Hostname: page-component-77c89778f8-fv566 Total loading time: 0 Render date: 2024-07-19T10:20:50.781Z Has data issue: false hasContentIssue false
  • English
  • Français

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
Get access Rights & Permissions [Opens in a new window]

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 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

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