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Other West EUROPE |
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Prime Manu.
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UAV Designation
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Production status
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Operational status E
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Power | plants | Dimensions (m) | Wieghts (kg) |
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 | 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) | Range (nm) | Max Endurance (h) | ||||
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Austria
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C Craft
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Eyrie Mk 7
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Complete; | Complete | Available | Multirole UAV | Mini-panoramic camera, FLIR, TV sensor(×10). | Wheel, pneumatic / hydraulic launcher | wheel aided braking and arresting wire. Landing run: 50 m without brake, 30 m (with brake)( | GCS | 80 hp Rotax 912 UL flat-four engine | Two-blade pusher propeller (Di 0.91 m) shrouded by annular duct. | 5.03 m | 3.81 m | 1.77 m | 0.55 m | 105 kg | 65 kg | 75 kg | 225 kg | 167 | 147 kt | 42 kt | 2,050 | 15,000 | 32 | 15.0 | ||||||||
| Mk 1 first flight in April, 1980. Mk 2 first flight in June 1981. | |||||||||||||||||||||||||||||||||||
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Schiebel
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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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Belgium
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Thales
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Epervier (Sparrow hawk)
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Complete | Complete | Deployed | Battlefield reconnaissance | Day / Night sensor (Day: 127 mm Omera AA3-70 camera, Night: 70 mm Onera AA6-62 flare camera) | M3 type booster rocker / 2.5 m rail. | 60 §³ parachute | Microwave | 110 lb st Lucas CT3201 turbojet. | 1.72 m | 2.38 m | 0.93 m | 0.32 | 101 kg | 25 kg | 20 kg | 147 kg | 270 kt | 2,362 | 10,000 | >50 | >25 min | |||||||||||
| 40 AV for Army in 1974. | |||||||||||||||||||||||||||||||||||
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Greece
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STN ATLAS - 3 Sigma AE
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Nearchos
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Underway | Mulitirole | TV camera, FLIR, ECM/ESM | Wheeled | Wheel, parachute | GCS | One 38 hp UEL AR 741 rotary engine. | 5.10 | 2.95 | 3.95 | 1.15 | 0.43 m | 60 kg | 16.8 | 132 | 119 | 54 | 25,000 | 54 | 8.0 - 12 | |||||||||||||
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Italy
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Meteor
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Mirach 26
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Complete | Complete | Deployed | Close-range tactical UAV. | Daylight TV camera; Low-light TV camera or FLIR sensor; EO sensor. | Ramp-launch from zero-length rail on ground or on board ship with 1,653 lb st booster rocket. | Parachute landing; fixed ventral skid in flat area. | 30 (12 control, 8 maintenance, 10 transportation and setup) | 8 AVs, 5 control and launch stations (4 mobile and one remote), 5 maintenance stations, 10 trucks, 6 generators. | One 27 hp Sachs SF-350 two-cylinder two-stroke engine. | Two-blade pusher prop. | 4.73 | 3.0 | 3.85 | 1.27 | 0.36 | 24 (33 liters) | 35 | 230 | 119 | 92 | 78 | 590 | 11,500 | 27 | 8.0 | |||||||
| First flight in 1992. | Italian Army (20 systems in 1994) | dia=0.76 | |||||||||||||||||||||||||||||||||
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Mirach 100 target/ recce
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Complete | Complete | Deployed | Reconnaissance UAV. | Low-light TV camera/ IR. | Pair of booster rockets.; Helicopter (Agusta A 109 or Eurocopter Dauphin / Panther) launch. | As described for target version. | One 331 sb st Microturbo TRS 18-076 turbojet. | 1,804 | 0.82 | 4.126 | 0.807 | 40 | 280 | 495 | 29,500 | 135 | 1.0 | Variant of aerial target | ||||||||||||||||
| Italian Army. | |||||||||||||||||||||||||||||||||||
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Mirach 150
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Complete | Underway | Deployed | IRLS, panoramic camera, high-altitude photographic camera, high-resolution TV camera and video recorder. | Mobile zero-length launch ramp; fixed-wing aircraft or helicopter launch. | Pardchute. | 33 (14 for control, enght for maintenance and 11 for transportation and set-up) | 8 AVs, 6 control and launch vehicles (five mobile and one remote), 5 maintenance vehicles. | One 331 lb st Microturbo TRS 18-1 turbojet. | 2.60 | 1.40 | 4.70 | 0.91 | 0.383 | 254 | 86 | 50 | 380 | 378 | 291 | 29,500 | 135 | 1.0 | Follow-on to the Mirach 100 | |||||||||||
| One system delivered in 1993 to Italian Army. | |||||||||||||||||||||||||||||||||||
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Mirach 2000 |
Underway |
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Medium- altitude endurance UAV. |
MTI radar and multispectral EO sensors. |
land or ship-board launch. |
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25,000 |
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Country
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Prime Manu.
