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弹箭与制导学报 >

2010 , Vol. 30 >Issue 5: 66 - 68

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2010.05.067

导弹与制导技术

高超声速飞行器自抗扰PID 姿态控制

  • 齐乃明 ,
  • 宋志国 ,
  • 秦昌茂
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  • 哈尔滨工业大学航天工程系,哈尔滨 150001

宋志国(1987-),男,黑龙江人,硕士研究生,研究方向:高超声速飞行器制导与控制。

收稿日期: 2010-01-18

  网络出版日期: 2025-05-28

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ADRC PID Attitude Control of a Hypersonic Flight Vehicle

  • QI Naiming ,
  • SONG Zhiguo ,
  • QIN Changmao
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  • Department of Astronautics Engineering, Harbin Institute of Technology, Harbin 150001,China

Received date: 2010-01-18

  Online published: 2025-05-28

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摘要

针对高超声速飞行器模型非线性、气动参数变化剧烈的特点,运用自抗扰技术中的跟踪微分器,设计了自抗扰PID控制器,实现了对高超声速飞行器俯仰通道的姿态控制。仿真结果表明,通过两个跟踪微分器构造的自抗扰PID控制器对于高超声速飞行器这样复杂的模型有很好的控制能力,并且有很好的滤波性能和鲁棒性。

关键词： 高超声速飞行器; 跟踪微分器; 自抗扰PID; 滤波

本文引用格式

齐乃明 , 宋志国 , 秦昌茂 . 高超声速飞行器自抗扰PID 姿态控制[J]. 弹箭与制导学报, 2010 , 30(5) : 66 -68 . DOI: 10.15892/j.cnki.djzdxb.2010.05.067

Abstract

The tracking differentiator (TD) of auto-disturbance rejection control (ADRC) was used to design ADRC PID controller considering the hypersonic vehicle model is non-linear and aerodynamic parameters change rapidly. Attitude control of hypersonic vehicle pitch channel was achieved. Simulation results show that ADRC PID controller constructed by two TD can well controls hypersonic vehicle such a complex model, and has good filter performance and robustness.

Key words： hypersonic flight vehicle; tracking differentiator; ADRC PID controller; filter

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参考文献

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