In order to realize the unsupported launch of a medium-sized launch vehicle, a movable deflector scheme is adopted. Deflector has gone through a complete development process such as scheme design, gas flow field simulation analysis, metal matrix production, ablation test, heat protection cap production, etc., and has finally been successfully applied in the unsupported launch of medium-sized liquid launch vehicles.

In the view of the difficulty of digital coordination of coordination hole of the carrier rocket part, the influencing factors of digital coordination processing are analyzed and the main reasons are determined, and the influence of measurement error and positioning on the machining accuracy is analyzed through comparative test and theoretical analysis. On this basis, the digital coordinated machining control scheme is put forward, and the typical part is taken as the object to carry out coordinated hole test, the test results show that the digital quantity coordination machining hole position accuracy meets the requirements of assembly coordination, and the test coordination with the tooling platform, laying the foundation for the engineering application of the end-frame digital quantity coordinated machining.

With the rapid development of commercial aerospace, traditional measurement and control resources are unable to meet the demand for high-density and rapid launch of commercial rockets. There is a shortage of measurement and control resources in the aviation area, and space-based measurement and control resources based on Tianlian satellites are not suitable for commercial space launch modes. The performance indicators of civil and commercial communication satellites are investigated, and the Ku frequency band space-based measurement technology based on APSTAR-6D satellite is studied. A space-based measurement and control system implementation scheme has been proposed by combining link calculations with satellite performance. Finally, it provides new measurement and control resources for commercial space rocket launches, and the measurement and control can cover the needs of typical SSO orbit launch vehicles.

In order to improve the efficiency of gas supply system in space launch, automatic charging technology of gas cylinders is proposed. Automatic charging schemes of gas cylinders based on PID control technology are designed, and the automatic control strategy is studied through the system simulation software AMESim. The results indicate that by setting the PID control module parameters reasonably, the schemes of gas charging can meet the automatic charging requirements of gas cylinders on launch vehicle. To improve the automatic charging control effect of gas cylinder, pressure sensor used in the control module should be installed close to the cylinders of launch vehicle.

The innovative technologies for the hardware construction of VR stereo vision systems are summarized and an innovative method for AI-generated VR vision of digital models in MBSE system engineering is proposed. By carefully selecting hardware such as large-screen displays, small-pitch LED displays, and active stereo display devices, the study innovatively realizes a VR visual hardware system that integrates high-resolution, multi-channel stereo synchronization, and multi-channel stereo stitching, all while incorporating functions for scientific research demonstrations, validation, and conference discussions. Furthermore, through data-driven Al algorithms, it accurately and efficiently generates VR vision for various types of digital models in MBSE system engineering. Technical references for the software and hardware construction of VR systems for other users are provided.

TDOA (Time Difference of Arrival) is a widely used passive positioning technology with high precision, strong ability of collaborating, high robustness. The issues of computational complexity and slow accuracy convergence for the positioning of moving target are addresses. Based on the positioning model in LOS (Line of Sight) environment, a positioning method suitable for a multi-station TDOA system is provided. After linearizing collaboration TDOA positioning relationship equations into a statistical estimation problem, this method online converges iteratively to solutions of targets' locations. A multiplatform collaborative positioning algorithm for different motion characteristics of the targets. Simulations results demonstrate that the provided method can achieve precise positioning. Moreover, the impact of motion patterns on positioning accuracy is analyzed, and simulation results provide guidance for system engineering design.

Focusing on the development of missile intelligent cooperation, the application of missiles in Unmanned Aerial Vehicle (UAV) swarms is focused on. The respective application characteristics of UAV swarm and missile systems are introduced, the application modes of missiles in UAV swarm are explored, the requirement on developing intelligent missile swam is analyzed. Based on the issues of observation, interaction, and collaboration in swarm intelligence, current challenges and key support technologies for missiles application in UAV swarm are analyzed. With the analysis on "MSET" and "Golden Horde" projects, the current situation and development of missiles in swam are analyzed, and the ability doubling points for the actualization of missile-UAV application are pointed out, which provides exploration for future research on intelligent missile system.

The hypersonic vehicle needs to separate from the booster stage in an environment with low altitude and high dynamic pressure. The current prediction of separation and attitude control based on limit deviation method is not real enough and the design is heavily redundant. For inserted separation with long stroke and small gap, the collision detection of two stages cannot be carried out during the attitude control design process. To solve the above problems, a coupling calculating method of separation and attitude control is proposed, which introduces the attitude control model into separation dynamic model. Design redundancy is reduced and the level of refine is improved. Also, collision detection can be realized in the whole process, providing support for ensuring the safety of the separation and attitude control process. The method provides a basis for the time to start attitude control of the upper stage, and has guiding significance for optimization design of separation time sequence.

The on-orbit refueling technologies of cryogen can reduce the total mass of propellants required in rocket vehicles, allowing a significant increase in the amount of payload delivered beyond low Earth orbit. It has great potential benefits in complex space transportation systems and deep space exploration tasks. A literature investigation on the key techniques of cryogenic propellant on-orbit refueling is conducted. The existing lab-scale and full-scale experimental studies are reviewed in detail. Moreover, advantages of using on-orbit refueling techniques comprehensive analysis in future space tasks are provided. Technical suggestions on the developments for on-orbit refueling of cryogenic propellants are proposed based on this research.

Taking the hydrogen-oxygen expansion cycle engine as the research object, based on the idea of modular modeling and simulation, the dynamic model of engine components is given, and the liquid rocket engine system model is constructed based on the working principle of the engine system, and the transient state of the hydrogen-oxygen expansion cycle engine is developed simulation Research. According to the simulation results and combined with the test data, the engine system model is verified and optimized, and the optimized model is simulated and calculated in the whole process of engine dynamics. The simulation results show that the main performance parameters during the dynamic change of the engine are in good agreement with the test data, which verifies the simulation model accuracy and design feasibility.