Abstract
The investigation of the thrust control system is aroused by the need for propulsion system of ducted rockets. Firstly the dynamic mathematical models of gas flow regulating system, pneumatic servo system and ducted rocket engine were established and analyzed. Then, to conquer the discussed problems of thrust control, the idea of information fusion was proposed to construct a new feedback variable. With this fused feedback variable, the thrust control system was designed. According to the simulation results, the introduction of the new fused feedback variable is valid in eliminating the contradiction between rapid response and stability for the thrust control system of ducted rockets.
| Original language | English |
|---|---|
| Pages (from-to) | 86-95 |
| Number of pages | 10 |
| Journal | Acta Astronautica |
| Volume | 69 |
| Issue number | 1-2 |
| DOIs | |
| State | Published - Jul 2011 |
Keywords
- Ducted rocket
- Information fusion
- Mathematical modeling
- Thrust cosntrol
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