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Robust adaptive switching control method for wide-area flight based on multimodal partitioning

A technology of robust self-adaptation and control method, which is applied in the field of robust self-adaptive switching control of wide-area flight, can solve the problems of poor practicability, achieve the effect of facilitating engineering application, realizing large-envelope flight, and improving robustness

Active Publication Date: 2022-08-09
NORTHWESTERN POLYTECHNICAL UNIV +1
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AI Technical Summary

Problems solved by technology

[0005] In order to overcome the shortcomings of poor practicability of the existing control methods for wide-area flight switching systems, the present invention provides a robust adaptive switching control method for wide-area flight based on multi-modal division

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  • Robust adaptive switching control method for wide-area flight based on multimodal partitioning
  • Robust adaptive switching control method for wide-area flight based on multimodal partitioning
  • Robust adaptive switching control method for wide-area flight based on multimodal partitioning

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Embodiment Construction

[0061] The present invention will now be further described in conjunction with the embodiments and accompanying drawings:

[0062] refer to figure 1 The specific steps of the robust adaptive switching control method for wide-area flight based on multi-modal division of the present invention are as follows:

[0063] 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-ramjet mode, scramjet mode and rocket mode 4 stable modes.

[0064] The RBCC aerospace vehicle attitude subsystem is written as the following multiple-input multiple-output switching system

[0065]

[0066] 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 are pitch angle, yaw angle, roll angle, roll angular velocity, yaw angular velocity and pitch angular velocity; u σ(t) =[δ x,σ(t) ...

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Abstract

The invention relates to a robust adaptive switching control method for wide-area flight based on multi-modal division, which is used to solve the technical problem of poor practicability of the existing wide-area flight switching control method. The technical solution is to consider a wide-area flight multi-mode switching system with uncertainty, use model transformation to obtain a second-order nonlinear switching system that can directly design a controller, and design a stable mode switching controller based on the dynamic inverse method; use neural network. Approaching the uncertainty of the system, the finite-time convergence robust term is designed based on the non-singular terminal sliding mode surface; the transition mode controller is designed based on the inertial link to ensure the soft switching of the multi-modal controller; the invention combines the wide-area flight multi-modality According to the process characteristics, the robustness of the controller is effectively improved by designing a robust adaptive switching control for wide-area flight based on multi-modal division, and the smooth switching of the control is realized, which ensures the flight safety and is suitable for engineering applications.

Description

technical field [0001] The invention belongs to the field of aircraft control, and relates to an aircraft control method, in particular to a wide-area flight robust adaptive switching control method based on multi-modal division. 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 horizontally from the ground and fly in a wide area. During the wide-area climb, the speed of the aircraft continues to increase to hypersonic speeds, which will play an important role in long-distance rapid transportation, space travel, and global rapid strikes. [0003] During wide-area flight, the aircraft may face different power modes, aerodynamic configurations and flight tasks, resulting in the existence of multiple flight modes. Multi-mode is a common feature of the aircraft's wide-area climb process. It is necessary to build different models and design dif...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B13/04
CPCG05B13/042Y02T90/00
Inventor 许斌程怡新尤明戴磊
Owner NORTHWESTERN POLYTECHNICAL UNIV
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