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Contact: Patrick Louden
Tel: (561) 796-6793
Web Site: www.pw.utc.com
Pratt & Whitney Space Propulsion - Booster Separation Motors (BSMs)
Booster separation motors (BSMs) are vital for NASA’s Space Shuttle launches.
Approximately two minutes into flight, 16 of these small but powerful motors (4 each
mounted on the aft and forward sections of the two solid motor boosters) execute split
second timing to provide the precise thrust required for safe separation of the spent
boosters away from the main fuel tank and the orbiter. During more than 100 space
shuttle missions, every one of the more than 1,700 BSMs has performed flawlessly.
P&W has been the sole supplier to the Shuttle program since its inception in the late
1970s, first directly to NASA in the early 1980s and then to the NASA subcontractors
USBI (up to late 1999) and United Space Alliance (USA), which is the current
subcontractor.
Characteristics (100% power)
Average thrust : 18,500 lb
Length: 31 in.
Diameter: 13 in.
Loaded weight: 167 lb
Action Time: 0.805 sec
Total impulse: 14,000 lb sec
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Contact: Patrick Louden
Tel: (561) 796-6793
Web Site: www.pw.utc.com
Pratt & Whitney Space Propulsion - COBRA
Pratt & Whitney and Aerojet have teamed to provide the widest range of main propulsion
options in support of second generation, reusable launch vehicles (2GRLV). Pratt &
Whitney’s strengths in reusable rocket turbo-machinery and health and maintenance
management systems used for jet engines complement Aerojet’s strengths in combustion
devices and the integration and production of large propulsion systems such as those used
for Titan.
Propulsion systems offered by Pratt & Whitney-Aerojet Propulsion Associates cover a
wide range of thrust, for both hydrogen and hydrocarbon propellants, allowing the
greatest flexibility for vehicle customers and NASA to select and execute optimum
2GRLV architecture.
One of these propulsion systems is the COBRA, a long-life, moderate-to high-thrust,
reusable booster engine that incorporates a safe, low-cost, low-risk, LH2/LOX single
burner, fuel-rich, staged combustion cycle. Mature, flight proven Space Shuttle Main
Engine alternate turbopumps reduce technical, schedule, and programmatic risk while at
the same time meet safety and reliability goals.
Description
Single pre-burner, fuel-rich staged combustion cycle
Double containment, failsafe powerhead, hot gas system
Incorporates flight-certified SSME Block II turbopumps
Long-life, robust, milled-channel nozzle construction eliminates hot side weld
joints
Smooth start transients avoid life-limiting thermal stress
Blanch-shielded, formed-platelet liner technology reduces hotwall stress
Turbine inlet temperature reduced 500°F relative to the SSME, promotes longer
life
Integrated engine controls and health management system enhance safety and
maintainability
Low development cost/risk based on use of flight-qualified hardware and mature
technologies
Characteristics
Thrust (vac): 200,000-1,000,000 lbf
Dry Weight (at 600k thrust): 8,000 lbm
Specific impulse (vac): 455 sec
Cycle: Staged combustion
Propellants: Liquid hydrogen / liquid oxygen
Mixture ratio: 5.5:1 to 6.5:1
Shutdown reliability: 0.9995
Catastrophic reliability: 0.999995
Mission life: > 100 missions
Time between overhauls: > 50 missions
Scheduled maintenance per flight: < 100 man-hours
Turnaround between flights: < 16 hours
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