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Analysis of the stability modes of the non-rigid airship

Published online by Cambridge University Press:  04 July 2016

M. V. Cook ,
J. M. Lipscombe  and
F. Goineau
M. V. Cook
Affiliation:
Flight Test and Dynamics Group, College of Aeronautics, Cranfield University, Cranfield, Bedford, UK
J. M. Lipscombe
Affiliation:
Flight Test and Dynamics Group, College of Aeronautics, Cranfield University, Cranfield, Bedford, UK
F. Goineau
Affiliation:
Flight Test and Dynamics Group, College of Aeronautics, Cranfield University, Cranfield, Bedford, UK
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Abstract

This paper describes and compares various analyses leading to the development of approximate models for the linear stability modes of the non-rigid airship. The progress of the analyses was variously dependent on assumptions made from the detailed scrutiny of linear numerical models for three airships. For each airship studied, the linear models were obtained from non-linear simulation models by linearising about a number of chosen trim speeds representative of a typical speed envelope. The decoupled linear models comprised the longitudinal and lateral-directional state equations of the neutrally buoyant airship, for speeds from the hover to 30m/sec. Since the fidelity of the earliest airship models was not known, the principal purpose of this paper is to re-visit the original analysis using a later airship model of known excellent fidelity.

The longitudinal modes of the airship comprise the surge mode, the heave-pitch subsidence mode and the oscillatory pitch-incidence mode. The lateral-directional modes of the airship comprise the sideslip subsidence mode, the yaw subsidence mode and the oscillatory roll pendulum mode. Approximate models for these modes are derived and expressed in terms of concise aerodynamic stability derivatives. The mode characteristics are discussed, and the approximate models are compared with the actual airship modes over the typical airspeed envelope.

Type
Research Article
Information
The Aeronautical Journal , Volume 104 , Issue 1036 , June 2000 , pp. 279 - 290
Copyright
Copyright © Royal Aeronautical Society 2000 

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