With the increasing complexity of aviation equipment and the transformation of maintenance modes， structural digital twin technology has become a key enabler for structural health management and predictive maintenance. Addressing common challenges in digital twin modeling-such as modeling assumption deviations， input uncertainty， and model response mismatch-this study proposes a residual-driven model optimization mechanism based on multi-parameter flight measurements. A dynamic closed-loop framework of “measurement–calibration–residual feedback–model correction” is established， with a rigorous theoretical proof of the residual feedback mechanism’s convergence and a quantitative analysis of error upper bounds. Furthermore， a multi-dimensional， quantifiable evaluation index system for model self-evolution is developed. Engineering verification， using the tail of a certain aircraft as an example， demonstrates that the proposed method effectively reduces model prediction errors under complex operating conditions and improves the accuracy and robustness of fatigue life prediction. The research outcomes provide theoretical support and methodological foundations for the engineering application and intelligent development of structural health management in aircraft.

As a strategic emerging industry， low-altitude economy is a new track for industrial development and a new engine for economic growth. Urban Air Mobility （UAM） is an important part of low-altitude economy. To gain insights into the key technological research trends and development dynamics within the UAM sector， identify hot topics of research， and unveil the knowledge structure and research scope in Urban Air Mobility. This includes exploring the technological evolution pathways and future application prospects to acquire a profound understanding of the current state of Urban Air Mobility research. A bibliometric analysis was conducted on data retrieved and extracted from the Web of Science Core Collection （WoSCC） database. From the result， UAM research forms a comprehensive framework from technology （e.g.， collision avoidance， high-precision positioning， plus-cruise vertical take-off， dynamic airspace sectorization， etc.） to operations （e.g.， urban air mobility operations， unmanned aerial vehicle logistics route network， hyper-local weather prediction） low-noise landing conditions and consumer intention. The aim is to achieve a safe， efficient， and environmentally friendly urban air traffic system， key technologies that face the unique challenge of addressing the complexity of low altitudes in cities， and the importance of air traffic management and environmental impact should be strengthened during the development of the urban air mobility.

As one of the most promising types of Unmanned Aerial Vehicles （UAVs） powered by new energy sources， hydrogen-powered UAVs are closely linked to the concept of green aviation and low-altitude economic scenarios. To provide a reference for the design of hydrogen powered UAVs， this paper summarizes the key areas and technical issues involved in the development of hydrogen powered UAVs， and reviews relevant research. The review first outlines the development history， technical advantages， application scenarios， and common examples of hydrogen powered UAVs. Subsequently， it categorizes and discusses the key issues related to hydrogen powered UAVs in four major technical areas： overall design technology， structural design technology， power system design technology， and flight control technology. Moreover， the technical frontiers faced in each area and the current research conducted by researchers both domestically and internationally are analyzed. Finally， combining the relevant technological advancements， the paper proposes suggestions and outlooks for the development of hydrogen powered UAVs. The research indicates that the development potential of hydrogen powered UAVs has not been fully explored， and joint efforts across multiple disciplines and fields to leverage hydrogen’s crucial role in extending UAV endurance are required so as to reduce onboard weight， and promote green aviation development.

With the rapid development of China’s low-altitude economy and the planning requirements outlined in the “14th Five-Year Plan”， low-altitude transportation is expected to become a significant mode of transport. However， the current low-altitude airspace remains largely undeveloped and not fully open in China. As a result， related studies on airspace and trajectory planning are still in their early stages， and are difficult to meet the surging demand for low-altitude operations. Therefore， it is essential to establish a robust and comprehensive theoretical framework for airspace and trajectory planning according to the unique characteristics of low-altitude environments. This paper firstly examines the fundamental characteristics of low-altitude airspace and systematically reviews the research on the limiting factors of low-altitude airspace planning， airspace designation， and trajectory planning both domestically and internationally. Existing findings and gaps in current research are discussed， and common challenges in the field are also highlighted. Next， the feasibility of employing block or tube airspace designation methods is assessed in the context of China’s current low-altitude development. A developmental trajectory that evolves from individual trajectories to trajectory clusters and ultimately to trajectory networks is proposed， emphasizing the need for accelerated technological integration to innovate airspace infrastructure. Finally， this paper outlines three key elements that should be prioritized for future low-altitude airspace and trajectory planning： first， incorporating environmental and social factors as central elements in airspace planning； second， exploring phased airspace designation， composite designation strategies， and specialized planning methods； third， designing generalized fast algorithms for trajectory planning to accommodate diverse operational scenarios.

