Falcon 5

From Free net encyclopedia

Falcon 5

Image:SpaceX falcon v.gif

Envelope

Length

154 ft (47 m)

Diameter

12 ft (3.65 m)

Mass

340,000 lb (max)
(155,000 kg)

Stages

Stage 1

Engines

5 Merlin

Thrust

425,000 lb_f
(1,890 kN)

Specific impulse

~255 s (sea level) (2.6 kN·s/kg)
~304 s (vacuum) (3.0 kN·s/kg)

Burn time

~200 s

Propellant

RP-1/LOX

Stage 2

Engines

1 Merlin

Thrust

92,000 lb_f
(409 kN)

Specific
impulse

304 s (vacuum)
(3.0 kN·s/kg)

Burn time

~300 s

propellant

RP-1/LOX

Payload

(See text)

The Falcon 5 is a two stage to orbit reusable launch vehicle designed and manufactured by SpaceX. The first stage includes five Merlin engines and the upper stage includes one Merlin engine. Both burn kerosene/liquid oxygen. Along with the Falcon 9, it will be the world's first fully reusable launcher.

The Falcon 5 will be the first American rocket since the Saturn V to have engine out capability. Failure of up to three Merlin engines can result in a successful flight, depending on when during flight the engine failure takes place. The Falcon 5 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 5 will be launched from:

Pad 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.

The maiden flight is planned for the fourth 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).

[edit]