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HIGH ALTITUDE ENDURANCE UAV |
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Prime Manu.
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UAV Designation
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Production status
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Operational status
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Power plants
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Dimensions (m)
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Wieghts (kg)
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Performance
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Comments
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Development
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Production
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Operation
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Purpose
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Mission payload
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Launch, take-off type
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Recovery, landing type
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Min ground crews need
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System composite
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Datalink, comm frequency
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Engine
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Propulsion
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Wing span
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Wing area (§³)
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Length overall
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Height overall
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Wheel track
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Wheel base
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Wing aspect ratio
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Fuselage max width
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Weight empty
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Max fuel weight
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Max Payload
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Max T-O/launch weight
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Max level speed (kt)
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Cruising speed (kt)
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Loiter speed (kt)
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Stall speed (kt)
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Service Ceiling (ft)
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Max rate of climb (ft/min)
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Range (nm)
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Max Endurance (h)
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Aero Vironment
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Hiline
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Complete(?) | High-altitude long endurance UAV. | IR | Conventional runway take-off. | Conventional runway landing. | One 42 hp Akkerman modified OMC-200 two-cylinder four-stroke engine with single-stage turbocharger. | 15.24 | appx 25 | 185 | 96.6 | 45.4 | 341 | 40,000 | >2,608 | 15 - 30 | ||||||||||||||||||
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ASC (Advanced Soaring Concepts, Inc.)
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APEX
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Underway | High-altitude research sailplane. | Data recording equipment. | Released at high altitude from ballon provided by National Science Bolloon Facility. | Gliding descent to conventional runway landing. | 12.24 | 11.87 | 6.40 | 12.6 | 272 | 100,000 | appx 5 | |||||||||||||||||||||
| First flight scheduled for early 2000. | 
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Aurora
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Perseus B
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Complete | Underway | In service | High-altitude UAV for atmospheric science, weather research and telecommunications research missions. | Conventional wheeled take-off from a 5000×100 ft runway. | Conventional wheeled landing on runway. | GCS | One 115 hp Rotax 914 four-cylinder four-stroke engine, modified with a three-stage turbocharger and electronic fuel injection and engine controls. | Two-blade variable-pitch pusher propeller. Dir : 2.44 m | 21.79 | 7.62 | 3.606 | 80-150 | 1,000 | 46-69 | 65,000 | 1,620 | 24 | |||||||||||||||
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SkyWatch
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Underway | Turboprop | 114.0 | 7,900 | 900 | 62,000 | 250 | 32.0 | ||||||||||||||||||||||||||
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Theseus 1/ 2
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Complete | Underway | Underway | High-altitude long- endurance atmospheric research UAV. | Three Perseus class payloads. | Conventional runway take-off. | Conventional runway landing. | Two 80 hp Arion „±a four-cylinder four-stroke turbocharged engines. / Two turboprops, each flat rated at 35 shp and capable of 16 shp at 25,000 m. | A two-blade pusher prop. (dia:2.69m) / Three-blade pusher props. (dia:4.42m) | 42.06 | 12.19 | 4.88 | 1,135 liters | 340 | / 4,990 | 82,000 | 7,000 | 36 | First destroyed November 1996; second under construction since mid-1997. | |||||||||||||||
| First flight on 24 May 1996. | ||||||||||||||||||||||||||||||||||
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Prime Manu.
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UAV Designation
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Production status
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Operational status
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Power plants
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Dimensions (m)
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Wieghts (kg)
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Performance
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Comments
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Development
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Production
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Operation
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Purpose
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Mission payload
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Launch, take-off type
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Recovery, landing type
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Min ground crews need
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System composite
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Datalink, comm frequency
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Engine
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Propulsion
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Wing span
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Wing area (§³)
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Length overall
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Height overall
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Wheel track
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Wheel base
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Wing aspect ratio
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Fuselage max width
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Weight empty
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Max fuel weight
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Max Payload
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Max T-O/launch weight
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Max level speed (kt)
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Cruising speed (kt)
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Loiter speed (kt)
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Stall speed (kt)
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Service Ceiling (ft)
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Max rate of climb (ft/min)
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Range (nm)
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Max Endurance (h)
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Frontier Systems
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Shadow / Arrow / W570A
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Underway | High-altitude endurance UAVs. | Conventional runway take-off. | Conventional runway landing. | One 700 lb st Williams F112 turbofan. / / Twin 2,300 lb st Willaims-Rolls FJ44-2E turbofans. | 19.81/ 35.13/ 48.79 | / 65.03/ 125.42 | 3.10/ 5.51/ 7.67 | 1.83/ 1.98/ 2.74 | 907/ 1,588/ 3,402 | 91/ 454/ 4,536 | 1,588/ 10,886/ 20,412 | M 0.7 | M 0.5 ~ M0.65 | 50,000/ 70,000/ 70,000 | 18,000 | 12/ 60/ 60 | ||||||||||||||||
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GA-ASI
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Altus ERAST
