Thrust Vectoring Control of Supersonic Flow Through an Orifice Injector

Traditional mechanical control systems in thrust vectoring are efficient in rocket thrust guidance but their costs and their weights are excessive. The fluidic injection in the nozzle divergent constitutes an alternative procedure to achieve the goal. In this paper, we present a 3D analytical model for fluidic injection in a supersonic nozzle integrating an orifice. The fluidic vectoring uses a sonic secondary injection in the divergent. As a result, the flow and interaction between the main and secondary jet has built in order to express the pressure fields from which the forces and thrust vectoring are deduced. Under various separation criteria, the present analytical model results are compared with the existing numerical and experimental data from the literature.

Authors:

• Ibrahim Mnafeg
• Azgal Abichou
• Lotfi Beji

Keywords:

• Flow separation
• Fluidic thrust vectoring
• Nozzle
• Secondary jet
• Shock wave.

References:

[1] Balu, R., ”Analysis of Performance of a Hot Gas Injection Thrust Vector
Control System”, Journal of Propulsion and Power, Vol. 4, pp.580-585,
1991.
[2] Spaid, F.W., and Zukoski, E. E., ”Study of the interaction of gaseous
jets from transverse slots with supersonic external flows”, AIAA J. 6(2),
pp.205.12., 1968.
[3] Spaid, F.W., and Zukoski, E. E., and Rosen, R., ”A study of Secondary
Injection of gases into a Supersonic Flow”, Technical Report 32-834,
NASA, 1966.
[4] Billig, F.S., J. ”Shock-wave shapes around spherical- and
cylindrical-nosed bodies”, Journal of Spacecraft and Rockets, Vol.4
No.6, 1967.
[5] Zmijanovic,V., Lago, V., Leger, L., Depussay, E., Palerm, S., Oswald, J.,
Sellam, M., and Chpoun, A., ”Thrust vectoring effects of a transverse
gas injection into a supersonic cross-flow of an axisymmetric C-D
nozzle”, 4th European Conference for Aerospace Sciences (EUCASS),
St. Petersburg, Russian, July 4-8, 2011.
[6] Rajendran, S. S., Aravind Kumar, T.R, Nareshkumar K.S, Ragothaman.
S, Raveendran, R., and Sanal Kumar.V.R, ”Studies on Thrust Vector
Control using Secondary Injection Sonic and Supersonic Jets”, 2nd Int.
Conference on Mechanical, Electronics and Mechatronics Engineering
(ICMEME’2013) June 17-18, London (UK), 2013.
[7] Mangin B., ”Vectorisation fluidique de la pousse d’une tuyre plane
supersonique”. PhD thesis, Universit d’Orleans, Decembre 2006.
[8] Hefner, J. N., and Sterrett, J. R., ”Secondary jet interaction with
emphasis on outflow and jet location”, AIAA J.Spacecr. Rockets, 09(11),
pp.845-847, 1972.
[9] Avduevskii, V. S., Medvedev, K. I., and Polyanskii, M. N., ”Interaction of
a supersonic flow with a transverse jet injected through a circular aperture
in a plate”, Fluid Dynamics J., 5(5):888-891, 1970.
[10] Vlagov, V.V., Masayakin, N. E. , and Polyanskii, M. N., ”Penetration
depth of a jet injected into an oncoming supersonic flow”, Fluid Dynamics
J., 15(4), pp.599-602, 1980.
[11] Maarouf N., Sellam M., Grignon M., Chpoun A., ”Thrust vectoring
through fluid injection in an axisymmetrical supersonic nozzle”, ISSW26
2, pp.1141-1147, 2007.
[12] Sellam M., Chpoun A., Zmijanovic V., Lago V., ”Fluidic thrust
vectoring of an axisymmetrical nozzle: an analytical model”, Int. J. of
Aerodynamics, Vol.2, No.2/3/4, pp.193 - 209, 2012.
[13] Schetz F.W., Billig E.E., ”Penetration of gaseous jets injected into a
supersonic stream”, AIAA Journal Vol.3, No.11, pp.1658-1665, 1966.
[14] Neilson J.H., Gilchrist A., Lee C.K., ”Side thrust control by secondary
gas injection into rocket nozzles”, Journal Mechanical Engineering
Science Vol. 10, No.3, pp.239-251, 1968.
[15] Guhse R.D. ”On secondary gas injections into supersonic nozzles”,
AIAA Journal Vol.3 No.1, pp.147-149, 1966.
[16] Dussauge J.-P., ”Compressible turbulence in interaction of supersonic
flows”, Springer Turbulence and Interactions NNFM 105, pp.35-54, 2009.