Documents / Report
This final report, dated September 10, 1996, was prepared by the Research Triangle Institute for the Department of the Air Force's 45th and 30th Space Wing safety offices. Titled Modeling Unlikely Space-Booster Failures in Risk Calculations, it shows how rare Mode-5 failures, in which a rocket veers well off its intended flight line, are modeled in the DAMP risk-analysis program. An appendix lists Atlas, Delta, Titan and Thor launch and failure histories through August 1996.
From the source:Release of 2026-05-08 Incident: 9/10/96, N/A. This report describes the Modeling of Unlikely Space-Booster Failures in Risk Calculations, documenting historical launch failure modes and recommending corrective actions to address them using novel modelling techniques.
“Mission Control”17 pages
D.2 Atlas Launch and Performance History Atlas space-launch vehicles, originally manufactured by General Dynamics and currently by Lockheed Martin, derived from the Atlas ICBM series developed in the 1950s. The primary one-and-one-half-stage vehicle played a major role in early lunar exploration activities (the unmanned Ranger, Lunar Orbiter, and Surveyor programs), and planetary probes (Mariner and Pioneer). Table 40 shows a summary of Atlas configurations since the beginning of the program.[1°1 Table 40. Summarv of Atlas Vehicle Configurations onfiguration scription A ICBM single-stage test vehicle B,C ICBM 1½-stage test vehicle D ICBM and later space-launch vehicle E,F First an ICBM (1960), then a reentry test vehicle (1964), then a space-launch vehicle (1968) LV-3A Same as D except Agena upper stage LV-3B Same as D except man-rated for Project Mercury SLV-3 Same as LV-3A except reliabilitv improvements SLV-3A Same as SLV-3 except stretched 117 inches LV-3C Integrated with Centaur D upper stage SLV-3C Same as LV-3C except stretched 51 inches SLV-3D Same as SLV-3C except Centaur uprated to D-lA and Atlas electronics integrated with Centaur (no longer radio guided) G Same as SLV-3D but Atlas stretched 81 inches H Same as SLV-3D except with E/F avionics and no Centaur I Same as G except strengthened for 14-ft payload fairing, ring laser gyro added II Same as I except Atlas stretched 108 inches, engines uprated, hydrazine roll-control added, verniers deleted, Centaur stretched 36 inches IIA IIAS Same as II except Centaur RL-l0s engines uprated to 20K lbs thrust and 6.5 seconds lsp increase from extendible RL-10 nozzles Same as IIA except 4 Castor IVA strap-on SRMs added Atlas A, B, and C were developmental ICBMs. Atlas D, E, and F configurations were deployed as operational ICBMs during the 1960s. During that time, some Atlas Ds were modified as space-launch vehicles in the LV series: LV-3A, 3B, and· 3C. The Standardized Launch Vehicle (SLV) series derived from a need to reduce lead times in transforming Atlas missiles to space-launch vehicles. The SLV series began with the SLV-3 vehicle, which used an Agena upper stage. The G and H vehicles evolved from the SLV series. Eventually the I, II, IIA, and IIAS configurations were developed with the aim of also supporting commercial launches. 9/10/96 101 RT!
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Report, from the pursue collection. The PDF is mirrored here; the original link is above. 181 pages are in the text index: search them above, or from the library's search.