A multi-mode non-interference switching control method for a high-altitude platform system

By employing a parallel controller-based non-disruptive switching method in the high-altitude test system, combined with active disturbance rejection control, non-singular terminal sliding mode control, and fastest feedback control, the control accuracy and response speed issues of the high-altitude test system under complex flight environments were solved, achieving non-disruptive switching and smooth control of multi-mode operation.

CN117270427BActive Publication Date: 2026-06-12BEIHANG UNIV +1
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
BEIHANG UNIV
Filing Date
2023-08-30
Publication Date
2026-06-12

AI Technical Summary

Technical Problem

The existing control framework of high-altitude test systems mainly adopts the PID control strategy, which is difficult to effectively solve the problem of rapid coordinated control of multiple targets, multiple tasks and multiple actuators in complex flight working environments, especially the lack of adaptive and rapid response capabilities in simulated high-altitude environments.

Method used

A parallel controller-based non-disruptive switching method is adopted. Through multi-modal design, combined with active disturbance rejection control, non-singular terminal sliding mode control and fastest feedback control, multi-modal non-disruptive switching of the high-altitude platform system is achieved. An integrated parallel non-disruptive controller is designed to smoothly switch the control process between different controllers.

Benefits of technology

It improves the control and tracking performance of the high-altitude test system under different modes, achieves smooth switching without disturbance, meets the needs of complex control tasks, and enhances control accuracy and response speed.

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Abstract

The application discloses a kind of multi-mode non-disturbance switching control methods for high-altitude test stand system, belong to high-altitude simulation test stand control field;First, the high-altitude test stand model containing air intake system and engine model is established, the initial condition of air intake system is set, and the height, mach number flight mission profile of engine is designed, which is converted into pressure and temperature instruction, and then converted into mass flow instruction of high-altitude test stand system by engine model again. Then, facing the air intake system and exhaust system of high-altitude test stand, respectively design active disturbance rejection control method, non-singular terminal sliding mode control method and fastest feedback control method;Finally, the control task is divided into three modes, according to the characteristics of different modes, the corresponding controller is designed.According to the characteristics of multi-mode and the need of control task, an integrated parallel non-disturbance controller is designed.The application realizes the effect that parallel controller switches in real time according to system mode, has the advantage of non-disturbance smooth switching, and has certain value in engineering.
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