BOREAS DEMONSTRATION FOR FUTURE LIQUID PROPULSION ENGINES

Paper number

IAC-17,C4,1,10,x40551

Author

Ms. Stephanie Dreyer, France

Coauthor

Mr. Julien Herp, Centre National d'Etudes Spatiales (CNES), France

Coauthor

Mr. Vincent Leudiere, CNES, France

Coauthor

Ms. Ariane Deneuve, Airbus Safran Launchers, France

Coauthor

Mr. Patrick Danous, Airbus Safran Launchers, France

Year

2017

Abstract

CNES, the French Space Agency, and Airbus Safran Launchers are preparing the future for new liquid propulsion rocket engines. 

The most promising technologies, with regards to cost and mass reduction, have been identified through Research and Technology activities and are now evaluated on a set of demonstrators. This maturation process will enable to decrease the development duration of the next liquid engine generation. 

These demonstrators are engine components (turbopumps, combustion chamber, valves, igniter …), at a scale harmonized around requirements for a low thrust LOx/LH2 engine (thrust: 10 kN, Isp: 450 s).

Among these specifications technologies are the bleed cycle, the low pressure igniter, and the engine operation in throttling or the idle mode.

A focus will be made on the status of these demonstrators including the main chamber design as well as firing test results obtained @ DLR P8 test stand.

Abstract document

IAC-17,C4,1,10,x40551.brief.pdf

Manuscript document

IAC-17,C4,1,10,x40551.pdf (🔒 authorized access only).

To get the manuscript, please contact IAF Secretariat.