Encyclopedia Astronautica
UM-129A


Solid propellant rocket stage. Loaded/empty mass 2,200/360 kg. Thrust 77.40 kN. Vacuum specific impulse 291 seconds.

Cost $ : 10.000 million.

Status: Retired 1992.
Gross mass: 2,200 kg (4,800 lb).
Unfuelled mass: 360 kg (790 lb).
Height: 2.34 m (7.67 ft).
Diameter: 1.34 m (4.39 ft).
Span: 1.34 m (4.39 ft).
Thrust: 77.40 kN (17,400 lbf).
Specific impulse: 291 s.
Specific impulse sea level: 220 s.
Burn time: 68 s.
Number: 13 .

More... - Chronology...


Associated Countries
Associated Engines
  • H-1-3 Nissan solid rocket engine. 77 kN. Isp=291s. Used on H-1 launch vehicle. First flight 1986. More...

Associated Launch Vehicles
  • H-1 Japanese license-built version of Delta launch vehicle, with Japanese-developed upper stages. More...
  • H-1 6R American orbital launch vehicle. Four stage version consisting of 6 x Castor 2 + 1 x ELT Thor N + 1 x LE-5 + 1 x UM129A 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...

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