Tuning of Active Disturbance Rejection Attitude Controller for Statically Unstable Launch Vehicle
Author:
Affiliation:
1. Nankai University, 300350 Tianjin, People’s Republic of China
2. Beijing Aerospace Technology Institute, 100074 Beijing, People’s Republic of China
3. University of South Africa, Florida 1710, South Africa
Funder
NRF incentive
Research Fund of Tianjin Key Laboratory of Process Measurement and Control
National Natural Science Foundation of China
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Space and Planetary Science,Aerospace Engineering
Link
https://arc.aiaa.org/doi/pdf/10.2514/1.A33604
Reference6 articles.
1. Tailoring theory to practice in tactical missile control
2. Stability margin-based PD attitude control tuning for unstable flight vehicle
3. PID pitch attitude control for unstable flight vehicle in the presence of actuator delay: Tuning and analysis
4. From PID to Active Disturbance Rejection Control
5. Practical solution to attitude control within wide envelope
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