Re-entry vehicle performance analysis under the control of lateral jet

S. P. Sanaka, R.K. Sharma, G. V. Ramana Murty, K. Durga Rao
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Abstract

Lateral jets are used to control the missiles and re-entry vehicles at high altitudes. The objective of the research paper is to investigate the effect of lateral jet interaction with the external flow on a blunted nose cone re-entry vehicle configuration and its flight speed. Structured mesh is used for the simulations, and the computational analysis is carried out by Ansys Fluent solver. The simulation results are validated, and the same methodology used for the parametric analysis. Simulations have been carried out at an external flow Mach number 6, 8.1, 12 and 16 at five degree angle-of-attack for jet-off and jet-on conditions. At 8.1 Mach number, the normal force coefficient is decreased by 45.6% due to jet interaction. The lateral jet interaction effectively reduces the nose down pitching moment. At 8.1 Mach number, the pitching moment coefficient was reduced by 48% with the jet-on condition compared to the jet-off condition.
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侧向射流控制下的再入飞行器性能分析
侧向喷气机用于控制导弹和高空再入飞行器。本文的目的是研究侧向射流与外部气流的相互作用对钝头锥再入飞行器结构及其飞行速度的影响。采用结构化网格进行仿真,采用Ansys Fluent求解器进行计算分析。对仿真结果进行了验证,并采用相同的方法进行了参数分析。在5度攻角条件下,分别进行了6、8.1、12和16马赫数的外流仿真。在8.1马赫数时,由于射流的相互作用,法向力系数降低了45.6%。侧向射流的相互作用有效地减小了机头向下的俯仰力矩。在8.1马赫数时,启动状态下的俯仰力矩系数比关闭状态降低了48%。
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