Multisource information fusion has undergone decades of development， expanding from classic signal processing issues to a multidisciplinary frontier field and covering a wide range of applications such as aerospace， intelligent transportation， industrial engineering， and security. This paper starts from the definition and principles of multisource information fusion， reviews the main development stages of information fusion technology， and summarizes the research progress of four basic scientific issues： fusion detection， fusion recognition， fusion estimation， and fusion association. The technology of multisource image fusion and machine learning methods oriented towards information fusion are also outlined. Based on this， the typical applications of information fusion in several fields are introduced. Finally， the development direction of information fusion technology and its applications are discussed.

Cooperative technology is the effective guarantee and approach for swarm systems to execute tasks and generate intelligence. The core of intelligent cooperation of swarm systems lies in the information exchange between individuals to complete complex cooperative behaviors， thereby achieving a significant improvement in overall task efficiency. By sorting out the functions and supporting relationships required for cooperative task execution in swarm systems， five key technologies required for swarm systems to complete tasks cooperatively are summarized. They are self-organizing interaction technology， cooperative perception technology， cooperative cognitive technology， cooperative decision-making technology， and cooperative guidance and control technology. An Interaction-Observation-Orientation-Decision-Action （IOODA） technology architecture for intelligent cooperation in swarm systems is proposed. The concept and connotation of the intelligent cooperative IOODA technology architecture for swarm systems are presented. The key technologies involved in the IOODA technology architecture and the existing progress are reviewed. The challenges faced by the IOODA technology system are analyzed， and prospects for future development of various key technologies are also discussed.

In the future， urban low altitude may face a large number of demands for operation of electric Vertical Take-Off and Landing （eVTOL）， which will result in potential problems of low airspace utilization， high collision risk， etc. To ensure the safety and efficiency of aircraft operation， it is necessary to establish appropriate safety interval standards. To study the safety interval of multi-model eVTOL in urban low altitude， a classical Event longitudinal， lateral and vertical collision model is established for composite-wing eVTOL， and an improved Event model based on the frustum of the cone collision box is established for multi-rotor eVTOL. The eVTOLs are classified into three categories of light， medium and heavy types according to their payload and number of passengers. The mainstream models are selected for statistical analysis， and the collision box sizes of the models are calculated. Considering the positioning error， the longitudinal， lateral and vertical overlap probability of the aforementioned parameters is calculated using the concept of Required Navigation Performance （RNP）. A simulation environment is established to calculate the parameter of relative velocity， taking into account the distribution of heading angle， pitch angle limitation， and velocity error distribution. Finally， the lateral， longitudinal and vertical safety intervals of different types of eVTOLs are calculated according to the established collision model. The target level of safety of light， medium and heavy eVTOL are set to 10^-7， 10^-8 and 10^-9 times/flight hour， respectively. The minimum intervals between different types of eVTOL are finally derived. These intervals are determined to be 82， 83， 93， 102 m， respectively， for light multi-rotor， light composite wings， medium composite wings， and heavy composite wings. The results of the study can provide a reference for the development of eVTOL interval standards.

