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
The best-fit values of B and A from Figure 30 and Figure 31 have been listed for convenient reference in Table 25. It is interesting to note that, for all breakup conditions, the currently-used value of B = 1,000 provided a better data fit than any other B that was investigated. Table 25. Shaping Constants for LLVl TB Breakup qa (sec) (deg-lb/£t2) B A 290 none 1,000 1.85 20,000 2.60 10,000 2.70 5,000 2.75 290 none 10,000 2.45 20,000 1,000 2.60 10,000 1,000 2.70 5,000 1,000 2.75 No launch-area risk calculations were made for LLVl. 6.6 Shaping Constants for Other Launch Vehicles Procedures for developing Mode-5 shaping constants A and B are fully· described in this report. For Atlas, Delta, Titan, and LLVl, best-fit values of A were derived for four breakup conditions (1) for the currently-used value of B = 1,000, and (2) for optimum-fit values of B. For any new launch vehicle requiring risk calculations, the same procedures should be followed to obtain suitable values for A and B. As an alternative and less time-consuming process, values of A and B can be estimated by comparing the new vehicle with one of the four vehicles referred to above and listed in Table 26. If the configuration and trajectory of the new vehicle and one of the listed vehicles are similar, values of A and B shown in the table for that vehicle and the assumed breakup condition can be used. There may, of course, be no similarity between the new vehicle and any of the listed vehicles. In that event and depending on assumed breakup conditions, one of the mean values shown in the last row of the table can be selected until better values can be developed. Table 26. Summary of A Values for B = 1,000 Vehicle IP Range (nm) at 30 sec Breakup qa (deg-lb/ ft2) 5,000 10,000 20,000 None Atlas HAS Delta-GEM Titan IV CLVl 0.3 5.2 1.9 33.4 3.45 4.30 3.50 2.75 3.20 2.75 3.10 2.90 3.25 2.95 2.70 2.60 1.90 1.90 2.00 1.85 Other vehicles 3.5 3.1 2.8 1.9 9/10/96 72 RTI
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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.