摘要
着陆缓冲机构是着陆器借以实现安全、稳定软着陆的一种重要装置。鉴于着陆初始条件的多样性,系统级缓冲性能需在有限的试验工况中进行充分验证。文章基于“阿波罗”登月舱3类相关试验方法,提出了一种无需额外设计和加工试验件,无需模拟其他重力场,在地球重力场下的全尺寸模型试验方法。在对各着陆初始条件大量组合工况的仿真结果统计分析后,给出了试验验证工况的确定原则;明确了试验实施过程中的质量配比原则、地球重力场对试验的影响、地貌特征模拟方法及试验测量参数与数据处理要求。该方法对于后续深空探测以及载人登月着陆缓冲机构综合缓冲性能的试验验证具有指导意义。
The landing gear system is an important mechanism for the safe and stable landing of a lunar lander.In view of the variety of the initial conditions upon landing,the vehicle-level attenuation characteristics should be sufficiently verified under limited test conditions.Based on the experience of three kinds of related experiments during the Apollo era,we propose a test method employing a full-scale model in the Earth gravity field,without the need of designing or processing the test sample,or simulating other gravity field.The basic scheme for determine the test conditions can be formulated after statistical analysis of massive simulation results considering all main factors at the landing moment.The following aspects are discussed for the implementation of the experiment:the balancing of mass properties,the influence of the Earth gravity during the impact procedure,the simulation of topographic characteristics,the measuring parameters and the data processing requirement.The method provides a guidance to the experimental verification of the landing gear system,especially of its integrated attenuation properties.
作者
齐跃
李委托
朱汪
杨建中
曾福明
满剑锋
QI Yue;LI Weituo;ZHU Wang;YANG Jianzhong;ZENG Fuming;MAN Jianfeng(Beijing Institute of Spacecraft System Engineering,Beijing 100094,China)
出处
《航天器环境工程》
2020年第6期576-581,共6页
Spacecraft Environment Engineering
基金
国家重大科技专项工程。
关键词
月球着陆器
着陆缓冲机构
缓冲
着陆试验
着陆冲击
lunar lander
landing gear mechanism
attenuation
landing test
landing impact
作者简介
齐跃(1987-),女,硕士学位,主要从事航天器机构设计与分析的研究。E-mail:laoqifighting@126.com。