To address the multidisciplinary coupling problem faced by the air-breathing hypersonic airframe/propulsion integrated design， a two-layer multidisciplinary optimization design method is proposed based on flight mission requirements and considers aerodynamics， trajectory， and control. Firstly， an optimization method for the geometric parameters is established using sequential quadratic programming to optimize the flight performance such as flight range and duration， with controllability as the constraint. Then， by solving the Reynolds Average Navier-Stokes（RANS） equations， the aerodynamic characteristics of the selected shape is obtained. With the obtained aerodynamic data， a mapping model from geometric parameters to aerodynamic characteristics is constructed. Subsequently， based on the existing dynamic data， a thrust model of the scramjet engine considering the influence of forebody parameters and nozzle parameters is established. After that， an internal trajectory optimization method is proposed. This method maintains the same optimization objective and constrain as geometric parameter optimization， and adopts the direct shooting method for discrete and the SQP algorithm for optimization. In addition， a control simulation model is constructed based on， which was combined with the to establish an aerodynamic， trajectory and control integrated design method inner trajectory optimization and outer parameter optimization are combined and the Active Disturbance Rejection Control （ADRC） technology is used evaluate trajectory controllability， achieving two-layer multidisciplinary optimization for airframe/propulsion integrated design. Finally， optimization of the shape parameters and aircraft trajectory of the SR-72-like hypersonic vehicle are carried out to achieve the optimal range. The optimization results show that the maximum range is increased by 28.98% during the whole flight mission， demonstrating the effectiveness of the proposed method.

Aircraft engine is the core key to achieving comprehensive improvement in combat capabilities of advanced fighter jets. The increasing requirements for high performance， high reliability， long lifespan， and good maintainability of fighter jet engines have posed significant challenges to the development of aircraft engine technology and products. This article focuses on the core technical requirements of advanced fighter jets for aviation engines in seven aspects： comprehensive temperature control， rotor structure system robustness， full authority digital control， aircraft-engine thermal management， health management， thrust vectoring， and high stealth. The technical paths and main key technologies for meeting these requirements are analyzed， which can provide technical support for the development of advanced aviation engines.

The rapid development of Unmanned Aerial Vehicle （UAV） technology has led to its continuous expansion in military and civilian fields， gradually becoming a powerful engine driving the development of low-altitude economy. Among the core components of UAVs， the satellite navigation system provides precise positioning and navigation information. However， due to the vulnerability of the satellite navigation system， satellite navigation often faces severe challenges brought by complex electromagnetic environments， causing UAVs to lose their positioning ability or deviate from the planned route， thereby seriously threatening flight safety and mission success rate. This paper systematically reviews the research status of anti-jamming technology for UAV satellite navigation systems. Firstly， starting from the main navigation interferences faced by UAVs， it analyzes the impact of oppressive interference and deception interference on UAV navigation systems. Secondly， it comprehensively summarizes the anti-jamming methods of UAV satellite navigation terminals. Regarding anti-oppressive interference， this paper focuses on discussing the technological progress at the receiving antenna end， radio frequency front end， and signal processing end. In terms of anti-deception interference， the methods of enhancing receiving processing capabilities and using advanced algorithms to detect and suppress deception interference are analyzed. In addition， the study studies the anti-jamming methods for UAV navigation in denied environments， including inertial navigation， visual navigation， celestial navigation， ultra-wideband， magnetic field navigation， radar navigation， and multi-information fusion navigation technologies. Moreover， for the formation navigation of multi-UAV clusters， the methods of inter-UAV cooperative and system improvement were explored to enhance the anti-interference capability of the entire UAV group. Finally， this paper identifies the current problems， outlines future research directions， and discusses potential technological advances. The research results of this paper not only provide a reference for the continuous progress of UAV navigation anti-jamming technology， but also offer theoretical and practical guidance for academic exploration and engineering application in related fields.

