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Study of wedge-shaped Jet tabs for effective Thrust vector control in Supersonic vehicles

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Abstract

This work explores the thrust vector control in a 2D convergent divergent nozzle with wedge shaped jet tab. The Computational analysis has been carried out with different thickness and height of jet tabs. The flow topology analysis is carried out qualitatively and quantitatively. The wedge-shaped jet tabs with 10%, 20%, 30% and 40% of height and 10 mm, 12 mm, 14 mm, 16 mm thickness are considered for right isosceles, left isosceles and isosceles shapes. The deflection angle is calculated to identify the best effective thrust deflection configuration. Results indicate that, when thickness and height of jet tab increases the deflection angle reduces due to the formation of mixing layer and shock wave generation. Also, depending on the shape of jet tab the oblique shock formation and angle of shock varied. The thickness-based CFD optimization shows that a 4.66° deflection angle with 10 mm thickness and 40% height isosceles tab produces the best deflection. The right jet tab with 12 mm and 14 mm thickness with 30% and 20% height shows 4.75° and 4.14° deflection angle. In the case of 16 mm thickness tab, left isosceles jet tab with 10% height shows 4.14° of deflection angle. It is concluded form the study that, the highest rate of deflection was produced by the right isosceles tab with 12 mm thickness and 30% height. This can be used for thrust deflection in supersonic aircrafts and missiles.

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Abbreviations

2D:

Two-dimensional

CFD:

Computational fluid dynamics

TVC:

Thrust vector control

NPR:

Nozzle pressure ratio

FMG:

Full multi-grid

M :

Mach number

T :

Thickness

D :

Diameter

M T :

Mass flow rate at throat

V T :

Velocity at the throat

P T :

Pressure at the throat

A T :

Area at the throat

F DUX :

Pressure force in the upper divergence nozzle wall

F DUY :

Pressure force in the lower divergence nozzle wall

F OX :

Pressure force in the obstacle

P O :

Static ambient pressure

References

  1. Bastian TW (1981) Jet tab contol mechanism for thrust vector control, general dynamics, pomona division, pomona, Cali, U.S. Patent

  2. Simmons JM, Gourlayt CM, Leslief BA (1987) Flow generated by ramp tabs in a rocket nozzle exhaust, university of queensland brisbane, Queensland, Australia ASA Lewis Research Centre, Grant NAG 3–35. J Propuls Power

  3. Wan C, Yu SCM (2011) Investigation of air tab’s effect in supersonic jets, Nanyang Technological University, Singapore. J Propuls Power 27(5). https://doi.org/10.2514/1.B34079

  4. Kostić OP, Stefanović ZA, Kostić IA (2015) CFD modelling of supersonic airflow generated by 2D nozzle with and without an obstacle at the exit section. University of Belgrade Faculty of Mechanical Engineering Innovation Centre. FME Trans. https://doi.org/10.5937/fmet1502107k

  5. Kaushik M, Rathakrishnan E (2015) Tab aspect ratio effect on supersonic jet mixing. Int J Turbo Jet Eng 32(3):265–273

    Google Scholar 

  6. Daljit Majil D (2016) Optimization of nozzle parameters for various thrust vectoring nozzle using cfd. In: International Conference on Trending researches in Engineering, Science & Technology

  7. Kostić O, Stefanović Z, Kostić I (2017) Comparative CFD analyses of a 2d supersonic nozzle flow with jet tab and jet vane, University of Belgrade Faculty of Mechanical Engineering Kraljice Marije 16, 11000 Belgrade, Serbia, O. Kostić i dr Usporedna CFD analiza 2D. strujanja supersoničnog mlaznika sa spojlerom i s mlaznim krilcem Tehnički vjesnik 24: 1335–1344

  8. Imdad M, Hussain M, Mehmood Baig M, Kanwal T (2016) CFD modeling of thrust vector control through jet vane. Department of Mathematics, NEDUET, Karachi, Pakistan. Sci Int (Lah) 28(2): 1151–1156. ISSN 1013–5316; CODEN: SINTE 8

  9. Zivkovic S, Stefanovic P, Gligorijevic N (2016) Experimental and simulation testing of thermal loading in the jet tabs of a thrust vector control system, University of Niš, University of Belgrade, Belgrade, Serbia. Thermal Sci J. https://doi.org/10.2298/TSC1150914208Z

    Article  Google Scholar 

  10. Bajpai A, Rathakrishnan E (2017) Control of a supersonic elliptical jet, Indian Institute of Technology Kanpur. Aeronaut J. https://doi.org/10.1017/aer.2017.114

