导弹抛底罩过程建模与分析
收稿日期: 2015-07-10
修回日期: 2016-02-26
网络出版日期: 2016-03-08
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
Received date: 2015-07-10
Revised date: 2016-02-26
Online published: 2016-03-08
Supported by
National Basic Research Program of China (2013CB733004);National Key Discipline Laboratory Open Foundation (HIT.KLOF.MST.201508)
李慧通 , 赵阳 , 田浩 , 黄意新 . 导弹抛底罩过程建模与分析[J]. 航空学报, 2016 , 37(6) : 1876 -1887 . DOI: 10.7527/S1000-6893.2016.0052
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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