To accomplish accurate injection, the attitude control system of launch vehicle must precisely control the attitude angles. However, the attitude control problem for launch vehicle is challenging because of the elastic properties. To improve the attitude control performance, a new attitude controller design method is developed based on parameter optimization. First, the controller model is established, which consists of a PID controller designed for the rigid properties and a high-order filter designed for elastic stability. Then, controller parameters are optimized through ALM and simplex method. Simulation results show that the performance of optimized controller is substantially enhanced compared with the original controller.
Attitude controller design for launch vehicle based on parameter optimization
2016-08-01
280941 byte
Conference paper
Electronic Resource
English
Launch vehicle attitude control
NTRS | 1975
Control of Attitude Trajectory of Launch Vehicle Using Optimal LQR-Based PID Controller
Springer Verlag | 2024
|NOVEL ATTITUDE CONTROL DESIGN OF SPACE LAUNCH VEHICLE
TIBKAT | 2021
|