Engine Performance
|
MA-5 Booster |
MA-5 Sustainer |
Propellant Combination
Oxidizer
Fuel |
Liquid Oxygen (LOX)
Kerosene (RP) |
Liquid Oxygen (LOX)
Kerosene (RP) |
| Engine Cycle: |
Gas Generator |
Gas Generator |
| Average Thrust: |
429,500 lbf
1,906 kN |
60,500 lbf
268,620 N |
| Chamber Pressure: (Pc) |
719 psia |
736 psia |
| Mixture Ratio: |
2.25 : 1 |
2.27 : 1 |
| Isp: |
265 sec |
220 sec |
| Nozzle Area Ratio: |
8 : 1 |
25 : 1 |
| Gimbal Capability: |
No |
No |
| Engine Mass: |
3,336 lb
1,513 kg |
1,035 lb
469 kg |
| Engine Thrust to Weight |
128.7 |
58.5 |
| Mixture Ratio Control: |
--- |
--- |
| Throttle Range: (% Pc) |
100% (only) |
100% (only) |
| Restart Capability: |
No |
No |
Engine Size:
Length / Diameter |
8.4 ft / 4.0 ft
2.6 m / 1.2 m |
8.1 ft / 4.0 ft
2.5 m / 1.2 m |
| Flight Status |
Flight Qualified |
Flight Qualified |
| Launch Vehicles: |
Atlas I & Atlas II First Stage |
Atlas I & Atlas II First Stage |
* Engine performance from Boeing Web Site.
|
