Engine Performance
|
LE-7 * |
LE-7A ** |
Propellant Combination
Oxidizer
Fuel |
Liquid Oxygen (LOX)
Liquid Hydrogen (LH2) |
Liquid Oxygen (LOX)
Liquid Hydrogen (LH2) |
| Engine Cycle: |
Staged Combustion |
Staged Combustion |
| Average Thrust: |
243,000 lbf
1,080 N |
246,960 lbf
1,096 N |
| Chamber Pressure: (Pc) |
2,090 psi
144 bar |
1,750 psi |
| Mixture Ratio: |
6.0 : 1 |
5.9 : 1 |
| Isp: |
445 sec |
440 sec |
| Nozzle Area Ratio: |
52 : 1 |
52 : 1 |
| Gimbal Capability: |
Yes |
Yes |
| Engine Mass: |
3,750 lb
1,700 kg |
3,750 lb
1,700 kg |
| Engine Thrust to Weight |
65.9 |
65.9 |
| Mixture Ratio Control: |
--- |
--- |
| Throttle Range: (% Pc) |
72 to 100% |
72 to 100% |
| Restart Capability: |
No |
No |
Engine Size:
Length / Diameter |
10.5 ft / - ft
3.2 m / - m |
10.5 ft / - ft
3.2 m / - m |
| Flight Status |
Flight Qualified |
Development |
| Launch Vehicles: |
H-II First Stage |
H-IIA First Stage |
* LE-7 Engine performance from
Steven J. Isakowitz "International Reference Guide to Space Launch Systems".
** LE-7A Engine performance from NASDA H-IIA Brief Description Document.
|
