We put stress upon investigating the effect of changing lift drag ratio and reentryAngle 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。
2
Using numerical calculation, optimal roll program, the ratio of lift and drag, reentryAngle 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。
3
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.