Report of the PRESIDENTIAL COMMISSION
on the Space Shuttle Challenger Accident
Volume 4 Index
Hearings of the Presidential
Commission on the Space Shuttle Challenger Accident: February 6, 1986
to February 25, 1986
FEBRUARY 6, 1986 SESSION [part1 of
2]
[112] [Ref. 2/6-68]
TYPICAL THRUST PROFILE.
[Ref. 2/6-69]
SRM
PROJECT PERFORMANCE
- OPERATIONAL RELIABILITY CONSIDERATIONS
- THE SRB HAS BEEN VERIFIED BY ANALYSIS AND GROUND TEST
- MANNED SPACE FLIGHT DESIGN SAFETY FACTORS (RELATIVE TO
OTHER SOLID ROCKET MOTORS) ARE APPLIED
- 1.4 X LIMIT LOAD ON STRUCTURE VS. 1.25 OR 1.15 ON
MILITARY WEAPONS SYSTEMS
- 1.5 X PREDICTED REQUIREMENT (CASE) AND 2.0 X
PREDICTED REQUIREMENT (NOZZLE) ON INSULATION THICKNESS
VS. 1.25 ON MILITARY WEAPONS SYSTEM
- PROOF TEST TO 112% MAXIMUM EXPECTED FLIGHT PRESSURE
- POST CASTING X-RAY VERIFIES PROPELLANT QUALITY
- 100% X-RAY OF PROPELLANT IN FIRST 68 SEGMENTS VERIFIED
THAT PROPELLANT CASTING PROCESS PROVIDES PROPER PROPELLANT
STRENGTH
- PROCESS CONTROL WITH RANDOM MONTHLY 100% X-RAY ON ONE
SEGMENT
- X-RAY REQUIRED FOR ALL SEGMENTS WITH
- PROCESS ANOMALIES
- PROCESS CHANGES
- DESIGN CHANGES
- 100% X-RAY OF NOZZLE ABLATIVE PARTS
VEIRIFIES NOZZLE LINER INTEGRITY
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