To address the engineering challenge of reduced accuracy in dynamic load identification in the thermal-vibration coupled environment of high-speed vehicle due to environmental interference, this study establishes a test platform for random load identification that considers thermal-vibration coupling effects. This platform integrates a shaker and a quartz lamp array to achieve precise application of random and thermal loads, respectively, and combines high-temperature accelerometers to measure dynamic responses under ground-based thermal conditions. To account for temperature effects, a random load identification method in thermal environments based on Tikhonov regularization is proposed. By incorporating model corrections that consider thermal effects and introducing a frequency response function deformation matrix into Tikhonov regularization to account for the application conditions of random loads, the method is used to perform inversion analysis on structural dynamic response data. Finally, comparative experiments were conducted under normal temperature (20 ℃) and high temperature (500 ℃) conditions. The results indicate that the platform can effectively simulate the thermal-vibration coupled test conditions of an aircraft and meet the requirements of load inversion in thermal-vibration coupling states. Based on load inversion results, it is concluded that the effects of thermal environment on structural parameters and thermal disturbance noise are key factors affecting load identification accuracy, providing a theoretical foundation and experimental support for the development of random load identification technology in complex thermal-vibration coupled environments.

The aircraft often faces a complex dynamic load environment during service, and its measurement cost is high and difficult to obtain by direct measurement. Dynamic load identification based on dynamic response information has become a feasible solution to obtain structural input. In this paper, the dynamic load identification problems of aircraft are reviewed from three aspects: “cognition, measurement and identification”. Firstly, the load characteristics at typical positions such as wings, tail, rudder surface, fuselage, and landing gear of the aircraft are analyzed, which provides necessary prior information for the subsequent selection of response measurement technology and the determination of dynamic load identification methods. Secondly, the main measurement techniques, application scenarios, advantages and disadvantages of aircraft structural response are summarized. Then, the research progress of aircraft dynamic load identification method is reviewed. Finally, the main challenges and future development trends in the field of dynamic load characteristics, measurement and identification of aircraft structures are discussed.

Aerospace vehicles represent a new class of equipment with highly integrated structural and electromagnetic characteristics. This integration demands the seamless fusion of load-bearing, high-temperature resistance, and other mechanical properties with advanced electromagnetic functionalities such as wave transparency, stealth, and radio frequency. Such a combination is essential to meet the complex and demanding requirements of modern aerospace applications. First, this paper conducts a comprehensive analysis of the primary features and practical requirements of aerospace vehicles. Through meticulous research and study, a tetrahedral design framework is established that integrates Load-bearing, Wave-transparent, Stealth, and Radio-frequency (LWSR). The scientific implications of the functions at each vertex of the tetrahedron are elaborated in detail, providing a profound understanding of the underlying principles and mechanisms. Second, the latest advancements in three typical types of electromagnetic functional structures for aerospace vehicles are reviewed, including radome structures, stealth skin structures, and integrated conformal antenna structures. Finally, the future development trends of electromagnetic functional structures for aerospace vehicles are thoroughly explored, discussing key challenges such as multi-physical field coupling, adaptation to extreme environments, multifunctional integration, intelligent perception and response, and control mechanisms.

High Mach flight has put forward more stringent requirements for the material and structure design of new generation of high-speed vehicles. This paper reviews the application of ceramic matrix composites（CMCs） in the structural design of aircraft from the aspects of selection, application, and evaluation, and then the future development direction is put forward to provide reference for aircraft ceramic matrix composite structure design. The selection criteria and corresponding preparation methods of CMCs in different application scenarios are comprehensively reviewed, the typical applications of CMCs in aircraft structures are systematically introduced, and the evaluation criteria and ground test methods of the materials under near-service conditions are analyzed. To order to meet the future demands of aircraft, it is necessary to integrate computer-aided optimization technology and innovative preparation methods to enhance the temperature resistance and fatigue performance of CMCs. Developing highly reliable, long-life joining techniques and integrated design solutions will fully leverage the advantages of these materials. Additionally, in-situ characterization techniques under multi-physical field coupling need to be developed to obtain the performance evolution behaviour of CMCs in actual use, providing a reliable basis for the lightweight structural design of aircraft.