Proteus Specifications
Specfication
|
|
Description.
|
| Wingspan |
|
77 ft, 7 in; 92 ft with removable tips installed.
|
| Wing area |
|
300 sq. ft.
|
| Canard span |
|
54.7 ft; 64.7 ft with removable tips installed.
|
| Canard area |
|
178.7 sq ft
|
| Length |
|
56.3 ft
|
| Height |
|
17.6 ft (on landing gear)
|
| Cabin dimensions |
|
9 ft long, 5 ft dia.
|
| Crew |
|
2, single-pilot operation.
|
| Empty weight |
|
5,900 lb
|
| Gross weight |
|
12,500 lb; 15,800 lb in military usage.
|
| Fuel capacity |
|
6,000 lb in fuselage, canard, and wing tanks.
|
| Flight control system |
|
Conventional manual pushrod/cable system with sidestick controllers; autopilot for hands-off flight when on station.
|
| Payload |
|
1,800 to 7,260 lb, depending on mission.
|
| Electrical power |
|
19kw up to 30kw, depending on payload requirements.
|
| Propulsion |
|
Two Williams Research/Rolls FJ44-2 turbofan engines, 2,300 lb thrust each.
|
| Airspeed |
|
190 kt at 20,000 ft, 280 kt at 40,000 ft, true air speed. Mach 0.42 at cruise.
|
| Takeoff distance |
|
2,500 ft at maximum gross weight.
|
| Rate of climb |
|
6,000 ft/min at 8,000 lb, 3,400 ft/min at 12,500 lb.
|
| Altitude |
|
Up to 65,000 ft at 7,000 lb; 58,000 ft at 12,500 lb.
|
| Endurance |
|
Up to 18 hr, depending on payload and altitude.
|
| Primary materials |
|
All composite airframe, graphite- epoxy sandwich construction. Crew compartment is grid-stiffened solid laminate construction.
|
|
