Science Fair Project Encyclopedia
Falcon I
| Falcon I | ||
|---|---|---|
| Length | 70 ft (21.3 m) | |
| Diameter | 5.5 ft (1.7 m) | |
| Mass | 60,000 pounds (27,200 kg) | |
| Stages | 2 | |
| 1 - 1st Stage | Engines | 1 * Merlin engine |
| Thrust | 318 kN (71,500 lbf) | |
| ISP | 261 s (sea level) | |
| Burn time | 169 s | |
| Fuels | RP-1/LOX | |
| 2 - 2nd Stage | Engines | 1 * Kestrel engine |
| Thrust | 33 kN (7,500 lbf) | |
| ISP | 325 lbf·s/lb (3.19 kN·s/kg) (vacuum) | |
| Burn time | 552 s | |
| Fuels | RP-1/LOX | |
The Falcon I is a Falcon family two stage to orbit RP-1 kerosene/liquid oxygen semi-reusable launch vehicle designed and manufactured by SpaceX. The lower stage includes one Merlin engine and the upper stage includes one Kestrel engine. The Falcon I is designed to minimize price per launch and to prove the components to be used in the larger Falcon V rocket. The first stage returns by parachute to a water landing and is recovered for reuse. The second stage is not reusable.
The Falcon I 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 I is planned for May, 2005 [1][2], from Vandenberg Air Force Base carrying a NRL Tacsat and a Space Services Incorporated space burial payload. Launch prices are expected to be US$5.9 million plus range fees.
Payload Capabilities
- 200 km, 28 degrees: 670 kg (1480 lb)
- 400 km, 51 degrees (International Space Station): 580 kg (1280 lb)
- 700 km, sun synchronous: 430 kg (950 lb)
Please note that these capabilities are subject to change, based upon further testing.
Sources and External Links
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