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In this thesis, a large slenderness ratio , axisymmetric missile under the combined effects of aerodynamic control and elastomer elastic vibration coupling dynamics analysis of flexible deformation of projectile motion parameters . Today , the rapid development of technology , along with the missile's range , lethality and accuracy improved growing missile payload , which prompted a missile slenderness ratio increases and the increased flexibility of the airframe . Elastic vibration of the airframe and aerodynamic control coupling of projectile motion parameters can not be ignored as a starting point , do the following research : First , rigid missile dynamics , control applied to the head of the missile , using rigid body dynamics theory , establish the dynamic model of the missile body under control and aerodynamic coupling ; then , the missile has a larger slenderness ratio elastomer , as flexible body , according to the Timoshenko beam bending theory , give full consideration to the aerodynamic control and missile body elastic vibration coupling , the establishment of a flexible elastomer vibration model , and further establish a flexible missile body control, aerodynamic and the projectile elastic vibration coupling dynamic model ; Finally, the establishment of a rigid missile dynamics simulation models and flexible missile dynamics simulation model , simulation and comparative experiments found flexible elastomer deformed projectile motion parameters precision produce large errors , which exchange that angle and sideslip angle slenderness ratio of the maximum error , elastomers , and the initial velocity of the missile body will reduce the accuracy of the motion parameters of the missile body . Given on the basis of the above research , the recommendations of the missile design and calculation .
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