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中文摘要：
为了对火星进入阶段火星进入动态方程的不确定性的传播规律的研究，提出了一种分析的初始状态的不确定性和不确定性因素对状态轨迹的系统状态的影响的一种改进方法。将该方法应用于一个美国宇航局火星探测任务的入口相当，仿真结果与Monte Carlo方法一致，尤其是飞行路径角模拟至少达到92%。研究发现，改进后的方法不仅可以预测的飞行轨迹角模拟和大的应用范围from-0.1degree至少92%到0.1degree高精度的不确定性的传播规律，采用局部线性化方法相比，也节省了几个小时，相对于蒙特卡罗方法。
英文摘要：
In order to research the uncertainty propagation laws of Mars entry dynamic equations for the Mars entry phase,an improved method was presented for analyzing the effect of the initial state uncertainties and uncertainty factor on the system state in the state trajectories.When applying the method to the entry phase of one of the NASA Mars exploration missions,the simulation results agreed well with the Monte Carlo method,especially the flight path angle simulation at least reaching 92%.It is found that the improved method can not only predict the uncertainty propagation laws with high accuracy of at least 92%in flight path angle simulation and large application scope from-0.1degree to 0.1degree,compared with local linearization method,but also save several hours relative to Monte Carlo method.
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