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Investigation on the aerodynamic performance of an ejection seat

Published online by Cambridge University Press:  03 February 2016

D. H. Chen ,
W. H. Wu ,
J. J. Wang  and
Y. Huang
D. H. Chen
Affiliation:
Beijing University of Aeronautics and Astronautics (BUAA), Beijing, China China Aerodynamics Research and Development Center (CARDC), Mianyang, China
W. H. Wu
Affiliation:
Beijing University of Aeronautics and Astronautics (BUAA), Beijing, China China Aerodynamics Research and Development Center (CARDC), Mianyang, China
J. J. Wang
Affiliation:
Beijing University of Aeronautics and Astronautics (BUAA), Beijing, China
Y. Huang
Affiliation:
China Aerodynamics Research and Development Center (CARDC), Mianyang, China
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Abstract

A unique experimental method is used, in combination with numerical calculation and engineering estimation, to study the aerodynamic performance of an ejection seat at M = 0·60, 0·90 and 1·20, angles-of-attack α = 0°~360°, and sideslip angles (β = 0°~–90°. Several basic characteristics of the aerodynamic performance are explored. The normal force of the ejection seat varies in a sinusoidal way and the axial force in a cosinoidal way, with the angle-of-attack. The model is statically unstable longitudinally at most attitude angles and the longitudinal stability could be improved by a stabiliser. These characteristics result from a large low pressure area caused by the leeward separation and the windward high pressure area in the ejection seat flow field, at all α, due to the blunt configuration. A set of engineering calculation formulae is deduced, based on the aerodynamic characteristics of the ejection seat.

Type
Research Article
Information
The Aeronautical Journal , Volume 111 , Issue 1120 , June 2007 , pp. 373 - 380
Copyright
Copyright © Royal Aeronautical Society 2007 

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References

1. Jines, A. and Roberts, E.O., Enhanced ejection seat performance with vectored thrust capability, August 1985, AFWAL-TR-84-3026, Air Force Wright Aeronautical Laboratories/Avionics Laboratories, Ohio.Google Scholar
2. Reichenau, D.E.A., Aerodynamic characteristics of a full-scale ACES-II ejection seat with a small female or large male manikin at Mach numbers from 0-2 to 1-4, August 1987, AEDC-TR-87-16, Tullahoma, Tennessee.Google Scholar
3. Habchi, S.D., Ho, S.Y., Hufford, G.S., et al. Computational aerodynamic analysis of the navy aircrew common ejection seat, January 1994, AIAA Paper 94-0395.Google Scholar
4. Habchi, S.D., Hufford, G.S. and Marquette, T., Navier-Stokes computational analysis of the B-1A escape capsule, January 1995, AIAA Paper 95-0187.Google Scholar
5. Lohner, R. and Parikh, P., Generation of three-dimensional unstructured grids by the advancing-front method, AIAA Paper 88-0515, 1988.Google Scholar
6. Spalart, P.R. and Allmaras, S.R., A One-equation turbulence model for aerodynamic flows, January 1992, AIAA Paper 92-0349.Google Scholar
7. Jameson, A., Schmidt, W. and Turkel., E., Numerical solution of Euler equations by the finite volume methods using Runge-Kutta time stepping schemes, 1981, AIAA Paper 81-1259.Google Scholar
8. Jameson, A. and Mavriplis, D., Finite volume solution of the two dimensional Euler equations on a regular triangular mesh, 1985, AIAA Paper 85-0453.Google Scholar