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Thrust shock vector control of an axisymmetric conical supersonic nozzle via secondary transverse gas injection

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Abstract

Transverse secondary gas injection into the supersonic flow of an axisymmetric convergent–divergent nozzle is investigated to describe the effects of the fluidic thrust vectoring within the framework of a small satellite launcher. Cold-flow dry-air experiments are performed in a supersonic wind tunnel using two identical supersonic conical nozzles with the different transverse injection port positions. The complex three-dimensional flow field generated by the supersonic cross-flows in these test nozzles was examined. Valuable experimental data were confronted and compared with the results obtained from the numerical simulations. Different nozzle models are numerically simulated under experimental conditions and then further investigated to determine which parameters significantly affect thrust vectoring. Effects which characterize the nozzle and thrust vectoring performances are established. The results indicate that with moderate secondary to primary mass flow rate ratios, ranging around 5 %, it is possible to achieve pertinent vector side forces. It is also revealed that injector positioning and geometry have a strong effect on the shock vector control system and nozzle performances.

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Acknowledgments

We would like to acknowledge support and assistance by Sandrine Palerm and Jean Oswald from the French space agency CNES, DLA department, as well as Luc Leger and Eric Depussay from CNRS-ICARE.

Author information

Correspondence to V. Zmijanovic.

Additional information

The paper was based on work that was presented at the 28th International Symposium on Shock Waves, 17–22 July, 2011, Manchester, UK.

Communicated by A. Hadjadj and K. Kontis.

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Zmijanovic, V., Lago, V., Sellam, M. et al. Thrust shock vector control of an axisymmetric conical supersonic nozzle via secondary transverse gas injection. Shock Waves 24, 97–111 (2014). https://doi.org/10.1007/s00193-013-0479-y

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Keywords

  • Thrust
  • Shock vector
  • Fluidic control
  • Nozzle
  • Supersonic
  • Cross-flow
  • Secondary injection