The DSL reference second stage is a LOX/LH2 liquid rocket engine propelled system with an initial mass of 200 Mg. This stage is air-launched from the supersonic carrier aircraft at M=2.7, at an altitude of about 20 km, and at a flight path angle of 12°. Ignition of the rocket engines occurs after reaching a sufficient safety distance at M=2.5 and a flight path angle of 10 deg .
Dimensions of the DSL reference second stage are about the size of the ARIANE 5 core stage (diameter 5.5m, overall length 37m). Fairing length is 12 m. The dry-mass of the ballistic stage necessary to reach LEO is estimated to be 19 Mg. The propulsion system is assumed to consist of two scaled SSME with an expansion ratio of 150.
Propulsion
Last modification of this page: 18. September 1996
Contribution(s) to this page: Martin Sippel