基于浮动基座偏载发射的初始扰动影响分析

Analysis of Initial Disturbance Base on Floating Platform Partial Load Launch

本文以某型浮动基座多联装偏载发射系统为研究对象,通过建立刚柔耦合发射系统动力学仿真模型,对浮动平台上偏载发射进行动力学仿真,并通过1:1弹射试验对仿真结果进行验证,经试验验证仿真置信度大于90%,仿真模型准确有效。以上述仿真模型为基础对浮动平台偏载发射和普通硬质场坪发射过程中弹体出筒姿态、筒口位移等数据进行仿真对比分析,得出浮动平台偏载发射的影响范围和主要影响原因,浮动基座在发射载荷作用下垂向出现较大位移,由此影响弹体侧向出筒姿态,侧向出筒角度、角速度、角加速度增加均超过2倍,同时在浮动基座支撑刚度和偏载发射耦合作用下,发射过程中发射筒出现较大侧向偏移,由此引起弹体出筒姿态的变化。仿真分析结果和相关数据为后续优化设计提供数据和理论支撑。

In this paper, taking the floating platform partial load launch as the research object. In order to analysis the dynamics of floating platform partial load launch, the rigid-flexible coupling multibody system model and 1:1 ejection test was established. Comparing with the test data, the simulation confidence greater than 90%. Based on this, analysis the missile position and canister head position by comparing the floating platform partial load launch and highway launch, the scope of influence and main cause of initial disturbance can be got. The floating platform has a large displacement in the sagging direction under the launch load, which affects the lateral exit attitude of the missile, and the lateral exit angle,angular velocity and angular acceleration increase by more than twice. At the same time, under the coupling effect of the support stiffness of the floating base and partial load launch, the launcher has a large lateral offset during the launch process,resulting in the change of the exit attitude of the missile. This paper conclusion provides data and method basis for further research.