Launch dynamics of airborne missile with large maneuvering flight

被引：1
|
作者：
Liu H. [1 ]
Zhou J. [1 ]
Zhang S. [2 ]
机构：
[1] School of Astronautics, Northwestern Polytechnical University, Xi'an
[2] Missile Launcher Department, China Airborne Missile Academy, Luoyang
来源：
Xi Tong Gong Cheng Yu Dian Zi Ji Shu/Systems Engineering and Electronics | 2018年 / 40卷 / 10期
关键词：
Coriolis force; Embedded ejection; Flexible system dynamics; Launch safety; Rigid-flexible-gas-liquid coupling;
D O I：
10.3969/j.issn.1001-506X.2018.10.22
中图分类号：
学科分类号：
摘要：
Advanced fighter needs to achieve embedded ejection of missile under large maneuvering flight, High overload centrifugal force and Coriolis effect has influences on launch dynamics, and harmful to the launch separation safety. research on launching safety of stealth aircraft was carried out that combines simulation and test. Based on finite element method and Lagrange multi-body dynamic equation, launch dynamics theory model of embedded ejection of stealth aircraft was established, and launch dynamics was simulated. The influence of high overload centrifugal force and Coriolis force on the ejection separation parameter was analyzed. Simulation and test results show that high overload centrifugal force has positive influences on launch safety, but Coriolis force has negative influences on launch safety. © 2018, Editorial Office of Systems Engineering and Electronics. All right reserved.
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页码：2305 / 2310
页数：5
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