嫦娥探测器分段渐倾转移机构设计

马超; 孙京; 刘宾; 李新立; 张大伟; 姜生元; 季节

doi:10.7527/S1000-6893.2019.23014

航空学报 >

2019 , Vol. 40 >Issue 10: 223014 - 223014

DOI: https://doi.org/10.7527/S1000-6893.2019.23014

固体力学与飞行器总体设计

嫦娥探测器分段渐倾转移机构设计

马超 ,
孙京 ,
刘宾 ,
李新立 ,
张大伟 ,
姜生元 ,
季节

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1. 北京空间飞行器总体设计部空间智能机器人系统技术与应用北京市重点实验室, 北京 100094;
2. 哈尔滨工业大学机器人技术与系统国家重点实验室, 哈尔滨 150080

收稿日期: 2019-03-19

修回日期: 2019-04-04

网络出版日期: 2019-07-15

基金资助

国家"973"计划（2013CB733000）；国家自然科学基金（11772102）

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Design of rover transfer mechanism for Chang'e probe

MA Chao ,
SUN Jing ,
LIU Bin ,
LI Xinli ,
ZHANG Dawei ,
JIANG Shengyuan ,
JI Jie

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1. Beijing Key Laboratory of Intelligent Space Robotic Systems Technology and Applications, Beijing Institute of Spacecraft System Engineering, Beijing 100094, China;
2. State Key Laboratory for Robotics and System, Harbin Institute of Technology, Harbin 150080, China

Received date: 2019-03-19

Revised date: 2019-04-04

Online published: 2019-07-15

Supported by

National Basic Research Program of China (2013CB733000);National Natural Science Foundation of China (11772102)

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摘要

巡视探测器转移机构是在地外空间环境执行巡视探测器转移释放任务的空间机构。与美国、苏联转移任务不同，中国探月工程（CLEP）二期着陆器采用腿式着陆缓冲机构及巡视器顶部搭载方式，转移任务沿着陆器周向展开距离及巡视器释放高度增加，转移难度增大。在设计阶段，转移机构是否符合探测任务严苛的工程约束及设计指标；在执行阶段，转移机构能否在月面非确知环境下正常展开、转移过程是否稳定可靠，是嫦娥探测器顺利完成探测任务的关键。为保障月球后续任务及火星探测任务中转移机构的设计需要，根据巡视器转移系统特点，以探月二期工程中首次探索并成功自主设计定型的嫦娥分段渐倾转移机构为例，对巡视器转移系统的组成、任务需求及设计约束予以阐述，并结合参研人员经验，对机构研制方案的选取、关键环节设计、工程状态及任务验证情况进行说明，以为后续工作及相关工程提供参考。

关键词： 探月二期; 嫦娥三号; 嫦娥四号; 转移机构; 机构设计; 任务验证

本文引用格式

马超 , 孙京 , 刘宾 , 李新立 , 张大伟 , 姜生元 , 季节 . 嫦娥探测器分段渐倾转移机构设计[J]. 航空学报, 2019 , 40(10) : 223014 -223014 . DOI: 10.7527/S1000-6893.2019.23014

Abstract

The rover transfer mechanism is a space mechanism that transfers and releases the rover in the extraterrestrial space environment. Different from the former transfer tasks of the United States and the Soviet Union, in the second phase of the China's Lunar Exploration Project (CLEP), the landing-leg buffer mechanism is used for the lander of the incorporates spacecraft and the rover is mounted on top of the lander. The transfer distance of the rover along the circumferential direction of the lander and the release height of the rover dramatically increase the difficulty of the transfer task. The keys to the completion of the exploration mission include the transfer mechanism meeting the strict engineering constraints and design indexes of the mission in the design phase and high reliability of transferring the rover in the uncertain lunar surface environment in the execution phase. This paper provides the research and design processes of the Chang'e transfer mechanism in the second stage mission of the CLEP. Based on the characteristics of the rover transfer system of the Chang'e probe, the compositions, requirements, and constraints of the design are introduced. In addition, drawing on the experience of the participants, the proposal selections, key design points, engineering status, and verifications of the transfer mechanism are described, providing reference and support for associated projects in the following Lunar and Mars exploration missions.

Key words： Lunar Exploration Phase II; Chang'e-3; Chang'e-4; transfer mechanism; mechanism design; mission verification

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