Static aeroelastic analysis of guided slender launch vehicles

Humbad, NG (1978) Static aeroelastic analysis of guided slender launch vehicles. Journal of Spacecraft and Rockets, 15 (1). pp. 12-17. ISSN 0022-4650

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Abstract

The static aeroelastic behavior of guided slender-body launch vehicles is explored by using a discrete system matrix method. An iterative procedure is used to calculate the effect of aerodynamic and elastic force interactions. Neutral stability, divergence, and controllability of guided vehicles are discussed. The theory is applied to a research launch vehicle, and numerical results are given to show the effect of dynamic pressure and pitch rate on the pitch control force and center of pressure shift. The results indicate that excessive pitch control force can be avoided by selecting the flight dynamic pressure less than the dynamic pressure corresponding to neutral stability. Fin-control reversibility on account of the vehicle flexibility has been observed.

Item Type:	Article
Uncontrolled Keywords:	Dynamics;Stability;Launch vehicles;Vehicles;Mathematical analysis;Aeroelasticity;13; Statics;Spacecraft;Dynamical systems;Rockets;Aerodynamics;Mathematical models; Flexibility; Iterative methods;Matrix methods;Aeroelasticity;Iterative solution;Launch vehicle configurations;Research vehicles13;
Subjects:	ASTRONAUTICS > Spacecraft Design, Testing and Performance
Depositing User:	Ms. Alphones Mary
Date Deposited:	24 Apr 2006
Last Modified:	24 May 2010 04:10
URI:	http://nal-ir.nal.res.in/id/eprint/1196

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