Volume 20, Issue 5 (May 2020)                   Modares Mechanical Engineering 2020, 20(5): 1211-1221 | Back to browse issues page

XML Persian Abstract Print

1- Aerospace Engineering Faculty, Shahid Satari Aeronautical University of Science & Technology, Tehran, Iran , sharafi@ssau.ac.ir
2- Aerospace Engineering Faculty, Shahid Satari Aeronautical University of Science & Technology, Tehran, Iran
Abstract:   (2419 Views)
In this research, the effect of several unconventional obstructions with cubic, spherical, cylindrical, and cone geometries on the propulsion vector of a convergent-divergent micro nozzle as a new method in propulsion vector control is experimentally investigated. For this purpose, a convergent-divergent nozzle was designed and constructed in small dimensions. This nozzle is such that the Mach number is its nominal output in full expansion conditions 2. The wall of this nozzle is designed to measure pressure variations with pressure holes. Also, in the nozzle wall, a duct has been created to apply a bulge inside the nozzle. Pressure sensors and the shadograph system have been used to pressure measurement and check the outlet flow field respectively. The total pressure of the calming chamber is constant in all experiments and is equal to 5.5 times. The results of this study show that the maximum deviation is related to an obstruction with a cubic geometry which is 2.1 degrees. Also, the geometries that have sharp corners are more shock-shaped and hit the opposite wall. In this research, the shock formed by a cubic barrier has hit the opposite wall, but with a spherical shaped and cone-shaped barrier, the shock comes out from the nozzle. Also, these results indicate that the axial force of the nozzle has been reduced to a very small extent.
Full-Text [PDF 1241 kb]   (1601 Downloads)    
Article Type: Original Research | Subject: Aerodynamics
Received: 2019/06/19 | Accepted: 2019/10/30 | Published: 2020/05/9

1. Sutton GP, Biblarz O. Rocket propulsion elements, 9th edition. New York: John Wiley & Sons; 2016. [Link]
2. Heidari MR, Noorolahi A. Liquid injection thrust vector control and effective parameters, Journal of Energetic Materials. 2008;3(1):15-24. [Persian] [Link]
3. Gubse RD, An experimental investigation of thrust vector control by secondary injection. Washington, DC: National Aeronautics and Space Administration; 1965. [Link]
4. Balu R, Marathe A, Paul P, Mukunda H. Analysis of performance of hot gas injection thrust vector control system. Journal of Propulsion and Power. 1991;7(4):580-585. [Link] [DOI:10.2514/3.23365]
5. Dhinagaran R, Bose TK. Comparison of Euler and navier-stokes solutions for nozzle flows with secondary injection. 34th Aerospace Sciences Meeting and Exhibit. UK: American Institute of Aeronautics and Astronautics; 1996. Paper 96-0453. [Link] [DOI:10.2514/6.1996-453]
6. Hollstein HJ. Jet tab thrust vector control. Journal of Spacecraft and Rockets. 1965;2(6):927-930. [Link] [DOI:10.2514/3.28316]
7. Eatough R. Jet tab thrust vector control system demonstration. 7th Propulsion Joint Specialist Conference. UK: American Institute of Aeronautics and Astronautics; 1971. Paper 71-752. [Link] [DOI:10.2514/6.1971-752]
8. Simmons JM, Gourlay CM, Leslie BA. The flow generated by ramp tabs in a rocket nozzle exhaust. 24th Aerospace Sciences Meeting. UK: American Institute of Aeronautics and Astronautics; 1986. Paper 86-0282. [Link] [DOI:10.2514/6.1986-282]
9. Hileman J, Samimy M. Effects of vortex generating tabs on noise sources in an ideally expanded Mach 1.3 jet. International Journal of Aeroacoustics. 2003;2(1):35-63. [Link] [DOI:10.1260/147547203322436935]
10. Phanindra BC, Rathakrishnan E. Corrugated tabs for supersonic jet control. AIAA Journal. 2010;48(2):453-465. [Link] [DOI:10.2514/1.44896]
11. Shin CS, Kim HD, Setoguchi T, Matsuo S. A computational study of thrust vectoring control using dual throat nozzle. Journal of Thermal Science. 2010;19(6):486-490. [Link] [DOI:10.1007/s11630-010-0413-x]
12. Zmijanovic V, Lago V, Sellam M, Chpoun A. Thrust shock vector control of an axisymmetric conical supersonic nozzle via secondary transverse gas injection. Shock Waves. 2014;24(1):97-111. [Link] [DOI:10.1007/s00193-013-0479-y]
13. Deng R, Kong F, KimHD. Numerical simulation of fluidic thrust vectoring in an axisymmetric supersonic nozzle. Journal of Mechanical Science and Technology. 2014;28(12):4979-4987. [Link] [DOI:10.1007/s12206-014-1119-x]
14. Deng R, Setoguchi T, Kim HD. Large eddy simulation of shock vector control using bypass flow passage. Journal of Heat and Fluid Flow. 2016;62:474-481. [Link] [DOI:10.1016/j.ijheatfluidflow.2016.08.011]
15. Salehifar M, Tahani M, Hojaji M, Dartoomian A. CFD modeling for flow field characterization and performance analysis of HGITVC. Applied Thermal Engineering. 2016;103:291-304. [Link] [DOI:10.1016/j.applthermaleng.2016.02.087]
16. Zivkovic S, Milinovic MM, Stefanovic PL, Pavlovic PB, Gligorijevic NI. Experimental and simulation testing of thermal loading in the jet tabs of a thrust vector control system. Thermal Science. 2016;20(1):275-286. [Link] [DOI:10.2298/TSCI150914208Z]
17. Mokhtari D, Hojaji M, Afrand M. experimental investigation of the effect of cylindrical protuberance with different penetration the thrust vector a c-d nozzle in supersonic regime. Modares Mechanical Engineering. 2019;19(5):1145-1154. [Persian] [Link]
18. Tahani M, Hojaji M, Mahmoodi Jezeh SV. Turbulent jet in crossflow analysis with LES approach. Journal of Aircraft Engineering and Aerospace Technology. 2016;88(6):717-728. [Link] [DOI:10.1108/AEAT-10-2014-0167]
19. Hojaji M, Soltani MR, Taeibi-Rahni M. New visions in experimental investigations of a supersonic under-expanded jet into a high subsonic crossflow. Journal of Aerospace Engineering. 2010;224(10):1069-1080. [Link] [DOI:10.1243/09544100JAERO748]
20. Viti V, Neel R, Schetz JA. Detailed flow physics of the supersonic jet interaction flow field. Physics of Fluids. 2009;21(4):1-16. [Link] [DOI:10.1063/1.3112736]

Rights and permissions
Creative Commons License This work is licensed under a Creative Commons Attribution-NonCommercial 4.0 International License.