Abstract
Structural vibration modal response analysis during lift off has been improved in the H I rocket development by considering its launch pad. The original analysis introduced through the technical assistance for the N-I and N-II development had ignored the launch pad. Consequently, the H-I rocket modal analysis has improved the procedure by taking into account of the boundary condition change between the rocket and its launch pad during vertical takeoff. This improvement includes the equations to connect the responses on fixed-free boundary conditions to those on free-free boundary conditions at the instant of lift Off. This paper covers:(1)structural vibration analysis techniques of the N-I, N-II, H-I and H-II rocket, (2)rocket vibration models by substructure modal synthesis method, (3)inherent improvement to introduce boundary condition change into modal response analysis at liftoff event, and (4)evaluation of above improvement by comparing an analysis with its flight data.
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