TECHNICAL MECHANICS
ISSN (Print): 1561-9184, ISSN (Online): 2616-6380

English
Russian
Ukrainian
Home > Journal Issues > No 4 (2020) Technical mechanics > 2
___________________________________________________

UDC 629.78.533.6.013:621.45

Technical mechanics, 2020, 4, 13 - 28

Increasing the efficiency of an interceptor system for rocket engine thrust vector control

DOI: https://doi.org/10.15407/itm2020.04.013

Strelnykov H. O., Tokareva O. L., Ihnatiev O. D., Pryadko N. S., Ternova K. V.

      ABOUT THE AUTHORS

Strelnykov H. O.
Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine

Tokareva O. L.
Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine

Ihnatiev O. D.
Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine

Pryadko N. S.
Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine

Ternova K. V.
Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine

      ABSTRACT

      This work is concerned with studying the static and dynamic characteristics of the gas-dynamic (interceptor) subsystem of a combined system for thrust vector control and identifying ways to increase its efficiency. The combined control system includes a mechanical and a gas-dynamic subsystem. The gas-dynamic thrust vector control subsystem is the most important and reliable part of the combined control system.
      Consideration is given to disturbing the supersonic flow by installing a solid obstacle (interceptor) in the middle part of the rocket engine nozzle. An important advantage of this method to gas-dynamically control the rocket engine thrust vector is that the thrust vector control loss of the specific impulse is nearly absent because the control force is produced without any consumption of the working medium. Injection through the interceptor protects it against exposure to the nozzle supersonic flow and produces an additional lateral force.
      By now, the optimum height of the mass supply opening in the interceptor that maximizes the control force has not been determined, and the dynamic characteristics of this system have not been studied.
      The aim of this work is to find the optimum position of the opening for working medium supply through the interceptor that maximizes the added control force and to determine the effect of the transfer functions of the interceptor system components on the characteristics of the control force production transient.
      As a result of the study of the static characteristics of the supersonic flow disturbance in a nozzle with an interceptor through which a secondary working medium is injected, it is concluded that in terms of thrust vector control efficiency and interceptor protection the injection opening should be situated in the upper part of the interceptor.
      The transfer function of interceptor control of the liquid-propellant rocket engine thrust vector is obtained with account for the production of an additional control force by the injection of a liquid propellant component. It is found that the loss of stability of the operation of an injection interceptor unit depends on the transient of the working medium injection control valve.
      Pdf (English)







      KEYWORDS

rocket engine, thrust vector control system, static and dynamic characteristics, gas-dynamic system, combined control system

      FULL TEXT:

Pdf (English)









      REFERENCES

1. Kovalenko N. D., Sheptun Yu. D., Kovalenko T. A., Strelnikov G. A. The new concept of thrust vector control for rocket engine. System Technologies. 2016. No. 6(107). Pp. 120-127. 2. Kovalenko N. D. Rocket Engine as an Actuator of the Rocket Flight Control System. Dnipropetrovsk: Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the National Space Agency of Ukraine, 2004. 412 pp. (in Russian). 3. Volkov K. N., Emelyanov V. N., Yakovchuk M. S. Flow structure and thrust change at gas jet injection into the supersonic part of a nozzle. Technical Physics. 2019. V. 89. No. 3. Pp. 317-323. https://doi.org/10.1134/S1063784219030265

4. Volkov K. N., Emelyanov V. N., Yakovchuk M. S. Multiparameter optimization of operating control by the thrust vector based on the jet injection into the supersonic part of a nozzle. Numerical Methods and Programming. 2018. V. 19. No. 2. Pp. 158 - 172. (in Russian). 5. Volkov K. N., Emelyanov V. N., Yakovchuk M. S. Numerical simulation of the interaction of a transverse jet with a supersonic flow using different turbulence models. Journal of Applied Mechanics and Technical Physics. 2015. V. 56. No. 5. Pp. 789-798. https://doi.org/10.1134/S0021894415050053

6. Volkov K. N., Emel'yanov V. N., Yakovchuk M. S. Transverse injection of a jet from the surface of a flat plate into the supersonic flow over it. Journal of Engineering Physics and Thermophysics. 2017. V. 90. No. 6. Pp. 1439-1444. https://doi.org/10.1007/s10891-017-1703-x

7. Erdem E., Albayrak K., Tinaztepe H. T. Parametric study of secondary gas injection into a conical rocket nozzle for thrust vectoring. AIAA Paper. 2006. No. 2006?4942. https://doi.org/10.2514/6.2006-4942

8. Huang W., Liu W. D., Li S. B., Xia Z. X., Liu J., Wang Z. G. Influences of the turbulence model and the slot width on the transverse slot injection flow field in supersonic flows. Acta Astronautica. 2012. V. 73. Pp. 1?9. https://doi.org/10.1016/j.actaastro.2011.12.003

9. Huang W., Wang Z. G., Wu J. P., Li S. B. Numerical prediction on the interaction between the incident shock wave and the transverse slot injection in supersonic flows. Aerospace Science and Technology. 2013. V. 28. No. 1. Pp. 91?99. https://doi.org/10.1016/j.ast.2012.10.007

10. Prince R.L., Rejith P., Balu R. Numerical simulation of a hot gas injection thrust vector control system performance. Procedia Engineering. 2012. V. 38. P. 1745?1749. https://doi.org/10.1016/j.proeng.2012.06.212

11. Kawai S., Lele S. K. Mechanisms of jet mixing in a supersonic crossflow: a study using large-eddy simulation. AIAA Paper No. 2008-4575, July 2008. https://doi.org/10.2514/6.2008-4575

12. Peterson. D. M. Candler G. V. Hybrid RANS/LES of a supersonic combustor. AIAA Paper No. 2008-6923, Aug. 2008. https://doi.org/10.2514/6.2008-6923

13. Strelnikov G. A., Tokareva E. L., Pryadko N. S., Yhnatev A. D. Development of a structural schematic of a bifunctional system for rocket engine thrust vector control. Teh. Meh. 2018. No. 4. Pp. 57 - 67. (in Russian). https://doi.org/10.15407/itm2018.04.057

14. Tokareva E. L., Pryadko N. S., Ternova K. V. Dynamic characteristics of a combined system for rocket engine thrust vector control. Teh. Meh. 2019. No. 3. Pp. 16-29. (in Russian).





Copyright () 2020 Strelnykov H. O., Tokareva O. L., Ihnatiev O. D., Pryadko N. S., Ternova K. V.

Copyright 2014-2020 Technical mechanics


____________________________________________________________________________________________________________________________
GUIDE
FOR AUTHORS
Guide for Authors ==================== Open Access Policy
Open Access Policy ==================== REGULATIONS
on the ethics of publications
REGULATIONS on the ethics of publications ====================