火星探测活动是当前深空探测领域发展的热点，火星探测着陆器进入过程的气动布局问题是火星探测器设计的关键之一。根据国外火星探测器气动布局及地球轨道再入返回舱气动布局，从大气环境和布局形式两个方面出发研究火星探测器的主要气动特点，基于工程算法讨论了探测器所处大气环境及其布局形式对其高超声速升阻特性、配平特性及静稳定性的影响规律。大气环境分析表明，在高超声速进入条件下，火星大气热力学性质的改变，会改变高超声速气动力的大小和分布，会增加探测器的升阻力系数，对探测器的升阻比和配平特性影响很小，略提高飞行静稳定性。布局形式分析认为，球锥布局的防热大底较球冠布局具有更大的气动阻力，有利于着陆器减速，且较小的法向偏移量可实现足够的配平需求；球锥布局俯仰静稳定度对轴向的敏感度较低，也是探测器从气动考虑选用球锥布局的原因。相关研究结论可为火星探测着陆器的气动布局设计提供理论参考和技术支持。%The Mars exploration mission is a hot spot in deep space exploration, and the aerodynam-ic configuration study is one of the key issues for Mars probe design.Based on the deep understand-ing of the aerodynamic configuration of both Mars probe and Earth return capsule, the main aerody-namic characteristics of Mars probe were investigated in the aspects of atmosphere environment and configuration pattern.The influences of atmosphere environment and configuration pattern on the hy-personic lift and drag characteristics, trimming characteristics and static stability were then discussed by means of engineering computation.Calculated results showed that the changes of atmosphere may alter gas thermal properties and hypersonic surface pressure.For the Martian gas, both the lift and drag coefficients increased, and thus the lift-to-drag ratio and trimming characteristics held, and there exited much stable domain compared with the air.For the configuration pattern, the sphere-conic heatshield will make bigger drag force than the spherical one, which is beneficial to descend-ing deceleration.Moreover, a small radial offset will meet the trimming requirement for the given an-gle of attack and the sphere-conic capsule is not so sensitive for static pitch stability in the axial di-rection, both of which are the reasons why to use the sphere-conic heatshield in the successful mis-sions.The aerodynamics prediction technique and the aerodynamic analysis method can be the foun-dation of future Mars probe design.
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