Hostname: page-component-848d4c4894-2pzkn Total loading time: 0 Render date: 2024-05-17T04:29:58.675Z Has data issue: false hasContentIssue false
  • English
  • Français

Theoretical Aspects of Thrust Vector Control by Secondary Gas Injection in Rocket Nozzles

Published online by Cambridge University Press:  04 July 2016

John H. Neilson ,
Alastair Gilchrist  and
Chee K. Lee
John H. Neilson
Affiliation:
University of Strathclyde, Glasgow, Scotland
Alastair Gilchrist
Affiliation:
University of Strathclyde, Glasgow, Scotland
Chee K. Lee
Affiliation:
University of Strathclyde, Glasgow, Scotland
Get access Rights & Permissions [Opens in a new window]

Extract

This work deals with theoretical aspects of thrust vector control in rocket nozzles by the injection of secondary gas into the supersonic region of the nozzle. The work is concerned mainly with two-dimensional flow, though some aspects of three-dimensional flow in axisymmetric nozzles are considered. The subject matter is divided into three parts. In Part I, the side force produced when a physical wedge is placed into the exit of a two-dimensional nozzle is considered. In Parts 2 and 3, the physical wedge is replaced by a wedge-shaped “dead water” region produced by the separation of the boundary layer upstream of a secondary injection port. The modifications which then have to be made to the theoretical relationships, given in Part 1, are enumerated. Theoretical relationships for side force, thrust augmentation and magnification parameter for two- and three-dimensional flow are given for secondary injection normal to the main nozzle axis. In addition, the advantages to be gained by secondary injection in an upstream direction are clearly illustrated. The theoretical results are compared with experimental work and a comparison is made with the theories of other workers.

Type
Supplementary Papers
Information
The Aeronautical Journal , Volume 72 , Issue 686 , February 1968 , pp. 171 - 177
Copyright
Copyright © Royal Aeronautical Society 1968 

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. Mager, A. On the Model of the Free, Shock-Separated Turbulent Boundary Layer. J. Aero Sci, Vol 23, pp 181–184, February 1956.Google Scholar
2. Bogdonoff, S. M. Some Experimental Studies of the Separation of Supersonic Turbulent Boundary Layers. Reprint of Papers, Heat Transfer and Fluid Mechanics Institute, University of California, June 1955.Google Scholar
3. Romeo, D. J. and Sterrett, J. R. Aerodynamic Inter-action Effects Ahead of a Sonic Jet Exhausting Perpendicularly from a Flat Plate into a Mach Number 6 Free Stream. NASA TN D-743, April 1961.Google Scholar
4. Vinson, P. W., Amick, J. L. and Liepman, H. P. Interaction Effects Produced by Jet Exhausting Laterally near Base of Ogive-Cylinder Model in Supersonic Main Stream. NASA Memo 12-5-58W, February 1959.Google Scholar
5. Wu, J. M., Chapkis, R. L. and Mager, A. An Approximate Analysis of Thrust Vector Control by Fluid Injection. ARS J 31, 1677-1685, December 1961.Google Scholar
6. Morgan, E. J. An Analysis of Gaseous Secondary Injection into Rocket Nozzles. ARS 2335-62, ARS Solid Propellent Rocket Conference, Waco, Texas, January 1962.Google Scholar
7. Neilson, J. H Gilchrist, A. and Lee, C. K. A Theory for the Side Force Produced in Two-Dimensional Nozzles by Secondary Gas Injection. (Paper 3 of this Series to be published in the AJRAeS, March 1968).Google Scholar
8. Neilson, J. H., Gilchrist, A. and Lee, C. K. Thrust Vector Control by Secondary Gas Injection into Rocket Nozzles. (To be published.) Google Scholar
9. Neilson, J. H., Gilchrist, A. and Lee, C. K. Thrust Vector Control by Secondary Gas Injection in Two-Dimensional Nozzles. AJRAeS, Vol 72, pp 77–81, January 1968.Google Scholar
10. Neilson, J. H., Gilchrist, A. and Lee, C. K. Control Forces in Rocket Nozzles Produced by a Secondary Gas Stream Inclined at Various Angles to the Nozzle Axis. (To be published.) Google Scholar