Recent developments in micro- and nano-satellites have attracted the interest of the research community worldwide. Many colleges and corporations have launched their satellites in space. Meanwhile, the space flexible ...Recent developments in micro- and nano-satellites have attracted the interest of the research community worldwide. Many colleges and corporations have launched their satellites in space. Meanwhile, the space flexible probe-cone docking system for micro- and nano-satellites has become an attractive topic. In this paper, a dynamic model of a space flexible probe-cone dock- ing system, in which the flexible beam technology is applied, is built based on the Kane method. The curves of impact force versus time are obtained by the Lagrange model, the Kane model, and the experimental method. The Lagrange model was presented in the reference and verified by both finite element simulation and experiment. The results of the three methods show good agreements on the condition that the beam flexibility and the initial relative velocity change. It is worth mentioning that the introduction of vectorial mechanics and analytical mechanics in the Kane method leads to a large reduction of differential operations and makes the modeling process much easier than that of the Lagrange method. Moreover, the influences of the beam flexibility and the initial relative velocity are discussed. It is concluded that the initial relative velocity of space docking operation should be controlled to a certain value in order to protect the docking system.展开更多
本文将 Kane 动力学方法与假设模态法相结合.给出一种分析机器人手臂弹性动力学的新方法.首先基于 Kane 方法的运动学概念,并应用假设模态法建立了手臂弹性运动学.推导出完整的弹性动力学方程.并以一简例说明了其应用过程.这种方法比较...本文将 Kane 动力学方法与假设模态法相结合.给出一种分析机器人手臂弹性动力学的新方法.首先基于 Kane 方法的运动学概念,并应用假设模态法建立了手臂弹性运动学.推导出完整的弹性动力学方程.并以一简例说明了其应用过程.这种方法比较简洁,兼具 Lagrange 法和 Newton-Euler 法的优点而克服了其不足,便于计算机数值分析.展开更多
现代航天器通常携带大量的液体推进剂,在轨运行时推进剂的消耗将导致等效模型参数的改变.为了获取准确的等效模型参数并将其引入GNC(guidance,navigation and control)系统闭环控制,提高航天器的姿态控制精度,文章提出一种基于平方根容...现代航天器通常携带大量的液体推进剂,在轨运行时推进剂的消耗将导致等效模型参数的改变.为了获取准确的等效模型参数并将其引入GNC(guidance,navigation and control)系统闭环控制,提高航天器的姿态控制精度,文章提出一种基于平方根容积卡尔曼滤波(SR-CKF)的等效模型参数在轨辨识策略.首先,为了建立适用于金属膜片贮箱的等效模型,在等效球摆模型的悬挂点施加扭簧-阻尼器以等效金属膜片对推进剂的刚度-阻尼效应,并借助Kane方法建立了航天器刚-液耦合动力学方程.其次,针对状态反馈反步控制器中等效模型参数未知的情形,提出一种基于SR-CKF的等效模型参数在轨辨识策略.该策略可在航天器完成一次大角度姿态机动任务的同时,根据星载角速度计数据在线辨识出等效模型的各项参数以及贮箱内推进剂的剩余量,并预测出推进剂的分布运动状态.最后,数值仿真结果表明了提出的在轨辨识策略的有效性和必要性.文章的工作对于航天器GNC系统中等效模型的校准迭代、研究推进剂在轨晃动行为及预测航天器服役年限具有重要参考价值.展开更多
To address the issues of low solving efficiency and poor decoupling accuracy in existing six-axis acceleration decoupling algorithms,a new decoupling algorithm is proposed along with a corresponding auto-compensation ...To address the issues of low solving efficiency and poor decoupling accuracy in existing six-axis acceleration decoupling algorithms,a new decoupling algorithm is proposed along with a corresponding auto-compensation algorithm.Firstly,based on Kane’s method,the dynamics model of the six-axis acceleration sensing mechanism is formed to determine the relationship between accelerations and branch forces.Then,with the trapezoidal rule,a solution algorithm for the dynamics model is developed.The virtual prototype tests show that the computation of this algorithm is five times more efficient than that of the ADAMS core algorithm.Besides,this solution algorithm is applied to the“12-6”configuration and“9-3”configuration.The results show that the efficiency of the former is nearly 3.3 times that of the latter.Finally,based on vibration theory,an auto-compensation algorithm for the solution algorithm is established.Virtual prototype tests indicate that with 40%noise interference,the auto-compensation algorithm achieves misjudgement rate and omission rate of only 4.0%and 4.5%,respectively,and the errors in the solving process converge.展开更多
