In allusion to the technique requirements such as reliably open, enough and greatly open-angle, automatically open or lock for the pressure tank, a method using function cycle time combination, and spatial multi-link coupled actuating strategy is proposed to develop a spatial multi-link Mechanism with a variable revolution axis to ensure of perpendicular inside out opening rapidly. A parametric dynamic model is established, the opening angle, horizontal size of the opening mechanism, and erecting cylinder load are used as outputs, and the Hinge-point parameters of the links are taken as inputs. Nondominated sorting genetic algorithm is used to solve the multiobjective problem and the max-min criterion is adopted to select a solution from the Pareto front. The optimized effect is compared with the results of ADMAS dynamic simulation, scale experiment and product experiment tests. The result shows that the proposed method provided a certain reference for optimization of perpendicular inside out opening mechanism.

The use of sinusoidal scanning vibration to simulate low-frequency transient vibration environment is a traditional testing method in the aerospace industry, and its environmental assessment of products may have both under testing and over testing simultaneously. Firstly, the equivalence between the two is analyzed, and then relevant theories such as impact response spectrum and maximum response spectrum are used to study the scanning rate and damping coefficient in the formulation of equivalent sinusoidal scanning vibration test conditions, and parameter selection suggestions are provided. Finally, steps are proposed to establish the testing conditions for sinusoidal scanning vibration environment, providing reference for the low-frequency transient environment adaptability assessment using sinusoidal scanning testing.

Starship is a new generation of reusable space transportation system developed by Space Exploration Technologies Corporation (SpaceX). The landing process of this type of spacecraft, which has the characteristics of large attitude maneuver, multiple constraints, and high accuracy requirements, is different from that of traditional spacecraft. The dynamics of the flipping and landing phase of the Starship-like aircraft is studied firstly, and the response of engine gimbal angle is introduced into the dynamics to suppress the oscillation of engine gimbal angle. Then, based on the convex optimization method, an optimization algorithm for the free-final-time flipping and landing trajectory of Starship-like vehicles is designed, which can consider the attitude maneuver and typical constraints. In order to improve the convergence of the algorithm, virtual control and penalized trust region are used, and a method for initial value selection is given. Finally, numerical examples are provided to analyze the influences of initial value selection method, the response of engine gimbal angle, engine number, and the selection of optimization objective functions on the flipping and landing phase.

Based on the huge requirement of LEO or MEO business satellite launch mission, responsive launch technology for large or middle launch vehicle is badly needed. According to the requirements of Long March-8, land-launched supporting system focus on horizontal assembly and erection technology, responsive and intelligent launch technology, which can improve the efficiency of launch mission, simplify the equipment of launch site, and save launch cost. The study mainly elaborates horizontal assembly equipment, erection equipment, intelligent gas supply system. Two horizontal assembly schemes of spreader and bracket car are introduced. The factors that affect the accuracy of erecting and butting of the whole transport are analyzed, and the method of raising the rigidity of the erecting bracket are given. The general scheme of intelligent gas supply and distribution, intelligent pressure reducing valve technology and fault diagnosis technology of gas supply and distribution equipment are introduced.