机载水平后向弹射同时离轨动力学响应研究

Here, to solve shortcomings of larger fuel consumption and weaker carrying capacity in self-powered launch of small rockets, and further improve their carrying capacity, an airborne horizontal backward ejection method based on existing cold ejection technology was proposed to realize cold ejection launch of small rockets from airborne platform, reduce required fuel for launch and improve rocket carrying capacity. Based on the theory of launch dynamics, the dynamic model for rocket airborne horizontal backward ejection was established. Finite element numerical simulations were performed for airborne horizontal backward ejection under multiple operating conditions to study the ejection mechanism and laws of backward ejection from airborne platform. The study results showed that modal shapes of finite element models mainly consisting of beam elements and shell elements are consistent, they have similar modal frequencies and frequency difference for their each order is within 10% ; flight attack angle has a less impact on ejection velocity and acceleration, but a larger impact on angular displacement and angular velocity, flight attack angle can' t affect the safety of rocket separation process; carrier vibration has a less impact on ejection dynamic response and can't affect the safety of rocket separation process.