临近空间高速飞行器微量气动力试验及计算

针对临近空间大气环境微量气动力风洞试验准确测量需求,研制了微量天平测力系统,实现了微量天平的结构设计和静态校准。采用钝锥简单外形进行试验验证,并对三角翼升力体复杂外形做了探索,结果表明:钝锥外形验证试验中,3次试验时天平各载荷单元的气动数据重复性精度均优于4.8%;探索试验中,三角翼升力体外形采用该风洞目前能达到最低密度状态,试验结果表明:该微量测力天平在极限状态下表现较好。在此基础上,利用数值计算方法对上述外形进行模拟,并将模拟结果与试验结果进行对比,表明数值计算得到的钝锥和三角翼升力体的气动力均与微量天平测力结果吻合较好;对于简单钝锥外形,在其试验条件下,钝锥表面压阻远高于摩阻;对于三角翼升力体外形,其试验条件下环境大气更加稀薄,三角翼表面摩阻占比与压阻相当。

Corrigendum to“Thermal Environment and Aeroheating Mechanism of Protuberances on Mars Entry Capsule”

In the article titled“Thermal Environment and Aeroheating Mechanism of Protuberances on Mars Entry Capsule”[1],there was an error in the author name details.The first name and surname of all authors were transposed.The correct author names are shown below,and they are corrected in the author list.