Numerical Studies on Thrust Vectoring Using Shock-Induced Self Impinging Secondary Jets
Numerical studies have been carried out using a
validated two-dimensional standard k-omega turbulence model for
the design optimization of a thrust vector control system using shock
induced self-impinging supersonic secondary double jet. Parametric
analytical studies have been carried out at different secondary
injection locations to identifying the highest unsymmetrical
distribution of the main gas flow due to shock waves, which produces
a desirable side force more lucratively for vectoring. The results from
the parametric studies of the case on hand reveal that the shock
induced self-impinging supersonic secondary double jet is more
efficient in certain locations at the divergent region of a CD nozzle
than a case with supersonic single jet with same mass flow rate. We
observed that the best axial location of the self-impinging supersonic
secondary double jet nozzle with a given jet interaction angle, built-in
to a CD nozzle having area ratio 1.797, is 0.991 times the primary
nozzle throat diameter from the throat location. We also observed
that the flexible steering is possible after invoking ON/OFF facility to
the secondary nozzles for meeting the onboard mission requirements.
Through our case studies we concluded that the supersonic self-impinging
secondary double jet at predesigned jet interaction angle
and location can provide more flexible steering options facilitating
with 8.81% higher thrust vectoring efficiency than the conventional
supersonic single secondary jet without compromising the payload
capability of any supersonic aerospace vehicle.
[1] George P Sutton and Oscar Biblarz, “Rocket propulsion elements,” 7th
Edn., John Wiley & Sons, Inc., New York, 2011.
[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] B. Berrier and R. Re, A review of thrust vectoring scheme for fighter
applications,” AIAA/SAE 14th Joint Propulsion Conference, Las Vegas,
July 1978, AIAA Paper No. AIAA 1978-1023.
[4] 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.
[5] J. H. Friddell, M.E.Franke, “Confined jet thrust vector control nozzle
studies,” Journal of Propulsion and Power 8:6, 1239-1244, 1992.
[6] P. J. Strykowski, A. Krothapalli, D. J. Forliti, “Counterflow thrust
vectoring of supersonic jets,” AIAA Journal 34:11, 2306-2314, 1996.
[7] M. R. Van der Veer, P. J. Strykowski, “Counterflow Thrust Vector
Control of Subsonic Jets: Continuous and Bistable Regimes.,” Journal of
Propulsion and Power 13:3, 412-420, 1997.
[8] G. F. Schmid, P. J. Strykowski, M. Madruga, D. Das, and A.
Krothapalli, “Jet Attachment Behavior using Counter flow Thrust
Vectoring,” Proceedings of 13th ONR Propulsion Conference,
Minneapolis, MN, 10-12 August, 2000.
[9] F. S. Alvi, P. J. Strykowski, A. Krothapalli, D. J. Forliti, “Vectoring
Thrust in Multiaxes Using Confined Shear Layers,” Journal of Fluids
Engineering 122:1, 3, 2000.
[10] Erinc Erdem, Thrust vector control by secondary injection, M.S Thesis,
Mechanical Engineering, Sept. 2006, Middle East Technical University.
[11] Kenrick A. Waithe and Karen A. Deere, “Experimental and
computational investigation of multiple injection ports in a convergentdivergent
nozzle for fluidic thrust vectoring,” 21st Applied
Aerodynamics Conference, 23-26 June 2003, Orlando, Florida, AIAA
2003-3802.
[12] Karen A. Deere, Bobby L. Berrier, Jeffrey D. Flamm, Stuart K. Johnson,
“Computational study of fluidic thrust vectoring using separation control
in a nozzle,” 21st Applied Aerodynamics Conference 23-26 June 2003,
Orlando, Florida, AIAA 2003-3803.
[13] Jeffrey D. Flamm, Karen A. Deeret, Mary L. Mason, Bobby L. Berrier,
and Stuart K. Johnson, “Design Enhancements of the Two-Dimensional,
Dual Throat Fluidic Thrust Vectoring Nozzle Concept,” 3rd AIAA Flow
Control Conference, 5 - 8 June 2006; San Francisco, California, AIAA
2006-3701.
[14] 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.
[15] Subanesh Shyam Rajendran, Aravind Kumar T.R, Nareshkumar K. S.,
Ragothaman. S, Riyana Raveendran, Sanal Kumar.V.R, “Studies
onThrust Vector Control using Secondary Injection Sonic and
SupersonicJets”, 2nd International Conference on Mechanical,
Electronics andMechatronics Engineering, PSRC Conference, London,
UK, 17-18 June 2013.
