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LOW ALTITUDE SHORT RANGE UAV |
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Prime Manu.
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UAV Designation
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Production
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Operational
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Power plants
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Dimensions (m) |
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 | Wing area (§³) | Length overall | Height overall | Wheel track | Wheel base | Wing aspect ratio | Fuselage max width |
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) | Cruising speed (kt) | Loiter speed (kt) | Stall speed (kt) | Service Ceiling (ft) | Max rate of climb (ft/min) | Range (nm) | Max Endurance (h) | |||
| Complete | Underway | Underway | Surveillance and target acquisition UAV. | IAI Tamam POP for Block 1 RQ-7A; Inframetrics 445G Mk„² for Block 2. | Hydraulic catapult or conventional wheeled take-off. | Autolanding main, wheeled landing or parachute / parafoil retrieval. | GCS/ PMCS (Potable Missiom Control Station)/ MCPS | RVT | 38 hp UEL AR 741 rotary engine. | Two-blade fixed-pitch wooden pusher propeller. Dia 0.66 m | 12.8 | 3.89 | 2.14 | 3.40 | 0.91 | 91.0 | 28.6 (39.7 liters) | 149 | 27.2 | 123 | 80-85 | 53 | 55 | 1,500 | 15,000 | 43 | 5 - 6 | |||||||
| (1991) | 
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FY03 44sys×4UAV, 176EA planned for US Army. | Army TUAV contract of US$41.8 milliom for four Shacow 200 systems. | 
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Shadow 400
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Complete | Underway | Underway | Multirole UAV. | AAI Model 1325 composite gimbal system coupled to one of four sensor packages: a CCD daylight camera with 10:1 zoom; a LLTV CCD camera with 10:1 zoom; a Kollmorgen high-resolution FLIR; a FLIR Systems Inc Model 2000 FLIR. | Conventional wheeled take-off; automatic take-off or catapult launch optional. | Automatic Shipborne Net & Wheeled recovery | GCS/ PMCS (Potable Missiom Control Station)/ MCPS | RVT | One 37 hp rotary engine. | 5.20 | 4.30 | 5.15m | 45.0 | 220 | 120 | 65 | 15,000 | 100 | 8 | ||||||||||||||
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| Complete | Underway | Underway | Multirole UAV. | 18 different payloads by October 1999. | Conventional wheeled take-off; automatic take-off or catapult launch optional. | Automatic wheeled landing; parachute. | GCS/ PMCS (Potable Mission Control Station)/ MCPS (S-250, S-280 shelters) | RVT | One 52 Hp UEL AR 801 rotary engine. @8000RPM | Four bladed fixed pitch wooden pusher prop. | 6.83 | 3.754 | 4.77 | 1.25 | 148.4 | 85.5 liters | 41.0 | 265 | 104 | 75 | 16,000 | 675 | 108 | 12-14 | ||||||||||
| Six air vehicles, five payloads, one GCS, one GDT, six VTRs, three nose cameras, plus ground support equipment, spares and manuals for Romania. | 
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Alliant Tech- systems
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OutRider
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Underway | Limited | TUAV | Army | |||||||||||||||||||||||||||||
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Prime Manu.
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UAV Designation
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Production
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Operational
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Power plants
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Dimensions (m) |
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 | Wing area (§³) | Length overall | Height overall | Wheel track | Wheel base | Wing aspect ratio | Fuselage max width |
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) | 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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BAE Systems
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SkyEye R4E-30/ R4E-40/ R4E-50
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Complete | Complete | Complete | Multimission UAV. | TV and FLIR camera. | Catapult-launch, ESCO hydraulic / pneumatic launcher. | Skid landing, parachute/ parafoil landing. | One 98 hp twin-rotor rotary engine. | Four-blade pusher prop. | 7.315 | 4.12 | 24.0 | 334 | 109 | 567 | 110 | 70 | 16,000 | 750 | 100 | 12.0 | ||||||||||||
| 1971- / R4D first flight in 1973. R4E-50 first flight in November 1986. | R4E-40 was supplied to the US Army in 1984-86. | Egypt (Army); Morocco; Thailand (AF); USA (Army); others. | 
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Daedalus
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Dakota (Truck)
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Complete | Complete | Limited | Reconnaissance/ Surveillance and aeronautical research UAV. | Daylight or LLTV or FLIR. | Conventional wheeled take-off. | Conventional wheeled landing. Parachute recovery optional. | One 24 hp Arrow A-200 flat-twin two-stroke engine. | Two-blade prop. | 3.86 | 1.86 | 0.34 | 1.07 | 0.91 | 0.81 | 0.41 | 32.2 | 6.8 (9.5 liters) | 22.7 | 60.3 | 110 | 36 | 15,000 | 1,850 | 120 | 3.4 | |||||||
