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Type
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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 |
Dimensions (m)
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Wieghts (kg) |
Performance
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Comments
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| Development | Production | Operation | Purpose | Mission payload | Launch, take-off type | Recovery, landing type | Min ground crews need | System composite | Datalink, comm frequency | Engine |
Propulsion
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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
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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) | ||||
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Conventinal helicopter |
Japan |
R-50/ R-Max
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Complete | Complete | Deployed | Agricultural and remote piloted helicopter and Recon. | Conventional helicopter take-off. | Cunventional helicopter landing. | One 12 hp 98cc Yamaha L 12 water-cooled two-cylinder two-stroke engine./ 21 hp Yamaha L 15. | Main rotor dia: 3.07/ 3.115 | Main rotor disc area= 7.40/ 7.62 | 3.85/ 3.63 | 1.08 | 0.70 | 44/ 58 | 20/ 30 | 67/ 88 | 300 | 0.1 | 0.5 | Helicopter | ||||||||||||||
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R-50: 1986/ R-MAX since 1997.
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R-50 1990- | More than 1,100 R-50s by1991-1999; more than 120 R-MAX sold in 2000. 132 in 2001. | Tain rotor dai= 0.50/ 0.56 | Tain rotor disc area= 0.212/ 0.25 | 
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11 | 30 | 0.5/ 1.0 | ||||||||||||||||||||||||||
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NAI China |
Soar Bird
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Complete | Complete | Available | Remotely piloted helicopter | Multiple special sensors | Conventional helicopter take-off | Conventional helicopter landing | One two-cylinder water-cooled piston engine | rotor | Main rotor Dia : 5.84 | tail rotor Dia : 1.17 | 7.07 | 2.25 | 280 | 30 | 81 | 9,840 IGE: 4920 | 81 | 4 | |||||||||||||||
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NRIST China |
Z-2
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Complete(?) | Complete(?) | available(?) | Remotely piloted helicopter | Conventional helicopter take-off | Conventional helicopter landing | One 11 hp piston engine | Rotor | Rotor Dia 3.25 | 2.85 | 58 | 1 | ||||||||||||||||||||||
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France |
Dragon Fly Heliot
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Complete | Underway | Deployed |
Multimission optionally piloted helicopter |
IFF transponder; RR401 peacetime radar transponder; thermal analysers; high-resolution field scanners; NBC and atmospheric sensors; camera systems; video and numeric datalinks. |
Conventional helicopter take-off. |
Conventional helicopter landing. |
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GCS, four-wheel-drive truck, towing a trailer, one AV. |
12-channel DGPS. |
One 105 hp Hirth F30A26AK four-cylinder two-stroke engine with twin spark ignition, modified. Fuel 64 liters. |
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Dia: 6.70/ 0.98 |
disc: 35.21 /7.86 |
7.86 |
0.50 |
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230 |
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120 |
450 |
VNE 80 |
70 |
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6,725 |
1.299 |
2.5 | PCS(Piloting Control System), MLS(DGPS mapping and locating system), TSDS, RRTES | |||
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Survey-Copter France |
Copter 1/ 2
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Complete | Underway | Deployed |
Aerial observation RPH. |
Can include CCD, zoom, IR or thermal imaging cameras |
Conventional helicopter take-off. |
Conventional helicopter landing. |
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1.2 - 2.5 GHz HF |
One 2 hp 23 cc single-cylinder two-stroke engine / 4 hp 46 cc two-cylinder two-stroke engine. |
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Dia: 1.82 |
2.20 |
0.50 |
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6.4/ 8 |
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4/ 10 |
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43 |
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660/ 1,600 |
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0.5/ 2.7 | 2.0 | Helicopter | |||
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| Conventional Helicopter |
Schiebel Austria |
Camcopter 5.1
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Complete | Complete | Deployed | Multirole VTOL | CCD, Camera | Convertional helicopter take-off. | Convertional helicopter langing. | GCS | E-band bidirection datalink | 38 hp UEL AR 741 rotary engine | Main rotor (Di 3.09 m), | 2.68 m | 0.80 m | 0.82 m | 43 kg | 17.4 kg | 25 kg | 68 kg | 49 kt | 590 | 9,840, OGE hover 5,575 | 54 | 6.0 | Helicopter | |||||||||
| Austria, US Army, Thales France, German Army. | |||||||||||||||||||||||||||||||||||
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Type
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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 |
Dimensions (m)
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Wieghts (kg) |
Performance
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Comments
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| Development | Production | Operation | Purpose | Mission payload | Launch, take-off type | Recovery, landing type | Min ground crews need | System composite | Datalink, comm frequency | Engine |
Propulsion
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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
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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) | ||||
