Research On Assembled Unit Of Space Large Structure And Performance Of Assembly

In recent years,Country's ground observation,space communication,deep space exploration and other businesses have developed rapidly.Large-scale deployable institutions are an effective way to solve the needs of high-stability,light-weight,and large-scale space structures.Quality,size and dynamic characteristics can not meet the future development needs of ultra-large spatial structures.With the development of onorbit service technology,on-orbit construction has become the focus of aerospace science and technology research in recent years.This paper proposes a spatial structure assembly unit for on-orbit construction.Firstly,the basic configurations of various space structure assembly units are designed and evaluation indexes are established.According to the optimization results,the configuration of the space structure assembly units in the unfolded state is determined as a hexagonal prism configuration.According to the established 20 m structure finite element model,the influence rules and sensitivities of different structural parameters on the fundamental frequency of large structures are obtained,and the structural parameters of the spatial structure assembly unit are optimized.A new type of spatial structure assembly unit is proposed.The folding technology is applied to the space structure assembly unit,and the large structure is designed as a whole system composed of many modules.It is carried in batches to lift off,unfolded on the rail,and assembled on the rail.The general scheme of large-scale structure on-rail construction is proposed,and the assembly scheme of large-scale structure on-rail construction is discussed and optimized;by comparing the docking mechanism scheme,a three-jaw docking interface suitable for on-rail construction is proposed And completed the design of space structure assembly unit and docking interface,and analyzed the key parameters of modular unfolding unit and interface.The assembly unit of the space mechanism is a deployable mechanism,and the kinematics analysis of the extendable mechanism is required to ensure the smooth deployment of each rod on the assembly unit of the space structure and the correctness of the configuration kinematics analysis is verified by ADAMS.The trajectory of the locking claw is obtained through the established kinematics of the locking claw.Through the ADAMS simulation analysis of the docking interface,the feasibility of the docking interface under a positioning tolerance is obtained,and the factors that affect the on-orbit assembly of the docking mechanism are studied.The relationship between the contact force of the docking mechanism and each influencing factor is obtained.The force analysis of the node of the basic unfolding element,according to the instability condition of the rod under pressure,calculate the range of force applied by the stay cable;based on the principle of energy equivalence,the dynamic equivalent model of the spatial structure assembly unit is established,which is free The models are simulated by ABAQUS to verify the effectiveness of the dynamic equivalent model established in this chapter.Finally,an analysis model of 50 m large-scale structure is established in ABAQUS and free modal analysis is carried out.The rationality and correctness of the configuration and equivalent dynamic model of the space structure assembly unit proposed in this paper are verified,which provides a useful reference for the on-orbit construction of ultra-large structures in aerospace engineering.