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About the Journal
Chinese Name:战术导弹技术
English Name: Tactical Missile 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
ISSN: 1009-1300
CN: 11-1771/TJ
Analysis on the development of foreign networked multi-missile cooperation
Ma Wenhui;Feng Xiaozhou;Shi Hua;Liu Mengyan;Di Bo;Cai Keping;With the escalation of systematic confrontation, multi-missile cooperative technology has been becoming one of the key hotspots worldwide due to its superior advantages and potential. An analytical review of the worldwide multi-missile cooperative projects is provided for prospecting the technology development directions based on the key factor of network information empowerment. The worldwide multi-missile cooperative projects are organized. The development status is systematically analyzed from the aspects of development trajectory, main characteristics and related concepts, etc. Based on the worldwide projects, the characteristics of the multi-missile cooperative technology are analyzed, and the key points of the multimissile cooperative technology development are summarized around the network. Focus on the key points, the development of multi-missile networked cooperative technology is discussed, alongside a look ahead at the key technology that merits special focus in the future. Research indicates that multi-missile cooperative technology has been becoming one of the key areas worldwide, wherein the multi-missile networked cooperative technology is the top priority for future systematic countermeasures to achieve "cost reduction and efficiency increase". Thus, improving the networked cooperative capability around low-cost, large-scale, and autonomy can offer innovative ideas for the construction of multi-missile cooperative capability under future confrontation.
Review of domestic and foreign developments in key technologies for aerial-aquatic vehicles
Guo Chuwei;Luo Yuepei;Xu Yinhan;Li Wenjia;Wu Fengying;Information Engineering University;A comprehensive overview of recent advancements in aerial-aquatic vehicle technologies over the past five years is presented, based on a systematic review of academic literature and patent databases from both domestic and international sources. Core breakthroughs are thoroughly summarized across three domains, i.e. shape and structural design, cross-media propulsion, and transition control technologies. It is revealed that the vehicle performance have been significantly enhanced with diversified innovative configurations, modular/deformable structures, and the integration of lightweight high-strength materials. In propulsion technology, explorations of hybrid and integrated propulsion systems are highlighted as enabling efficient transitions and stable operations across air-water media. Meanwhile, dynamic stability control and trajectory planning technologies are emphasized as critical for achieving precise cross-media maneuvering. By examining current research trends, technical challenges are identified, and future development directions are forecasted. The importance of biomimetic and morphing technologies, advanced power/energy systems, intelligent control algorithms, and prototype field testing/validation is underscored. This work seeks to assist researchers in grasping the latest technological frontiers, pinpointing research bottlenecks and gaps, and exploring potential application scenarios within this field.
Study on rolling characteristics of canard-configuration miniature missiles with spinning wraparound tail fin
Gao Xiang;Li Xiaojian;Shen Zhicheng;Challenges in achieving effective rolling control are often encountered by missiles with a canard configuration. Traditional tail fins used in miniature missiles tend to be structurally complex and constrained by limited dimensions. Spinning tail fins are represented as a promising technical solution for enhancing roll control performance. Advantages in reducing missile volume and conserving internal space are offered by wraparound tail, making them particularly suitable for tube-launched applications. To evaluate the effectiveness of the spinning wraparound fins technology in canard-configured miniature missiles, wind tunnel study are conducted using three configurations: spinning wraparound fins, fixed wraparound fins, and no fins. The wind tunnel tests are yielded comprehensive data on rolling characteristics and control capabilities under various operational conditions. Results indicate that the influence of different tail fin configurations on the missile's lift-to-drag ratio is minor. However, a significant induced rolling moment is generated by fixed wraparound fins, which compromises the rolling control effectiveness of the canard surfaces. In contrast, the aerodynamic interference on the canard is effectively mitigated by spinning wraparound fins, thereby enabling superior rolling control. Comparative analysis under identical test conditions reveals that the rolling control effectiveness of the fixed wraparound fin configuration is only 40% that of the spinning wraparound fin configuration. For canard-configuration miniature missiles, free-rolling wraparound tail fin is an effective solution to improve its roll control ability.
Research on disturbance anslysis and improvement method of interstage separation spring
Zhao Wenwen;Yang Jiandong;Cai Kerong;Liu Haodong;Xu Eyan;Shanghai Academy of Spaceflight Technology;The interstage separation spring is often used in the interstage separation system of the aircraft,which plays an important role in improving the robustness of the separation system. The disturbance angular velocity generated by the separation spring device during the stage separation process is analyzed. When the mass and length of the two stage are equivalent, about half of the sum of the angular velocity of the carrier and the main stage is transmitted to the main stage, which adversely affects the start-up and control of the main stage stabilizer. Based on the analysis of the disturbance of the separation spring, the method of suppressing the disturbance angular velocity of the separation spring is studied. The concrete realization form of this method is to add hinges at both ends of the spring actuator, which can increase the robustness and suppress the angular velocity of the implicated disturbance. The principle analysis and numerical simulation show that the separation method is effective and has obvious inhibitory effect on the strong disturbance separation condition.The experimental results show that the mechanism meets the requirements of use and have certain reference significance.
Thoughts on passive thermal protection design, thermal sealing and product assurance for hypersonic aircraft
Li Jiangman;Chen Weixiong;Addressing the bottlenecks of complex thermal protection system design, insufficient material performance, and product assurance challenges for hypersonic aircrafts under extreme service environments, the design processes, material, and field maintenance mechanisms are systematically investigated. It is focused on ten core stages of the thermal protection design process. A systematic design approach from target requirements to verification methods is clarified. The performance differences and application scenarios of silicon-based, carbon-based, and ceramic-based materials are compared and analyzed, revealing the core advantages of lightweight and high-temperature resistant composite materials. The risk of heat seal failure during long-term flight and the need for field maintenance support are explored, and key technical requirements such as low-temperature curing and rapid repair are also proposed. Based on multi-field coupling analysis, it is further recommended to enhance the ability to better understand material properties, reduce material types to mitigate the risk of thermal matching, and promote theoretical research on differences in space and ground experiments. The results can provide important support for the lightweight, high reliability design and engineering application of thermal protection systems for hypersonic aircrafts.
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Official Journal of the Unmanned Aerial Vehicle Branch of the Chinese Society of Astronautics
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