No abstract

In this paper, based on the development of the non-pyrotechnic low impact connection and separation device for heavy load connection of large space vehicles, the design method of connection and separation device is studied. The traditional heavy load connection separation device has a strong loading capacity, but the release of system energy will cause a huge impact during separation. This paper considers the transfer of impact energy in the mechanism design process, reduces separation impact based on energy flow analysis. Based on the analysis of the DOF (Degree of Freedom) constraint function of the separation system and the working requirements of the separation mechanism, the movability model of separation system was established. According to the research on DOF constraints and release, the key of force constraints in DOF constraints of the separation mechanism is obtained, and the separation mechanism that can implement the force constraints and release is analyzed. Furthermore, based on the energy flow analysis of the separation mechanism, the design method of the low impact separation mechanism is proposed, obtained a non-self-locking thread pair connection separation mechanism. The effectiveness of the design method was verified by the energy conversion analysis of the separation mechanism.

Considering the deployment characteristics of the folding wing, this paper proposed three deployment modes, synchronous deployment, fixed-axis–non-fixed-axis stepwise deployment, and non-fixed-axis–fixed-axis stepwise deployment, to obtain the optimal deployment scheme of the orthogonal biaxial folding wing of Unmanned Aerial Vehicles (UAVs) at different airspeeds. On this basis, combined with the folding wing deployment action, the Lagrange method was used to establish the aerodynamic model of the folding wing, and the Fluent simulation software was used to simulate the aerodynamic simulation of multiple deployment modes of the orthogonal biaxial folding wing, which analyze the influence of the UAV deployment mode and airspeed towards the driving torque of the folding wing. Based on the driving moment of the folding wing, the optimal deployment mode at different airspeeds was obtained. The comparison of simulation results shows that when the airspeed is less than 40 m/s, the optimal deployment mode is synchronous deployment. When the airspeed is greater than or equal to 40 m/s, the optimal deployment mode is non-fixed-axis–fixed-axis stepwise deployment. The accuracy of the folding wing aerodynamics model can be proven according to the comparison of the simulation results with the theoretical results.

In this paper, the mechanism scheme and parametric design of a capture and lock system are studied based on the high reliability of locking systems. By analyzing the workflow and boundary conditions of the capture and lock system, a positioning design is carried out by combining it with the layout of a distributed capture and lock system. Based on the error domain for the passive end in the presence of errors in the manipulator, planning for the capture trajectory and configuration of the design for the active end are carried out. The influence of the passive end on the dynamic performance of the system is comprehensively considered to design the configuration of the passive end. According to the structure of the active end, a mathematical model for the capture and lock mechanism is established, and an analysis of the influence of trajectory parameters on the active end is carried out. The layout design of the capture hook for the active end is carried out based on an analysis of the influence of its layout on posture adjustment. The large-tolerance capability of the system layout is verified with a tolerance simulation analysis and a ground simulation capture test.