Upper stage options for reusable launch vehicle ``pop-up'' missions

Details Upper stage options for reusable launch vehicle ``pop-up'' missions Upper stage options for reusable launch vehicle ``pop-up'' missions

Jan 1997

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1997aipc..387.1201e&link_type=abstract

Space technology and applications international forum (STAIF - 97). AIP Conference Proceedings, Volume 387, pp. 1201-1208 (1997

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Spaceborne And Space Research Instruments, Apparatus, And Components

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Suborbital separation of an expendable upper stage from a small, single-stage Reusable Launch Vehicle (RLV) to transfer spacecraft into Geosynchronous Equatorial Orbit (GEO) was investigated and found to significantly increase spacecraft mass into GEO (over 400%) although operational issues exist. An assessment of propulsion system options for this ``Pop-Up'' Mission was performed to determine the propellant combinations, stage configurations, and propulsion technologies that maximize spacecraft mass and minimize size. Propellants included earth and space storable combinations, cryogenic LH2/LO2, and Class 1.3 solids. Stage configurations employing cylindrical metal and overwrapped tanks, isogrid tanks, and toroidal tanks were considered. Non-toxic earth storable propellants provided comparable performance (5-10%) to existing storables while the use of pressure-fed engines gave about 15% lower performance than pump-fed. Solid stage performance was within 5% of existing storable propellants. Stages employing toroidal tanks packaged more efficiently in length constrained RLV payload bays than 4-cylindrical tank configurations, giving up to 30% greater mass into GEO. The use of Extendable Exit Cones (EEC) for length constrained cases resulted in about 5-10% higher stage performance.

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