Simulation study of control system for flexible launch vehicle
Abstract
Digital simulation in the time domain is used in design of a closed-loop attitude control system for a multistage launch vehicle with solid boosters and stabilizing fins; the booster body structure is assumed to be flexible with very low natural structural damping. Both bang bang and proportional control systems are considered, and the study is carried out for maximum dynamic pressure conditions.
- Publication:
-
Aeronautical Society India Journal
- Pub Date:
- November 1975
- Bibcode:
- 1975AeSIJ..27..164D
- Keywords:
-
- Aeroelasticity;
- Attitude Control;
- Control Simulation;
- Flexible Bodies;
- Launch Vehicle Configurations;
- Off-On Control;
- Proportional Control;
- Automatic Flight Control;
- Bending Vibration;
- Digital Simulation;
- Dynamic Stability;
- Feedback Control;
- Rocket Flight;
- Launch Vehicles and Space Vehicles