Numerical Studies on Thrust Vectoring Using Shock Induced Supersonic Secondary Jet
Numerical studies have been carried out using a
validated two-dimensional RNG k-epsilon turbulence model for the
design optimization of a thrust vector control system using shock
induced supersonic secondary jet. Parametric analytical studies have
been carried out with various secondary jets at different divergent
locations, jet interaction angles, jet pressures. The results from the
parametric studies of the case on hand reveal that the primary nozzle
with a small divergence angle, downstream injections with a distance
of 2.5 times the primary nozzle throat diameter from the primary
nozzle throat location warrant higher efficiency over a certain range
of jet pressures and jet angles. We observed that the supersonic
secondary jet opposing the core flow with jets interaction angle of
40o to the axis far downstream of the nozzle throat facilitates better
thrust vectoring than the secondary jet with same direction as that of
core flow with various interaction angles. We concluded that fixing
of the supersonic secondary jet nozzle pointing towards the throat
direction with suitable angle at a distance 2 to 4 times of the primary
nozzle throat diameter, as the case may be, from the primary nozzle
throat location could facilitate better thrust vectoring for the
supersonic aerospace vehicles.
<p>[1] George P Sutton and Oscar Biblarz, “Rocket propulsion elements,” 7th
Edn., John Wiley & Sons, Inc., New York, 2001.
[2] A. E. Wetherbee, Jr "Directional Control Means for April Supersonic
Vehiclo (OCR), U.S Patent 2,943,821, Issue Date: July 5 1960 .
[3] A. J. Porzio and M.E.Franke "Experimental study of a confined jet thrust
vector control nozzle", Journal of Propulsion and Power, Vol. 5, No. 5
(1989), pp. 596-601.
[4] Erinc Erdem, Thrust vector control by secondary injection, M.S Thesis,
Mechanical Engineering, Sept. 2006, Middle East Technical University.
[5] Balar, R., et al., “Comparison of Parallel and Normal Fuel Injection in
aSupersonic Combustor”, AIAA Paper 2006-4442, July 2006.
[6] Erdem, E., et al., “Parametric Study of Secondary Gas Injection into a
Conical Rocket Nozzle for Thrust Vectoring”, AIAA Paper 2006-4942,
July 2006.
[7] Dhinagram, R., BOSE, T. K., “Comparison of Euler and Navier Stokes
Solutions for Nozzle Flows with Secondary Injection”, AIAA Paper 96-
0453, Jan. 1996.
[8] Inouye, T., “Experiments on Rocket Thrust Vector Control by Hot Gas
Injection”, Journal of Spacecraft and Rockets, Vol. 3, No.4, 1966, pp.
737-739.
[9] Zeierman, I., Timnat, Y. M., “Full Control of Solid Propellant Rockets
by Secondary Injection”, Journal of Spacecraft and Rockets , Vol. 10,
No. 3, 1973.
[10] Masuya, G., “Secondary Gas Injection into a Supersonic Conical
Nozzle”, AIAA Journal, Vol. 15, No.3, 1977, pp. 301-302.
[11] Ko, H., Yoon, W., “Performance Analysis of Secondary Gas Injection
into a Conical Rocket Nozzle”, Journal of Propulsion and Power, Vol:
18, 2002, pp. 585-591.
[12] Broadwell, J.E., “Analysis of Fluid Mechanics of Secondary Injection
for Thrust Vector Control”, AIAA Journal, Vol. 1, No. 10, 1963, p1067.
[13] Newton, J.F., Spaid, F.M., “Interaction of Secondary Injectants and
RocketExhausts for Thrust Vector Control”, Journal of the American
Rocket Society, August 1962, pp, 1203-1211.
[14] Balu, R., “Analysis of Performance of a Hot Gas Injection Thrust Vector
Control System”, Journal of Propulsion and Power, Vol. 4, 1991, pp.
580-585.
[15] Robert A.Wasko., “Performance of annular plug and expansiondeflection
nozzles including external flow effects at transonic Mach
numbers,” NASA Technical Note, Lewis Research Center, Ohio, 1968.
[16] John J. Korte, “Parametric model of an aerospike rocket engine,” AIAA
Paper 2000-1044.
[17] Hanumantharao.K, Ragothaman.S, Arun Kumar.B, Giri Prasad.M, and
V.R. Sanal Kumar, “Studies on Fluidic Injection Thrust Vectoring in
Aero Spike Nozzles,” AIAA Aerospace Science Conference, Florida,
Jan 2011, Paper No.AIAA-2011-0293.
[18] Subanesh Shyam Rajendran, Aravind Kumar T.R, Nareshkumar K.S,
Ragothaman. S, Riyana Raveendran, Sanal Kumar.V.R, “Studies on
Thrust Vector Control using Secondary Injection Sonic and Supersonic
Jets”, 2nd International Conference on Mechanical, Electronics and
Mechatronics Engineering, PSRC Conference, London, UK, 17-18 June
2013.</p>
<p>[1] George P Sutton and Oscar Biblarz, “Rocket propulsion elements,” 7th
Edn., John Wiley & Sons, Inc., New York, 2001.
