吸气式高超声速飞行器助推分离过程数值仿真

Numerical simulation of booster separation for an air-breathing hypersonic vehicle

针对吸气式高超声速冲压发动机验证性试验特殊的飞行环境和助推分离条件,以某轴对称吸气式高超声速飞行器级间分离问题为具体研究对象,采用非结构网格局部网格重构技术和非定常问题非定常六自由度问题仿真方法,对该复杂构型飞行器助推分离过程进行数值计算。研究得到弱干扰冷态分离状态下飞行器及助推器的运动参数和气动力参数在分离过程中的发展规律。对0.3 s内助推器的位移轨迹进行分析,判断分离方案的可行性,并给出最佳的分离工况条件。

Aiming at the special environment of the air-breathing hypersonic ramjet flight test,especially the booster separation conditions,the multi-body separation of an axisymmetric hypersonic aircraft was studied.Six degrees of freedom solver and local mesh reconstruction based on non-structured mesh method were proposed to simulate the separation process.Results include motion parameters of the booster and the aerodynamic characteristics ranging from 0 ms to 300 ms for the aircraft under the weak perturbance states.Meanwhile,the trajectory curve of separation was demonstrated.Finally,the feasibility of the subsequent scheme was estimated and the optimal conditions for the separation reached requirement of mild interference.