This article addresses the problem of time-coordinated strike against weakly maneuvering targets. The implicit cooperative guidance problem based on the constant velocity motion model and the explicit cooperative guidance problem based on the velocity time-varying model are studied to enhance the breakthrough and destruction capabilities of anti-tank missiles against high-value targets. Firstly， based on the assumption of missile motion at a constant velocity， the idea of predictive correction and the optimal error dynamics theory are employed. Time-constrained bias terms are added to the proportional navigation guidance law， and a time-constrained guidance law is derived based on optimal error dynamics. An implicit time-coordinated guidance law scenarios depending weakly on communication is then proposed. To address the issue that inaccurate time prediction affects the performance of implicit cooperation caused by variable speed missile strikes， a neural network-based explicit time-coordinated guidance method is further proposed. This method adopts the predictive correction guidance framework， and designs the predictor by using transfer learning integrated neural networks according to the characteristics of proportional navigation guidance law to accurately predict the remaining flight time. Consistency dynamics with specified time convergence is proposed to coordinate the lengths of missile trajectories in the distributed communication architecture， ensuring that multiple missiles simultaneously hit the target. Simulation results show that the proposed implicit time-coordinated guidance method can ensure that multiple missiles simultaneously hit the target accurately， and the neural network-based explicit time-coordinated guidance method proposed can ensure coordinated strikes against multiple missiles under variable speed conditions.

Advanced manufacturing theory and technology are the cornerstone of technological progress and social development， as well as the foundation for supporting the aerospace industry and national defense construction. They are also the key to promoting innovation in high-end equipment. However， with the development of new materials and new structures， traditional manufacturing techniques are unable to meet the processing requirements of key components in the aerospace industry. Therefore， advanced manufacturing theory and technology have become an important research direction in the aerospace field， experiencing rapid development. This paper first introduces the connotation and characteristics of advanced manufacturing theory and technology in aerospace. Besides， it summarizes the basic principles， application areas， and application material scope of typical advanced manufacturing theories and technologies in the aerospace field， such as high/ultra-high speed machining， precision forming manufacturing， micro and nano machining， atomic and near atomic scale machining， modern special machining， rapid prototyping manufacturing， and green manufacturing. Secondly， the latest research progress in advanced manufacturing theory and technology is summarized， Including high speed and efficient machining technology， high performance composite machining technology， intelligent control machining technology， large scale， miniaturization， and emerging material technology. Then， the main challenges and future development trends faced by current advanced manufacturing theories and technologies are discussed in depth. Subsequently， the engineering application and design manufacturing integration of advanced manufacturing theory and technology are elaborated， and its important position in the aerospace manufacturing field is emphasized. Finally， the frontier fields involved in the new generation of advanced manufacturing theory and technology in aviation and aerospace are analyzed， and the principal development points for the future are clarified， the pivotal development directions are indicated.

With the development of the low-altitude economy， Urban Air Mobility （UAM） confronts the challenges in risk management and efficiency due to dense flight operations. This study addresses the pre-flight phase of urban low-altitude Unmanned Aerial Vehicle （UAV） swarms， and introduces a two-stage optimal scheduling approach for flight plans utilizing complex network. Initially， considering the potential third-party risks of UAV flight， the four-dimensional trajectory for individual UAVs is pre-planned within a digital airspace grid environment to generate an initial four-dimensional flight plan for the UAV swarm. Subsequently， to address flight uncertainty， a conflict detection model is proposed to construct a complex network where flight plans are nodes and conflicts are edges. Important flight plans are identified by analyzing topological metrics of the complex network. Finally， an integrated flight plan optimal scheduling model is established， incorporating strategies such as ground holding， speed adjustment， and local re-routing. A two-stage optimization algorithm frame is developed to globally optimize key flight plans and then locally adjust remaining conflicts， and is solved based on the improved Fata morgana algorithm. Experimental results demonstrate that this method can significantly reduce or eliminate flight conflicts considering flight uncertainty， ensuring that delayed flight plans constitute no more than 3% of the total and increasing operational risk by no more than 1%. These findings offer technical support for urban low-altitude flight plan scheduling management， and are instrumental in fostering safe and orderly progression of urban air traffic.

