When the power unit of the series hybrid vehicle is overloaded suddenly, the engine torque load rate would be too high, which would lead to abnormally operation. In order to solve this problem, a load compensation strategy based on fuzzy control is designed. By controlling the torque of generator, the engine torque load rate could be regulated, so that avoiding the engine working near the critical condition. The simulation and test results show that the strategy improves the working characteristics of the power unit effectively, makes it operates stable and smoothly until achieve the expected operating point, improves the robustness of the power unit.

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.

A product-oriented virtual test framework for structural strength of aircraft bodies is proposed, under which the classical elastic-plastic damage constitutive of materials and general finite element technology are developed, and a human-computer interactive virtual test platform for aircraft cabin structure is created based on the virtual test plug-in tool developed by Abaqus built-in Python software. Using the accurate confirmation technology of step-by-step inspection, the virtual/real test comparison from the specimen to the complex cabin is carried out to verify the feasibility of the virtual test of the cabin structure. The results show that the virtual test can simulate the load-bearing failure of the cabin structure with high fidelity, and the prediction accuracy of the ultimate load-bearing capacity is 4.6%.

Aiming at the damage problem of experimental facilities caused by unsteady chamber pressure in experiment of high temperature gas flow wind tunnel, the mechanism of the influence of collector positions and dimensions on the stability of experimental flow field is studied. Study mainly focuses on the interaction between the waves and separated vortexes. Utilizing CFD method, the pressure distribution is obtained in the chamber. Then the relationship between the interaction of the waves and separated vortexes and experimental stability are also explored, which will provide a reference for the optimal design of the collector. The results show that appropriate collector position and reasonable collector dimensions can reduce the overflow in the chamber. It can also avoid the separated vortex dominating the collector port, and increase the flow of mainstream. It is helpful to the conduction of experiment.

In radar countermeasures, the jammer detects the radar signal, then the signal is sampled by AD and input to FPGA for processing and generating interference signal. When using the FFT IP core officially provided by the FPGA platform Xilinx to perform FFT processing on the data output by the high-speed ADC, data preprocessing of "parallel-serial" is required, which greatly slows down the FFT processing speed. At the same time, the internal resources of FPGA is not maximized. An data processing method based on FPGA input block remapping is proposed. This method uses the data input remapping module to optimize the input data into a parallel block data stream format. Then the FFT butterfly networks process the input data into blocks to obtain the discrete Fourier transform data. Finally, parallel data are output. Experimental results show that this method can effectively save FPGA computing time, improve radar data processing speed, optimize the utilization of FPGA internal resources, and has the characteristics of good real-time performance and high flexibility.

In the aspect of evaluating UAV performance, in order to improve the disadvantages, such as strong subjectivity from the experts, too sensitive to data, the UAV capability modeling is proposed. It not only shields the heterogeneity and resource diversity of UAV from the upper layer, but also retains the important characteristics of UAV, which can present the UAV's capability to support the design of upper layer model and algorithm, and reduce the prior workload of the upper-level research and promote the development of related research. Furthermore, the differential entropy weighting method based on UAV capability is also proposed to evaluate the capabilities and comprehensive performance of UAV effectively. This method determines relative weight of each feature according to the feature vector corresponding to the maximum eigenvalue of the judgment matrix, and the final evaluation result is obtained through weighted calculation. Experimental results show that the method overcomes subjective bias from experts and increases the horizontal comparison among indicators to improve the stability of calculation.

The combat effectiveness of equipment strongly depends on the support of ground equipment. Under system combat conditions, how to achieve system empowerment, system enhancement and system collaboration through innovative ground equipment is a major issue of the overall ground profession. An equipment system is taken as the research object. Firstly, the capability requirements of the system operation on the weapon system are analyzed, and the combat mode, task flow and system composition of the weapon system are combined to form a condensed list of the support capability requirements. Secondly, aiming at improving the operational accompanying support management ability and improving the allocation of accompanying support resources, the technical approaches of applying intelligent technology to mobile operations support and enhancing the effectiveness of ground equipment are sorted out, and a technical scheme of intelligent support of equipment is formed. Based on the above research, the preliminary design of information and intelligent support vehicle scheme is completed, and its mobile combat support capability is evaluated.

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.

The reusable launch vehicle based on liquid oxygen methane engine has excellent performance in reuse and maintenance, and is easier to achieve low cost. Countries around the world are accelerating relevant research and engineering development. Typical representatives include the Vulcan launch vehicle of the United States, and the ZhuQue-2 launch vehicle of LandSpace. The technical characteristics and technical challenges of the reusable launch vehicle based on liquid oxygen methane engine are analyzed. The following key research contents are proposed, including the overall design and evaluation of reuse, GNC technology for ascent and reentry and return landing, large-scale lightweight structure and manufacturing technology, reuse of LOX engine, health prediction management and reuse operation and maintenance technology, reuse thermal protection technology etc. It will lay a foundation for further development of liquid oxygen methane reusable launch vehicle.

In order to investigate the evolution of vertical water-entry cavity of a sphere, a numerical simulation for modeling the vertical water-entry of a sphere was performed, which is based on Navier-Stokes equations, volume of fluid model and dynamic mesh. It showed that numerical results compared favorably with the experimental results, which verified the accuracy of the simulation method. In addition, during the early period of the water entry, there was a high impact load on the sphere and a splash rose from the surface, and then a water-entry cavity which was open to the atmosphere formed. The cavity experienced development, closure and collapse periods after its formation. Pressure acting on the cavity was the main cause of the deep closure, and high speed up-jet and down-jet appeared after the closure.