ACTA AERONAUTICAET ASTRONAUTICA SINICA >
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)
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
LI Huitong , ZHAO Yang , TIAN Hao , HUANG Yixin . Modeling and analysis of separation for missile tail cover[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016 , 37(6) : 1876 -1887 . DOI: 10.7527/S1000-6893.2016.0052
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