International Space Station has been in orbit for more than 20 years, forming a relatively mature cargo transport system and exploring the development path of low-cost and highly reliable commercial cargo transport system. As China's Space Station enters the stage of application and development, the demand for materials up and down will significantly increase. It will be particularly important to form a rich and stable cargo transport system and significantly reduce cargo costs under normal operating modes. The development and current situation of cargo transport system of the International Space Station are analyzed, the composition of the International Space Staion, commercial orbital transportation service plans, and recent cargo transportation situations are focused on, providing reference and suggestions for China's Space Station's cargo transport system.

The e ^N method based on linear stability analysis is currently one of the most widely used methods for transition prediction; however, the selection of the transition criterion N_T value shows significant scatter at high Mach numbers. The linear stability analysis and e ^N method are used to conduct stability analysis and N-factor envelope calculations for the lifting calibration model at Mach numbers of 5 and 8, and for Reentry F at a Mach number of 20. Combining the transition onset locations obtained from wind tunnel results and flight data, the calibration of the transition criterion N_T value at high Mach numbers is carried out. The results show that for the lifting calibration model, the transition criterion N_T is approximately 5.3 to 6.5 under different angles of attack at Mach number of 5, and approximately 4.8 to 5.3 at Mach number of 8. For Reentry F, the transition onset locations vary significantly at different altitudes, but the transition criterion N_T does not change significantly, being approximately 9.55 to 9.73.

A TDOA joint optimization model (TDOA-PSO-NI-GD) that integrates Particle Swarm Optimization (PSO) and Newton's Iteration-Gradient Descent (NI-GD) method is proposed in response to the problem of insufficient positioning accuracy of multi-stage rocket debris, which improves the localization performance through the synergistic mechanism of global search and local optimization and constructs the multi-debris signal separation constraint model and the environmental interference compensation model. Experiments show that the model reduces the positioning error from 1~10 km to less than 0.5 km in the traditional single-stage optimization algorithm in the rocket debris recovery mission, and the multi-debris signal separation rate reaches 96.2%, and maintains the sub-kilometer accuracy under the mountainous terrain and strong wind disturbances; the validation of the Chan-Taylor algorithm combined with the least-squares method shows that its anti-jamming and positioning reliability are significantly better than that of the existing methods. The algorithm can be extended to mobile communications, unmanned vehicles and other fields, with both theoretical innovation and engineering application value.

To control the position of the windward side along the vehicle for reducing the impact of harsh re-entry force and thermal environment on the vehicle, an active continuous roll control method based on the aerodynamic coefficient fitting model is proposed. Firstly, an aerodynamic coefficient fitting model combining quadratic term and negative exponential term model is established, and the aerodynamic coefficients are fitted using the least squares method. Secondly, based on the coordinate system transformation relationship, the windward angle model and the windward error angle model are proposed to describe the trajectory of the windward side along the cone of the vehicle. Then, based on the BTT/STT composite control method, linear roll control commands are designed, and the effect of different roll control commands on the flight process is compared and analyzed. Furthermore, nonlinear rolling control commands are created based on the loads to ensure that the roll rate is consistent with the trend of the loads. Finally, the proposed roll control commands are verified to generate excellent roll control effect through six degrees of freedom simulation, and can make the windward side evenly distributed along the vehicle. The standard deviation of the load on each meridian of the vehicle in rolling condition is 20% of that without rolling.

In the final assembly process of various solid and liquid rocket models, there are many tasks involved, such as the docking of the rocket body and the transfer of the entire rocket body workstation. Currently, the completion of this series of complex tasks mainly relies on manual guarantee. When the operator's skills are insufficient, the factory quality of the rocket body cannot be guaranteed. And in recent years, with the new production of larger tonnage and diameter rocket models, it has caused a significant physical consumption of workers and also reduced labor productivity. Through long-term technological breakthroughs and physical verification experiments, a large tonnage electric propulsion device with lightweight, ultra overload, stepless speed regulation, and adjustable interface tooling has been developed, which solves the problems of difficult docking of most sections of the rocket body, high labor intensity of the entire rocket body workstation transfer, and intermittent overload of the rocket conveying pipe during cabin penetration in the overall aerospace assembly.

