| abstract |
The present invention relates to an oxidant over-liquid single propellant of an ADN or HAN system for a dual mode binary propellant chemical rocket engine. These engines may be used in a variety of applications including: 1) orbit elevation, orbital maneuvering and maintenance, spacecraft attitude control and orbit deviations, and / or 2) propellant fixation, missile posture and roll control, launch devices, May be part of the propulsion system to be used in the < / RTI > |