基金supported in part by the National Natural Science Foundation of China (Nos. 91216201, 51205403)
文摘Recent developments in micro- and nano-satellites have attracted the interest of the research community worldwide. Many colleges and corporations have launched their satellites in space. Meanwhile, the space flexible probe-cone docking system for micro- and nano-satellites has become an attractive topic. In this paper, a dynamic model of a space flexible probe-cone dock- ing system, in which the flexible beam technology is applied, is built based on the Kane method. The curves of impact force versus time are obtained by the Lagrange model, the Kane model, and the experimental method. The Lagrange model was presented in the reference and verified by both finite element simulation and experiment. The results of the three methods show good agreements on the condition that the beam flexibility and the initial relative velocity change. It is worth mentioning that the introduction of vectorial mechanics and analytical mechanics in the Kane method leads to a large reduction of differential operations and makes the modeling process much easier than that of the Lagrange method. Moreover, the influences of the beam flexibility and the initial relative velocity are discussed. It is concluded that the initial relative velocity of space docking operation should be controlled to a certain value in order to protect the docking system.
文摘本文将 Kane 动力学方法与假设模态法相结合.给出一种分析机器人手臂弹性动力学的新方法.首先基于 Kane 方法的运动学概念,并应用假设模态法建立了手臂弹性运动学.推导出完整的弹性动力学方程.并以一简例说明了其应用过程.这种方法比较简洁,兼具 Lagrange 法和 Newton-Euler 法的优点而克服了其不足,便于计算机数值分析.
文摘现代航天器通常携带大量的液体推进剂,在轨运行时推进剂的消耗将导致等效模型参数的改变.为了获取准确的等效模型参数并将其引入GNC(guidance,navigation and control)系统闭环控制,提高航天器的姿态控制精度,文章提出一种基于平方根容积卡尔曼滤波(SR-CKF)的等效模型参数在轨辨识策略.首先,为了建立适用于金属膜片贮箱的等效模型,在等效球摆模型的悬挂点施加扭簧-阻尼器以等效金属膜片对推进剂的刚度-阻尼效应,并借助Kane方法建立了航天器刚-液耦合动力学方程.其次,针对状态反馈反步控制器中等效模型参数未知的情形,提出一种基于SR-CKF的等效模型参数在轨辨识策略.该策略可在航天器完成一次大角度姿态机动任务的同时,根据星载角速度计数据在线辨识出等效模型的各项参数以及贮箱内推进剂的剩余量,并预测出推进剂的分布运动状态.最后,数值仿真结果表明了提出的在轨辨识策略的有效性和必要性.文章的工作对于航天器GNC系统中等效模型的校准迭代、研究推进剂在轨晃动行为及预测航天器服役年限具有重要参考价值.
基金supported by the Opening Project of State Key Laboratory of Mechanical Transmission for Advanced Equipment(No.SKLMT-MSKFKT202330)the National Natural Science Foundation of China(NSFC)(No.52575022)the Postgraduate Research&Practice Innovation Program of Jiangsu Province(No.KYCX24_1295)。
文摘To address the issues of low solving efficiency and poor decoupling accuracy in existing six-axis acceleration decoupling algorithms,a new decoupling algorithm is proposed along with a corresponding auto-compensation algorithm.Firstly,based on Kane’s method,the dynamics model of the six-axis acceleration sensing mechanism is formed to determine the relationship between accelerations and branch forces.Then,with the trapezoidal rule,a solution algorithm for the dynamics model is developed.The virtual prototype tests show that the computation of this algorithm is five times more efficient than that of the ADAMS core algorithm.Besides,this solution algorithm is applied to the“12-6”configuration and“9-3”configuration.The results show that the efficiency of the former is nearly 3.3 times that of the latter.Finally,based on vibration theory,an auto-compensation algorithm for the solution algorithm is established.Virtual prototype tests indicate that with 40%noise interference,the auto-compensation algorithm achieves misjudgement rate and omission rate of only 4.0%and 4.5%,respectively,and the errors in the solving process converge.
