Research On Modular Unit Structure Design And Interface Of Reconfigurable Spacecraft

On-orbit satellite service technology is an effective way to address space environmental pollution.On the background of the on-orbit satellite service technology,a concept of reconfigurable and modular spacecraft is proposed,which decomposes the traditional spacecraft into a number of standardized and intelligent modular units,and integrates the subsystem components required by the spacecraft in each unit,thereby realizing connection between units through interfaces.This thesis focuses on the study of the key components of reconfigurable spacecraft,namely modular unit and interface.Firstly,from the design requirements and design criteria,the structure design of the unit and interface device was carried out,including the structural shell design of the unit box,the locking device design based on the cylindrical cam mechanism in the mechanical interface and the electrical transmission device design based on the power pin in the power interface.Secondly,after completing the design of the relevant parts of the interface structure,it is necessary to analyze the factors that cause the transmission errors of the interface.One of the purposes of studying errors is to suppress and reduce errors.Understanding these factors causing transmission errors of the interface is helpful to reduce errors.Therefore,in order to reduce the transmission errors of the interface,the motion law of the follower of the cam mechanism in the interface was designed,and the quadratic term correction constant velocity motion law and simple harmonic modified constant velocity motion law were optimized respectively.Finally,the quadratic term correction constant velocity motion law was selected as the curve groove form of the cam in this thesis.Thirdly,the unit and interface structures should meet the design requirements of the spacecraft during the launch and orbit operation phases.As the spacecraft is under a complex mechanical environment,during the whole life cycle of mission termination,units and interfaces are subjected to vibration dynamic environment and extreme temperature environment,therefore,it is necessary to conduct accurate finite element analysis of units and interfaces to avoid "under-design" of structures caused by inadequate consideration of dynamic environment and extreme temperature environment.In this thesis,thermal analysis and modal analysis of the unit and interface structures were carried out by ANSYS Workbench software and the structures were checked to meet the use requirements.Finally,study the contact-impact force theory and dynamic modeling theory of the dynamic analysis software ADAMS,and the interface dynamic model for unit connection was established in ADAMS software,and the feasibility of the designed interface to achieve locking and electrical signal transmission functions was verified.The factors of motion law of the follower affecting the connection accuracy of the interface were simulated and analyzed,and the accuracy of the follower motion law selected in this thesis was proved.Through the ground test on the principle prototype of the interface,it was verified that the principle prototype of the interface can achieve the locking function and the docking function of the related parts in the power interface.