NDLI: Effect of Aerodynamic Loads on Dynamic Stability of Slender Launch Vehicle Subjected to an End Rocket Thrust

Content Provider	The American Society of Mechanical Engineers (ASME) Digital Collection
Author	Ohshima, Tsukasa Sugiyama, Yoshihiko
Copyright Year	2002
Abstract	This paper deals with dynamic stability of a slender launch vehicle subjected to aerodynamic loads and an end rocket thrust. The flight vehicle is simplified into a uniform free-free beam subjected to an end follower thrust. Two types of aerodynamic loads are assumed in the stability analysis. Firstly, it is assumed that two concentrated aerodynamic loads act on the flight body at its nose and tail. Secondly, to take account of effect of unsteady flow due to motion of a flexible flight body, aerodynamic load is estimated by the slender body approximation. Extended Hamilton’s principle is applied to the considered beam for deriving the equation of motion. Application of FEM yields standard eigen-value problem. Dynamic stability of the beam is determined by the sign of the real part of the complex eigen-values. If aerodynamic loads are concentrated loads that act on the flight body at its nose and tail, the flutter thrust decreases by about 10% in comparison with the flutter thrust of free-free beam subjected only to an end follower thrust. If aerodynamic loads are distributed along the longitudinal axis of the flight body, the flutter thrust decreases by about 70% in comparison with the flutter thrust of free-free beam under an end follower thrust. It is found that the flutter thrust is reduced considerably if the aerodynamic loads are taken into account in addition to an end rocket thrust in the stability analysis of slender rocket vehicle.
Sponsorship	Applied Mechanics Division
Starting Page	109
Ending Page	115
Page Count	7
File Format	PDF
ISBN	0791836592
DOI	10.1115/IMECE2002-33034
Volume Number	5th International Symposium on Fluid Structure Interaction, Aeroelasticity, and Flow Induced Vibration and Noise
Conference Proceedings	ASME 2002 International Mechanical Engineering Congress and Exposition
Language	English
Publisher Date	2002-11-17
Publisher Place	New Orleans, Louisiana, USA
Access Restriction	Subscribed
Subject Keyword	Stability Approximation Flight Hamilton's principle Unsteady flow Equations of motion Finite element methods Stress Vehicles Rockets Finite element model Flutter (aerodynamics) Dynamic stability Rocket thrust Eigenvalues Thrust
Content Type	Text
Resource Type	Article

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