The wide-velocity-range (WVR) reusable flight vehicle, due to its extensive flight airspace and broad Mach number range, is challenging to select a fixed working state as the design point. Moreover, due to a large number of factors affecting the overall performance of the vehicle, as well as the varying impact and sensitivity of these factors in integrated air-launch system design, it has brought considerable difficulty to the integrated optimization design. A single-stage-to-orbit (SSTO) reference trajectory for the WVR reusable flight vehicle is established, conducting sensitivity analysis on key parameters from three major aspects of design: aerodynamics, propulsion, and structures. Through perturbation analysis of the reference design parameters, the impact of different parameters on the overall performance of the flight vehicle under varying operating conditions is comparatively analyzed. This successfully identifies several design parameters that significantly influence the vehicle's performance. Finally, based on the sensitivity analysis results, the study makes reasonable recommendations on subsequent optimization directions for the wide-speed-domain reusable flight vehicle from four aspects: schematic design, aerodynamics, propulsion, and structures.

A primitive time synchronization method is proposed based on the FC-AE-1553 bus technology, aiming at the comprehensive development of onboard measurement systems and the background demand for real-time data sensitivity. This method enables each node in the FC-AE-1553 bus to have the same-time reference. On the basis of time synchronization, a scheduling timing based on time synchronization wasdesigned to collect real-time data from various NT nodes, meeting the requirements of real-time data for onboard measurement systems. The experimental results show that the FC-AE-1553 bus designed has nanosecond time synchronization, dual redundancy, and other functions, which meet the application requirements-of onboard measurement systems and improve the comprehensive level of onboard measurement systems.

In response to the pressing demand for the large-scale and high-frequency development of space transportation, horizontal takeoff and horizontal landing-reusable launch vehicle (HTHL RLV) which does not rely on fixed launch sites and can operate as conveniently as aircraft, represents a crucial development direction for establishing a future scheduled space transportation system. The technical characteristics and developmental path of HTHL RLV are systematically elucidated, providing a comparative analysis of the strengths, weaknesses, and applicability of different technical approaches. On this basis, it focuses on key technical challenges and potential breakthroughs in the field, including multidisciplinary-coupled overall system design, wide-speed-range aerodynamic configuration, high-performance combined-cycle propulsion, lightweight structures, adaptive guidance and control, reusability, and intelligent operation and maintenance. Furthermore, prospective pathways for future technology development are also outlined.

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.

The new generation of rocket-borne electrical system architecture fully embodies the characteristics of distributed information synthesis, which can realize the physical separation of rocket-borne electrical system, information sharing and dynamic resource allocation through appropriate unified real-time network design, reduce the impact of cross-domain information interaction, and improve the determinacy, reliability and fault-tolerant ability of system networking. Combined with the different real-time guarantee ability of real-time network flow control mechanisms, the information transmission requirements of rocket-borne integrated electronic system are analyzed, the time-sensitive flow control mechanisms are selected, the message and traffic type are matched, the time trigger window is designed through the joint optimization of path and scheduling, and the network simulation model is built using the OMNet++ to simulate and evaluate the performance of the network system. Through simulation, the matching relationship between all traffic and time-sensitive network flow control mechanisms in typical rocket-borne integrated electronic system are verified, and the feasibility of time-sensitive network application in rocket-borne integrated electronic system is demonstrated.

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.

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.

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.

Achieving low cost, high frequency, and rapid-response launche remains the core objective of space transportation development. Since the mid-20th century, the United States pioneered reusable launch vehicle (RLV) development. Government agencies like NASA and the U.S. Air Force led numerous flight test programs and engineering initiatives, progressing through multiple phases: early exploration, the Space Shuttle era, spaceplane concepts, and second-generation RLV development. Breakthroughs in key reusable technologies were ultimately achieved by commercial entities, notably SpaceX. This evolution exhibits multiple iterative cycles and parallel development paths. Systematically analyzing the U.S. RLV development route, including key projects and technical strategies, offers valuable insights for China's reusable launch vehicle advancement, supporting the planning and execution of major national projects.

Periodic-disturbance may cause serious effects on spacecraft. The attenuation of them is demanded. A fundamental study on the optimal design of constant compensations against periodic disturbance for meteorological satellites is investigated. An analytical solution about the relationship between the frequency and amplitude ratios and the response of a typical second order vibration system is firstly derived. The compensate and disturbance torques are determined according to practical engineering. The criterions for designing the optimal compensations are based on the analytical results. Then the criterions are applied on the flexible spacecraft actuated by constant control torque in the presence of sustained periodic disturbance. The optimal compensate torque parameters for spacecraft is acquired draw on the former criterions. Its compensation effectiveness is provided and compared with results of other selections in frequency ratio domain and amplitude ratio domain. Numerical simulation results and experimental results clearly demonstrate the good performance of proposed design in periodic disturbance compensation. This work provides a significant reference for the vibration attenuation of meteorological satellites in the present of periodic-disturbance.