Uploaded December 2024 | Updated September 2026, 2 weeks ago
The selected Titan IIIL booster is designated as the 1207-4
spread configuration. The booster stage consIsts of a sixteen foot
diameter liquid fuel core with five (Aerojet Liquid Rocket Company)
LR-87 engines and four 120 inch (United Technology Center) UA 1207
solid rocket motors mounted in the yaw plane, two on either side of
the core. The liquid fueled core utilize nitrogen tetroxide as an
oxidizer and Aerozine-50, a solution of Hydrazine and UDMH, as a
fuel. Five core engines supply a total sea level thrust of 1,133,370
pounds. The liquid rocket engines are precanted 90 in pitch to compensate for the CG Z-axis offset. The center engine is hinged in pitch
to facilitate CG tracking while the outboard engines heve gimbal
capabilities of plus or minus 4.5 degrees in pitch and yaw. The four
solid rocket motors develop a total of 5,570,400 pounds-thrust. The
engine nozzles are precanted six degrees in a plane rotated 30 degrees
out of pitch. The cant and rotation angles are chosen to facilitate
CG tracking and to minimize the individual SRM moment arms at the end
of web action time.
#rocketlaunch #rocket #spaceexploration
The selected Titan IIIL booster is designated as the 1207-4
spread configuration. The booster stage consIsts of a sixteen foot
diameter liquid fuel core with five (Aerojet Liquid Rocket Company)
LR-87 engines and four 120 inch (United Technology Center) UA 1207
solid rocket motors mounted in the yaw plane, two on either side of
the core. The liquid fueled core utilize nitrogen tetroxide as an
oxidizer and Aerozine-50, a solution of Hydrazine and UDMH, as a
fuel. Five core engines supply a total sea level thrust of 1,133,370
pounds. The liquid rocket engines are precanted 90 in pitch to compensate for the CG Z-axis offset. The center engine is hinged in pitch
to facilitate CG tracking while the outboard engines heve gimbal
capabilities of plus or minus 4.5 degrees in pitch and yaw. The four
solid rocket motors develop a total of 5,570,400 pounds-thrust. The
engine nozzles are precanted six degrees in a plane rotated 30 degrees
out of pitch. The cant and rotation angles are chosen to facilitate
CG tracking and to minimize the individual SRM moment arms at the end
of web action time.
#rocketlaunch #rocket #spaceexploration
