Encyclopedia Astronautica
UA-156


CSD solid rocket engine. 8924.3 kN. Tested 1968. Isp=263s. Proposed as strap-on booster for Saturn INT-27, Saturn V-25(S)B, Saturn V-25(S)U.

Thrust (sl): 8,076.000 kN (1,815,557 lbf). Thrust (sl): 823,538 kgf.

Status: Study 1968.
Gross mass: 544,311 kg (1,200,000 lb).
Unfuelled mass: 37,195 kg (82,000 lb).
Height: 34.00 m (111.00 ft).
Diameter: 3.96 m (12.99 ft).
Thrust: 8,924.30 kN (2,006,262 lbf).
Specific impulse: 263 s.
Specific impulse sea level: 238 s.
Burn time: 157 s.

More... - Chronology...


Associated Countries
See also
Associated Launch Vehicles
  • Saturn INT-27 American orbital launch vehicle. UA study, 1965. Saturn variant using various combinations of 156 inch rocket motors as first and second stages, with S-IVB upper stage. More...
  • Saturn V-25(S)B American orbital launch vehicle. Boeing study, 1967. 4 156 inch solid propellant boosters; Saturn IC stretched 498 inches with 6.64 million pounds propellant and 5 F-1 engines; S-II standard length with 5 J-2 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 J-2 engine. More...
  • Saturn V-25(S)U American orbital launch vehicle. Boeing study, 1968. 4 156 inch solid propellant boosters; Saturn IC stretched 498 inches with 6.64 million pounds propellant and 5 F-1 engines; S-II standard length with 5 J-2 engines. This vehicle would place Nerva nuclear third stage into low earth orbit, where five such stages would be assembled together with the spacecraft for a manned Mars expedition. More...

Associated Manufacturers and Agencies
  • CSD American manufacturer of rocket engines. Chemical Systems Division, 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...

Associated Stages
  • UA 156 inch Solid propellant rocket stage. Loaded/empty mass 544,311/37,195 kg. Thrust 8,924.48 kN. Vacuum specific impulse 263 seconds. More...
  • UA 156 inch 4 Segment Solid propellant rocket stage. Loaded/empty mass 725,500/49,250 kg. Thrust 18,181.00 kN. Vacuum specific impulse 263 seconds. 4 Segment version of basic 3-segment UA 156 motor. More...

Home - Browse - Contact
© / Conditions for Use