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Rigid body separation dynamics for space launch vehicles

Published online by Cambridge University Press:  03 February 2016

B. N. Rao ,
D. Jeyakumar ,
K. K. Biswas ,
S. Swaminathan  and
E. Janardhana
B. N. Rao
Affiliation:
Structural Analysis and Testing Group, Aeronautics Entity, Vikram Sarabhai Space Centre, Trivandrum, India
D. Jeyakumar
Affiliation:
Launch Vehicle Design Entity, Vikram Sarabhai Space Centre, Trivandrum, India
K. K. Biswas
Affiliation:
Launch Vehicle Design Entity, Vikram Sarabhai Space Centre, Trivandrum, India
S. Swaminathan
Affiliation:
Launch Vehicle Design Entity, Vikram Sarabhai Space Centre, Trivandrum, India
E. Janardhana
Affiliation:
Launch Vehicle Design Entity, Vikram Sarabhai Space Centre, Trivandrum, India
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Abstract

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This paper presents a systematic formulation for the simulation of rigid body dynamics, including the short period dynamics, inherent to stage separation and jettisoning parts of a satellite launcher. This also gives a review of various types of separations involved in a launch vehicle. The problem is sufficiently large and complex; the methodology involves iterations at successively lower levels of abstraction. The best choice to tackle such problems is to use state-of-the-art programming technique known as object oriented programming. The necessary classes have been identified to represent various entities in the launch vehicle separation process (e.g., gravity, aerodynamics, propulsion and separation mechanisms etc.). Simple linkages are modelled with suitable objects. This approach helps the designer to simulate a launch vehicle separation dynamics and also to analyse separation system performance. To examine the influence of the design variables on the separating bodies, statistical analyses have been performed on the upper stage separation process and pull out of ongoing stage nozzle from the spent stage of a multistage rocket carrier using retro rockets.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 110 , Issue 1107 , May 2006 , pp. 289 - 302
Copyright
Copyright © Royal Aeronautical Society 2006 

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