0002] Hypersonic vehicle generally refers to an aircraft with the fastest flight speed that can reach and exceed Mach 5. It is not only a kind of economical and reliable means of entering space, but also has unique advantages in reconnaissance and surveillance, communication support, intercontinental transportation, etc.; Precise, stable and flexible re-entry ground guidance weapons are irreplaceable in functions such as anti-interception, lightning strikes, rapid orbit changes, and dexterous task switching. Hypersonic vehicles used as weapons face more specific complex environments, such as laser and microwave ablation. Laser weapons against hypersonic vehicles need time to accumulate energy to burn through the vehicle's shell. Therefore, an ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B23/02
CPCG05B23/0243G05B2219/24065
Inventor 胡开宇李吉孙文靖杨春霞刘妍白洋梁秀枝
Owner 北京京航计算通讯研究所
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