Encyclopedia Astronautica
GEM 60


Hercules solid rocket engine. 851.5 kN. In production. Isp=275s. Used as strap-on boosters for Delta 3 , Delta IV Medium. First flight 2002.

Thrust (sl): 758.000 kN (170,405 lbf). Thrust (sl): 77,350 kgf. Chamber Pressure: 90.00 bar. Area Ratio: 11. Propellant Formulation: HTPB.

Status: In production.
Gross mass: 33,199 kg (73,191 lb).
Unfuelled mass: 3,250 kg (7,160 lb).
Height: 16.20 m (53.10 ft).
Diameter: 1.52 m (4.98 ft).
Thrust: 851.50 kN (191,425 lbf).
Specific impulse: 275 s.
Specific impulse sea level: 245 s.
Burn time: 90 s.
Number: 2 .

More... - Chronology...


Associated Countries
See also
Associated Launch Vehicles
  • Delta 3 American orbital launch vehicle. Delta 3 was an attempt by the manufacturer to provide the ultimate development of the original Delta booster. The core vehicle was beefed-up to accomodate much larger solid rocket boosters and a new cryogenic upper stage. However problems were incurred during development, resulting in the first two launches being failures. Meanwhile the satellite launch market crashed and the new vehicle was left without customers. The venerable Delta 7925 soldiered on for NASA, and the new Delta 4 series captured the USAF EELV requirement. More...
  • Delta IV Medium+ (4.2) American orbital launch vehicle. As Delta 4 medium but with 2 x GEM-60 solid rocket boosters and a 4 m diameter payload fairing. More...
  • Delta IV Medium+ (5.2) American orbital launch vehicle. As Delta 4 medium but with 2 x GEM-60 solid rocket boosters and a 5 m diameter payload fairing. More...
  • Delta IV Medium+ (5.4) American orbital launch vehicle. As Delta 4 medium but with 4 x GEM-60 solid rocket boosters and a 5 m diameter payload fairing. More...

Associated Manufacturers and Agencies
  • Hercules American manufacturer of rocket engines and rockets. Hercules, Wilmington, Delaware, USA. More...

Associated Propellants
  • Solid Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. More...

Bibliography
  • Isakowitz, Steven J, Hopkins, Joshua B, and Hopkins, Joseph P, International Reference to Space Launch Systems, AIAA, Washington DC, 2004.

Associated Stages
  • GEM 60 Solid propellant rocket stage. Loaded/empty mass 33,798/3,849 kg. Thrust 826.55 kN. Vacuum specific impulse 275 seconds. 90.5 bar chamber pressure, 11.0 nozzle expansion ratio. Figures for TVC version. Fixed nozzle version is 599 kg lighter. More...

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