Optionally Personed Unmanned Vehicle
  Prime Manu.
  UAV Designation
Production status  
Operational status          
Power plants
Dimensions (m)            
  Wieghts (kg)  
        Performance      
 
Comments
 Development
Production
Operation
 Purpose
Mission payload
Launch, take-off type
Recovery, landing type
Min ground crews need
System composite
Datalink, comm frequency
Engine
Propulsion
Wing span
Wing area (§³)
Length overall
Height overall
Wheel track
Wheel base
Wing aspect ratio
Fuselage max width
Weight empty
Max fuel weight
Max payload
Max T-O/launch weight
Max level speed (kt)
Cruising speed (kt)
Loiter speed (kt)
Stall speed (kt)
Service ceiling (ft)
Max rate of climb (ft/min)
Max range (nm)
Max endurance (h)
Aeromet
AURA
Complete Complete Underway Opteionally manned surrogate UAV. FLIR, video or other sensor as required. Conventional wheeled take-off; runway 915 m. Conventional wheeled landing.       115 hp Textron Lycoming O-235 flat-four engine. A two-blade pusher porp. 7.96 7.62 5.34           363 197 liters. 181 726 190 110-167   65 20,000   2,000 12  
1983 -     US and NATO armed forces.                                                          
Aurora Flight Sciences
Chiron
 Complete Complete In service Optionally Piloted Vehicle. Satcom & RF com relays; EO cameras and atmospheric sensors. Conventional wheeled take-off. Conventional wheeled landing.       Two 210 hp Teledyne Continental IO-360 flat-six engines, modified with electronic ignition, electronic fuel injection and single lever power control. 11.58   8.89 2.87         1,270     2,200  192  70-165     20,000     10  
                                                               
 CIRPAS
Pelican
 Complete Underway In service  Optionally Piloted Vehicle.   Conventional wheeled take-off. Conventional wheeled landing.           12.80                    150 2,086   90     25,000     24  
 First flight as a UAV UAV was made on December 1998.                                                                
  Prime Manu.
  UAV Designation
Production status  
Operational status          
Power plants
Dimensions (m)            
  Wieghts (kg)  
        Performance      
 
Comments
 Development
Production
Operation
 Purpose
Mission payload
Launch, take-off type
Recovery, landing type
Min ground crews need
System composite
Datalink, comm frequency
Engine
Propulsion
Wing span
Wing area (§³)
Length overall
Height overall
Wheel track
Wheel base
Wing aspect ratio
Fuselage max width
Weight empty
Max fuel weight
Max payload
Max T-O/launch weight
Max level speed (kt)
Cruising speed (kt)
Loiter speed (kt)
Stall speed (kt)
Service ceiling (ft)
Max rate of climb (ft/min)
Max range (nm)
Max endurance (h)

Kaman Aerospace Corporation

K-Max BURRO

Complete

Underway

Deployed, BURRO

Optionally piloted helicopter    Convertional helicopter take-off. Convertional helicopter landing.      

One Honeywell T53-17A-1 turboshaft, flat rated at 1,007 kW(1,135 shp).

 

 Rotor dai=14.73

Rotor disc:  340.9  12.73 4.14 3.68 4.11     2,334 699 (865 liters)

 

 2,948

100        15,000 IGE: 26,300 OGE: 29,120

2,500

300

 

 

     US Marine Corps                                                          
SAIC
Vigilante 496/ * 500/600 (UAV)
Complete Underway   Multirole VTOL UAV. IAI Tamam POP in 496/500; Versatron 12DS in 600. Vertical take-off (automatic in Vigilante 600). Vertical landing (automatic in Vegiliante 600); compatible with UCARS.       One 95 hp Hirth F 30 flat-four engine in 496/500; 150 hp Zoche diesel engine planned for 600.   Main rotor dia=7.01    6.02         1.22 274/ 266/ 284     499/ 499/  117/ 117/ 135       12,000/ 13,000/ 15,000   120 8.0/ 8.0/ 11  
                                                     

 

 

 

 

SCI

Proteus

Underway

 

 

Optionally piloted, high-altitude, long- operation (HALO) vehicle.   Conventional runway take-off. Conventional runway landing.      

Two 2,300 last Williams FJ44-2A trubofans.

 

23.65

27.92 17.17 5.38         2,658 2,676

2,268

7,166

272 190     64,000

3,400

500

22