MA-2 (rocket stage)
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| Manufacturer | Lockheed Martin |
|---|---|
| Country of origin | United States |
| Used on | Atlas-D, Atlas-Agena and Atlas LV-3B |
| General characteristics | |
| Height | 3.43 metres (11.3 ft) |
| Diameter | 4.9 metres (16 ft) |
| Gross mass | 3,050 kilograms (6,720 lb) |
| Associated stages | |
| Derived from | MA-1 |
| Derivatives | MA-3 |
| Launch history | |
| Status | Retired |
| MA-2 | |
| Powered by | 2 XLR89-5 |
| Maximum thrust | 1,517.42 kN (341,130 lbf) |
| Specific impulse | 282 seconds (2.77 km/s) |
| Propellant | LOX/RP-1 |
MA-2 was an American liquid fueled rocket stage, developed by Lockheed Martin for use on the Atlas-D, Atlas-Agena and Atlas LV-3B ).[1][2][3][4]
Design
MA-2 functioned as the "half stage" in the Atlas's "stage-and-a-half" design, meaning they functioned as a booster attached to a central sustainer core, but did not include their own fuel tanks.[2] Instead, fuel was drained out of the tanks of the sustainer core, until partway through the launch the booster segment was jettisoned. Similar to the booster segment on previous Atlas rockets,[5][3] MA-2 consisted of a thrust structure with attachment points and fuel lines for two XLR89-5 rocket engines, each contained in a nacelle for aerodynamic reasons. The middle was left empty to accommodate the LR-105-5 engine of the sustainer stage. The two booster engines shared a common gas generator located at one of the engines, but separate turbopumps.[2]
See also
References
- ^ "Atlas MA-2". www.astronautix.com. Retrieved 2025-09-22.
- ^ a b c "Atlas "stage-and-a-half" drive system". www.b14643.de. Archived from the original on 2016-01-22. Retrieved 2025-09-22.
- ^ a b "Atlas Family". Gunter's Space Page. Retrieved 2025-09-22.
- ^ "CONVAIR LV-3B / SM-65D ATLAS". Official United States Air Force Website.
- ^ "Atlas MA engine series". www.astronautix.com. Retrieved 2025-09-22.