Encyclopedia Astronautica
PAM-S


Solid propellant rocket stage. Loaded/empty mass 2,182/220 kg. Thrust 66.60 kN. Vacuum specific impulse 288 seconds.

Cost $ : 4.060 million.

AKA: TE-M-711-17.
Status: Out of Production.
Gross mass: 2,182 kg (4,810 lb).
Unfuelled mass: 220 kg (480 lb).
Height: 2.00 m (6.50 ft).
Diameter: 1.22 m (4.00 ft).
Span: 1.22 m (4.00 ft).
Thrust: 66.60 kN (14,972 lbf).
Specific impulse: 288 s.
Specific impulse sea level: 270 s.
Burn time: 80 s.
Number: 8 .

More... - Chronology...


Associated Countries
Associated Engines
  • MR-106 Redmond hydrazine monopropellant rocket engine. 0.027 kN. Spacecraft and upper stage attitude control and velocity corrections, PAM A/S,. Radarsat, GPS Block 2R, HAS/Peace Courage, Titan Centaur, Atlas Centaur. In Production. Isp=232s. More...
  • Star 48 Thiokol solid rocket engine. 67.2 kN. Used in Delta 3900; Conesotga; PAM-S; PAM-D. Total flown included in total for Star-48-8. Total impulse 575,682 kgf-sec. Motor propellant mass fraction 0.946. Isp=286s. First flight 1982. More...

Associated Launch Vehicles
  • Atlas E/SGS-2 American orbital launch vehicle. Atlas E + 1 x Star 48 + 1 x Star 48 upper stages. 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...

Home - Browse - Contact
© / Conditions for Use