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Introduction of Aerospace Technology
Chinese Name:空天技术
English Name: Aerospace Technology
Publication cycle: Bimonthly
Language: Chinese
Director: China Aerospace Science and Industry Corporation Limited (CASIC)
Sponsor: Beijing HIWING Scientific and Technology Information Institute
Editor in chief: LIU Haifeng
Review on landing mechanism of reusable launch vehicle for vertical take-off and landing
Dou Jicai;Xie Weiqi;Cheng Long;Yang Jianrui;With the growing demand for rocket launches, the high launch costs of traditional launch vehicles have severely constrained the development of spaceflight. Rocket reusability technology, as a key technology that can significantly reduce launch costs and improve resource utilization efficiency, has become a research hotspot in the current aerospace field. A review, analysis, and comparison method is adopted for the landing mechanism of vertical take-off and landing reusable launch vehicles. Key aspects of its structural configuration, damping materials, and dynamic analysis are studied and the main principles and methods of these technologies are elaborated, along with their advantages, disadvantages, inherent relationships, and future optimization directions. Insights are presented regarding the development of vertical take-off and landing reusable launch vehicle landing mechanisms. The conclusion highlights that the development of landing systems must be driven by multidisciplinary integration as the core force. Through innovative configurations, material breakthroughs, and optimized dynamic models, it provides critical technological support for enhancing the reliability and economic viability of reusable launch vehicles.
The application of intelligent algorithms in the identification of aerodynamic parameters of aircraft
Cui Han;He Kaifeng;He Zhengchun;Yao Xiongliang;Aerodynamic parameter identification for aircraft is a technique that reverse-engineers aerodynamic characteristics in real flight environments through kinematic responses during flight. It constitutes a core component in aircraft dynamics modelling, aerodynamic design, and performance evaluation. The advantages of applying intelligent algorithms to aircraft aerodynamic parameter identification are discussed. The application progress of two categories of intelligent algorithms are reviewed systematically: Intelligent optimisation and machine learning, in core algorithms for aerodynamic parameter identification. It further summarises research dynamics, algorithmic complementarity forms, and identification capability enhancement strategies in the field of composite intelligent algorithms, which integrate multiple intelligent algorithms. Three future development trends are anticipated: Introducing novel intelligent algorithms, exploring multi-algorithm fusion, and advancing intelligent online identification techniques. This provides valuable reference for innovative applications and development of intelligent algorithms within this domain.
Study on the optimization design of variable cross-section heat pipe for high-speed aircraft nose cone structure
Li Fugui;Chen Qiang;Fei Qingguo;Li Yanbin;To meet the thermal protection requirements of high-speed aircraft nose cone structure, a variable section heat pipe structure with varying diameter along the length direction is proposed to achieve an effective balance between structural form and thermal management performance. The effects of filling rate, angle and thermal power on the performance of variable section heat pipes are analyzed. Based on the radial basis neural network agent model and non-dominated sorting genetic algorithm, a dynamic iterative optimization design scheme was proposed to optimize the variable cross section heat pipe with liquid filling rate, angle and thermal power as design variables, and heat pipe isothermal and heat transfer performance as optimization objectives. The results show that when the angle of the heat pipe is small, the increase of the angle helps to reduce the equivalent thermal resistance, but when the angle exceeds the critical value, the equivalent thermal resistance will increase significantly. The proposed dynamic iterative optimization scheme significantly improves the optimization efficiency. Compared with the initial design, the optimized isothermal performance is improved by 34.43%, and the heat transfer performance is improved by 33.88%.
Design and thermal deformation analysis of adjustable thermal expansion sandwich structure
Wei Yanjing;Dai Ting;Thermal protection system plays an important role in dealing with the harsh thermal load conditions of aircraft flying at high speed. According to the performance requirements and structural characteristics of the thermal protection system, a dual-material coordinated composite structure with adjustable thermal expansion property is proposed. The influence factors of deformation coordination combination are obtained through mechanical derivation, and the thermal protection structure design of sandwich is carried out. The basic model is compared with the traditional sandwich structure, and the thermal response mechanism is studied numerically from the key design parameters such as the selection of the sandwich structure material, the cross section area of the core rod and the angle of the core rod. The results show that the designed sandwich structure can effectively reduce the thermal expansion amount when it is subjected to thermal load. By adjusting the design parameters of the sandwich structure, the thermal expansion coefficient of the designed sandwich structure can be changed from positive to negative. When the thermal expansion performance gap between the two materials is larger, the cross section area of the core rod is smaller and the angle of the core rod is smaller, which means the concave configuration of the structure is more obvicus. The negative thermal expansion effect of the structure is better.
Design of terminal sliding mold guidance law based on depth deterministic strategy gradient adjustment
Xu Changji;Wei Xuefei;Liu Wangang;Aiming at the problems of complex and changeable flight environment, high-frequency angle jitter and difficult dynamic response characteristics of traditional sliding mode guidance law in response to high maneuvering targets, this paper proposes a nonsingular adaptive terminal sliding mode(NATSM) guidance strategy based on sliding mode variable structure control theory and deep deterministic policy gradient(DDPG) algorithm, combined with nonlinear disturbance observer(NDO) and adaptive gain super twisting algorithm(AGSTA). This method can dynamically adjust the gain parameters of the sliding mode variable structure, so as to improve the adaptability of the system in complex environment. The simulation results show that the designed guidance law can effectively reduce the fluctuation of terminal inclination rate, has better stability than the traditional sliding mode guidance method, and has higher control accuracy and environmental adaptability for the precise attack of high-speed maneuvering targets.
Investigation on the ground proximity separation of a parallel arrangement vehicle based on CFD/RBD coupled method
Luo Xingdong;Hou Zihao;Yuan Ya;Bo Jinglong;Zhai Maochun;Li Shaowei;Zhang Shenrong;To meet the safety analysis requirements for ground proximity separation of parallel configuration vehicles during maglev electromagnetic boost launch， a multi-body separation prediction method based on CFD/RBD coupling is established， a constrained separation strategy with auxiliary separation mechanism is developed， and the flow field structure， aerodynamic load and constrained load characteristics during constrained separation and free separation are explored. The effect of attitude control engine working time on the separation characteristics is also studied. The results show that the ground proximity shock wave interference structure is basically unchanged in the constrained separation stage， and the ground reflected shock wave of the head of the vehicle directly interferes with the vehicle wings in the free separation stage. With the vehicle's head up， the supersonic ground effect gradually weakens， the aerodynamic lift gradually approaches the free stream state， and the vertical constraint load decreases continuously. With the release of constraints and the free separation stage， the head reflected shock wave enhances the lift force and the nose-down moment of the vehicle. When the dimensionless working time of the attitude control engine is 280， the vertical displacement of the vehicle gravity center will meet the safety distance condition at the dimensionless time 1466， when the pitch Angle is 6.1° and the constraint time is just right， safe separation can be better realized.
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