The continuous reduction of fuel during the rocket launch causes the rocket structure to change continuously, and the natural frequency and modal shape of the structure also change accordingly. Aiming at the inaccuracy of the finite element model, the moment of inertia of the section is used as the correction parameter, and the minimum error between the numerical simulation results and the experimental test results under different states is the objective function, and an optimization model for multi-state model correction is established. The objective function is explicitly processed by sensitivity analysis and first-order Taylor expansion, and the optimal solution of design variables is obtained by sequential linear programming. At the same time, for the multi-state structure, taking the multi-section simply supported beam model as an example, the simply supported beam is tested by the hammering method, and the magnetic attraction weight scheme is designed to simulate the multi-state model. An optimization model is established for the objective function, and the multi-section simply supported beam model is revised to a single-section simply supported beam model after modification, and the ratio of the moment of inertia of the section to the area is met, which verifies the accuracy of the multi-state model modification method.

In order to solve the possible problems of filling accuracy and kerosene quality in the drainage process of the closed filling pipeline at the end of the kerosene, the pipeline deformation caused by the change of pressure and temperature is discussed by analyzing the influencing factors that affect the change of kerosene in the pipeline. The thermodynamic calculation model of temperature, pipe diameter and deformation pressure is constructed, and the accuracy of the model calculation is verified by experiments. According to the numerical calculation results of the model, the optimization measures for the drainage process are proposed to ensure the reliability of the drainage process of the filling pipeline.

Modelling methods of the high-altitude wind uncertainty have significant influence on aerodynamic loads and the overall performance optimization of launch vehicles. The commonly used methods in engineering do not consider the correlation between wind speeds at different altitudes, and the simulated wind samples are inconsistent with actual wind characteristics, therefore disable to accurately predict the aerodynamic loads. A modelling method using $U/V$ wind speed components as non-stationary Gaussian processes about the height is proposed. The statistical distribution parameters of massive actual historical wind samples are analyzed, and the expansion optimal linear estimation (EOLE) method is adopted to generate wind samples with the same distribution as actual wind samples. Results indicate that the proposed method can simulate the actual wind profile more precisely than traditional methods. The simulation program of real launch vehicle is used to calculate the wind loads, and the results show that the wind loads predicted by the proposed method is far more accurate than traditional methods, which is of great significance to improve the launch efficiency and launch probability of launch vehicles.

The expansion and locking process of aircraft folding rudder is a dynamic process of multi-load synthesis. The dynamic process is studied by simulation. The dynamic simulation model is established, considering aerodynamic load and friction action in the whole dynamic process. The influence of different aerodynamic load on dynamic process is analyzed by dynamically simulating the condition of obstruction, no-load and promoting aerodynamic load. By comparing the result of no-load expansion test with the simulation result of no-load condition, the accuracy of the dynamic simulation model is verified. Based on this dynamic simulation model, the friction work under different aerodynamic load condition is identified by using angular acceleration method and angular velocity method respectively from load and energy dimensions. The result of the study shows that the friction torque is affected by aerodynamic load. The friction work increases with the increase of aerodynamic promotion. The angular acceleration method and angular velocity method are both reasonable to identify the friction work. The research provides theoretical reference for engineering design and analysis of aircraft folding rudder.

To analyze the correlation characteristics between visible-infrared spectrum and infrared radiation of photonic crystal films, three kinds of Ge/ZnS photonic crystal films with different visible reflectance and the same infrared emissivity are designed. By simulating the infrared radiation characteristics of photonic crystal structures, the influence of solar illumination and reflection spectrum on the infrared radiation characteristics of the films in vacuum and atmospheric environments is discussed. The simulated results show that the difference of visible reflectance will lead to the discrepancy of surface temperature in the presence of sunlight. For infrared radiation, the high reflection surface will reflect solar radiation at low temperature for $3 \sim {5\mu}\mathrm{m}$ waveband, which has a negative impact on infrared camouflage. For $8 \sim {14\mu}\mathrm{m}$ waveband, when the infrared emissivity is low enough, the infrared radiation emittance of the photonic crystal structures is close. The fabrication of samples and the measurement of reflection spectrum and infrared thermography are carried out. The test results show the consistency with the simulation, and verify the infrared camouflage performance of three films. The research results are helpful to understand the visible-infrared spectrum and infrared radiation correlation characteristics of photonic crystal films, and provide reference for the spectral design and application scheme of visible-infrared camouflage materials compatible with microwave camouflage.

The use of deformable wing rudder technology can solve the problem of strong constraints on the launch platform size of missiles, improve the lift to drag ratio and ballistic maneuverability of missiles, achieve optimal aerodynamic shape throughout the flight, and adapt to the needs of multi mission operations. The development of deformable wing rudder technology at home and abroad is summarized, the composition of deformable wing rudder scheme is briefly introduced. The missile's demand for deformable wing rudder technology is analyzed, and the development path of single step deformation, reciprocating expansion deformation, flexible continuous deformation and the key technologies of each stage are put forward. The research results provide a reference for the in-depth research and application of deformable wing rudder technology in the field of missile weapons.

The safety of solid rocket launch vehicles under the abnormal side tumbling condition in the process of railway transportation is studied. Based on investigation and analysis of various vibration absorption schemes, the technical scheme of energy absorption system with the combination of cushion airbag and honeycomb is put forward. The side-rolling simulation analysis is carried out using Hypermesh and LS-DYNA software. The results show that the acceleration of the rocket's side-rolling down decreases from 27g to 8.91g, and the contact collision force between the launcher and the carriage decreases from 382.59kN to non-contact by using the above technical scheme. Meanwhile, it can obviously improve the safety of solid rocket launch vehicles under abnormal conditions such as railway transport rollover. Finally, it provides important guidance for the design of special solid rocket launch vehicles.

Super Heavy-Starship is a two-stage fully reusable heavy-lift launch vehicle proposed by Space Exploration Technologies Corp. (SpaceX). In Super Heavy-Starship, mechanisms are widely utilized to implement various functions of the launch vehicle, such as connection, separation, aerodynamic control and landing shock absorption. In addition, traditional pyrotechnics are replaced by high-pressure cold air as power source of mechanisms. Focusing on the landing shock absorption mechanism, grid rudder mechanism, flap rudder mechanism, stage separation mechanism, and pneumatic mechanism of Super Heavy-Starship, the mechanism composition, working principle, design ideas, merits and demerits are clarified. The innovation points of SpaceX's mechanisms are summarized. Furthermore, the gaps and deficiencies in the development and application of launch vehicle mechanisms in China are analyzed, and corresponding suggestions are put forward as well.

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 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.