Falcon 5
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| Falcon 5 | |
 Early Falcon 5 design |
|
| Fact sheet | |
|---|---|
| Function | Man-rated re-usable orbital launch vehicle |
| Manufacturer | SpaceX |
| Country of origin | United States |
| Size | |
| Height | 47 m (154 ft) |
| Diameter | 3.65 m (12 ft) |
| Mass | 155,000 kg (340,000 lb) |
| Stages | 2 |
| Capacity | |
| Payload to LEO | 4,100 kg |
| Payload to Geosynchronous transfer orbit |
1,050 kg |
| Launch History | |
| Status | Cancelled |
| Launch sites | SLC-3W Vandenberg AFB Omelek Island LC-36 Cape Canaveral Kodiak Island Wallops Island |
| First Stage | |
| Engines | 5 Merlin |
| Thrust | 1,890 kN (425,000 lbf) |
| Specific impulse | Sea level: 255 sec (2.6 kN/kg) Vacuum: 304 sec (3.0 kN/kg) |
| Burn time | 200 seconds |
| Fuel | LOX/RP-1 |
| Second Stage | |
| Engines | 1 Merlin |
| Thrust | 409 kN (93,000 lbf) |
| Specific impulse | Vacuum: 304 sec (3.0 kN/kg) |
| Burn time | 265 seconds |
| Fuel | LOX/RP-1 |
The Falcon 5 was a proposed two stage to orbit partially reusable launch vehicle designed by SpaceX, since canceled and replaced by the Falcon 9. The first stage was to be powered by five Merlin engines and the upper stage by one Merlin engine, both burning kerosene with a liquid oxygen oxidizer. Along with the Falcon 9, it would have be the world's only launch vehicle with all stages designed for reuse [1]
The Falcon 5 would have been the first American rocket since the Saturn V to have engine out capability (although the Space Shuttle also has the capability). Failure of up to three Merlin engines could result in a successful flight, depending on when during flight the engine failure takes place. The Falcon 5 was also the first American orbital launch vehicle designed to be man-rated (i.e., certified for human transportation) since the Shuttle.
Proposed Falcon 5 launch sites included:
- Space Launch Complex 3W at Vandenberg Air Force Base
- Launch Complex 36 at Cape Canaveral Air Force Station
- Omelek Island in the Marshall Islands
- Kodiak Island
- Wallops Island.
Contents |
[edit] Launcher versions
| Version | Falcon 5 (cancelled) |
|---|---|
| Stage 0 | — |
| Stage 1 | 5 × Merlin 1C |
| Stage 2 | 1 × Merlin 1C |
| Height (max; m) |
47 |
| Diameter (m) |
3.6 |
| Initial thrust (kN) |
1,890 |
| Takeoff weight (tonnes) |
154.5 |
| Fairing diameter (Inner; m) |
3.6 or 5.2 (large fairing) |
| Payload (LEO; kg) |
4,100 |
| Payload (GTO; kg) |
1,050 |
| Price (Mil. USD) |
18 |
| minimal Price/kg (LEO; USD) |
4,390 |
| minimal Price/kg (GTO; USD) |
17,143 |
| Success ratio (successful/total) |
— |
[edit] Falcon 9 derivative redesign
The original Falcon 5 design evolved in 2005 and 2006 into the new, larger Falcon 9, with 9 engines on the first stage, compared to the Falcon 5's five.
[edit] Payload capabilities
[edit] References
- ^ "SpaceX press release", Space.com, 8 Stptember 2005.
- ^ "SpaceX Falcon Data Sheet", Space Launch Report, 5 July 2007.
- ^ "Monster Progress Update (Mostly Falcon 9)", SpaceX, 17 August 2007.
- ^ "Falcon 1 Overview", SpaceX, 28 September 2007.
- ^ "Falcon 9 Overview", SpaceX, 28 September 2007.
- ^ "Falcon 9 Heavy Overview", SpaceX, 28 September 2007.
