This paper presents a method to control a manipulator system grasping a rigid-body payload so that the motion of the combined system in consequence of externally applied forces to be the same as another free-floating rigid-body (with different inertial properties). This allows zero-g emulation of a scaled spacecraft prototype under the test in a 1-g laboratory environment. The controller consisting of motion feedback and force/moment feedback adjusts the motion of the test spacecraft so as to match that of the flight spacecraft, even if the latter has flexible appendages (such as solar panels) and the former is rigid. The stability of the overall system is analytically investigated, and the results show that the system remains stable provided that the inertial properties of two spacecraft are different and that an upperbound on the norm of the inertia ratio of the payload to manipulator is respected. Important practical issues such as calibration and sensitivity analysis to sensor noise and quantization are also presented.
Lightweight Model Predictive Control for Spacecraft Rendezvous Attitude Synchronization
Space Applications Group, e:fs TechHub GmbH（e:fs技术中心空间应用组）；Faculty of Electrical Engineering and Information Technology, Ingolstadt University of Applied Sciences（应用科学大学英戈尔施塔特电气工程与信息技术学院）
Optimization of body configuration and joint-driven attitude stabilization for transformable spacecrafts under solar radiation pressure
Institute of Space and Astronautical Science（宇宙航空研究开发机构空间与宇航科学研究所）；Japan Aerospace Exploration Agency（日本宇宙航空研究开发机构）；Tokyo Institute of Technology（东京工业大学）
Intelligent Control of Spacecraft Reaction Wheel Attitude Using Deep Reinforcement Learning
Swinburne University of Technology（斯winburne大学）；University of South Australia（南澳大利亚大学）；Systems Research Institute Polish Academy of Sciences（波兰科学院系统研究所）
Diffusion Policies for Generative Modeling of Spacecraft Trajectories
Jet Propulsion Laboratory, California Institute of Technology（加州理工学院喷气推进实验室）；NASA Jet Propulsion Laboratory, California Institute of Technology（美国国家航空航天局加州理工学院喷气推进实验室）
Model Evaluation of a Transformable CubeSat for Nonholonomic Attitude Reorientation Using a Drop Tower
Faculty of System Informatics, Kobe University（神户大学系统信息学系）；Department of Mechanical Engineering, Aoyama Gakuin University（山梨大学机械工程系）；Department of Applied Mechanics and Aerospace Engineering, Waseda University（早稻田大学应用力学与航空工程系）
Imitation Learning for Satellite Attitude Control under Unknown Perturbations
Mechanical and Aerospace Engineering Department, Rutgers, the State University of New Jersey（机械与航空航天工程系，新泽西州立大学拉特格斯分校）；Aerospace Engineering Department, Embry-Riddle Aeronautical University（航空航天工程系，埃姆布里-瑞德航空大学）
EasyUUV: An LLM-Enhanced Universal and Lightweight Sim-to-Real Reinforcement Learning Framework for UUV Attitude Control
Tsinghua Shenzhen International Graduate School, Tsinghua University（清华大学深圳国际研究生院，清华大学）；Department of Mechanical Engineering, The University of Hong Kong（香港大学机械工程系）；Department of Data and Systems Engineering, The University of Hong Kong（香港大学数据与系统工程系）；School of Civil Engineering, Southwest Jiaotong University（西南交通大学土木工程学院）；School of Information and Software Engineering, University of Electronic Science and Technology of China（电子科技大学信息与软件工程学院）；Department of Data Science, New Jersey Institute of Technology（新泽西理工学院数据科学系）；Ocean College, Zhejiang University（浙江大学海洋学院）
