自备动力逃逸载人飞船上升段气动特性研究  

Research on Aerodynamic Characteristic for Self-propulsion-escape Manned Spacecraft During Launch Phase

作　　者：陈鑫[1] 左光[1] 屈峰[1] 陈冲[1] 

机构地区：[1]中国空间技术研究院载人航天总体部,北京100094

出　　处：《航天器工程》2018年第1期45-51,共7页Spacecraft Engineering

基　　金：国家重大科技专项工程

摘　　要：自备动力逃逸技术是载人飞船重要的发展方向之一,能提升载人飞船发射段的安全性。文章对自备动力逃逸载人飞船上升段的气动特性开展研究,利用气动数值模拟方法对上升段逃逸全过程进行仿真,完成自逃逸上升段静态气动特性分析、两舱分离气动特性研究和上升段气动加热分析。研究结果表明:返回舱与推进舱能否安全分离受分离时刻的气动干扰影响较大,配置稳定翼在低空情况下可显著改善载人飞船的静稳定性。上述研究结果可为我国新一代载人飞船逃逸系统的方案设计提供参考。Self-propulsion-escape technology is one of the important development directions for manned spacecraft,which can improve the safety during launch phase.Based on the CFD(computational fluid dynamic)numerical simulation,the aerodynamic characteristics of the manned spacecraft escape process during launch phase are investigated,which includes static characteristic,separate characteristic,and aerodynamic heating characteristic.The research results show that the safety of the separate process for the reentry module and propulsion module is impacted on the aerodynamic disturbance characteristic and the empennage has a significant impact on the stability for the manned spacecraft in the low altitude.The results can provide a reference for the conceptual design of the new manned spacecraft in China.

关 键 词：载人飞船 自备动力逃逸 上升段 气动特性 分离安全 

分 类 号：V423.5[航空宇航科学与技术—飞行器设计]