Nuclear thermal rockets, as a revolutionary potential space luanch vehicle, have the capability to significantly reduce the scale of space transportation missions or enhance transportation capacity. The historical research of nuclear thermal propulsion (NTP) technology in the United States and Russia (The Soviet Union) is reviewed, the development challenges of nuclear thermal rocket are analysed. By proposing feasible lunar return missions and manned Mars exploration transportation tasks for nuclear thermal rocket, the study examines key technological challenges form an engineering application perspective, including optimization of overall parameters, high-power thermal propulsion, nuclear safety design and protection. At the end of the research, it is suggested to strengthen the research and development of key nuclear thermal rocket technologies and promote the construction of non nuclear and nuclear testing capabilities.

To achieve the design goals of high performance and reliability of propulsion systems for attitude control in the future, study on the dynamic characteristics has important scientific and engineering value. The dynamic simulation method for the MMH/NTO dual component propulsion system for attitude control is studied based on AMESim software. Firstly, the dynamic models of each components are determined and their simulation modules are established based on the system scheme. Secondly, the simulation model of each component is built by the AMESim software and the simulation model of the whole system is established. Finally, the processes of tank pressurization and multi thrust chamber pulse and interactive working are simulated. The changes in key parameters like pressure and flow rate of the thrust chamber are analyzed and the modeling method is verified. Meanwhile, the stability of the check valve is analyzed. The influences of working parameters and structural parameters on the stability of the valves are discussed. The results indicate that the dynamic simulation model established in this study can be used to accurately simulate the processes of multi thrust chamber pulse interaction. The inlet pressure and the throttle area of the check valve have an obvious impact on the stability of the system. The dynamic simulation method can be used for dynamic characteristics and stability analysis, which can provide useful references for the system scheme design and dynamic characteristics study.

High-speed centrifugal pumps are widely used in industry and aerospace, and their performance is affected by the matching of the number of inducer and impeller blades. In order to study the effect of different matching relationships on the pump performance, numerical simulations based on the RNG k-ε model are carried out using ANSYS-CFX software, and the accuracy of numerical calculations is verified by external characteristic tests. By analyzing six matching relationships of inducer blades with 3 and 4, and impeller blades with 5, 6, and 7, the results indicate that when the number of impeller blades is fixed, the head is improved at small flow rates but reduced at large flow rates while increasing the number of inducer blades. Keeping the number of inducer blades unchanged, the head is improved while increasing the number of impeller blades, especially at large flow rates. Increasing the number of inducer blades expands the range of vacuole distribution, while changing the number of impeller blades has less effect on cavitation performance.

In order to optimize the rational design of the thermal structure of solid rocket motor and accurately measure the erosion morphology of the insulation layer, a three-dimensional scanning technology is employed for this purpose. This study proposes a three-dimensional laser scanning strategy and a method for processing solid rocket motor three-dimensional data to analyze the wrapping characteristics of the insulation layer and cylindrical cylinder section of the shell. The proposed approach enables realization of three-dimensional data on erosion morphology in solid rocket motor insulation layers, facilitating determination of corresponding erosion amounts. Compared to traditional methods, this intelligent, comprehensive, and efficient method offers great application prospects for measuring erosion thickness in solid rocket motor insulation layers.

Aiming at the high temperature environment of the attitude control solenoid valve, the affected performance of the valve is simulated and analyzed. At the same time, the high temperature experiment of the valve is carried out. The results of simulation analysis and high temperature experiment indicate that the moving distance of the armature reduced due to the Non-metallic expansion of the core at high temperature, which causes the valve unable to open normally. And with the swelling effect of the oxidant to the core, the reliable operation temperature of oxidant valve is lower than fuel valve. By taking measures of enlarging the moving distance and replacing the core material to PFA, the high temperature environmental adaptability of the solenoid valve is improved.

