Falcon V
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|
| Falcon V | ||
|---|---|---|
| Length | 100 ft (30 m) | |
| Diameter | 12 ft (3.65 m) | |
| Mass | Max 400,000 lb (181,000 kg) | |
| Stages | 2 | |
| 1 - 1st Stage | Engines | 5 * Merlin engine or "upgraded" Merlin engines |
| Thrust | 1600 kN (357,500lbf) or 2,240 kN (500,000 lbf) | |
| ISP | ~261 s (sea level) ~310 s (vacuum) | |
| Burn time | ~200 s | |
| Fuels | RP-1/LOX | |
| 2 - 2nd Stage | Engines | 2 * Kestrel engine or 1 * Merlin engine |
| Thrust | 66 kN (15,000 lbf) or 320 kN (71,500 lbf) | |
| ISP | 325 s (vacuum) or 310 s (vacuum) | |
| Burn time | ~300 s | |
| Fuels | RP-1/LOX | |
The Falcon V is a Falcon family two stage to orbit RP-1 kerosene/liquid oxygen semi-reusable launch vehicle designed and manufactured by SpaceX. The 1st stage includes five Merlin engines and the upper stage includes one Merlin engine. The first stage returns by parachute to a water landing, where it is picked up by ship in a procedure similar to that of the Space Shuttle solid rocket boosters. The Falcon V is designed for maximum reliability and safety, being the first American rocket since the Saturn V to have "engine out" capability on the first stage, with failure of up to three Merlin engines resulting in a successful flight, depending on when during flight the engine failure takes place. The Falcon V is also the first American orbital launch vehicle designed to be man-rated (i.e., certified for human transportation) since the Space Shuttle.
The Falcon V will be launched from Pad 3W at Vandenberg Air Force Base, Launch Complex 36 at Cape Canaveral Air Force Station, Marshall Islands, Kodiak Island, and Wallops Island. The maiden flight of the Falcon V is planned for the second quarter of 2006 from Vandenberg Air Force Base carrying a Bigelow Aerospace Genesis Pathfinder expandable space station module prototype. Launch costs are expected to be US$15.8 million plus range fees for a launch into low earth orbit (LEO), and US$20 million for a launch into geosynchronous transfer orbit (GTO).
Payload capabilities
- 200 km, 28 degrees: 6,020 kg (13,270 lb)
- 400 km, 51 degrees (International Space Station): 5,450 kg (12,015 lb)
- 700 km, sun synchronous: 4,780 kg (10,540 lb)
- GTO, 9 degrees: 1,920 kg (4,230 lb)
- Escape velocity (no kick stage): 1,200 kg (2,645 lb)
Please note that these capabilities are subject to change, based upon further testing.
Sources and external links
- SpaceX Falcon V details page (http://www.spacex.com/index.html?section=falcon&content=http%3A//www.spacex.com/falcon_v.php)