考虑进气约束的高超声速飞行器预定性能控制

丁一波; 岳晓奎; 代洪华; 崔乃刚

doi:10.7527/S1000-6893.2020.24838

航空学报 >

2021 , Vol. 42 >Issue 11: 524838 - 524838

DOI: https://doi.org/10.7527/S1000-6893.2020.24838

论文

考虑进气约束的高超声速飞行器预定性能控制

丁一波 ,
岳晓奎 ,
代洪华 ,
崔乃刚

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1. 西北工业大学航天学院, 西安 710072;
2. 哈尔滨工业大学航天学院, 哈尔滨 150001

收稿日期: 2020-10-05

修回日期: 2020-11-15

网络出版日期: 2020-12-25

基金资助

国家自然科学基金（12102343，U2013206）；上海航天科技创新基金（SAST2020-072）；中央高效基本科研业务费专项资金（D5000210833）

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Prescribed performance controller for flexible air-breathing hypersonic vehicle with considering inlet airflow constraint

DING Yibo ,
YUE Xiaokui ,
DAI Honghua ,
CUI Naigang

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1. School of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China;
2. School of Astronautics, Harbin Institute of Technology, Harbin 150001, China

Received date: 2020-10-05

Revised date: 2020-11-15

Online published: 2020-12-25

Supported by

National Natural Science Foundation of China (12102343, U2013206); Shanghai Space Science and Tehnology Innovation Fund (SAST2020-072); the Fundamental Research Funds for the Central Universities (D5000210833)

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摘要

针对高超声速飞行器跟踪误差瞬态性能约束与发动机进气条件约束问题，提出约束预定性能控制方案。首先，设计新型设定时间性能函数用于限定跟踪误差的瞬态与稳态性能。相比传统方法，新型方案可保证性能函数在设定时刻精确收敛至稳态值，同时可灵活调整函数初始收敛速率，避免控制饱和。其次，将速度与高度受约束跟踪误差进行无约束转换，通过控制转化误差有界满足原始跟踪误差的预定性能约束。在高度子系统中，通过结合预定性能控制限定攻角变化范围，能够满足发动机进气需求。最后，以考虑参数摄动的吸气式高超声速飞行器为对象执行对比仿真，结果表明所提方法能够有效满足跟踪误差的性能约束与发动机进气约束。

关键词： 吸气式高超声速飞行器; 有限时间控制; 进气约束; 瞬态性能约束; 设定时间性能函数; 预定性能控制

本文引用格式

丁一波 , 岳晓奎 , 代洪华 , 崔乃刚 . 考虑进气约束的高超声速飞行器预定性能控制[J]. 航空学报, 2021 , 42(11) : 524838 -524838 . DOI: 10.7527/S1000-6893.2020.24838

Abstract

To solve transient performance constraints of tracking errors and inlet airflow constraint of scramjet for air-breathing hypersonic vehicle, a constrained prescribed performance controller is proposed. Firstly, a novel setting-time performance function is presented to limit the transient and steady state performance of tracking errors. Compared with traditional methods, the novel function can guarantee that the performance function converges to the steady state precisely at the setting time. Meanwhile, the initial convergence rate of the performance function can be adjusted freely. Then, velocity and height tracking errors are unconstrained via coordinate transformation. By means of controlling the errors of transformation bounded, the prescribed performance constraints of original tracking errors can be satisfied. In the height subsystem, by combining prescribed performance control to limit the range of angle of attack, the inlet airflow requirements of scramjet can be satisfied. Finally, comparative simulations on the air-breathing hypersonic vehicle with parametric uncertainties are performed to demonstrate that the method presented can effectively satisfy the performance constraints of tracking errors and inlet airflow constraint of scramjet.

Key words： air-breathing hypersonic vehicle; finite-time control; inlet airflow constraint; transient performance constraint; setting-time performance function; prescribed performance control

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