[2] A. E. Wetherbee, Jr "Directional Control Means for April Supersonic
Vehiclo (OCR), U.S Patent 2,943,821, Issue Date: July 5 1960 .
[3] A. J. Porzio and M.E.Franke "Experimental study of a confined jet thrust
vector control nozzle", Journal of Propulsion and Power, Vol. 5, No. 5
(1989), pp. 596-601.
[4] Erinc Erdem, Thrust vector control by secondary injection, M.S Thesis,
Mechanical Engineering, Sept. 2006, Middle East Technical University.
[5] Balar, R., et al., “Comparison of Parallel and Normal Fuel Injection in
aSupersonic Combustor”, AIAA Paper 2006-4442, July 2006.
[6] Erdem, E., et al., “Parametric Study of Secondary Gas Injection into a
Conical Rocket Nozzle for Thrust Vectoring”, AIAA Paper 2006-4942,
July 2006.
[7] Dhinagram, R., BOSE, T. K., “Comparison of Euler and Navier Stokes
Solutions for Nozzle Flows with Secondary Injection”, AIAA Paper 96-
0453, Jan. 1996.
[8] Inouye, T., “Experiments on Rocket Thrust Vector Control by Hot Gas
Injection”, Journal of Spacecraft and Rockets, Vol. 3, No.4, 1966, pp.
737-739.
[9] Zeierman, I., Timnat, Y. M., “Full Control of Solid Propellant Rockets
by Secondary Injection”, Journal of Spacecraft and Rockets , Vol. 10,
No. 3, 1973.
[10] Masuya, G., “Secondary Gas Injection into a Supersonic Conical
Nozzle”, AIAA Journal, Vol. 15, No.3, 1977, pp. 301-302.
[11] Ko, H., Yoon, W., “Performance Analysis of Secondary Gas Injection
into a Conical Rocket Nozzle”, Journal of Propulsion and Power, Vol:
18, 2002, pp. 585-591.
[12] Broadwell, J.E., “Analysis of Fluid Mechanics of Secondary Injection
for Thrust Vector Control”, AIAA Journal, Vol. 1, No. 10, 1963, p1067.
[13] Newton, J.F., Spaid, F.M., “Interaction of Secondary Injectants and
RocketExhausts for Thrust Vector Control”, Journal of the American
Rocket Society, August 1962, pp, 1203-1211.
[14] Balu, R., “Analysis of Performance of a Hot Gas Injection Thrust Vector
Control System”, Journal of Propulsion and Power, Vol. 4, 1991, pp.
580-585.
[15] Robert A.Wasko., “Performance of annular plug and expansiondeflection
nozzles including external flow effects at transonic Mach
numbers,” NASA Technical Note, Lewis Research Center, Ohio, 1968.
[16] John J. Korte, “Parametric model of an aerospike rocket engine,” AIAA
Paper 2000-1044.
[17] Hanumantharao.K, Ragothaman.S, Arun Kumar.B, Giri Prasad.M, and
V.R. Sanal Kumar, “Studies on Fluidic Injection Thrust Vectoring in
Aero Spike Nozzles,” AIAA Aerospace Science Conference, Florida,
Jan 2011, Paper No.AIAA-2011-0293.
[18] Subanesh Shyam Rajendran, Aravind Kumar T.R, Nareshkumar K.S,
Ragothaman. S, Riyana Raveendran, Sanal Kumar.V.R, “Studies on
Thrust Vector Control using Secondary Injection Sonic and Supersonic
Jets”, 2nd International Conference on Mechanical, Electronics and
Mechatronics Engineering, PSRC Conference, London, UK, 17-18 June
2013.</p>
@article{"International Journal of Mechanical, Industrial and Aerospace Sciences:51523", author = "Jerin John and Subanesh Shyam R. and Aravind Kumar T. R. and Naveen N. and Vignesh R. and Krishna Ganesh B and Sanal Kumar V. R.", title = "Numerical Studies on Thrust Vectoring Using Shock Induced Supersonic Secondary Jet", abstract = "Numerical studies have been carried out using a
validated two-dimensional RNG k-epsilon turbulence model for the
design optimization of a thrust vector control system using shock
induced supersonic secondary jet. Parametric analytical studies have
been carried out with various secondary jets at different divergent
locations, jet interaction angles, jet pressures. The results from the
parametric studies of the case on hand reveal that the primary nozzle
with a small divergence angle, downstream injections with a distance
of 2.5 times the primary nozzle throat diameter from the primary
nozzle throat location warrant higher efficiency over a certain range
of jet pressures and jet angles. We observed that the supersonic
secondary jet opposing the core flow with jets interaction angle of
40o to the axis far downstream of the nozzle throat facilitates better
thrust vectoring than the secondary jet with same direction as that of
core flow with various interaction angles. We concluded that fixing
of the supersonic secondary jet nozzle pointing towards the throat
direction with suitable angle at a distance 2 to 4 times of the primary
nozzle throat diameter, as the case may be, from the primary nozzle
throat location could facilitate better thrust vectoring for the
supersonic aerospace vehicles.
", keywords = "Fluidic thrust vectoring, rocket steering, supersonic
secondary jet location, TVC in spacecraft.", volume = "7", number = "8", pages = "1629-7", }