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UAV Designation
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Production status
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Operational status E
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Power | plants | Dimensions (m) | Wieghts (kg) |
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 | 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) | Range (nm) | Max Endurance (h) | ||||
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Spain
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INTA
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ALO (Avion Ligero de Observacion)
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Complete(?) | Underway | Deployed (?) | Surveillance UAV. | CCD colour TV camera or FLIR with real time video imagery downlink. | By bungee catapult | Parachute recovery to belly landing. | 2 | Transported and operated from a single Unimog all-terrain vehicle. | One 6.5 hp piston engine. | Two-blade prop. | 3.03 | 1.75 | 6 | 20 | 108 | 27 | 4,920 | 27 | 2.0 | |||||||||||||
| Evaluated by Spanish Army in 1995-1996; in service by 2000. | |||||||||||||||||||||||||||||||||||
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Ceselsa/ INTA (Spain)/ EADS Dornier (Germany)
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SIVA
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Complete | Underway | Surveillance UAV | IAI Tamam Moked 400 FLIR/ CCD TV; IRLS module. | OKT Norge 10/150 hydraulic catapult, or two booster rockets. | Parachute system. Twin under fuselage airbags cushion landing impact. | GCS | Real-time datalink E-band (2.2-2.4 GHz) | One 26 hp Sachs SF2-350 two-cylinder two-stroke engine -> 49.6 hp Rotax 503 UL flat-twin. | Two-blade fixed-pitch prop. | 4.828 | 3.33 | 3.78 | 0.95 | 0.42 | 160 | 40 | 30 | 230 | 102 | 76 | 9,800 | 669 | 81 | 10 | |||||||||
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Sweden
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Scandicraft / FAO (Swedish National Defence Research
Establishment)
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APID (Autonomous Probe for Industrial Data acquisition)
-1 Iron bird
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Complete | Underway | Deployed | Fully autonomous multipurpose unmanned helicopter. | Piston | Rotor = 9.8 | 20 | 1,000 | 14 | 1.0 | Helicopter | ||||||||||||||||||||||
| 200 hours and more operated for R & D work. | |||||||||||||||||||||||||||||||||||
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APID-2
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Complete |
Underway |
Deployed |
EW (jamming) application |
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fully automatic take-off and landing. |
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One 12.3 hp Comer K-100 two-stroke piston engine with electric starting and electronic ignition. |
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Rotor dia 2.98 / tail rotor dia 0.62 |
6.98 |
3.615 |
1.08 |
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35 |
4 liters |
20 |
55 |
54 |
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985 |
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4 |
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By mid-1998, conpleted in EW configuration with |
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APID-3
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Underway |
Underway |
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Prototype |
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TechMent
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Midget RPG (Remotely Piloted Gyroplane) Mk I
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Complete | Underway | Deployed | Lightweight, cost-effective model, intended for civilian or military observation applications. | Colour or monochrome video, pan-and-tilt CCD camera. | Conventional jump-start autogyro take-off. | Autorotative autogyro landing. | Each UAV unit comprises three groups: a ground station group with six soldiers, a UAV group with four soldiers and a maintenance group with four soldiers. | Three air vehicles, one GCS, and a Hägglunds Bv206 tracked vehicle with trailer, and can be operated by divisional intelligence units. Each group is equipped with a Hägglunds Bv206 tracked vehicle with trailer; the GCS antennasare mounted on the trailer, enabling them to be placed at up to 500 m from the GCS. | One 13 hp piston engine. | Four-blade rotor. | rotor dia 1.50 | 1.40 | 0.40 | 5 liters | 5 | 25 | 54 | 13.5 | 2.5 | Unstabilised camera platform. | |||||||||||||
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Various prototypes since 1990. |
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Midget RPG Mk II
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Complete |
Underway |
Deployed |
Slightly larger and more capable version with reconfigured tail unit shape and specification details tailored to Swedish Army requirements. |
Controp SALS video camera on gyrostabilised platform. |
Conventional jump-start autogyro take-off. |
Autorotative autogyro landing. |
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One 17 hp piston engine. |
Two-blade rotor. |
rotor dia 1.80-2.20 |
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1.50 |
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0.60 |
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15 liters |
15 |
50 |
65 |
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27 |
3 |
Gyro- stabilised camera plaform. |
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Delivered one system(two air vehicle and a GCS) to Swedish Army in 1994. |
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Midget RPG Mk III
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Underway |
Underway |
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Brigade-level tactical version. Similar to Mk„±, but larger and able to carry combined IR and TV sensor. |
Combined infra-red and videocamera payload on gyrostabilised platform. Military Mk„² has provision for future installation of synthetic aperture radar, connunications relay or EW payload. |
Conventional jump-start autogyro take-off. |
Autorotative autogyro landing. |
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One 24 hp piston engine. |
Four-blade rotor. |
rotor dia 2.60 |
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2.0 |
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0.60 |
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25 liters |
25 |
90 |
81 |
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2,000 |
54 |
3-5 |
Auto gyro |
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Country
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Prime Manu.
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UAV Designation
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Production status
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Operational status E
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Power | plants | Dimensions (m) | Wieghts (kg) |
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 | 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) | Range (nm) | Max Endurance (h) | ||||
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Switzerland
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Swiss Aircraft and Systems Enterprise Corp (SF)
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ADS-95 Ranger
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Complete | Underway | Deployed | Reconnaissance, surveillance and target acquisition UAV | IAI Tamam MOSP TV camera with zoom capability and a FLIR sensor; options are a laser range-finder/ target designator, communication relay or EW payload. | By mobile hydraulic catapult. | Wheeled landing and parachute for emergency. | 3-4 operators, 2 mechanics and 2 electronics technicians. | Three to six air vehicle, one GCS, one remote communication terminal (RCT), one launcher, one RAPS autoland position sensor, one or more stand-alone mobile receiving units, plus training, maintenance and logistics equipment. | Microwave primary uplink and video / telemetry downlink and UHF back-up uplink. | One 42.2 hp Hirth F 31 two-cylinder two-stroke engine. | Two-blade fixed pitch pusher prop. | 5.708 | 3.41 | 4.611 | 1.125 | 0.42 | 40 liters + 20 liters auxiliary tank can be carried. | 45 | 275 | 119 | 97 | 49 | 14,700 | 81 | 5.0 / 6.0 (with auxiliary tank) | Teamed with IAI | ||||||
| First flight in December 1988. | First six preproduction in September 1989. | ||||||||||||||||||||||||||||||||||