Technical Memorandum of National Aerospace Laboratory
巻
216
ページ
36
発行年
1972-02
抄録（英）
In this paper, are estimated the peak deflection angles and the total injectants required to control an aero-stable solid propellant rocket vehicle (the 1st stage) by SITVC (secondary injection thrust vector control) system. It is desirable to minimize those values under the given constraints; to minimize the aerodynamic load on the body, to minimize the flow rate capacity of the injection valves and to minimize the capacity of the injectants feed system. In order to realize the mini-mum deflection angles, the load relief auto-pilot method is used. A non-gravity-turn nominal trajectory is presented to reduce the effects of wind disturbance. The results of the computer simulation are discussed.
安定板を有する固体ロケットの操舵要求軽減法
naltm00216.pdf
(1.46MB)
