The geometrically non-linear stiffness response of morphing aircraft structures is crucial for applications with large deformations. In order to study the nonlinear mechanical behavior of zero Poisson's ratio honeycomb structure with sinusoidal corrugated walls during large deformation in plane, a nonlinear mechanic model with consideration for geometric nonlinear is established based on nonlinear beam theory. It is verified by comparison with non-linear structural analysis with FEM. The stress-strain relationships with different parameters are obtained. The results show that the geometric nonlinear increases the equivalent stiffness with the increase in strain, and the stress-strain curves are greatly affected by corrugation ratio, thickness ratio, and inclination angle, but not by height ratio.

For multi-axle vehicle which use integrated design and integral body structure, rigid-flexible coupling virtual prototype model is established, which analyzes ride comfort of distributed driving multi-axle vehicle. On base of different connective with cab and body and different cab structure, ride comfort of vehicle is given with different load and different run case. Root mean square value of vibration acceleration of the truss structure cab with inclined support is effectively reduced. Comfort of the cab with no-connectivity top structure is better. Through optimize cab's structure form and top link shape, ride comfort of vehicle improves better on case of empty-load and full-load, which can satisfy the demands.

The hanging process is one of the key links in the Mid-Air retrieval of launch vehicle. According to the whole process of the launch vehicle tail cabin hanging in the air, the design of the hanging device based on the helicopter as the recovery platform is carried out. The hanging device includes tension sensor, load shedding device, overload protection device and the actuator in the end of the hanging device. Parafoil and parachute eject from the bottom of the tail cabin of launch vehicle. The hanging device can realize the hanging operation of the retrieval by hanging attached apex drogue on the top of parafoil. Through the simulation analysis of the hanging process, it can be seen that when the weight of the retrieval increases, the overload increases significantly. When the parachute retraction time increases, the load reduction effect is obvious

In order to solve the issue of missing high-frequency information of flight data in servo system of launch vehicles, a high-frequency feature restoration method based on wavelet multi-resolution analysis is proposed. Initially, features are extracted from ground hot firing test data through wavelet multi-resolution analysis. Subsequently, leveraging the correlation between the angular velocity signal and high-frequency features, a feature matching approach is put forward for predicting the high-frequency features of the flight data. Finally, the linear superposition method is conducted to achieve feature fusion, thus completing the feature restoration process of the flight data. The experimental verification is carried out. It shows that, compared to the baseline data, the restoration results have a consistent commutation frequency pattern, which imply that the proposed feature restoration method is feasible and effective. The study can provide data support for obtaining the characteristics of actual flight profile for aerospace servo products.

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.

Under the background of networked hypersonic weapon platforms, the research on hypersonic glide vehicles is no longer limited to the guidance methods under multiple constraint, but urgently needs to break through the technical difficulties of multiple vehicles cooperative guidance and control. Firstly, in order to lead to the necessity of research on multiple vehicles cooperative guidance and control, the development process of hypersonic glide vehicles of major military powers is summarized, and the development status and trend of multiple vehicles are analyzed. Secondly, to explore ideas for multiple hypersonic vehicles cooperative operations, the research status of formation communication maintenance control, collaborative guidance control with flight time constraint, and collaborative guidance control with flight angle constraint are summarized. Finally, the future development direction of multiple vehicles collaborative guidance and control is prospected.

Considering the dispersion of small signal flow characteristics of servo valve, the control parameters of electro-hydraulic servo system need to be matched and adjusted. An off-line self-optimizing method for electro-hydraulic servo system control parameters based on particle swarm optimization is proposed. The control system task book and manual debugging results decide optimization target characteristics, and the parameter optimization range is determined by the analysis results of servo system stability and statistics of batch production data envelopment. This parameter optimization method takes about 100-240 seconds. Compared with manual approaches, it can greatly improve the mass production debugging efficiency of the control parameters for electro-hydraulic servo system.

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.

In order to timely and accurately understand the development trend of world aerospace field in 2023, the latest developments in world space transportation system, ballistic missile and hypersonic technology are comprehensively reviewed, involving key model research and development, flight tests and major hot events in the aerospace field of the United States, Russia and other countries. The development of world aerospace field in 2024 is forecasted by summarizing and analyzing.

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.