Falcon 5

Early Falcon 5 design

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 SLC-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.

Overview

The first stage of Falcon 5 was to be powered by five Merlin engines and the upper stage by one Merlin engine, both burning RP-1 with a liquid oxygen oxidizer. Along with the Falcon 9, it would have been the world's only launch vehicle with all stages designed for reuse.

The Falcon 5 would have been the first American rocket since the Saturn V to have full engine out capability (the Space Shuttle has partial engine out capability). The Falcon 5 also would have been the first American orbital launch vehicle designed to be man-rated (i.e., certified for human transportation) since the Shuttle.

Launcher versions

Payload capabilities

200 km, 28 degrees: 4,100 kg
GTO, 9 degrees: 1,050 kg

Falcon 1
Falcon 9

Falcon 5 Pictures

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Source: WikiPedia