design studies of 3 expendable launch vehicle configurations that could serve as a backup to the space shuttie---1he Ti tan 34D7/Centaur , the A11 as I I /Cent.aur , and the shuttle-derived SRB-X—as well as studies of advanced shuttle-derived launch vehicles with much larger payload capabilities than the shuttle. The 3 candidate complementary launch vehicles are judged to be roughly equivalent in cost, development time, reliability, and pay1oad-1o-orbit performance. Advanced shuttie-derived vehicles are considered viable candidates to meet future heavy 1i f t 1 aunch requi rements; however, they do not appear 1ike1y to resu1t in significant reduction in cost-per-pound to orbit. (GRA) Keywords: ♦ATLAS CENTAUR LAUNCH VEHICLE; ♦PAYLOADS; ♦SHUTTLE DERIVED VEHICLES; ♦TITAN CENTAUR LAUNCH VEHICLE; CDS! REDUCT IUN; DESIGN ANALYSIS; EVALUATION Subject Classification: 7515 Launch Vehicles & Space Vehicles (1975-) C0SATI Code: 2 2D Spacecraft Launch Vehicle s ? Ground Support Large payload launch vehicles examined. BRAHNEY, J. H. Aerospace Engineering (ISSN 0736-2536), vol. 5, April 1985, p. 28-33. Language: Enq1ish. Country of Origin: United States. Country of Publication: United States Document Type: JOURNAL ARTICLE Most documents available from AIAA Technical Library Journal Announcement: IAA8512 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 Marshall Center have included SRB-X, side mount and in-line boostered configurations, each an evolutive concept incorporating STS features to deliver 144, C00- 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 Mlb 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 a reusable, long-life liquid oxygen/hydrocarbon fueled booster. The 5-6 yr development span would require associated selections of launch sites and the construction of launch facilities which would not interfere with STS op er ati on s. (M.S.K.) S ource of Ab stract (Subfile): AIAA/TIS Keywords: ♦HEAVY LIFT LAUNCH VEHICLES; ♦MULTISTAGE ROCKET VEHICLES; ♦PAYLOAD DELIVERY (STS); ♦SHUTTLE DERIVED VEHICLES; ♦SPACE SHUTTLE PAYLOADS ; ♦TECHNOLOGICAL FORECASTING; AEROSPACE ENGINEERING; BOOSTER ROCKET ENGINES ; HIGH THRUST; REUSABLE SPACECRAFT; ROCKET ENGINE DESIGN Subject Classification: 7515 Launch Vehicles & Space Vehicles (1975-)
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