Hydrogen-oxygen mixtures are widely used as aerospace propellant. Their thermodynamic properties, transport properties and chemical reaction processes are far more complex than pure air, and it is more difficult to analyze and predict their flow process. The self-developed device-detonation tunnel is used to provide high temperature hydrogen-oxygen combustion gas. Combined with CFD, the flow and aerodynamic heating characteristics of air and combustion gas under the same total temperature and total pressure are analyzed. It is found that, when flowing in the nozzle, the combustion gas has higher temperature, speed and smaller Mach number; the standoff distance and stagnation pressure of the combustion gas are smaller than air; the skin friction and wall heat flux are greater than air. Active chemical reactions in combustion gas make aerodynamic heating more serious.

As artificial intelligence technology developing rapidly, the intelligence level of unmanned systems is much increasing. Specially, intelligent reconnaissance technology is more mature and widely used. To solve the above problems, an adversarial patch attack based camouflage and deception method is proposed. Convolutional neural network is used to build a classifier as the attack object, and a novel patch generation method and loss function are designed to attack target samples, which effectively maps the attacked target samples to the specified wrong target category. A directed evaluation method and wealthy experiments are provided to verify the advancement and effectiveness of this method.

In response to the current reality that cryogenic liquid launch vehicles have become the mainstay of space missions and the urgent need to enhance personnel competency, this study proactively addresses the training requirements of launch sites for the upcoming universal ground-based testing, launch, and control systems. By fully considering scenarios such as normal testing and launch procedures, troubleshooting under abnormal conditions, and emergency response operations, research, design, and development of a simulation and training system for cryogenic liquid launch vehicle testing and launch procedures are conducted. This system thoroughly analyzes the universal characteristics of the product and aligns with the training needs of launch sites for the soon-to-be-deployed universal ground-based testing, launch, and control systems. It develops hardware equipment and testing software consistent with actual products, covering all phases of testing operations across launch site systems. It supports comprehensive, full-process operational training for all systems and positions, fully meeting the training needs of personnel involved in cryogenic launch vehicle testing and launch operations. The system is capable of fostering a more technically proficient testing and launch team, thereby comprehensively supporting the foundational capacity building of a leading spacefaring nation.

The stability of lubricating grease performances is a significant factor that restricts the long-term storage reliability of aerospace electro-mechanical servo actuators. The rheological properties of lubricating grease can directly affect the transition characteristics of servo actuators. Accelerated degradation test at high temperature stresses is designed and carried out. Three grades of lubricating grease with different base oil systems, including soap based, non-soap based and mixed lubricating grease are investigated for their theological properties. The rheological properties of different lubricating grease changed in thermal aging time and temperature stress are analyzed. It is found that the viscosity of lubrication dose not change unidirectionally with the increase of thermal aging time. In addition, the rheological properties of mixed lubricating grease at high temperature is better than that of soap based lubricating grease and non-soap based lubricating grease, which is valuable to evaluate the properties of lubricating grease during long-term storage of aerospace electromechanical servo system.

With the increasing frequency of human space activities, there are surviving debris of re-entry spacecraft and debris that impact the Earth's surface, causing typical damage cases and affecting the future technological development of spacecraft. Firstly typical re-entry damage cases and disposal methods of foreign spacecraft that have attracted significant social attention are analyzeds. Secondly the main international norms and standards for re-entry casualty risk are introduced. Then those assessment methods of re-entry casualty risk are studied together with re-entry risk analysis tools of NASA and ESA. Finally it's looked forward to the furture development and existing problems of major space powers in the technical directions of active deorbit, assisted deorbit, large-scale reentry, and reusable spacecraft. Research shows that although the re-entry casualty risk of spacecraft and debris is still difficult to predicte very accurately, it is expected to be moderately controlled by the design of risk-reduction measures along with technological development.