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Abort Guidance System
Auxiliary Power Unit
Abort to Orbit
Russian Micropurification Unit (Russian)
Carbon Dioxide Removal System
Colony Forming Unit
Control Moment Gyroscope
Cell Performance Monitor
Compound Specific Analyzer-Combustible Products
Extravehicular Mobility Unit
Electrical Power System
Fuel Cell Monitoring System
Functional Cargo Block (Russian)
Flight Safety Office
Galley Iodine Removal Assembly
Guidance, Navigation, and Control
General Purpose Computer
Global Positioning System
Inertial Measurement Unit
International Space Station
Internal Thermal Control System
Launch Control Officer
Low Iodine Residual System
Loss of Crew
Loss of Vehicle
Minimum Duration Flight
Master Events Controller
Main Landing Gear
Micro-Meteoroid Orbital Debris
Marshall Space Flight Center
NASA Standard Initiator
Office of Safety & Mission Assurance (NASA HQ)
Protuberance Air Load
Precision Approach Path Indicator
Primary Avionics Software System
Pyrotechnic Initiator Controller
Partial Pressure of CO2
Reaction Control System/Subsystem
Remote Manipulator System
Russia or Russian
Return to Launch Site
Safety & Mission Assurance
Solid Fuel Oxygen Generator
Solid Rocket Booster
Condensate Water Processor Unit (Russian)
Space Shuttle Main Engine
Space Shuttle Program
Thermal Protection System
Loss of Crew
Crew Injury/Illness and/or Loss of Vehicle or Mission
Related or Recurring event
SR-71 | 7/30/1966 | Crew: 2 | Loss of Crew (1)
Loss of control at high speed and altitude.
On January 25, 1966 the SR-71 aircraft disintegrated during a high-speed, high-altitude test flight when the breakdown of super sonic airflow resulted in engine cutoff (also known as engine un-start). This occurred during a turn at speeds exceeding Mach 3.17 and a bank of 35 degrees. The bank immediately increased to 60 degrees. The nose pitched up and the aircraft broke apart. The pilot was thrown clear (his ejection seat never left the plane). He blacked out during the accident, but recovered and landed on the ground safely. His Reconnaissance System Officer did not survive the high-g bailout.
M21-D21 | 7/30/1966 | Crew: 2 | Loss of Crew (1)
D21 drone collided with M21 during launch, causing M21 breakup. Crew survived breakup but one was lost after water landing.
On July 30, 1966 as the M-21 mothership was performing a flight test for launching the D-21 drone, while traveling at high Mach speeds the drone was not able to penetrate the shock wave coming off the mothership. The D-21 had almost cleared the rudders of the M-21 when the drone bounced off the shockwave and pitched down, striking the M-21 and breaking it in half. The Pilot and Launch Control Officer (LCO) stayed with the tumbling wreckage of the plane a short time until a lower altitude was reached, then ejected over the Pacific Ocean.
Both crew members made safe ejections and landings, but after landing the LCO opened his helmet visor by mistake and his suit filled with water, causing him to drown. All subsequent flights of the D-21 were as D-21Bs, which were reconfigured to launch the drone from an under wing pylon of a B-52 (much like the X-15 had been), boosted to Mach 3 by a rocket motor that was jettisoned after the D-21Bs Marquardt ramjet was started.
LANDING & POSTLANDING