[16] Jerin John, Subanesh Shyam. R., Aravind Kumar T. R., Naveen. N.,
Vignesh. R., Krishna Ganesh. B., Sanal Kumar V. R., “Numerical
Studies on Thrust Vectoring Using Shock Induced Supersonic
Secondary Jet,” World Academy of Science, Engineering and
Technology International Journal of Mechanical, Aerospace, Industrial
and Mechatronics Engineering Vol:7, No:8, 2013.
[17] Lefebvre, A. H., Atomization and Sprays, CRC Press, Boca Raton, FL,
1989. Lefebvre, A. H., Atomization and Sprays, CRC Press, Boca Raton,
FL, 1989.
[18] Bayvel, L. and Orzechowski, Z., Liquid Atomization, CRC Press, vol.
1040, Boca Raton, FL, 1993.
[19] Bush, J. W. M. and Hasha, A. E., On the collision of laminar jets: Fluid
chains and fishbones, J. Fluid Mech., vol. 511, pp. 285–310, 2004.
[20] Yang, V. and Anderson, W., Liquid rocket engine combustion
instability: Progress in Astronautics and Aeronautics, vol. 196, AIAA,
1995. [21] Xiaodong Chen,Dongjun Ma,Vigor Yang, and St´ephane Popinet, High
–fidelity simulations of impinging jet atomization, Atomization and
Sprays, 23 (12): 1079–1101 (2013).
[22] Vidhyasagar, L.S, and Sanal Kumar, V.R., “An Attempt to Correlate the
Collision Theory with Aerodynamic Lift”, 42nd AIAA Fluid Dynamics
and allied Conferences and Exhibit / 30th AIAA Applied Aerodynamics
Conference , New Orleans, USA, 25-28 June 2012, Paper No. AIAA
2012-2772.
[23] Craig A. Hunter, “Experimental Investigation of Separated Nozzle
Flows,” NASA Langley Research Center, Hampton, Virginia 23681,
AIAA Journal of Propulsion and Power, Vol. 20, No. 3, May–June 2004.
[1] George P Sutton and Oscar Biblarz, “Rocket propulsion elements,” 7th
Edn., John Wiley & Sons, Inc., New York, 2011.
[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] B. Berrier and R. Re, A review of thrust vectoring scheme for fighter
applications,” AIAA/SAE 14th Joint Propulsion Conference, Las Vegas,
July 1978, AIAA Paper No. AIAA 1978-1023.
[4] 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.
[5] J. H. Friddell, M.E.Franke, “Confined jet thrust vector control nozzle
studies,” Journal of Propulsion and Power 8:6, 1239-1244, 1992.
[6] P. J. Strykowski, A. Krothapalli, D. J. Forliti, “Counterflow thrust
vectoring of supersonic jets,” AIAA Journal 34:11, 2306-2314, 1996.
[7] M. R. Van der Veer, P. J. Strykowski, “Counterflow Thrust Vector
Control of Subsonic Jets: Continuous and Bistable Regimes.,” Journal of
Propulsion and Power 13:3, 412-420, 1997.
[8] G. F. Schmid, P. J. Strykowski, M. Madruga, D. Das, and A.
Krothapalli, “Jet Attachment Behavior using Counter flow Thrust
Vectoring,” Proceedings of 13th ONR Propulsion Conference,
Minneapolis, MN, 10-12 August, 2000.
[9] F. S. Alvi, P. J. Strykowski, A. Krothapalli, D. J. Forliti, “Vectoring
Thrust in Multiaxes Using Confined Shear Layers,” Journal of Fluids
Engineering 122:1, 3, 2000.
[10] Erinc Erdem, Thrust vector control by secondary injection, M.S Thesis,
Mechanical Engineering, Sept. 2006, Middle East Technical University.
[11] Kenrick A. Waithe and Karen A. Deere, “Experimental and
computational investigation of multiple injection ports in a convergentdivergent
nozzle for fluidic thrust vectoring,” 21st Applied
Aerodynamics Conference, 23-26 June 2003, Orlando, Florida, AIAA
2003-3802.
[12] Karen A. Deere, Bobby L. Berrier, Jeffrey D. Flamm, Stuart K. Johnson,
“Computational study of fluidic thrust vectoring using separation control
in a nozzle,” 21st Applied Aerodynamics Conference 23-26 June 2003,
Orlando, Florida, AIAA 2003-3803.
