Tuesday, April 01, 2003

RS-68 SSME Saturn-V engines RS-68 SSME Saturn-V engines (Some links to information on some big engines to get you to space. - LRK -)   http://www.google.com/search?sourceid=navclient&;ie=UTF-8&oe=UTF-8&q=RS%2D68 5040 matches for RS-68 in 0.11 seconds - guess will need to narrow that a bit. :-)  - LRK - ==================================================================================   http://www.astronautix.com/engines/rs68.htm Manufacturer Name: RS-68. Designer: Rocketdyne. Developed in: 1998. Application: . Used on stages: Delta RS-68. Used on launch vehicles: Delta IV Large, Delta IV Medium, Delta IV Medium+ (4, 2), Delta IV Medium+ (5, 2), Delta IV Medium+ (5, 4), Delta IV Small. Propellants: Lox/LH2 Thrust(vac): 337,807 kgf. Thrust(vac): 3,312.00 kN. Isp: 420 sec. Isp (sea level): 365 sec. Mass Engine: 6,597 kg. Chambers: 1. Chamber Pressure: 95.92 bar. Area Ratio: 21.50. Country: USA. Status: In Production. In the 1990's Rocketdyne was simultaneously developing the first two new large liquid-fueled rocket engines in the United States in more than 25 years. One of these - the RS-68 - would power the Delta IV evolved expendable launch vehicle (EELV) being developed by The Boeing Company. The bell nozzle RS-68 is a liquid hydrogen-liquid oxygen booster engine that develops 650,000 lb. of sea level thrust. The RS-68 utilizes a simplified design philosophy resulting in a drastic reduction in parts compared to current cryogenic engines. This design approach results in lower development and production costs. The engine can be throttled to 60% of full thrust level. Designed for booster applications. Gas generator, pump-fed.   snip =========================================================================================== http://www.google.com/search?sourceid=navclient&;ie=UTF-8&oe=UTF-8&q=SSME 9070 matches for SSME - hmmm ===========================================================================================   http://www.astronautix.com/engines/ssme.htm Manufacturer Name: RS-24. Designer: Rocketdyne. Developed in: 1972. Application: . Used on stages: Shuttle Orbiter, Starlifter. Used on launch vehicles: Saturn Shuttle, Shuttle, Shuttle ASRM, Shuttle LRB, Starlifter. Propellants: Lox/LH2 Thrust(vac): 232,301 kgf. Thrust(vac): 2,278.00 kN. Isp: 453 sec. Isp (sea level): 363 sec. Burn time: 480 sec. Mass Engine: 3,177 kg. Diameter: 1.6 m. Length: 4.2 m. Chambers: 1. Chamber Pressure: 204.08 bar. Area Ratio: 77.50. Oxidizer to Fuel Ratio: 6.00. Thrust to Weight Ratio: 73.12. Country: USA. Status: In Production. First Flight: 1981. Last Flight: 1998. Flown: 279. References: 225 . Comments: Used in Shuttle Orbiter. Space Shuttle Main Engine. Staged combustion, pump-fed.     =========================================================================================== http://www.google.com/search?sourceid=navclient&;ie=UTF-8&oe=UTF-8&q=Saturn%2DV+engines 5390 mataches for Saturn V engines ===========================================================================================   http://www.astronautix.com/lvfam/saturnv.htm After the Saturn V drawings had been issued, Marshall engineers immediately turned to considering further developments of the basic launch vehicle. These would be required for Apollo Applications, Manned Orbiting Research Laboratory, Mars fly-by, and Mars landing missions in the 1970's and 1980's. Contracts were let for a variety of trade studies. There were limits to how far the core stack could be stretched, dictated by the 410 foot maximum overhead crane height in the Vertical Assembly Building at Kennedy Space Center (this did not prevent 470 foot versions being proposed, including the nuclear NERVA third stage, for manned missions to Mars - they'd just have to raise the roof, darn it). Given these limits, a variety of strap-on solid motors were considered. The most feasible, lowest development cost improvement would have used upgraded F-1 motors, an S- IC first stage stretch, modest upgrades to the J-2 upper stage motors, and proven 120 inch solid rocket motor strap-ons. If a follow-on Saturn V production contract had ever been issued, it probably would have been for this configuration. More advanced versions would have used Flox oxidizer (liquid fluorine mixed with the liquid oxygen oxidizer - nasty to handle, but increased performance with minimal changes to the existing motors and pumps), new technology engines (plug nozzles or high-pressure combustion engines - the ancestors of the Shuttle SSME's). Instead America abandoned its heavy lift capability and further manned exploration of space. The two unused flightworthy Saturn V's from the inital production run of 15 became tourist displays at Cape Canaveral and Huntsville. A third Saturn V, exhibited in Houston, is made up of static test article stages. snip 7:00:46 AM    comment []