First Aerodynamics Division, National Aerospace Laboratory(NAL)
First Aerodynamics Division, National Aerospace Laboratory(NAL)
First Aerodynamics Division, National Aerospace Laboratory(NAL)
National Space Development Agency of Japan(NASDA)
National Space Development Agency of Japan(NASDA)
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-793
巻
793
ページ
48
発行年
1983-12
抄録（英）
A wind tunnel investigation of a roll-controllable two-stage rocket model was made at free-stream Mach numbers from 0.5 to 2.5. The model has ailerons on front-fins to generate rolling moment and free-rolling tail-fins to eliminate the effect of the induced rolling moment on tail-fins. The results confirmed the feasibility of this type of roll-controllable rocket. The characteristics of the induced rolling moment were investigated by tests of a model with fixed tail-fins. The characteristics were compared with theoretical results based on the strip-theory. Values of roll-damping coefficient of the tail-fins were obtained by analysing their rolling rate. The effect of the free-rolling tail-fins on other aerodynamic characteristics, such as normal force coefficient, center of pressure and axial force coefficient, were also evaluated. A computer simulation of the rolling motion of the TT-500A rocket, which has a similar configuration to the present model, was made based on the results of the present study, whose results agreed well with the flight-data.
小型二段式ロケットの前後翼のロール干渉とロール制御に関する研究
naltr00793.pdf
(2.74MB)