The aero-engine， with the multi-electric technology as its new feature， optimizes the system’s multiple energy architectures and significantly improves system maintainability and reliability， which is now a core component of the multi-electric aero-engine research field. As the power generation system jumps from the hundred kW level to the MW level， the high-power， highly integrated multi-node power distribution system and the power-using system including high-power pumps and actuators together constitute a complex multi-electric control system. This system is characterized by multi-nodes and superposition of dynamic and static changes， and is facing the challenges in different application environments. Based on the electrification foundation， this paper firstly classifies the source-grid-load architecture of the aero-engine multi-electrical control system， and elaborates on the basic concepts， compositional characteristics， and challenges of the source， grid， and load systems. Then， the source-grid-load integrated system is analyzed， and the research status of four key technologies， the lightweight and high-reliable motor technology， power conversion topology and motor drive control， multi-node microgrid networking and control research， and electromagnetic compatibility modeling analysis and suppression methods， is comprehensively analyzed. Finally， the development trend of source-grid-load system and the layout of multi-position architecture are summarized and the prospects are discussed to promote the development of aero-engine multi-electrical control system.

Undesirable model vibration often occurs in a conventional wind tunnel force test. Large amplitude model vibrations may adversely affect test data and even threaten the safe operation of equipment. It is therefore of great importance to fully understand the mechanism of model vibration occurrence and reduce the vibration amplitude by effective means in wind tunnel tests. This paper first introduces the harms of model vibration， followed by a summary of model vibration types. The progress of reducing model vibrations by various methods are then presented， and the key points and technical difficulties involved in the active control method analyzed. The existing literature shows that the active control method with the piezoelectric stack as the actuator can best meet the requirements of the engineering practice， with better vibration damping effect than others. Finally， suggestions regarding future research on model vibration control in large-scale wind tunnels are presented.

Generative models， which have achieved disruptive applications in the fields of natural language processing and computer vision， are becoming the cornerstone of digital intelligence technologies， serving as a crucial engine driving the future development of intelligent aircraft technology. This paper reviews the application progress of aircraft technologies empowered with generative models. Firstly， the development history of generative model architectures is summarized. Detailed introduction to the fundamental principles and improvement directions of variational autoencoders， generative adversarial networks， diffusion models， and Transformers is provided. Secondly， typical applications and transformative impacts of generative models in aircraft aerodynamics， trajectory prediction， and target detection are generalized， with a focus on the development trends in key technologies of aircraft aerodynamic design， including parameterized modeling， aerodynamic prediction model and inverse design.Intelligent implementation methods of real-time trajectory prediction， complete trajectory prediction， collaborative trajectory prediction and prediction error compensation are studied. From the perspective of improving existing target detection methods， the roles of generative models in multi-scale fusion， super-resolution enhancement and data enhancement are analyzed. Finally， we propose future research directions for aircraft technologies empowered with generative models from the perspectives of model method and application scenario expansion. Development suggestions are proposed for building interpretable general models and promoting vertical domain applications.

Since the end of the last century， the phenomenon of aircraft icing in Supercooled Large Drop （SLD） icing conditions （14 CFR Part 25 Appendix O） have attracted much attention. Its impact on flight safety is worse than that under atmospheric icing conditions （14 CFR Part 25 Appendix C）. The successive promulgation of Amendment of FAR 25-140 and EASA CS-25 16 indicates that the implementation of SLD icing airworthiness compliance verification is a mandatory condition for China’s large civil aircraft to obtain European and American airworthiness certificates. The simulation of SLD icing conditions is a pre-requisite for the ground SLD icing test， and is very important for the design of SLD anti-icing system and the verification of icing test. In this paper， the typical characteristics of the drop diameter distribution simulation under the icing conditions of SLD， namely， large drop diameter span with bimodal distribution and low Liquid Water Content （LWC）， are analyzed. The research and development of the simulation methods of drop diameter distribution under SLD icing conditions in the world’s major icing research institutions in the past 30 years are reviewed. It is found that the technology for simulating the drop diameter distribution of Freezing Drizzle （FZDZ） mainly goes through four stages： increasing the Median Volume Diameter （MVD） of the spray， alternately producing MVD clouds with different sizes， regulating water pressure and simultaneously producing clouds with different MVD， and using two sets of independently controllable MVD cloud generation systems. Simulation of the drop diameter distribution for Freezing Rain （FZRA） is even more challenging and is still in the initial stages of development. The main achievements are introduced and the problems are discussed. Finally， the research direction， key technical problems and solutions of drop diameter distribution simulation in SLD icing conditions are discussed.

