As an important component of aviation control and power systems, the suction characteristics of DC electromagnetic coils used in aviation valves are a key factor in the design of electromagnetic coils. Taking the magnetic-proof ring magnet in the DC magnets for aviation valves as the research object, the magnetic-proof ring magnetis modeled in ANSYS Maxwell and the magnetic field distribution is given. The effects of different air gap, different parameters and armature length of the magnetic-proof ringon the suction characteristics of the electromagnet are analyzed. On this basis, two optimization methods are applied to the multi-objective design of the suction force at different positions of the electromagnet. One is to use the orthogonal test method to carry out the primary and secondary analysis of the factors that affect the suction force characteristics of the electromagnet more obviously. The other is to use the optimization software optislang to carry out the sensitivity analysis of the factors and the optimization design based on the evolutionary algorithm. Finally, a comparative analysis of the improvement effect of the two pairs of methods on the suction characteristics is carried out. The results show that optislang optimization is more in line with the requirements of electromagnet suction.

In response to the application background of satellites passing over or observing a ground target within a specific time, the Walker constellation scheme design is carried out for meeting the revisiting time requirements. The models of a satellite coveraging a ground target are constructed. The methods for calculating the time-windows of a satellite passing over a ground target, and onboard circle/rectangular-field-of-view sensor observing a ground target are designed. On this basis, a Walker constellation scheme design algorithm which satisfies the revisiting time requirement with the minimum satellite number is developed. The simulations and analyses are provided for three simulation scenarios. The results of the developed algorithm are compared with STK, and the average error of revisiting times is less than 1.1 s, which verifies the accuracy and rationality of the models and the algorithm. The relevant research results can provide reference for the design of Earth observation constellation schemes.

Research advances in fluid-structure interaction (FSI) during vehicle water entry, encompassing theoretical modeling, experimental testing, and numerical simulation are reviewed. The theoretical analysis systematically traces the evolution from classical potential flow theory to nonlinear multiphysics-coupled models, while critically analyzing their applicability and limitations in complex entry scenarios. Experimental investigations summarize measurement techniques for capturing transient parameters and revealing physical mechanisms, highlighting their crucial role in validating theoretical and numerical frameworks, with particular attention to instrumentation constraints and boundary condition effects. Numerical advancements are examined through grid-based and meshless methodologies, emphasizing their computational characteristics in resolving multiphase flow evolution and FSI dynamics. Finally, current technical bottlenecks are identified, followed by forward-looking perspectives on multiscale coupling modeling and intelligent algorithm integration.

In the future reusable space transportation system, the plane-symmetric reusable launch vehicle has a high development priority, and the plane-symmetric launch vehicle control technology is one of the critical technologies. Firstly, the research significance and difficulties of plane-symmetric and liquid propellant rocket are analyzed according to the engineering requirements. Then, the research progress is summarized from four aspects, including attitude control, active load relief (LR) control, elastic vibration suppression and liquid sloshing suppression. Finally, in view of the unsolved problems in the existing research and the new problems brought by the special structure of liquid propellant plane-symmetrical rocket, prospecting its future development and putting forward several feasible research directions from the requirements of high-precision, high reliability and intelligent.

High-speed underwater vehicles are critical carriers for underwater high-speed penetration. To address their higher drag reduction demands, higher-performance underwater drag reduction technologies and more precise control techniques are required. Supercavitation drag reduction is primarily explored, which holds significant development potential, discussing its drag reduction mechanisms, component functions, and cavitation morphology changes. The current status and development level of supercavitation drag reduction technology theory, experimental validation techniques, and typical equipment are analyzed both domestically and internationally. Further, key issues in motion control for high-speed underwater vehicles are examined, researching control techniques such as linear feedback, robust pole placement, sliding mode variable structure, H-infinity robust control, and intelligent control, conducting research and application analysis on motion control methods. Areas requiring further research in current supercavitation drag reduction are also analyzed, including cavity stability issues, flow field simulation and validation for complex force-thermal physical processes, multiphase flow complex thermophysical process modeling, and robust stability design in highly nonlinear environments. Finally, from a future development perspective, it identifies unresolved problems such as perfecting fundamental mechanisms, intelligent control, algorithm innovation, structural innovation and interdisciplinary integration, and engineering validation. References for research on drag reduction and control technologies for high-speed underwater vehicles can be provided.

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 airline-flight-mode launch capability is essential for future spaceports and a key indica-tor of their space launch capacity. Spaceports face challenges in improving this capability. These challenges include a lack of top-level planning, infrastructure pressure, an urgent need for technology upgrades, and management and safety risks. To tackle these issues, this anal-ysis proposes ten countermeasures. These strategies cover system architecture, overall lay-out, operation modes, rocket families, and testing and launch technologies. They provide valuable guidance for spaceports to enhance their airline-flight-mode launch capability.

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.

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.

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.