Aiming at the deformation matching damage problem of the arrayed bonded thermal insulation tile assembly, this study extracts four typical aircraft skin deformation conditions, combines with Digital Image Correlation (DIC) technology and force-displacement synchronous measurement methods, conducts experiments and obtains quantitative results.​The results show that when the skin is depressed in a large area, the 80% compression of the gap between tiles is the compaction threshold of the filler strip, exceeding this threshold will cause local extrusion damage at the edge of the thermal insulation tile, and this threshold can be used as the safety upper limit for the gap design of thermal insulation tiles. When the discontinuous skin undergoes relative deformation, the thermal insulation tile will flip and become unstable after 60% compression of the gap between tiles, and debonding failure occurs in the bonding layer; the corresponding deformation can guide the skin deformation control of the docking areas such as the cabin door and the airframe. When the skin is locally depressed, debonding failure occurs in the bonding layer and spreads rapidly from the middle of the thermal insulation tile to the edge within 2 seconds. When the skin is locally bulged, debonding damage occurs in the bonding layer and spreads rapidly from the edge of the thermal insulation tile to the center after approximately 10 seconds; the corresponding deformation thresholds can guide the stiffness design of the skin in local areas such as access panels. The results of this study can guide the deformation matching design of thermal insulation tile assemblies, and the experimental scheme can provide references for similar designs and verifications.

Addressing the issues of low reliability and severe wear of dynamic seals in high-speed aircraft under extreme thermal environments, this study focuses on high-temperature dynamic sealing performance testing technology and develops an integrated testing system to validate the performance of novel multi-material composite seals. An independently designed integrated testing platform for high-temperature wear and sealing is developed to comprehensively evaluate the friction coefficient, sealing performance, and compression resilience of seals under high-temperature conditions. Experiments demonstrate that the developed testing system operates stably in high-temperature environments up to 800 ℃, yielding highly reproducible test data. The system provides an effective experimental means for performance evaluation and optimization of high-temperature dynamic seals.

EEPROM as a core non-volatile memory device in critical systems such as aerospace, automotive electronics, and industrial control, its long-term reliability is directly related to the data security of the equipment. Traditional static burn-in (BI) technology only use high temperature and bias voltage to accelerate failure, which is difficult to simulate the electrical stress damage under the actual dynamic working state, and the fault coverage is limited. Dynamic BI technology can effectively activate early failures by simulating real workloads, thereby improving the reliability of the device. XX28C010 device is taken as the research object. Firstly, the working principles of dynamic and static BI, device working principles and graphic algorithm are introduced, then the system architecture, test algorithm program and hardware design are introduced, and finally the test results are analyzed, which provide a reference for the research on dynamic BI technology of EEPROM.

With the wide application of cognitive technology in the military field, cognitive Electronic Warfare (EW) has become the inevitable trend of future military war. Given the development of EW combat object in the cognitive direction leading to a decline in the operational effectiveness of traditional EW, an in-depth exploration and analysis of key technologies in cognitive electronic warfare are conducted, including cognitive reconnaissance, cognitive jamming, jamming evaluation, and dynamic knowledge base. Moreover, the basic concepts of cognitive EW are sorted out, by analyzing the numerous challenges to traditional EW. Then, the system architecture and composition of cognitive EW are studied. On this foundation, the key technologies of cognitive EW are summarized. Finally, based on the characteristics of cognitive EW, the development direction of cognitive EW has been prospected.

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.

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.

Aerodynamic configuration design is an important technology for hypersonic vehicles. Combined with other relative specialties, it is the key to obtain good flight performance and ensure essential flight quality. As a fundamental research area of modern hypersonic vehicles, air-breathing vehicle has become an indispensable way to realize the sustainable hypersonic flight. The typical hypersonic air-breathing vehicles are focused on and the design concept of configurations is investigated. Proposed from the perspective of combined-cycle propulsion systems, the relationship between propulsion systems and aerodynamic configuration is studied which provides a reference for the aerodynamic configuration design work.

Aiming at the problem of rapid repair of the debonding defect between the solid rocket motor insulation layer and the case in the battlefield environment, a comparative performance analysis of the bonding materials required for the rapid repair of the debonding between the nitrile rubber insulation layer and the steel case is carried out through experiments, and the adhesives suitable for the corresponding conditions and performance requirements are screened out. Firstly, combined with the requirements for the rapid repair of the debonding between the solid rocket motor insulation layer and the case, the curing conditions and performance indicators required for the adhesives used for rapid repair are analyzed. Further, mechanical property and ablation tests of 11 kinds of adhesives from three major categories, namely acrylate, epoxy resin, and silicone, are conducted. Finally, a grouting machine for rapid repair is designed and a fluidity test is carried out. The test results show that the X701-1 adhesive can meet the curing conditions and performance requirements for the rapid repair of the debonding between the nitrile rubber insulation layer and the steel case.

The sparse reconstruction theory can obtain distance information in the emitters localization. In the case of traditional emitter sparse reconstruction poor algorithm performance and off grid, an Off-Grid and multiple emitters direct localization algorithm are proposed based on GDP distribution and Sparse Bayesian Learning (SBL). This GDP-SBL-DPD algorithm assumes that the reconstructed signal follows a Generalized Double Pareto (GDP) distribution and leverages a coarse-to-fine search and signal hyper parameter quadratic updating method to enhance the performance of Emitters Direct in off-grid scenarios. Simulation results demonstrate that the GDP-SBL-DPD algorithm outperforms the grid mismatch algorithms based on Orthogonal Matching Pursuit (OMP), Alternating DirectionMethod of Multipliers (ADMM), and SBL coarse-to-fine search in multiple emitters grid mismatch scenarios, with higher accuracy and stronger robustness.

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.