Mobile Launcher (ML) is one of the critical ground supporting systems, which is going to be in service for Space Launch System (SLS). The function of ML includes stacking, assembly, process checkouts and launch support for the SLS rocket and Orion spacecraft. The structure layouts, operations and functions from Apollo and Saturn V are valued and baselined. The ground support equipment like umbilicals and accessories are researched and renewed. Besides, ML is aimed to be possessed of strong applicability and generality for different heavy-lift rockets, including SLS. The generality design is then performed, and modules and equipment are borrowed from previous launchers. Comprehensive tests of function, security and reliability are carried on. The research in the paper will provide reference for the launcher of heavy-lift rocket in China.

C/SiC composite material for hypersonic vehicle structure has a broad application in near-space area. The active / passive ablation performance of the C/SiC composite is studied numerically. An approach for active sublimation ablation performance up the ${2000}^{\circ}\mathrm{C}$ of $\mathrm{C}/\mathrm{{SiC}}$ composite materials is proposed and some wind tunnel experiments have been designed and completed. The results show that the ablation performance proposed has good accuracy compared with the wind tunnel results. The results can provide a reference for the structure and thermal protection design and safety assessment of the hypersonic vehicles based on C/SiC composite material.

Aerodynamic heating is a key issue in the research of hypersonic vehicles flying in near-space. It has an important influence on the aerodynamic, thermal environment and safety of the aircraft. Due to the limitation of experimental methods, wind tunnel experiments cannot simulate real flight conditions accurately. CFD is an important tool for studying aerothermodynamics problems. The format dissipativeness and grid are two important factors that affect aerothermodynamics simulation. The smaller the format dissipation, the better the CFD performance, but low dissipation will cause shock instability phenomena. A hybrid HLLCE format which has both the HLLE format stability and the low dissipativity of the HLLC format is constructed. This format exhibits the low dissipation properties of HLLC at a lower Mach number and can overcome shock instability phenomena at high speed. The thickness of the linear bottom layer of the boundary layer is used as the reference scale, and 1/10 of the thickness of the linear bottom layer calculated by the feature length is taken as the minimum grid scale for thermal environment calculation. The performance of low dissipation scheme is verified by hypersonic sphere example with the proposed grid scale

As an important component of aircraft guidance system, non-metal radomes have multiple functions such as heat protection, wave transmission and load bearing. It is connected to the aircraft body through high-temperature resistant adhesive agent. Radome is frequently subjected to harsh mechanical and thermal loads during the period of service, and the joint structure is often the weakness of strength design. Therefore, accurate simulation for mechanical behavior of the joint structure and achieving accurate prediction of load-carrying capacity are crucial for the structural design and optimization of radome. Based on bilinear cohesive model, the failure behavior of radome adhesive interface is numerically described by ABAQUS. And then the damage evolution of adhesive layer is simulated, and the accurate prediction of bearing performance of radome joint structure under flight thermo-mechanical environment is achieved. The corresponding experimental study is carried out. The experimental results are in good agreement with the simulated ones, verifying the validity of numerical method. It provides an effective way to solve bearing problem of aircraft-level radome joint structure.

Currently, in fuze two levels of environmental force arming, high dynamic overload is often used as one insurance element. Generally, one arming method is used of the inertia mass block's movement trip under trajectory overload. Mass blocks are limited by mechanical movement and are difficult to integrate in fuze systems, and is poor in testability. A scheme based on MEMS sensor technology is proposed and designed to arm the fuze. The principle, composition, function of the system, software workflow and the test and verify situation are introduced. This method has a wide scope of use can improve the flexibility of fuze systems and is easy to system integration.

The optics window is usually faced with severe aerodynamic heating, and there is a prominent image saturation problem because of high temperature. Therefore, researchers often use film cooling to isolate the direct heat convection from the outflow. A tangential high-density cooling film generation structure is designed which is used for high pressure and heat flux. Through reasonable ground test, numerical simulation and engineering calculation, the main factors affecting the cooling efficiency are studied. The preliminary results show that tangential high density gas film can reliably reduce the surface heat at high pressure and high heat flux. The research effectively adapts to the increasingly harsh optical observation environment.

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 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 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.

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.