CAJ | 학술논문

可展开的软着陆机构是月球探测器的重要组成部分.以带间隙的多体系统动力学理论为基础,针对一型采用四支撑悬臂式软着陆机构的月球探测器在ADAMS中建立了虚拟样机模型,分别就主着陆腿系统结构柔性,主着陆腿与基体连接间隙,展开驱动力及探测器自旋等因素对软着陆机构展开过程的影响进行了仿真分析.结果表明,在机构展开锁定瞬间由于结构柔性会产生难以衰减的振动,而间隙在一定程度上有利于该振动衰减.展开驱动力越大,展开越快,锁定激振振幅越大,但由展开进入稳定状态所需总时间可更短.探测器自旋则有助于机构的展开,但自旋速度较高时对结构振动有明显影响.该结果可为软着陆机构展开方案的设计提供帮助.
가전개적연착륙궤구시월구탐측기적중요조성부분.이대간극적다체계통동역학이론위기출,침대일형채용사지탱현비식연착륙궤구적월구탐측기재ADAMS중건립료허의양궤모형,분별취주착륙퇴계통결구유성,주착륙퇴여기체련접간극,전개구동력급탐측기자선등인소대연착륙궤구전개과정적영향진행료방진분석.결과표명,재궤구전개쇄정순간유우결구유성회산생난이쇠감적진동,이간극재일정정도상유리우해진동쇠감.전개구동력월대,전개월쾌,쇄정격진진폭월대,단유전개진입은정상태소수총시간가경단.탐측기자선칙유조우궤구적전개,단자선속도교고시대결구진동유명현영향.해결과가위연착륙궤구전개방안적설계제공방조.
Deployable landing gear is an important part of Lunar lander. The ADAMS model of a Lunar lander with four strut groups was built in this paper. The effects of the flexibility of primary strut, joint clearance, deploying driver force and the spin of mainbody on the dynamic character of landing gear during deploying were analyzed. The simulation results show that the vibration excitated on the lock instantaneousness is difficult to be attenuated because of the flexibility of primary strut. And joint clearance is helpful to attenuation this vibration in a certain extent. The deploy velocity of landing gear increase with the augment of deploying driver force, and the swing of the vibration excitated on the lock instantaneousness also increase. But the whole time of deploying can be shorter. If the mainbody spins, the landing gear will deploy faster. The effects of spin on the vibration will increase with the angle velocity increasing. These results are useful to the design of deploy projects.