Response Reduction at Payload Using Isolation System in a Typical Launch Vehicle

Lakshmi Priya, S and Sundararajan, T and Rao, Balakrishna K (2016) Response Reduction at Payload Using Isolation System in a Typical Launch Vehicle. In: National Conference, IDEAS-16, Recent Advances in Civil and Sustainable Engineering,, 31/03/2016, UKF College of Engineering, Paripally, Kerala, Ind.

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Abstract

Launch vehicles present an efficiently viable method for placing satellites into orbit. A typical launch vehicle consist of propulsion modules either solid and/or liquid stages connected by interstages and payload module.Dynamic analysis is used to find out the response of the structure, mainly at the satellite interface due to various excitations encountered during flight. The basic objective of the work is to reduce the dynamic loads on the satellite by vibration isolation methods. In this work analysis is carried out by incorporating an isolation system at various locations and the results are compared to show the effectiveness of isolation system

Item Type: Conference or Workshop Item (Paper)
Uncontrolled Keywords: launch vehicle, mode shape, natural frequency, frequency response, acceleration, vibration isolation.
Subjects: Engineering > MIT Manipal > Civil Engineering
Depositing User: MIT Library
Date Deposited: 21 Oct 2016 15:18
Last Modified: 21 Oct 2016 15:18
URI: http://eprints.manipal.edu/id/eprint/147335

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