We put stress upon investigating the effect of changing lift drag ratio and reentry Angle on reentry orbit.
着重研究了改变升阻比和再入角对再入轨道的影响。
Using numerical calculation, optimal roll program, the ratio of lift and drag, reentry Angle and reentry time of spacecraft are gotten.
通过数字计算，得到飞船的最优滚转程序、升阻比、再入角和再入终端时间。
The mathematical model of reentry maneuvering trajectory is established. The fitting expression of aerodynamic coefficient function on velocity, attack of Angle and altitude is presented.
建立了再入机动弹道数学模型，给出了气动力系数为速度、迎角、高度的函数拟合式，进行了最佳再入机动弹道设计和仿真计算。
On the reasonable assumption of match AOA (Angle of attack) flight, the mathematics simulation model of the reentry flight of a spaceship is formulated in this paper.
在配平迎角飞行的合理假设下，建立了描述载人飞船再入飞行段弹道的数学仿真模型。
This paper gives the method that is effective in decreasing the roll Angle and roll rate in roll channel of the reentry vehicle.
针对再入飞行器滚动通道产生较大的滚动角及滚动角速率，给出了一种能够有效地减小滚动角和滚动角速率的方法。
This paper gives the method that is effective in decreasing the roll Angle and roll rate in roll channel of the reentry vehicle.
针对再入飞行器滚动通道产生较大的滚动角及滚动角速率，给出了一种能够有效地减小滚动角和滚动角速率的方法。
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