    Article  Google Scholar 

  11. Singh Chand D, Pradeep Shekhar B, John Bosco A, Singh Bali R (2015) Manipulation of shock train for under expanded jets by tabs. Department of Aeronautical Engineering, Tagore Engineering College, Chennai. Int J Eng Res Technol (IJERT) ISSN: 2278-0181

  12. Maruthupandiyan K, Rathakrishnan E (2018) Tab location effect on supersonic jet mixing, Department of Aeronautical Engineering, Institute of Aeronautical Engineering Hyderabad India, Royal Aeronautical Society. Aeronaut J. https://doi.org/10.1017/aer.2018.61

  13. Kanwal T, Cong R, Ye Y, Zhao Z, Wu J, Zhang C (2019) Numerical research on jet tab thrust vector nozzle aerodynamic characteristics, High Speed Aerodynamic. Journal of Physics. Institute of China Aerodynamic Research and Development Center, Mianyang, China

  14. Rathakrishnan E (2009) Experimental studies on the limiting tab, Indian Institute of Technology, Kanpur 208 016, India. AIAA J. https://doi.org/10.2514/1.43790

    Article  Google Scholar 

  15. Hollstein HJ (1965) Jet tab thrust vector control, lockheed missiles and space company, Sunny vale, 2(6), AIAA

  16. Zaman Internal KBMQ, Reeder MF, Samimy M (1993) Control of an axi- symmetric jet using vortex generators. , Physics of Fluids. Department of Mechanical Engineering NASA Lewis Research Center, Cleveland, Ohio

  17. Naren Shankar R, Thanigaiarasu S, Elangovan S, Rathakrishnan E (2017) Co-flowing jet control using lip thickness variation. J Int Turbo Jet-Eng. https://doi.org/10.1515/tjj-2018-0024

    Article  Google Scholar 

  18. Samimy M, Zaman KBMQ, Reeder MF (1991) Supersonic jet mixing enhancement by vortex generators, Ohio State University, Department of Mechanical Engineering, Ohio. In: AIAA/SAE/ASM E/ASEE 27th Joint Propulsion Conference, AIM-91–2263-CP

  19. Zaman KBMQ, Reeder MF (1991) Supersonic jet mixing enhancement by vortex generators, Ohio State University, Department of Mechanical Engineering, Ohio. In: AIAA/SAE/ASM E/ASEE 27th Joint Propulsion Conference, AIM-91–2263-CP

  20. Zivkovic S, Milinović M, Adamec N (2014) Experimental and numerical research of a supersonic planar thrust vectoring nozzle via mechanical tabs, Military Technical Institute, Ratka Resanovića 1, 11030 Belgrade, Serbia. FME Trans 42(3): 205–211

  21. Ahmed A, Baig A, Shah BH, Rafique M (2016) Numerical study of the effect of geometric parameters on jet tab based TVC system. In: 2016 13th International Bhurban Conference on Applied Sciences and Technology (IBCAST), Islamabad, Pakistan, 2016, pp. 509–514. https://doi.org/10.1109/IBCAST.2016.7429926.

  22. Jyothy VM, Jims John Wessley G (2023) A Numerical study of different jet tab configurations for thrust vector control in supersonic vehicles. In: ASTFE 8th Thermal and Fluids Engineering Conference (TFEC) March, 26-29, 2023, College Park, MD, US. https://doi.org/10.1615/TFEC2023.ahp.046347

  23. Jyothy VM, Jims John G, Wessley N (2023) Study of jet tabs in 2-D convergent-divergent nozzle for thrust vectoring in aerial vehicles. Int J Intell Unmann Syst. https://doi.org/10.1108/IJIUS-11-2022-0131. (ISSN: 2049-6427)

    Article  Google Scholar 

  24. Kaushik M, Deb D, Muresan V, Unguresan M (2020) Assessment of short rectangular-tab actuation of supersonic jet mixing. Res Gate J. https://doi.org/10.3390/act9030072. (Department of Aerospace Engineering, Indian Institute of Technology, Kharagpur)

    Article  Google Scholar 

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Authors and Affiliations

  1. Department of Aerospace Engineering, Karunya Institute of Technology and Sciences, Coimbatore, 641114, India

    V. M. Jyothy & G. Jims John Wessley

  2. Department of Mechanical Engineering, Karunya Institute of Technology and Sciences, Coimbatore, 641114, India

    A. Brusly Solomon

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  1. V. M. Jyothy
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  2. G. Jims John Wessley
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  3. A. Brusly Solomon
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Correspondence to G. Jims John Wessley.

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Jyothy, V.M., Wessley, G.J.J. & Solomon, A.B. Study of wedge-shaped Jet tabs for effective Thrust vector control in Supersonic vehicles. AS (2023). https://doi.org/10.1007/s42401-023-00257-y

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