CAJ | 학술논문

将磁流变阻尼器应用到月球着陆器着陆机构中,进行减震与缓冲.考虑到着陆初始姿态角的不定和月面斜角的未知,建立起着陆器软着陆动力学模型.基于磁流变液在高速流与长冲程时的阻尼特性,分析了磁流变阻尼器的力学特性.应用安全角面的概念定义安全着陆所要求的着陆初始姿态角与月面斜角之间的关系,建立状态跳跃控制策略,实现软着陆半主动控制.通过与某型被动控制的着陆器进行对比分析,研究了半主动控制.研究结果表明:当允许的最大加速度响应不超过8g时,磁流变半主动状态跳跃控制的安全角面为理想安全角面的0.977 4,是被动控制安全角面的4.2倍,最大加速度变化的相对标准差为被动控制的0.59;而且当着陆初始姿态角以及月面斜角很大时,月球着陆器姿态角变化少,保证月球着陆器平稳着陆.
장자류변조니기응용도월구착륙기착륙궤구중,진행감진여완충.고필도착륙초시자태각적불정화월면사각적미지,건립기착륙기연착륙동역학모형.기우자류변액재고속류여장충정시적조니특성,분석료자류변조니기적역학특성.응용안전각면적개념정의안전착륙소요구적착륙초시자태각여월면사각지간적관계,건립상태도약공제책략,실현연착륙반주동공제.통과여모형피동공제적착륙기진행대비분석,연구료반주동공제.연구결과표명:당윤허적최대가속도향응불초과8g시,자류변반주동상태도약공제적안전각면위이상안전각면적0.977 4,시피동공제안전각면적4.2배,최대가속도변화적상대표준차위피동공제적0.59;이차당착륙초시자태각이급월면사각흔대시,월구착륙기자태각변화소,보증월구착륙기평은착륙.
Magnetorheological (MR) damper is applied to lunar landing system for shock absorption and vibra-tion reduction. In consideration of the uncertain initial landing attitude angle of lunar lander and the unknown slope of lunar surface, a soft landing dynamic model is built The mechanical property of MR damper is ana-lyzed in view of the damping characteristics of MR fluid with high-speed and long-stroke. The concept of safe angle scope is used to define the relationship between initial landing attitude angle and lunar slope, and a state-jump algorithm is developed to realize semi-active control during soft landing. Compared with a certain type of passive lunar lander, the semi-active control is analyzed. Numerical results show that the safe angle scope of semi-active state-jump control for MR is 0. 977 4 times that of the perfect one, and 4.2 times that of the pas-sive one when the allowable peak acceleration response does not exceed 8g. It is found that the relative stand-ard deviation of the maximal acceleration variation is 0.59 times that of the passive one. Furthermore, when the initial landing attitude angle and lunar slope are very large, the attitude angle of lunar lander changes little, which ensures a smooth landing of the lunar lander.