电弧等离子体风洞是一种能产生高温、高压的热源设备，用于在地面模拟航天用再入式飞行器的气动环境。
Plasma wind tunnel is equipment which can generate high-temperature and high-pressure to simulate the air environment of aerospace reentry vehicles.
轨迹优化是新型高超声速滑翔式再入飞行器方案设计的关键技术之一。
Trajectory optimization is one of the key factors in scheme planning of the new type of hypersonic gliding reentry vehicles.
分析了沿最优轨迹飞行的物理原因和基本迎角控制规律，可为滑翔式再入飞行器的最优轨迹方案设计提供依据。
The physical causation of the optimal trajectory and the corresponding angleofattack profile are presented. It is a good reference for schematic trajectory design for gliding type reentry vehicles.
长期以来返回式飞行器为承受再入气动载荷和着陆冲击，采用具有防热层的刚性飞行器壳体，导致返回舱的质量和外形大于有效载荷的数倍。
A rigid aeroshell for aerodynamic deceleration and landing impact will result in mass and sizes of the re_entry vehicles exceeding several times those of the payload bus.
航天飞行器在再入大气过程中会受到严重的气动加热。返回式卫星、飞船返回舱及航天飞机等采取高空机动再入，再入时间长，其峰值加热过程一般在60-90千米高空。
Spacevehicles such as spacecraft and space shuttle are subjected to severe aerothermal environment with the peak heating at height of 60~90km while they maneuver to reentry the earth's atmosphere.
弹道式飞行器再入时，常常要求在规定高度上发出开伞信号，过载延时控制方法误差太大，不能满足精度要求。
The opening parachute signal is required to sent on the fixed height when the vehicle reentry. The height controlled error through axis apparent acceleration can not meet the required precision.
欧洲再入大气层试验飞行器是简单的不载人座舱式飞行器。它将随“阿里安5”火箭的第二次鉴定飞行发射升空。
The second qualification flight of Ariane - 5(V502) will carry an atmospheric Reentry Demonstrator(ARD) which is a simple unmanned capsule - type vehicle.
欧洲再入大气层试验飞行器是简单的不载人座舱式飞行器。它将随“阿里安5”火箭的第二次鉴定飞行发射升空。
The second qualification flight of Ariane - 5(V502) will carry an atmospheric Reentry Demonstrator(ARD) which is a simple unmanned capsule - type vehicle.
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