[13] Jeffrey D. Flamm, Karen A. Deeret, Mary L. Mason, Bobby L. Berrier,
and Stuart K. Johnson, “Design Enhancements of the Two-Dimensional,
Dual Throat Fluidic Thrust Vectoring Nozzle Concept,” 3rd AIAA Flow
Control Conference, 5 - 8 June 2006; San Francisco, California, AIAA
2006-3701.
[14] 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.
[15] Subanesh Shyam Rajendran, Aravind Kumar T.R, Nareshkumar K. S.,
Ragothaman. S, Riyana Raveendran, Sanal Kumar.V.R, “Studies
onThrust Vector Control using Secondary Injection Sonic and
SupersonicJets”, 2nd International Conference on Mechanical,
Electronics andMechatronics Engineering, PSRC Conference, London,
UK, 17-18 June 2013.
[16] Jerin John, Subanesh Shyam. R., Aravind Kumar T. R., Naveen. N.,
Vignesh. R., Krishna Ganesh. B., Sanal Kumar V. R., “Numerical
Studies on Thrust Vectoring Using Shock Induced Supersonic
Secondary Jet,” World Academy of Science, Engineering and
Technology International Journal of Mechanical, Aerospace, Industrial
and Mechatronics Engineering Vol:7, No:8, 2013.
[17] Lefebvre, A. H., Atomization and Sprays, CRC Press, Boca Raton, FL,
1989. Lefebvre, A. H., Atomization and Sprays, CRC Press, Boca Raton,
FL, 1989.
[18] Bayvel, L. and Orzechowski, Z., Liquid Atomization, CRC Press, vol.
1040, Boca Raton, FL, 1993.
[19] Bush, J. W. M. and Hasha, A. E., On the collision of laminar jets: Fluid
chains and fishbones, J. Fluid Mech., vol. 511, pp. 285–310, 2004.
[20] Yang, V. and Anderson, W., Liquid rocket engine combustion
instability: Progress in Astronautics and Aeronautics, vol. 196, AIAA,
1995. [21] Xiaodong Chen,Dongjun Ma,Vigor Yang, and St´ephane Popinet, High
–fidelity simulations of impinging jet atomization, Atomization and
Sprays, 23 (12): 1079–1101 (2013).
[22] Vidhyasagar, L.S, and Sanal Kumar, V.R., “An Attempt to Correlate the
Collision Theory with Aerodynamic Lift”, 42nd AIAA Fluid Dynamics
and allied Conferences and Exhibit / 30th AIAA Applied Aerodynamics
Conference , New Orleans, USA, 25-28 June 2012, Paper No. AIAA
2012-2772.
[23] Craig A. Hunter, “Experimental Investigation of Separated Nozzle
Flows,” NASA Langley Research Center, Hampton, Virginia 23681,
AIAA Journal of Propulsion and Power, Vol. 20, No. 3, May–June 2004.
@article{"International Journal of Mechanical, Industrial and Aerospace Sciences:70508", author = "S. Vignesh and N. Vishnu and S. Vigneshwaran and M. Vishnu Anand and Dinesh Kumar Babu and V. R. Sanal Kumar", title = "Numerical Studies on Thrust Vectoring Using Shock-Induced Self Impinging Secondary Jets", abstract = "Numerical studies have been carried out using a
validated two-dimensional standard k-omega turbulence model for
the design optimization of a thrust vector control system using shock
induced self-impinging supersonic secondary double jet. Parametric
analytical studies have been carried out at different secondary
injection locations to identifying the highest unsymmetrical
distribution of the main gas flow due to shock waves, which produces
a desirable side force more lucratively for vectoring. The results from
the parametric studies of the case on hand reveal that the shock
induced self-impinging supersonic secondary double jet is more
efficient in certain locations at the divergent region of a CD nozzle
than a case with supersonic single jet with same mass flow rate. We
observed that the best axial location of the self-impinging supersonic
secondary double jet nozzle with a given jet interaction angle, built-in
to a CD nozzle having area ratio 1.797, is 0.991 times the primary
nozzle throat diameter from the throat location. We also observed
that the flexible steering is possible after invoking ON/OFF facility to
the secondary nozzles for meeting the onboard mission requirements.
Through our case studies we concluded that the supersonic self-impinging
secondary double jet at predesigned jet interaction angle
and location can provide more flexible steering options facilitating
with 8.81% higher thrust vectoring efficiency than the conventional
supersonic single secondary jet without compromising the payload
capability of any supersonic aerospace vehicle.", keywords = "Fluidic thrust vectoring, rocket steering, self-impinging
secondary supersonic jet, TVC in aerospace vehicles.", volume = "9", number = "6", pages = "1118-7", }