To ensure the efficient matching of the supersonic Bump inlet with the engine across the entire flight envelope， this paper explores the dominant mechanism for enhancing its stable operational margin. Taking the four-lip forward-swept cowl Bump inlet as the subject of study， the evolution of the three-dimensional flow structure from supercritical to subcritical conditions at the designed Mach number is analyzed. The research findings indicate that under low mass flow （or high back pressure） conditions， the interaction between the normal shock and the boundary layer on the compression surface of the inlet， which combines a forward-swept cowl and a conical bump， generates a three-dimensional separation vortex that is expelled to the exterior of the inlet entrance. In contrast， an inlet with the same forward-swept cowl combined with a flat wedge experiences a “quasi-two-dimensional” flow separation under low mass flow conditions， with most of the separated flow being ingested into the inlet to result in a narrower stable margin as compared with the Bump inlet. Therefore， the generation of a three-dimensional separation vortex and its expulsion out of the entrance of the duct is the core mechanism for enhancing the aerodynamic performance of the Bump inlet and broadening its stable operational margin.

The assessment of hypersonic flight technology at home and abroad always relies on flight tests， which are time-consuming and expensive， and have posterior risks. The development of advanced hypersonic ground test facilities has been a fundamental research topic in aerodynamics frontier for decades； however， the existing test facilities are still inadequate for the required technology development of air-breathing hypersonic engines at high Mach numbers. The successful development of the JF-22 hypervelocity wind tunnel under the National Major Scientific Research Instrument Project supported by the National Natural Science Foundation of China is a major breakthrough in this area. This paper first reviews the research background of the hypersonic wind tunnel and introduces the four basic requirements of the wind tunnel based on engineering practice. Considering thermo-chemically reacting gas flows， the necessity of revolutionary change of the wind tunnel test simulation criteria of experimental aerodynamics from “flow similarity simulation” to “flight condition reproduction” is discussed. Then， the theories and technologies for detonation-driven hypervelocity shock tunnels are systematically expounded， and the engineering problems solved with the theories and technologies are also discussed. Finally， the technology system of the JF-22 hypervelocity wind tunnel， developed on the basis of these theories is summarized and evaluated with the JF-22 calibration results. These results not only verify the theories of detonation-driven hypervelocity shock tunnel， but also show a comprehensive assessment of the JF-22’s technology system. The success of the JF-22 hypervelocity wind tunnel is a new milestone in developing advanced hypersonic test facilities. The JF-22 remarkable performances， such as high flow velocity， high total temperature and high stagnation pressure， and wide speed range and altitude are of significance for supporting the research on air-breathing hypersonic engines， aerospace aircrafts， and the frontier of high-temperature gas dynamics.

As one of the fastest-growing directions in deep learning， the generative model has achieved remarkable success in realms such as computer vision and has also introduced novel paradigms and methodologies for research endeavors within the scientific fields like aerodynamics. This paper focuses on the latest research advancements of generative models in the field of aircraft aerodynamic configuration design， and systematically summarizes the relevant research achievements in recent years. Firstly， a representation-generation-evaluation framework for generative aerodynamic configuration design of aircraft is established. Subsequently， the key technologies and current development progress involved in aerodynamic configuration design are examined and discussed from the perspectives of aerodynamic configuration representation， the development of generative aerodynamic configuration design models， and methods for evaluating design quality. Additionally， a brief overview of aerodynamic data construction methods and typical datasets is provided， serving as a data foundation for generative aerodynamic design. Lastly， the future key development directions in the field of generative aerodynamic configuration design are discussed， including exploration of hybrid generative model architectures， construction of large models and domain-specific agents for aerodynamic design， establishment of a comprehensive evaluation system for generative aerodynamic design quality， and integration of domain knowledge into generative aerodynamic design models.