摘要
针对某型可回收火箭验证机整流罩气动外形优化问题,提出一种CAD/CFD集成仿真优化方法.首先,针对原始外形开展了气动特性计算,揭示了整流罩对全箭气动性能的影响规律.随后,利用FloEFD+HEEDS联合优化方法,以最大法向力作为优化目标,开展了 128个不同整流罩外形的气动性能仿真.结果表明,不合适的整流罩外形会导致小迎角条件下法向力、俯仰力矩系数线性度变差.正迎角条件下,整流罩上下表面的压差引起了负法向力和抬头力矩,从而抵消了箭体产生的部分法向力和俯仰力矩.通过自动寻优算法,得到了满足当前尺寸约束条件下的可回收火箭验证机返回时整流罩最优气动外形,优化后的气动外形法向力系数提升了 8倍.
Abstract
The CAD/CFD integrated simulation method was proposed to optimize the aerodynamic shape of a recoverable rocket fairing.Firstly,the aerodynamic performance simulation of the original shape was carried out.The effect of the fairing on the aerodynamic performance of the rocket was re-vealed.Then,the combined optimization method of FloEFD+HEEDS was used to carry out the aero-dynamic performance simulation of 128 different fairing shapes with the maximum normal force as the optimization objective.The results show that the linearity of the normal force and pitching moment coefficients become worse under the condition of small angle of attack due to the improper fairing shape.Under the condition of positive angle of attack,the pressure difference between the upper and lower surfaces of the fairing causes negative normal force and upward force moment,thus cance-ling out part of the normal force and pitching moment generate by body of the rocket.Through the automatic optimization algorithm,the optimal aerodynamic fairing shape of the reusable demonstra-tion rocket is obtained under the constraint of the current size.The normal force coefficient of the optimized aerodynamic shape is increased by 8 times.
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