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 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.

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.

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.

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.

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.

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.

The response of roads under hundred-ton-level impact loads is complex and affects the success of operations. Finite element models of elastoplastic roads can simulate road settlement responses under impact loads, but the accuracy of numerical simulation results lacks experimental validation. Additionally, model parameters exhibit significant variability, making it difficult to determine them in practical engineering applications. Different parameter settings greatly influence the accuracy of simulation results, making them difficult to support engineering operations. To predict the road response under impact loads and ensure operational success, this study selects a typical road layer structure and designs equivalent impact load tests to investigate the settlement response patterns of typical roads under impact loads. Based on experimental findings, appropriate constitutive models are selected for typical materials in each layer of the typical road. Methods are developed to adjust the nonlinear constitutive model parameters of loess subgrade through engineering parameters such as moisture content and compaction degree. A finite element model of the typical road is established for simulation. The simulation results are compared with experimental data in three dimensions: peak pavement settlement, residual settlement, and the geometric state of overall road surface settlement. The deviations are within 10%, verifying the effectiveness of the finite element modeling approach for typical roads. The related research results can be widely used in road transient impact response simulation.

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.