ADRC PID Attitude Control of a Hypersonic Flight Vehicle

QI  Naiming; SONG  Zhiguo; QIN  Changmao

doi:10.15892/j.cnki.djzdxb.2010.05.067

Journal of Projectiles, Rockets, Missiles and Guidance >

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

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

MISSILES AND GUIDANCE TECHNOLOGY

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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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

Cite this article

QI Naiming , SONG Zhiguo , QIN Changmao . ADRC PID Attitude Control of a Hypersonic Flight Vehicle[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2010 , 30(5) : 66 -68 . DOI: 10.15892/j.cnki.djzdxb.2010.05.067

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