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| AESTUS & AESTUS II (RS-72) - Specifications |
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Engine Performance
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Aestus * |
Aestus II ** |
RS-72 ** |
Propellant Combination
Oxidizer
Fuel |
N2O4
/ MMH |
N2O4
/ MMH |
N2O4
/ MMH |
| Engine Cycle: |
Pressure Fed |
Gas Generator |
Gas Generator |
| Average Thrust: |
6,140 lb
27.5 kN |
10,300 lb
46 kN |
12,000 lb
53 kN |
| Chamber Pressure: (Pc) |
145 psia
10 bar |
725 psia
50 bar |
856 psia
59 bar |
| Mixture Ratio: |
2.05 : 1 |
2.05 : 1 |
2.05 : 1 |
| Isp: |
324 sec |
337.5 sec |
338.8 sec |
| Nozzle Area Ratio: |
83 : 1 |
280 : 1 |
318 |
| Gimbal Capability: |
± 6 degrees
(electronic) |
± 6 degrees
(electronic) |
± 6 degrees
(electronic) |
| Engine Mass: |
300 lb (estimated)
136 kg (estimated) |
327 lb
148 kg |
340 lb
154 kg |
| Engine Thrust to Weight |
20.5 |
27.7 |
35.2 |
| Mixture Ratio Control: |
--- |
--- |
--- |
| Throttle Range: (% Pc) |
--- |
--- |
--- |
| Restart Capability: |
No |
Yes |
Yes |
Engine Size:
Length / Width |
--- |
7.25 ft / -- ft
2.2 m / -- m |
8.75 ft / -- ft
2.67 m / -- m |
| Flight Status |
Flight Qualified |
Development |
Development |
| Launch Vehicles: |
Ariane 5 Second Stage |
Ariane 5 Perfo 2000 Second Stage |
--- |
* Aestus engine performance from Steven J.
Isakowitz "International Reference Guide to Space Launch Systems".
** Aestus II and RS-72 engine performance from Boeing web site and product data sheets.
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