Kakuda Branch Office, National Aerospace Laboratory(NAL)
Kakuda Branch Office, National Aerospace Laboratory(NAL)
Kakuda Branch Office, National Aerospace Laboratory(NAL)
Kakuda Branch Office, National Aerospace Laboratory(NAL)
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory(NAL)
雑誌名
航空宇宙技術研究所報告
雑誌名(英)
Technical Report of National Aerospace Laboratory TR-409
巻
409
ページ
13
発行年
1975-02
抄録（英）
This paper presents an experimental result of secondary injection thrust vector control and an approximate analysis of estimating the control forces produced by liquid injection. The experiment was conducted with the solid rocket motors of about 400kg thrust. The control forces produced by the secondary injection were measured by a four-component test stand. The nozzle was conical, of which expansion ratio was 1:8.1. Fluids of various kinds were used as the injectants, i.e.hydrogen peroxide(90％wt), decomposed gas of hydrogen peroxide(90％wt), Freon 114B2 and strontium perchlorate(70％wt). The effects of injection location and the injectant flow rate on the produced control forces have been well illustrated by the experiment. An approximate analytical model to predict the disturbance induced by secondary liquid injection has been presented also. The estimated control forces based on the flow model are compared with the experimental results for cases of hydrogen peroxide and Freon 114B2.
二次噴射による固体ロケットの推力方向制御の研究
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