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Hypersonic aircraft guaranteed-performance fault-tolerant control method considering faults of executing mechanism

A technology of executive mechanism and fault-tolerant control, applied in the field of aircraft control

Active Publication Date: 2020-07-14
ZHONGBEI UNIV
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Problems solved by technology

[0004] In order to solve the problem of accurate tracking control of a hypersonic vehicle for a given altitude / speed command under limited fault conditions, the present invention provides a guaranteed performance and fault-tolerant control method for a hypersonic vehicle considering the failure of the actuator

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  • Hypersonic aircraft guaranteed-performance fault-tolerant control method considering faults of executing mechanism
  • Hypersonic aircraft guaranteed-performance fault-tolerant control method considering faults of executing mechanism

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Embodiment Construction

[0052] The present invention will be further described below in conjunction with specific examples.

[0053] A guaranteed performance and fault-tolerant control method for hypersonic aircraft considering the failure of the actuator, the process is as follows figure 1 shown, including the following steps:

[0054] (1) Establish a parameterized dynamic model of AHV considering the failure of the actuator:

[0055]

[0056] in:

[0057]

[0058]

[0059]

[0060]

[0061] Where h is height, V is velocity, α is angle of attack AOA, γ is ballistic angle FPA, Q is pitch rate PR, N i is the generalized force under the action of hybrid power, f i , g i (i=V, α, γ, Q) respectively represent the lumped interference and AHV nominal model; d Ve , d γe , d αe and d Qe Represents the external disturbance, Δ represents the coefficient of aerodynamic disturbance; the initial conditions of the hypersonic vehicle are V(0)=7685ft / s, h(0)=86030ft, γ(0)=0rad, α(0)=0.27rad, ...

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Abstract

The invention discloses a hypersonic aircraft guaranteed-performance fault-tolerant control method considering faults of an executing mechanism, relates to the field of flight vehicle control, and mainly solves the problem of accurate tracking control of a given height / speed instruction under a limited fault condition of a hypersonic flight vehicle. The method comprises the following steps: constructing a novel preset performance mechanism based on a Korean tracking differentiator to realize priori adjustment of errors, and overcoming the problem of transient buffeting caused by rapid constraint of traditional preset performance control; designing a minimum parameter learning (MLP) neural network learner with low computational complexity to eliminate the influence of lumped disturbance onthe AHV model in real time; finally, integrating the MLP observer and a novel preset performance mechanism, and achieving accurate tracking control over a given height / speed instruction under the limited fault condition. According to the method, the MLP observer and a novel preset performance mechanism are integrated, and the method is of great significance in realizing accurate tracking control of a given height / speed instruction under a limited fault condition.

Description

technical field [0001] The present invention relates to the field of aircraft control, and specifically relates to a performance-guaranteed fault-tolerant control method for a hypersonic aircraft considering actuator faults, which mainly solves the problem of precise tracking control for a given altitude / speed command under limited fault conditions of a hypersonic aircraft. Background technique [0002] An air-breathing hypersonic vehicle (Airbreathing Hypersonic Vehicle, AHV) generally refers to an aircraft whose flight Mach number is not less than 5 Ma and which is powered by an air-breathing scramjet engine. AHV has important civil and military value and strategic significance, and has many advantages such as high speed, high maneuverability, and large flight envelope. With the increase of flight time and the emergence of control loss, the reliability of AHV actuators decreases, and failure modes such as loss of accuracy and efficiency attenuation inevitably occur, which ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/12G05B13/04
CPCG05D1/12G05B13/042Y02T90/00
Inventor 邵星灵李杰张文栋刘俊
Owner ZHONGBEI UNIV
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