航空学报 > 2016, Vol. 37 Issue (6): 1876-1887   doi: 10.7527/S1000-6893.2016.0052

导弹抛底罩过程建模与分析

李慧通, 赵阳, 田浩, 黄意新   

  1. 哈尔滨工业大学 航天学院, 哈尔滨 150001
  • 收稿日期:2015-07-10 修回日期:2016-02-26 出版日期:2016-06-15 发布日期:2016-03-08
  • 通讯作者: 赵阳 男,博士,教授,博士生导师。主要研究方向:飞行器仿真,振动与冲击。Tel:0451-86417756 E-mail:yangzhao@hit.edu.cn E-mail:yangzhao@hit.edu.cn
  • 作者简介:李慧通 男,博士研究生。主要研究方向:飞行器仿真,多体动力学。Tel:0451-86417756 E-mail:lihuitongyx@126.com;田浩 男,硕士,副教授。主要研究方向:飞行器仿真,柔体动力学。Tel:0451-86402079 E-mail:dongda@hit.edu.cn;黄意新 男,博士研究生。主要研究方向:航天器机构动力学,线缆动力学。Tel:045-86417756 E-mail:huangyixinde@hit.edu.cn
  • 基金资助:

    国家"973"计划(2013CB733004);国防重点学科开放基金(HIT.KLOF.MST.201508)

Modeling and analysis of separation for missile tail cover

LI Huitong, ZHAO Yang, TIAN Hao, HUANG Yixin   

  1. School of Astronautics, Harbin Institute of Technology, Harbin 150001, China
  • Received:2015-07-10 Revised:2016-02-26 Online:2016-06-15 Published:2016-03-08
  • Supported by:

    National Basic Research Program of China (2013CB733004);National Key Discipline Laboratory Open Foundation (HIT.KLOF.MST.201508)

摘要:

导弹冷发射采用底罩保护一级发动机,发射后需要将底罩抛离。为了防止底罩撞击地面设备,采用了铰链连接的利用弹簧作为分离能源的侧抛分离方案。对分离运动及动力学特性进行了研究,建立了底罩旋抛过程的运动学和动力学模型。对导弹底罩分离过程中受到的气动力、弹簧力和空气负压力等多种不确定性因素进行了灵敏度分析,通过仿真得到了底罩脱离角度和弹簧相关参数对分离过程的影响,并进行了参数优化。最后对考虑多个偏差影响下的分离方案进行正交仿真试验,得到了主发动机点火时底罩质心散布范围和底罩落点范围。

关键词: 铰链, 动力学建模, 分离, 灵敏度分析, 仿真

Abstract:

Tail cover, which is used to protect the first stage engine during cold launch of missile, should be thrown after launch. In order to prevent the tail cover from hitting the ground equipment, the detailed separation scheme of lateral fling with connected hinge is adopted using spring as separation energy in the separation. The separation movements and dynamic characteristics are studied, and the kinematics and dynamics models of separation are built. The sensitivity analyses of multiple uncertain factors influencing tail cover are conducted such as aerodynamic force, spring force and negative air pressure during separation. Moreover, the impacts of separation angle of tail cover and the related coefficients of spring on separation process are obtained by simulating and optimizing the coefficients. Ultimately, centroid spreading range when the main engine gets started and landing point's range of tail cover are achieved by the orthogonal test for separation scheme considering complex deviations.

Key words: hinge, dynamic modeling, separation, sensitivity analysis, simulation

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