Engine Performance
|
LE-5A * |
LE-5B ** |
Propellant Combination
Oxidizer
Fuel |
Liquid Oxygen (LOX)
Liquid Hydrogen (LH2) |
Liquid Oxygen (LOX)
Liquid Hydrogen (LH2) |
| Engine Cycle: |
Expander Hydrogen
Bleed |
Expander Hydrogen
Bleed |
| Average Thrust: |
27,000 lbf
120,000 N |
30,870 lbf
137,060 N |
| Chamber Pressure: (Pc) |
555 psi
38 bar |
526 psi
36.3 bar |
| Mixture Ratio: |
5.0 : 1 |
5.0 : 1 |
| Isp: |
452 sec |
450 sec |
| Nozzle Area Ratio: |
130 : 1 |
130 : 1 |
| Gimbal Capability: |
Yes |
Yes |
| Engine Mass: |
--- |
--- |
| Engine Thrust to Weight |
--- |
--- |
| Mixture Ratio Control: |
--- |
--- |
| Throttle Range: (% Pc) |
100% |
100% |
| Restart Capability: |
Yes |
Yes |
Engine Size:
Length / Diameter |
--- |
--- |
| Flight Status |
Flight Qualified |
Qualification |
| Launch Vehicles: |
H-II Second Stage |
H-IIA Second Stage |
* LE-5A Engine performance from
Steven J. Isakowitz "International Reference Guide to Space Launch Systems".
** LE-5B Engine performance from NASDA H-IIA Brief Description Document.
|
