Wide-area flight intelligent backstepping switching control method oriented to aerodynamic unknown
A control method and intelligent technology, applied in the field of flight control, can solve problems such as poor practicability, and achieve the effects of facilitating engineering applications, preventing jumps, and improving estimation accuracy
Active Publication Date: 2021-06-25
NORTHWESTERN POLYTECHNICAL UNIV +1
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Problems solved by technology
[0005] In order to overcome the shortcomings of poor practicability of the existing wide-area flight switching system control methods, the present invention provides an intelligent backstepping switching control method for wide-area flight facing unknown aerodynamics
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[0081] Now in conjunction with embodiment, accompanying drawing, the present invention will be further described:
[0082] refer to figure 1 , the present invention is oriented to the aerodynamic unknown wide-area flight intelligent backstepping switching control method. The specific steps are as follows:
[0083] Step 1: Consider a class of Rocket based combined cycle (RBCC) aerospace vehicles, whose wide-area climb process can be divided into ejection mode, sub-fuel ram mode, scram mode and rocket mode 4 stable modes.
[0084] Write the RBCC aerospace vehicle attitude subsystem as the following multi-input multi-output switching system
[0085]
[0086] Among them, the three-channel attitude angle X 1 =[θ ψ φ] T and attitude angular velocity X 2 =[ω x ω y ω z ] T are the state variables, θ, ψ, φ, ω x , ω y and ω z They are pitch angle, yaw angle, roll angle, roll angular velocity, yaw angular velocity and pitch angular velocity; u σ(t) =[δ x,σ(t) δ y,σ(t...
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The invention relates to a wide-area flight intelligent backstepping switching control method oriented to pneumatic unknown, which is used for solving the technical problem of poor practicability of the existing wide-area flight switching control method. According to the technical scheme, a wide-area flight multi-mode switching system with aerodynamic parameter uncertainty is considered, and a stable mode switching controller is designed based on a backstepping method technical framework; a first-order filter is introduced to process the virtual control quantity, and the problem of complexity explosion is solved; a neural network intelligent system is used to approach uncertainty, a prediction error representing the uncertainty estimation performance is constructed based on a parallel estimation model, and the prediction error is used to adjust a neural network weight update law; and a transition mode controller is designed based on an inertial link, and soft switching of a multi-mode controller is ensured. According to the invention, in combination with the characteristics of the wide-area flight multi-mode process of the aircraft, the uncertain estimation precision is effectively improved by designing the pneumatic unknown wide-area flight intelligent backstepping switching control, the smooth switching of the control is realized, and the flight safety is ensured.
Description
technical field [0001] The invention belongs to the field of flight control, and relates to an aircraft control method, in particular to an aerodynamically unknown wide-area flight intelligent backstep switching control method. Background technique [0002] With the rapid development of aerospace technology, the envelope of the aircraft is getting wider and wider, making it possible for the aircraft to take off from the ground level and perform wide-area flight. During the wide-area climb, the speed of the aircraft continues to increase to hypersonic speed, and it will play an important role in long-distance rapid transportation, space travel, global rapid strikes, etc. [0003] During wide-area flight, the aircraft may face different power modes, aerodynamic configurations and flight tasks, resulting in multiple flight modes. Multi-mode is a common feature of the aircraft's wide-area climb process. It is necessary to establish different models and design different controll...
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Login to View More IPC IPC(8): G05B13/04
CPCG05B13/042Y02T90/00
Inventor 许斌程怡新尤明戴磊
Owner NORTHWESTERN POLYTECHNICAL UNIV