A modular hierarchical power supply and distribution method is proposed for electrical system of launch vehicles in order to avoid large scale power supply cable, complex topology and potential path. Each stage of electrical system is planned as an independent power supply and distribution unit, and the integrated power supply and distribution framework is realized in the unit. Electrical isolation is designed among different power supply and distribution units and ground equipment to prevent the electrical coupling and potential circle path and reduce the system complexity. The power and distribution system has the advantage of modularization in system level and the plug and play with units, which provides a technical basis for the standardized design of the power supply and distribution structure of the future electrical system and hierarchical test of the launch vehicle.

Trans-media aircraft refers to a new concept special aircraft with both air flight capabilities and underwater submarine capabilities, which includes submersible aircraft and submarine-launched drones. Aircraft that can span multiple domains is focused on. Through literature research, this study elaborates on trans-media aircraft and their characteristics and applications, introduces in detail the development status of trans-media aircraft at home and abroad, analyzes the technical difficulties of achieving trans-media flight, and summarizes the key technologies required for trans-media aircraft. Finally, based on the investigation and the current development at home and abroad, the prospects of the trans-media aircraft are prospected and development suggestions are put forward.

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.

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.

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.

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.

The structure of S-shaped cable is complex. When S-shaped cable is separated at high speed, it has large deformation and complex nonlinear contact. The analysis of dynamic deformation and mechanical characteristics of S-shaped cable is one of the difficulties in engineering design. ABAQUS is used to establish the dynamic simulation separation model of separation cable. The dynamic deformation mechanism and mechanical characteristics of S-shaped cable are analyzed, and the correctness of the modeling method is further verified by the ground experiment. The influence of various sensitive factors, such as length, section diameter, tail length and separation speed of S-shaped cable is studied, which can provide analysis method and reference for engineering application.

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.

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 active aircraft defense problem with unknown attacking missile's guidance law is considered, and the one-way and two-way cooperation modes for a target aircraft and a defending missile are introduced. Cooperative guidance laws for the target and defender are proposed by using sliding mode control, which can enhance the measurement observability and meanwhile guarantee the successful defensive interception. A sliding surface is firstly constructed, considering both the requirements of estimation enhancement and successful interception. And then the one-way and two-way cooperative guidance laws are derived, by adopting the double-power reaching law and the state-feedback based exponential reaching law respectively. Compared with one-way cooperative guidance law, the two-way cooperative guidance law is optimized by introducing the cost function of control effort for the target and defender. Meanwhile, in two-way cooperation mode, the target aircraft can take the cooperative maneuver to help defender impact the attacking missile with less control effort. Simulation results show that the proposed cooperative guidance law can guarantee both the good measurement observability and the well defensive guidance accuracy.