Reusable orbital transfer vehicle spacelift concepts study results

Journal Article · Wed Jan 01 00:00:00 EST 1997 · AIP Conference Proceedings

DOI:https://doi.org/10.1063/1.51937· OSTI ID:627627

Feuchter, C A; Grobman, J H ^[1]

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1. Office of Aerospace Studies 3550 Aberdeen Ave. S.E. Kirtland AFB New Mexico87117 (United States)

This paper reports on the feasibility and cost-effectiveness of expendable and reusable orbital transfer vehicle concepts utilizing innovative low thrust, high specific impulse electric and thermal propulsion technologies. Comparisons are made to launch systems using current chemical upper stages. These innovative technologies often produce significant savings over chemical upper-stages when used with the current fleet of expendable launch vehicles, and evolved expendable launch vehicles. Savings are driven by the ability of the innovative technologies to lower combined payload and upper stage mass, allowing payloads to be launched on smaller, less expensive launch vehicles. {copyright} {ital 1997 American Institute of Physics.}

• Sponsoring Organization: USDOE
• OSTI ID: 627627
• Report Number(s): CONF-970115-; ISSN 0094-243X; TRN: 9808M0043
• Journal Information: AIP Conference Proceedings, Vol. 387, Issue 1; Conference: Space technology and applications international forum (STAIF - 97), Albuquerque, NM (United States), 26-30 Jan 1997; Other Information: PBD: Jan 1997
• Country of Publication: United States
• Language: English

Related Subjects

42 ENGINEERING NOT INCLUDED IN OTHER CATEGORIES
SPACE VEHICLES
FEASIBILITY STUDIES
DESIGN
COST
PROPULSION SYSTEMS