为解决小型火箭自力发射消耗燃料较大、运载能力较弱的不足，进一步提高小型火箭运载能力，本文在现有冷弹射技术的基础上提出一种机载水平后向弹射方法，实现小型火箭机载平台冷弹射发射，以减小发射所需燃料、提高火箭运载能力。本文基于发射动力学理论，建立火箭机载水平后向弹射动力学模型，实现多工况机载水平后向弹射有限元数值仿真，研究机载平台后向弹射的弹射机理和规律。研究结果表明，以梁单元和壳单元为主的有限元模型模态振型一致，特征频率相近，各阶频率相差在10%以内；进一步研究表明，飞机攻角对弹射速度和加速度影响较小，但对角位移、角速度影响较大，飞行攻角不会影响火箭分离过程的安全性；载机振动对弹射动力学响应影响较小，且不会影响分离过程的安全性。

In order to solve the shortcomings of large fuel consumption and weak carrying capacity of small rocket self-propelled launch, and further improve the carrying capacity of small rocket, this study proposes an airborne horizontal backward ejection method based on the existing cold ejection technology to realize the cold ejection of small rocket airborne platform. Based on the theory of launch dynamics, a rocket airborne horizontal backward ejection platform is constructed, and the finite element numerical simulation of airborne horizontal backward ejection under multiple working conditions is realized. The ejection mechanism and law of airborne platform backward ejection are studied. The results show that the modal shapes of the finite element model based on beam element and shell element are consistent, the characteristic frequencies are similar, and the frequency difference of each order is within 10 %. Further research shows that the angle of attack has little effect on the ejection velocity and acceleration, but has a great influence on the angular displacement and angular velocity, and the flight angle of attack will not affect the safety of the rocket separation process. The vibration of the carrier has little effect on the dynamic response of the ejection, and will not affect the safety of the separation process.