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本文根据航天飞机再入大气轨道的运动方程,求出了升阻比为常值条件下的数值解。着重研究了改变升阻比和再入角对再入轨道的影响。并将精确数值解与近似解进行比较。此外,文中还估算了作用于航天飞机的最大热流。
Based on the equation of motion of the space shuttle reentrying into the atmosphere orbit, a numerical solution of the lift-drag ratio is obtained. Emphasis is placed on the effect of changing the lift-drag ratio and reentry angle on reentry orbit. The exact numerical solution is compared with the approximate solution. In addition, the article also estimated the maximum heat flow acting on the space shuttle.