Affiliation:
1. Vikram Sarabhai Space Centre Aerodynamics Division Trivandrum, India
2. Indian Institute of Technology Department of Aerospace Engineering Kanpur, India
Abstract
The dynamics associated with the jettisoning of heat shield fairings from the parent launch vehicle is investigated. The analysis considers a zip-cord based mechanism employed to jettison the fairings from the accelerating on-going stage. A scheme for characterization of the zip-cord system is described. The geometry of collision is analysed for a known, precomputed structural response. The no- collision domain is constructed in flexibility parameter space for an arbitrarily assumed impulse level. Alternatively, the minimum impulse required for a collision-free separation is also computed as a function of design parameters. Finally, the analysis enables generation of the upper limits on payload size as well as that of the external mountings for a clean separation. This methodology has led to the successful separation of shield heat fairings for the two developmental flights of the Indian launcher Polar Satellite Launch Vehicle (PSLV).
Subject
Mechanical Engineering,Aerospace Engineering
Cited by
4 articles.
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1. Pressure Drop Prediction Using CFD for a Launch Vehicle Payload Fairing Separation Ground Test;Lecture Notes in Mechanical Engineering;2024
2. Separation dynamics of large-scale fairing section: a fluid–structure interaction study;Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering;2012-10-08
3. Boat Tail Effect of a Payload Fairing on the Elastic Displacement Response;Journal of Spacecraft and Rockets;2000-09
4. Dynamics of nose cone jettisoning from spinning rockets;Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering;2000-06-01