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Complete | Underway | Deployed | High- altitude scientific research UAV. | Various ERAST and other aumospheric research payloads. | Conventional wheeled take-off. | Convertional wheeled landing. | One 100 hp Rotax 914EFI flat-four engine, initially with single turbocharger | Two-blade pusher porp. | 16.86 | 12.17 | 6.63 | 23.3 | 150 | 740 | 45,000 | 300 | 30.0 | One UAV for NASA ERAST | ||||||||||||||
| First flight in 1996.; Total of 193 hours flown, in 68 sorties, by April 1999 | One system for NASA Dryden Flight Research Center. | 
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Dia= 2.50 | ||||||||||||||||||||||||||||
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Altus„±
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Complete |
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Conventional wheeled take-off. | Convertional wheeled landing. |
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Rotax 914EFI flat-four engine with twin turbochargers in Altus „± | Two-blade pusher porp. Dia= 2.13 |
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975 |
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65,000 |
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300 |
30.0 |
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| First flight of Altus „± on 29 June 1998. |
US Department of Energy, two systems for R&D. |
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General Atomics Aeronautical Systems Inc / NASA |
Predator B-001
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Underway |
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Scientific research UAV |
Lynx SAR; Skyball E-O sensor; 6 hour VCR; Communications relay; Mode „³ IFF. |
Conventional wheeled take-off. | Wheeled landing. |
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L-3 Communications D-band OTH commercial satcom. |
B-001, B-003: One Honeywell TPE331-10t turboprop, flat rated at 579 kW (776 shp) for max continuous operation. / B-002: One 2,300 lbst Willams FJ44-2A turbofan. | McCaulley three-bladee, variable-pitch aluminium pusher prop. |
19.51 |
23.78 |
11.04 |
3.59 |
3.09 |
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1.15 |
3.65 |
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1,361 |
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2,903 |
210 |
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70 |
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50,000 |
2,400 | 2,250 |
25 |
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Began in 1999 as a company-funded venture. First flight 2 February 2001. |
Proof-of-concept protorype with enlarged RQ-1 airframe, turboprop engine and Y configuration tail unit. |
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Predator B-002
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Underway |
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// |
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19.51 |
23.78 |
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1,361 |
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2,903 |
270 |
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70 |
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60,000 |
2,900 |
1,781 |
12 |
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Planned to fly in September 2001. |
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Second prototype RQ-1 with turbofan engine.. |
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Predator B-003 Altair
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Underway |
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// |
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25.60 |
28.06 |
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1,588 |
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3,175 |
210 |
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65 |
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52,000 |
2,600 |
2,585 |
32 |
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Third currently planned aircraft, targeted to fly in March 2002. enlarged wings and tail surfaces. Being developed specifically for scientific and commercial applications |
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Prime Manu.
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UAV Designation
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Production status
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Operational status
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Power plants
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Dimensions (m)
|
Wieghts (kg)
|
Performance
|
Comments
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Development
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Production
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Operation
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Purpose
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Mission payload
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Launch, take-off type
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Recovery, landing type
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Min ground crews need
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System composite
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Datalink, comm frequency
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Engine
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Propulsion
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Wing span
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Wing area (§³)
|
Length overall
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Height overall
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Wheel track
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Wheel base
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Wing aspect ratio
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Fuselage max width
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Weight empty
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Max fuel weight
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Max Payload
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Max T-O/launch weight
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Max level speed (kt)
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Cruising speed (kt)
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Loiter speed (kt)
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Stall speed (kt)
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Service Ceiling (ft)
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Max rate of climb (ft/min)
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Range (nm)
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Max Endurance (h)
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Lockheed Martin
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DarkStar (RQ-3A)
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Completed. | Underway | Cancelled | Turbofan | 69.0 | 8,600 | 45,000 | OTH | 8.0 | Teamed with Boeing. | |||||||||||||||||||||||
| 1996 first flight |
vehicle: $10M |
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Northrop Grumman
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Completed | Underway | FY 02 | High-altitude endurance (HAE) surveillance UAV. | Raytheon Systems reconnaissance suite, liked to GCS via satellite. EO/IR sensor (digital Kodak CCD camera and 3 to 5 micron IR sensor). I/J-band SAR. | Conventional take-off (runway 1,525 m). | Conventional landing. | X-band or Ku-band SATCOM | One 7,600 lb st Rolls-Royce Allison AE 3007H turbofan. | 35.42 | 50.17 | 13.53 | 4.63 | appx 3.28 | appx 4.50 | 25.00 | 1.46 | 4,193 | 6,577 | 907 | 11,612 | 343 | 65,000 | 3,000 (Ferry: 13,500) | 36.0 | $10M exclusive of Ground Station | ||||||||
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Scarab
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Complete | Complete | Limited | Tactical reconnaissance UAV. | A CAI/Recon Optical KS-153A; a Loral D-500 IRLS or a CAI/Recom Optical CA-860. | Booster- launched by modified Harpoon rocket mortor. | Parachute system, Inflatable airbags. | One 970 lb st Teledyne Continental 373-8c turbojet. | 3.35 | 2.23 | 6.15 | 0.86 | 696 | 568 liters | 131.5 | 1,077 | M 0.8 | 43,000 | 521 | 2.0 | ||||||||||||||
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D-2
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NASA/ Scaled Composites
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Raptor Demonstrator D1/ D2
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Underway | HALE testbed UAV | TDRSS satelite transponder payload; NASA payload Environment Data system (PEDS). | Conventional wheeled take-off; launch form roof fo HMMWV truck for high-altitude. | Conventional wheeled landing | 65 hp modifide Rotax 912 flat-four engine for low alt./ modified Rotax 912 core. | 20.04 | 17.08 | 6.71 | 23.7 | 367 | 381 | 34 | 835 | 80 | 65,000 | 5,573 | 150 | 48.0 | ||||||||||||||
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1992 ~, first flight in 1993. | ||||||||||||||||||||||||||||||||
