Rapid self-adaptive sliding mode fault-tolerant control method for hypersonic flight vehicle

An adaptive sliding mode and hypersonic technology, applied in the field of aircraft control, can solve problems such as loss of actuator benefits, achieve the effect of solving jitter problems and fast convergence speed

Active Publication Date: 2018-11-09
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0006] Purpose of the invention: In order to solve the problem of actuator benefit loss failures that are prone to occur during the flight of hypersonic vehicles, this paper designs an adaptive sliding mode fault-tolerant control law based on integral sliding mode surface and fast double power reaching law

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  • Rapid self-adaptive sliding mode fault-tolerant control method for hypersonic flight vehicle
  • Rapid self-adaptive sliding mode fault-tolerant control method for hypersonic flight vehicle
  • Rapid self-adaptive sliding mode fault-tolerant control method for hypersonic flight vehicle

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Embodiment Construction

[0050]The present invention will be further explained below in conjunction with the accompanying drawings. The computer sends flight instructions to the hypersonic vehicle, and the engine throttle setting value η c and elevator deflection angle δ e is sent to the motor and rudder in the actuator, but there is a benefit loss fault in the actuator, so after passing through the actuator, the original input becomes f 1 n c and f 2 δ e , and input this into the hypersonic aircraft model, and then feed back to the aircraft command for adjustment through the measurement system.

[0051] Step 1: Establish an accurate feedback linearization model of the hypersonic vehicle,

[0052] choose As the system state of , the accurate feedback linearization model of the hypersonic vehicle is as follows:

[0053]

[0054] Among them, h (4) Indicates the fourth differential with respect to height, η c Indicates the setting value of the engine throttle valve, δ e Indicates the elevat...

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Abstract

The invention discloses a rapid self-adaptive sliding mode fault-tolerant control method for a hypersonic flight vehicle. The method comprises the following steps that 1, an accurate feedback linearization model for the hypersonic flight vehicle is established; 2, a fault model for the hypersonic flight vehicle is established on the basis of the first step; 3, a basic controller is designed; and 4, self-adaptive fault-tolerant controller is designed by adding a self-adaptive law on the basis of the third step. The rapid self-adaptive sliding mode fault-tolerant control method for the hypersonic flight vehicle has the advantages that under the condition that the failure time and the efficiency loss coefficient are not known, the fault is processed in a self-adaptive mode, an asymptotic tracking flying output reference command is completed, and high efficiency is achieved.

Description

technical field [0001] The invention relates to an aircraft control method, in particular to a fast adaptive sliding mode fault-tolerant control method for a hypersonic aircraft. Background technique [0002] Hypervehicle refers to a winged or wingless aircraft with a flight Mach number above five and capable of long-term maneuvering flight in the atmosphere or across the atmosphere. The main application forms include: hypercruise missiles, aerospace vehicles, etc. Due to the characteristics of large airspace and high maneuverability of hyper-flying aircraft, coupled with the complex and changeable environment, it is very difficult to study its modeling and control methods. In the design process, the influence of many aspects should be considered comprehensively. Many literatures point out that the research on the related technology of hyper-flying vehicles is a challenging research task. [0003] Fault-tolerant control (FTC) means that when the system fails, the controller...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 朱平江驹甄子洋万月丰蒋烁莹
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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