摘要
针对一种升力式再入飞行器———通用航空飞行器进行全球攻击时离轨推力的控制和相应的下降轨道特点,对其再入角的选择等关键技术进行了深入分析,最终得到了依据远地点半径和可施加的Δv的范围来确定最优离轨推力角和下降椭圆轨道的有工程意义的结论。在此基础上进一步分析了切线制动和非切线制动的再入轨道特点,同时依据已知条件得到了再入角的最佳控制范围。所得结论亦可用于一般升力式再入飞行器初步轨迹的设计。
In this paper, de-orbit thrust operations, descending orbit characteristics and the choice of reentry angle for the common aero vehicle that is a new weapon delivery platform are studied. The method to make sure the optimal thrust angle α according as apogee radius and accepted scope of △v is acquired. On this condition, reentry orbits for tangential and non-tangential retro are investigated. Finally, the optimal operation scope of the reentry angle is studied. These conclusions may be used in preliminary design phase of generic lifting reentry vehicles.
出处
《飞行力学》
CSCD
北大核心
2006年第2期35-39,共5页
Flight Dynamics
关键词
通用航空飞行器
离轨控制
再入角
common aero vehicle
de-orbit operation
reentry angle
