Science Fair Project Encyclopedia
Falcon V
| 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 lbf.s/lb (sea level) ~310 lbf.s/lb (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 lbf.s/lb (vacuum) or 310 lbf.s/lb (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
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