CAJ | 학술논문

为降低在轨分离冲击载荷对挠性航天器的影响，进行了基于磁流变阻尼缓冲器( Magneto-rheological)的减振研究，将磁流变阻尼缓冲器应用于航天器冲击减振。基于有限元和Lagrange方法，建立了发生大范围运动的挠性航天器状态模型，采用趋近律滑模控制算法控制阻尼器输出，并提出一种二维模糊控制方法控制趋近系数来提高系统的动态品质，同时抑制趋近律中切换项导致的抖振现象。数值计算表明，采用此方法控制的磁流变阻尼缓冲装置显著降低了冲击载荷对基座的影响，并有效抑制了抖振现象，减弱了基座与挠性附件之间的运动耦合，使挠性附件的速度、加速度变化更为平稳。此控制方法较传统滑模控制能更好地跟踪输出值，且有较好的稳态输出值。
위강저재궤분리충격재하대뇨성항천기적영향，진행료기우자류변조니완충기( Magneto-rheological)적감진연구，장자류변조니완충기응용우항천기충격감진。기우유한원화Lagrange방법，건립료발생대범위운동적뇨성항천기상태모형，채용추근률활모공제산법공제조니기수출，병제출일충이유모호공제방법공제추근계수래제고계통적동태품질，동시억제추근률중절환항도치적두진현상。수치계산표명，채용차방법공제적자류변조니완충장치현저강저료충격재하대기좌적영향，병유효억제료두진현상，감약료기좌여뇨성부건지간적운동우합，사뇨성부건적속도、가속도변화경위평은。차공제방법교전통활모공제능경호지근종수출치，차유교호적은태수출치。
In order to reduce the influence of the impact load during the on-orbit separation,a Magneto-rheological ( MR) shock absorber was used. The configuration of shock absorber was also introduced.Flexible spacecraft dynamic model with large reference displacement was established based on finite element and Lagrange method,and sliding mode was used to control the output of the MR shock absorber.A new two dimensional fuzzy sliding mode control was proposed to control the reaching coefficient of the reaching law to improve the dynamic characteristics of the MR shock absorber.Numerical simulation results show that MR shock absorber con-trolled by the proposed method obviously decreases the impact influence and reduces the chattering. The coupling of the base and flexible appendages is weakened,and velocity and acceleration of the flexible appendages become smoother.Furthermore,the pro-posed method has a better steady value and tracking characteristic compared with traditional sliding mode control.