| In this paper, based on a new type of rocket launcher and full consideration of the components' deformation affecting its dynamic characteristics, the nonlinear finite element structural dynamics model is built. Through modal analysis, transient model dynamic analysis and dynamic analysis, structural and dynamic characteristic of the rocket launcher are studied.The modal of the rocket launch system is extracted based on Lanczos method. Through modal analysis, the weak links of the rocket launch system is shown. The impact of launching angle and reducing the number of the uncontrolled missile in the launching process for rocket launch system is studied to avoid vibration coupling and to provide a basis for determining a reasonable launching interval. The modal of the rocket launch system in marching transport is built. Modal superposition procedure is applied to transient modal dynamic analysis after modal analysis. Some key components of the rocket launch system separately under the vibration inertia force, braking inertia force, centrifugal inertia force are analyzed for rigidity and strength to verify whether the structure is reasonable and reliability. Taking full account of friction and collision between missile and orientator, the non-linear finite element modal of the rocket launch in launching is built. Explicit dynamic analysis was applied for the rocket launch in imitation of launching. The vibration characteristics of rocket launch are impacted separately by the clearance between missile and orientator, and the length of orientator is studied. The reasonable clearance between missile and orientator is established by controlling the initial disturbance of missile. On this basis, and on the condition of avoiding the collision between missile and muzzle, and based on controlling the initial disturbance of missile, the length of reasonable orientator is established in order to improve concentration of missile and to provide theory for improving the rocket launch. |
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