Initiating explosive devices on rockets are disposable products. Test items on the ground are rarely, and directly related telemetry data are little in flight. By means of data correlation, the present telemetry data can be fully utilized to analyse the performance of initiating explosive devices. Several portion of flight telemetry data closely related to the initiating explosive devices is selected, a analysis on its performance is made, and the result with performance indicators and the test dates on ground are contrasted. The analytical method is verified to be right.

Permanent magnet synchronous motor (PMSM), owing to its high power factor, high efficiency, and high power density, have been widely employed in aerospace vehicles to enable high-dynamic servo motion. However, during long-term tracking control or attitude holding, PMSMs are prone to interturn short-circuit faults (ITSC). Under servo operating conditions, the fault signals exhibit non-periodic characteristics in the time domain, which poses considerable challenges for fault diagnosis. To address this issue, an ITSC diagnosis method is proposed based on the high-frequency negative-sequence current. First, a simplified analytical model of PMSM with ITSC faults is established to reveal the characteristic impacts of the fault on electrical quantities. Second, a high-frequency voltage signal is injected into the control system, and the high-frequency current response of the motor is extracted through a band-pass filters. Finally, the negative-sequence component of the high-frequency current is calculated as the diagnostic indicator, enabling real-time fault identification. By employing the high-frequency negative-sequence current as the fault feature, the proposed method can effectively distinguish healthy and faulty states of the motor under servo conditions, while improving both diagnostic speed and robustness. Simulation results demonstrate that the proposed method achieves reliable diagnosis under servo operating conditions with rapid variations in position, speed, and load, with a diagnostic time of less than one fundamental cycle, showing strong potential for engineering applications.

In order to meet diverse mission requirements and reduce design and production costs, modular design has become an important development direction for flight vehicle system design. For modular flight vehicle, general components are key components and also the primary prerequisite and important foundation for carrying out modular design. To address the problem of poor module universality in traditional flight vehicle design, a general component construction method based on self-organizing mapping neural network is proposed. Firstly, the characteristics and content of modular flight vehicle design are introduced. Secondly, in response to the problem of long computation time and easily getting in the local optimization in self-organizing mapping algorithm, the calculation process for the general component construction method combining self-organizing mapping and neural network is proposed. Finally, simulation experiments are conducted using a modular flight vehicle design example to validate the proposed general component construction method. The results show that the method can effectively meet the requirements of modular flight vehiclegeneral component construction, and significantly improve computation time and solution accuracy compared to a single self-organizing mapping algorithm.

The cryogenic exhaust valve is a key component of the liquid rocket propulsion system, and the main failure mode is the stuck guide. To improve its action reliability, a "metal-nonmetal" composite guiding structure is proposed. The non-metal hot pressing forming process is studied, and the theoretical calculation and simulation analysis of the guiding clearance variation under low temperature are carried out. An experimental system is built to verify the reliability of the forming process of the composite guiding structure and the rationality of the clearance calculation. The research results show that the nonmetal composite guiding structure of the cryogenic exhaust valve can adapt to the low temperature operating conditions, and has higher action reliability and tolerance to contaminants.

Addressing challenges such as low data storage efficiency, weak real-time data retrieval responsiveness, and the separation between data storage and analysis in space missions, an integrated data-access-computation platform architecture is proposed. First, based on the characteristics of data acquisition and usage in the aerospace domain, a requirements analysis for the integrated platform is conducted. Subsequently, an overall architecture is constructed, outlining its core business processes and functional framework. The functional architecture comprises five layers: infrastructure, data acquisition, data storage, data computation, and data application, supporting multi-source heterogeneous data acquisition, operator invocation, task scheduling, and timed execution. Following this, a full-chain technical solution for real-time data acquisition, storage, retrieval, and computation is designed in detail, targeting the core functions of the integrated architecture. This solution provides decision-making support for space missions and lays a technical foundation for intelligent data analysis. Finally, key technologies are elaborated, including intelligent generation of aerospace test reports, data flow modeling, and visual analysis process orchestration.