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Innovative thrust vectoring system with moveable jet vanes integrated with a moveable diffuser – Measurement and analysis of selected nozzle performance parameters

Treść / Zawartość
Identyfikatory
Warianty tytułu
Języki publikacji
EN
Abstrakty
EN
The aim of the study described herein was to design, construct and test a demonstrator of a system to control the direction of the resultant thrust vector of a rocket motor to be used in short range anti-tank missiles with a mass of up to 15 kg. The novelty of the system is that the direction of the resultant thrust vector is manipulated by means of moveable jet vanes integrated with a moveable nozzle diffuser through telescopic connectors. The technology demonstrator was built using different materials and different manufacturing processes. The first versions were 3D printed from plastic materials. Minor modifications to the design were made at an early stage. The final version had the main components made of aluminum using CNC machining. The system, with and without jet vanes, was tested on a specially developed test rig equipped with a multi-axis sensor to measure forces and torques. The nozzle performance parameters measured and analyzed in this study were the components of the thrust vector, the moments and the effective vectoring angle. The findings show that the experimental data are in good agreement with the results of earlier simulations and that the demonstrator is fully operational.
Rocznik
Strony
art. no. e148444
Opis fizyczny
Bibliogr 22 poz., rys.
Twórcy
  • Kielce University of Technology, Department of Mechatronics and Armament Engineering, Faculty of Mechatronics and Mechanical Engineering, al. Tysiąclecia Państwa Polskiego 7, 25-314 Kielce, Poland
autor
  • Kielce University of Technology, Department of Mechatronics and Armament Engineering, Faculty of Mechatronics and Mechanical Engineering, al. Tysiąclecia Państwa Polskiego 7, 25-314 Kielce, Poland
autor
  • Kielce University of Technology, Department of Mechatronics and Armament Engineering, Faculty of Mechatronics and Mechanical Engineering, al. Tysiąclecia Państwa Polskiego 7, 25-314 Kielce, Poland
  • Kielce University of Technology, Department of Mechanical Engineering and Metrology, Faculty of Mechatronics and Mechanical Engineering, al. Tysiąclecia Państwa Polskiego 7, 25-314 Kielce, Poland
Bibliografia
  • [1] M.S.R.C. Murty, M.S. Rao, and D. Chakraborty, “Numerical simulation of nozzle flow field with jet vane thrust vector control,” J. Aerosp. Eng., vol. 224, pp. 541–548, 2009, doi: 10.1243/09544100JAERO677.
  • [2] D. Daljit Majil, M. Saleem, and S. Kumaresan, “Computational study on reduction of thrust loss in jet vane thrust vectoring nozzle,”. Int. J. Aerosp. Mech. Eng., vol. 3, no. 5, pp. 1–6, 2016.
  • [3] W.-H. Kim, J.-Ch. Bae, S.-T. Lim, and S.-H. Park, “Jet vane thrust vector control system,” U.S. Patent US007313910B2, Jan. 1, 2008.
  • [4] M.S.R.C. Murty and D. Chakraborty, “Numerical Characterisation of Jet-Vane based Thrust Vector Control Systems,” Def. Sci. J., vol. 65, no. 4, pp. 261–264, 2015, doi: 10.14429/dsj.65.7960.
  • [5] C.S. Shin and H.D. Kim, “A Fundamental Study of Thrust-Vector Control Using a Dual Throat Nozzle,” Proc. Spring Conference 2010 of the Korean Society of Propulsion Engineering, 2010, pp. 339–342.
  • [6] R. Chouicha, M. Sellam, and S. Bergheul, “Effect of chemical reactions on the fluidic thrust vectoring of an axisymmetric nozzle,” Int. J. Aviat. Aeronaut. Aerosp., vol. 5, no. 5, pp. 1–15, 2019, doi: 10.15394/ijaaa.2019.1377.
  • [7] S. Forde, M. Bulman, and T. Neill, “Thrust augmentation nozzle (TAN) concept for rocket engine booster applications,” Acta Astronaut., vol. 59, pp. 271–277, 2006, doi: 10.1016/j.actaastro.2006.02.052.
