Environmental effects of space activities. BAUER, S. J. (Technische Un1 versitaet, Graz) Institut fuer We1traumforschung, Graz (Austria). Corp. Source Code: 11195031 Sep. 1984. 38P. I... a n g u a g e: E n g 1 i s h Country of Origin: Austria. Country of Publication: Austria Document Type: REPORT Most documents available from AIAA Technical Library Other Availability: NTIS HC A03/MF AOI Journa1 Announcement: 8TAR8511 Environmental effects of atmospheric chemical releases and 1arge sca1e launch and orbital operations are discussed . Whereas the past and anticipated use of chemical releases for scientific experiments, and the launch and orbital activities of past and present propulsion systems seem to have no si gni f i cant en vi ronmental effects, this may not be true for the proposed Solar Power Satellite Program. The launch equivalent in cost, development time, reliabi1ity, and pay1oad-to-orbit performance. Advanced shuttle-derived vehicles are considered viable candidates to meet future heavy lift launch requirements; however,, they do not apper likely to result in significant reduction in cost-per-pound to orbit. (GRA) Descriptors: *ATLAS .CENTAUR: LAUNCH VEHICLE; ♦PAYLOADS; ♦SHUTTLE DERIVED VEHICLES; ♦ I TIAN CENTAUR LAUNCH VEHICLE; COST REDUCTION; DESIGN ANALYSIS; EVALUATION Subject Classification: 7515 Launch Vehicles ?< Space Vehic1es (19 7 5 - ) CDSAT I Code: 22D Spacecraft Launch Vehicles & Ground Support Large payload launch vehicles examined. BRAHNEY, J. H. Aerospace Engineering (ISSN 0736-2536), vol. 5, April 1985, P- 28.33. Lanquage: Engish. Country of Origin: United States. Country of Publication: United States Document Type: J0URNAL ARTICLE Most d ocuments a va i1 ab1e from AIAA Tec hni ca1 L i b r ary J ou. r n al An n o u neem e n t: IA A 8 512 Several Shuttle-derived vehicle (SDV) designs have been envisioned for near-term NASA and DOD heavy lift launch vehicle (HLLV) missions into the 21st century. Studies performed at the Marshal 1 Center have included SRB-X, side mount and in-line boostered configurations, each an evolutive concept incorporating STS features to deliver 144,000- 195,000 lb payloads into LEO or 10,000 lb into GEO. A three- stage multi tank design sporting a cluster of eight 1.757 Nib thrust engines on the first stage is emerging as a favored HLLV. The second stage would be lofted by four 481,000 lb thrust SSME derivative engines and the third stage would have? two of the derivatives. All stages would be drogue- parachuted to water touchdown for reuse. The technology requiring the greatest advances to realize the design is
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