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Bostan USA |
ACRW
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Underway | Experimental VTOL UAV. | Vertical take-off. | Vertical, short or conventional landing. | One 337 lb st Microturbo TRS 18-1 turbojet lift engine; 38 hp UEL AR 741 rotary engine. | Wing Dia =1.52 | 3.20 | 1.14 | 0.41 | 15.9 | 136.1 | 160 | 132 | 1,000 | 30 | 3.0 | |||||||||||||||||
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Dragonfly USA |
DP4
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Complete | Underway | Limited | Remotely piloted helicopter | Vertical take-off. | Vertical landing. | One 17 hp Quadra Aerrow QA-200XL 200cc two-cylinder two-stroke engine. | Rotor dia= 2.59 | tail rotor dia= 0.55 | 3.01 | 1.12 | 0.81 | 31.8 | 4.1 (5.7 liters) | 63.5 | 87 | 7,000 | 1 | 1.0 | Helicopter | |||||||||||||
| DP3: 1991 ~ | |||||||||||||||||||||||||||||||||||
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D-Star USA |
D'Humbug
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Underway | Piston | Span = 6.5 | 25 | 150 | 18,000 | 27 | 4.0 | Rotor-in-Wing | ||||||||||||||||||||||||
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Type
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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 |
Dimensions (m)
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Wieghts (kg) |
Performance
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Comments
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| Development | Production | Operation | Purpose | Mission payload | Launch, take-off type | Recovery, landing type | Min ground crews need | System composite | Datalink, comm frequency | Engine |
Propulsion
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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
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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) | ||||
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Frontier Systems USA |
A160 Hummingbird
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Underway | Long- endurance RPH. | Conventional helicopter take-off. | Conventional helicopter landing. | One 400 hp Leading Systems piston engine. | Main rotor dia= appx 11.3 | 181.4 | appx 1,814 | appx 140 | 30,000; OGE 15,000 | 2,000- 2,970 | 30 - 40 | |||||||||||||||||||||
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Fuji Japan |
RPH-2 / F-5000/ |
Complete | Underway | Deployed | Agricultural and environmental RPH. |
Twin chemical tanks (combined capacity 60 litres; 19.6 US gallons; 13.2 lmp gallons) and spraybars; alternatively atmospheric, EO, IR or NBC sensor. |
Conventional helicopter take-off. | Cunventional helicopter landing. | One 83.5 hp 679 cc Fuji Robin three-cylinder two-stroke engine. | Main rotor dia= 4.80, Tail rotor dia= 0.80 | 1.80 | 1.30 | 205 | 20 | 60 | 325 | 65 | 6,560 | 81 | 3.5 | ||||||||||||||
| Since 1990 .. | Japanese Ministry of Agriculture, Forestry and Fishery | ||||||||||||||||||||||||||||||||||
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Fuji Japan |
FFOS (Forward- Flying Observation System) |
Complete | Underway | Underway | Self-defence fire supporting |
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Conventional helicopter take-off. | Cunventional helicopter landing. | ||||||||||||||||||||||||||
| Since 1990 earlier RPH-1 for Japan Defence Agency. First flight Feb 1996 and trial flight finished in 1997. | |||||||||||||||||||||||||||||||||||
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Schweizer/ Kawada Japan/USA |
RoboCopter 300 / Argus
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Underway | Multipurpose unmanned helicopter | Four-axis gyrostabilised IR/TV sensor. | Conventional helicopter take-off. | Conventional helicopter landing. | One 168 hp modified (derated) Textron Lycoming HO-360-C 1A flat-four engine initially; -> four-cylinder Oldsmobile motocar engine. |
Dir: M-r 8.18 , T-r 1.30 |
disc area: M-r 52.5 T-r 1.32 |
9.40 |
2.65 |
1.99 |
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1.30 |
499 |
57 liters |
295 | 794 |
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1.7 | |||||||||
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Northrop Grumman USA |
Fire Scout
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Complete | Underway | FY03(MC), FY07(Navy) 75EA planned | VTOL surveillance UAV. | Northrop Grumman ESSS/IAI Tamam U-MOSP multimission (EO/IR) sensor and laser designator.; 200 (MMP-EO/IR, laser designator / ranger finder) | Conventional helicopter take-off. | Conventional helicopter landing using Sierra Nevada UCARS system. | Ku-band /UHF | One 420 shp Rolls-Royce 250-C20W turboshaft. | Main rotor dia=8.38/ Tail rotor dia=1.30 | 55.18/ 1.32 | 6.98 | 2.87 | 1.75 | 661 | 360 | 91 | 1,156 | 125 | OGE 5,000 | 110 | 4.2 | |||||||||||
| The first full autonomous test flight on 12 Jan 2000. | 23sys×3UAV | ||||||||||||||||||||||||||||||||||
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argus
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Orion USA |
Seabat
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Underway | VTOL UAV for maritime and other applications. | IR | Autonomous tail-sitting vertical take-off. | Autonomous vertical landing. | Two UEL AR 731 single -rotary engines (each 22.4 kW; 30 hp). | 3.05 | 1.83 | 1.83 | 52.2 | 22.7 | 90.7 | 200 | 180 | 10,000 | 1,500 | 100 | 4.0 | Tail-Sitter` | ||||||||||||||
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USA |
Vigilante 496 (OPV)/ 502 (UAV) |
Complete | Underway | Multirole VTOL UAV. | IAI Tamam POP in 496/500; SAR/MTI, laser rener finder/designator | 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 | |||||||||||||||||
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Steadicopter Israel |
Helivision
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Underway | Small Rotary wing UAV | Vertical take-off. | Vertical landing. Parechute for emergency. | 1.50/2.00 | 9 / 14 | 30 | 10,000 | ||||||||||||||||||||||||||