  • [8] E. Resta, R. Marsilio, and M. Ferlauto, “Thrust Vectoring of a Fixed Axisymmetric Supersonic Nozzle Using the Shock-Vector Control Method,” Fluids, vol. 6, p. 441, 2021, doi: 10.3390/fluids6120441.
  • [9] V. Zmijanovic, V. Lago, L. Léger, E. Depussay, M. Sellam, and A. Chpoun, “Thrust vectoring effects of a transverse gas injection into a supersonic cross flow of an axisymmetric convergent-divergent nozzle,” Prog. Propuls. Phys., vol. 4, pp. 227–256, 2013, doi: 10.1051/eucass/201304227.
  • [10] J.J. Isaac and C. Rajashekar, “Fluidic thrust vectoring nozzles,” Propulsion Division National Aerospace Laboratories (Council of Scientific & Industrial Research), Bangalore 560017, India, 2014. [Online]. Available: https://core.ac.uk/download/pdf/151646399.pdf
  • [11] J. Harris and N. Slegers, “Performance of a fire-and-forget anti-tank missile with a damaged wing,” Math. Comput. Model., vol. 50, pp. 292–305, 2009, doi: 10.1016/j.mcm.2009.02.009.
  • [12] W. Bużantowicz and J. Pietrasieński, “Dual-control missile guidance: A simulation study,” J. Theor. Appl. Mech., vol. 56, no. 3, pp. 727–739, 2018, doi: 10.15632/jtam-pl.56.3.727.
  • [13] M. Grzyb, Ł. Nocoń, Ł. Nowakowski, and P. Szmidt, “Rocket motor exhaust nozzle,” PL Patent Pat.241948, filed 4 June 2020, and issued 13 October 2022.
  • [14] M. Grzyb, Ł. Nocoń, Ł. Nowakowski, and P. Szmidt, “Rocket motor exhaust nozzle,” PL Patent Pat.241949, filed 4 June 2020, and issued 13 October 2022.
  • [15] M. Grzyb, Ł. Nocoń, Ł. Nowakowski, and P. Szmidt, “Rocket motor exhaust nozzle,” PL Patent Pat.241946, filed 4 June 2020, and issued 13 October 2022.
  • [16] M. Grzyb, Ł. Nocoń, Ł. Nowakowski, and P. Szmidt, “Rocket motor exhaust nozzle,” PL Patent Pat.241947, 13 October 2022.
  • [17] M. Grzyb, Ł. Nocoń, Ł. Nowakowski, and P. Szmidt, “Rocket motor exhaust nozzle,” PL Patent Pat.241945, 12 October 2022.
  • [18] M. Grzyb, Ł. Nocoń, Ł. Nowakowski, and P. Szmidt, “Rocket motor exhaust nozzle,” PL Patent Pat.241969, 17 October 2022.
  • [19] Z. Koruba and Ł. Nocoń, “Modified linear-quadratic regulator used for controlling anti-tank guided missile in vertical plane,” J. Theor. App. Mech., vol. 58, pp. 723–732, 2020, doi: 10.15632/jtam-pl/122205.
  • [20] Ł. Nocoń, M. Grzyb, P. Szmidt, Z. Koruba, and Ł. Nowakowski, “Control Analysis with Modified LQR Method of Anti-Tank Missile with Vectorization of the Rocket Engine Thrust,” Energies, vol. 15, no. 1, p. 356(1–17), 2022, doi: 10.3390/en15010356.
  • [21] Ł. Nocoń and Z. Koruba, “Modification of control actuation systems of ATGM,” in Proc. 23rd International Conference on Engineering Mechanics, Czech Republic, 15-18 May 2017, pp. 714–717.
  • [22] Z. Koruba and Ł. Nocoń, “Optimal Compensator for Anti-Ship Missile with Vectorization of Engine Thrust,” Appl. Mech. Mater., vol. 817, pp. 279–288, 2016, doi: 10.4028/www.scientific.net/AMM.817.279.
Uwagi
Opracowanie rekordu ze środków MNiSW, umowa nr SONP/SP/546092/2022 w ramach programu "Społeczna odpowiedzialność nauki" - moduł: Popularyzacja nauki i promocja sportu (2024).
Typ dokumentu
Bibliografia
Identyfikator YADDA
bwmeta1.element.baztech-1a98b3fa-faf0-474c-ab61-4e717f6a47e0
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