Structural stability of slender aerospace vehicles: Part I Mathematical modeling

Trikha, M and Mahapatra, Roy D and Gopalakrishnan, S and Pandiyan, R (2010) Structural stability of slender aerospace vehicles: Part I Mathematical modeling. In: International Journal of Mechanical Sciences, 52 (7). pp. 937-951.

PDF Aero.pdf - Published Version Restricted to Registered users only Download (414kB) | Request a copy

Abstract

A detailed mechanics based model is developed to analyze the problem of structural instability in slender aerospace vehicles. Coupling among the rigid-body modes, the longitudinal vibrational modes and the transverse vibrational modes due to asymmetric lifting-body cross-section are considered. The model also incorporates the effects of aerodynamic pressure and the propulsive thrust of the vehicle. The model is one-dimensional, and it can be employed to idealized slender vehicles with complex shapes. Condition under which a flexible body with internal stress waves behaves like a perfect rigid body is derived. Two methods are developed for finite element discretization of the system: (1) A time-frequency Fourier spectral finite element method and (2) h-p finite element method. Numerical results using the above methods are presented in Part II of this paper. (C) 2010 Elsevier Ltd. All rights reserved.

Item Type:	Journal Article
Publication:	International Journal of Mechanical Sciences
Publisher:	Elsevier Science
Additional Information:	Copyright of this article belongs to Elsevier Science.
Keywords:	Launch vehicle;Stability;Rigid body dynamics;Flexible body dynamics;Follower force;Stress wave
Department/Centre:	Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited:	13 Jul 2010 07:14
Last Modified:	19 Sep 2010 06:10
URI:	http://eprints.iisc.ac.in/id/eprint/28975

Actions (login required)

View Item