无控火箭箭架系统扰动分析  

Disturbance analysis of rocket-launcher system for free-flight rocket

作　　者：赵宪斌[1] 杨明星 介于洁 姬铮 张乐 杨森 曾志[1] 康文俊 

机构地区：[1]中国航天科技集团公司四院四十一所,西安710025 [2]中国航天科技集团公司四院四十三所,西安710025

出　　处：《固体火箭技术》2018年第1期130-134,共5页Journal of Solid Rocket Technology

摘　　要：无控火箭发射时,箭架系统耦合振动使得半约束期发射扰动引起的火箭偏转角速度变化和下沉量加剧,成为影响火箭落点散布的关键因素。以某型火箭发射系统为基础,采用物理模型和软件分析方法研究发射装置液压缸振动、发射仰角和箭架配合间隙等因素对出轨扰动的影响。根据液压缸压力变化结果,计算出燃气流作用下箭架系统的扰动频率,进而计算出燃气流扰动下火箭在半约束状态下受牵连运动影响的初始扰动值。理论计算结果显示,箭架振动幅值约占整个扰动角速度的1/5。计算和试验测量结果吻合较好,分析结果对火箭精度、箭架结构匹配性分析和发射装置设计具有指导意义。In the free-flight rocket launching,the coupling vibrations in the rocket-launcher system made the rocket angular velocity and the amount of subsidence caused by the launching disturbance in semi-constrained period be intensified, and became the key factors affectting the distribution of the rocket. In this paper, based on a certain rocket launcher system, the influences of the factors, such as vibration in hydraulic cylinder,launch elevation,fit clearance between rocket and launcher, on the derailment disturbance in the launcher device were studied by using a physical model and the software analysis method.The disturbance frequency of rocket-launcher system under gas flows was calculated according to the oil-cylinder pressure changing resuhs, and then, the initial disturbance values of the rocket at the semi-confinement state under the disturbance of the gas flow were calculated.The theoretical calculation results showed that the amplitude value of the vibration were about one fifth of the total disturbance angular velocities. Therefore, the calculated results were in good agreement with the actual test results. It is instructive for rocket accuracy, matching analysis of rocket-launcher and launcher design.

关 键 词：无控火箭 燃气流 牵连运动 发射扰动 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]