Abstract:

To reduce the ejection load and improve the launch accuracy of rockets， a telescopic canister gas ejection system was proposed. The dynamic characteristics of this ejection system were studied based on theoretical analysis and numerical calculation. The maximum relative error between the simulated and theoretical velocities of the rocket exiting the canister was -0.98%， and the accuracy of the finite element model of the ejection system was verified. Based on the finite element model， the depressurization effects of the ejection system and the effects of launch angle， thrust misalignment， and wind load on the rocket’s motion attitude and the inner canister’s vibrational response were investigated. The results show that compared to the single canister ejection system， the average and maximum depressurization effects of the ejection system are about 30.3% and 35.1%， respectively. Larger launch angle， thrust misalignment， and wind load indicate worse motion attitude of the rocket and vibrational response of the inner canister. The launch angle is the main factor affecting the launch accuracy of the rocket， and the maximum effect of the launch angle on the launch accuracy is 2.3 to 4.4 times that of the other two factors. The research can provide references for the design and optimization of telescopic canister gas ejection systems.

Key words: telescopic canister, dynamics, finite element, depressurization, launch accuracy

摘要：

为降低弹射载荷并提高火箭的发射精度，提出了一种伸缩筒燃气弹射系统。基于理论分析和数值计算方法研究了该弹射系统的动力学特性。火箭出筒速度的仿真值和理论值的最大相对误差为-0.98%，验证了该弹射系统有限元模型的正确性。基于有限元模型，开展了该弹射系统的降压效果及发射角度、推力偏心和风载荷对火箭运动姿态和内筒振动响应影响的研究。结果表明：相比单筒弹射系统，该弹射系统的平均降压效果和最大降压效果约为30.3%和35.1%；发射角度、推力偏心和风载荷越大，火箭运动姿态与内筒振动响应越恶劣；其中，发射角度是影响火箭发射精度的主要因素，且发射角度对发射精度的最大影响效果是其他2个因素最大影响效果的2.3~4.4倍。该研究成果可为伸缩筒燃气弹射系统的设计与优化提供参考。

关键词: 伸缩筒, 动力学, 有限元, 降压, 发射精度