| Space on-orbit service is currently a research hotspot in the field of aerospace.With the continuous advancement of aerospace technology,in order to facilitate the operation of on-orbit services,the design of spacecraft is moving towards modularization.The spacecraft’s modular design is a prerequisite for the spacecraft to be assembled in orbit,module replacement,function expansion,performance upgrade,etc.,and the realization of the above functions needs to solve the basic problems of docking between modules.Therefore,research on the technology of docking mechanism of replaceable modules in space orbit has become an urgent need for human exploration in deep space.Based on the thorough investigation of the existing domestic and foreign docking mechanism technology,this paper proposes a new configuration of rotating T-head type small weak impact docking mechanism.Unlike traditional docking mechanisms that require complex latches,the principle of the rotating T-head docking mechanism to capture the lock is simple,but the action of the T-head has strict timing requirements.In this paper,the assembly composed of a special-shaped cross-section part body and a spring has different movement characteristics under different load conditions.A single power source is used to realize the complex timing sequence of the T-shaped head in the axial and circumferential cycles during the docking mechanism capture process.action.The design of the complicated capture lock of the traditional docking mechanism is avoided.At the same time,in view of the modular docking requirements,an optimized design of the layout of the docking and docking mechanism was implemented to realize a docking mechanism,which is common to multi-size modules.Based on the analysis of the tolerance capability of the docking mechanism,the mathematical model of the capture domain of the docking mechanism is established,and the capture domain of the docking mechanism is obtained,and the extreme pose is extracted as the input condition.The whole process of docking under the extreme pose condition of the docking mechanism is obtained.Perform dynamic simulation to obtain the centroid-time curve of the module satellite docking process,verify whether the docking mechanism can complete reliable docking under extreme conditions,obtain the contact force-time curve of the T-head and the passive end,and verify the active and passive in the docking process The end contact force is sufficient to meet the design index.According to the finite element analysis of the docking mechanism,the deformation of each component under different load conditions and extreme ambient temperature conditions is obtained.The docking mechanism is modal analyzed to verify the reliability of the mechanism locking mechanism.The principle prototype was developed,and the principle prototype was tested for function and performance.The single and double docking mechanisms were respectively tested for locking and separation functions,proving that the single and double docking mechanisms can reliably complete the docking task.The quality,envelope size,linear travel and other performance indicators proposed by the design requirements for docking were tested to verify whether they met the design indicators.The indirect measurement of strain gage strain is designed to indirectly achieve the measurement of the locking force of the docking and docking mechanism,and verify that the locking force meets the performance index.The connection stiffness test was carried out on the docking mechanism with the tensile machine,which proved that the stiffness in the locked state meets the performance index. |
