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首页> 外文期刊>Journal of Spacecraft and Rockets >Guidance, Navigation, and Control System Performance Trades for Mars Pinpoint Landing
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Guidance, Navigation, and Control System Performance Trades for Mars Pinpoint Landing

机译：火星精确着陆的制导，导航和控制系统性能交易

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Landing site selection is a compromise between safety concerns associated with the site’s terrain and scientificninterest. Therefore, technologies enabling pinpoint landing performance (sub-100-m accuracies) on the surface ofnMars are of interest to increase the number of accessible sites for in situ research, as well as allow placement ofnvehicles nearby prepositioned assets. A survey of the performance of guidance, navigation, and control technologiesnthat could allow pinpoint landing to occur at Mars was performed. This assessment has shown that negligiblenpropellant mass fraction benefits are seen for reducing the three-sigma position dispersion at the end of thenhypersonic guidance phase (parachute deployment) below approximately 3 km. Four different propulsive terminalndescent guidance algorithms were examined. Of these four, a near propellant-optimal analytic guidance law showednpromise for the conceptual design of pinpoint landing vehicles. The existence of a propellant optimumwith regard tonthe initiation time of the propulsive terminal descentwas shown to exist for various flight conditions. Subsonic guidednparachutes were shown to provide marginal performance benefits, due to the timeline associated with descentnthrough the thinMars atmosphere. This investigation also demonstrates that navigation is a limiting technology fornMars pinpoint landing, with landed performance being largely driven by navigation sensor and map tie accuracy.
机译：选择登陆站点是在与站点地形相关的安全问题和科学兴趣之间做出折衷的选择。因此，关注能够在nMars表面精确定位降落性能（精确度低于100-m）的技术，以增加用于现场研究的可访问站点的数量，并允许将车辆放置在预定资产附近。对制导，导航和控制技术的性能进行了调查，n可以使精确的着陆发生在火星上。该评估表明，可以忽略不计的推进剂质量分数有益于在人身引导阶段（降落伞部署）结束时将三西格玛位置分散降低到大约3 km以下。研究了四种不同的末期推进制导算法。在这四个之中，接近推进剂-最佳的分析制导律对精确的登陆车的概念设计没有承诺。相对于各种飞行条件而言，存在关于推进末下降的起始时间的最佳推进剂的存在。由于与通过稀薄的火星大气层下降有关的时间表，亚音速制导的降落伞显示出可提供边际效益。这项研究还表明，导航是nMars精确着陆的一项限制技术，着陆性能很大程度上取决于导航传感器和地图的精确度。

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