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Insitu
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Seascan
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Complete | Underway | Underway | Small reconnaissance UAV. | Insitu/Hood Technology digital, daylight colour video camera with 12:1 zoom. | On land, car-top cradle. At sea, low-pressure pneumatic catapult. Launch speed appx 50 kt. | Insitu- developed Skyhook retrieval system. | One 1.3 hp piston engine. | Two-blade pusher prop. | 3.04 | 0.72 | 1.20 | 0.41 | 11.0 | 4.3 | 3.2 | 15.4 | 68 | 49 | 43 | 16,000 | 492 | 810 | 15 | |||||||||
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in 2002 | 
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GSE
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Vindicator
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Complete | Underway | Short-range tactical UAV. | Multipurpose combined EO/IR sensor in ventral ball turret. | Conventional runway take-off. | Conventional runway landing. | One 105 hp Tempest six-cylinder two-stroke diesel engine, with turbocharger; 80 hp Jabiru 2200 four-stroke petrol engine. | Two-blade constant-speed or variable-pitch prop with large spinner. | 7.04 | 4.83 | 4.79 | 17.3 | 268 | 106 liters | 90.7 | 476 | 200 | 80-90 | 56 | 30,000 | 1,600 | 110 | 20 | ||||||||||
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Prime Manu.
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UAV Designation
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Production
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Operational
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Power plants
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Dimensions (m) |
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 | Wing area (§³) | Length overall | Height overall | Wheel track | Wheel base | Wing aspect ratio | Fuselage max width |
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) | 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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IAI/AAI inter- national
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Pioneer RQ-2A/ RQ-2B
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Complete | Complete | Deployed | Short/ medium-range surveillance and intelligence -gathering UAV | Tamam gyrostabilised high-resolution TV (Moked 200) or FLIR (Moked 400) day/night sensor. Can include EW, ECM, decoy, Com(UHF & VHF) relay and laser designator / range-finder packages. Versatron SmallBall dual-sensor (EO/IR). | Wheeled take-off, Pneumatically operated twin-rail launcher or rocket assisted EX 125 Mod 2 jettisonable JATO booster. | Wheeled landing, Sierra Nevada UCARS (UAV Common Automatic Recovery system). | GCS-2000/ LRS/ MCPS/ TCU | C-band (4.55 GHz) | One 26 hp Sachs SF 350 two-cylinder two-stroke engine. 38 hp UEL AR 741 rotary. | Two-blade pusher prop. | 5.11 | 4.26 | 125/ 138 | 29.9/ 32.7 | 45.4 | 190/ 205 | 100 | 80 | 80 | 12,000/ 15,000 | 807 | 100 | 5.5 | |||||||||
| 1985 | 
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(1986) 175EA/25EA, Sunset system | 
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IAI/TRW inter- national
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RQ-5A Hunter/ B-Hunter/ Shipboard type/ E-hunter
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Complete | Underway | Deployed | Short-range reconnaissance, surveillance and target acquisition UAV | Tamam MOSP(TV/FLIR); Elta airborne data relay system; UHF/VHF com relay; laser designator/ range-finder for Hellfire missiles; radar jammer; lightweight comint; com jammer; EW (sigint, 2000). | Conventional wheeled take-off; Rocket assisted take-off optional. | Conventional wheeled landing using retractable hook and arrester cable. Parachute for emergency recovery. Automatic landing system tested successfully in 2001. | IAI Elta GCS 3000/ MCPS with RVT; Control from the cockpit of an AH-64 Apache helicopter was tested in mid-2000. | Two J-band (20MHz) uplinks & two downlinks | One P 73 rotary piston engine. | Two-blade pusher prop. | 8.90 | 6.95 | 1.65 | 540 | 136 | 113 | 726 | 110 | 80 | 60 | 15,000 | 761 | 81 | 8.0/ 12 | Teamed with TRW (prime) | |||||||
| (1991) | 
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72EA/42EA, Sunset system | 
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Prime Manu.
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UAV Designation
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Production
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Operational
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Power plants
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Dimensions (m) |
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 | Wing area (§³) | Length overall | Height overall | Wheel track | Wheel base | Wing aspect ratio | Fuselage max width |
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) | 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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Meggitt
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Sentry
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Complete | Complete | Deployed | Short-range RSTA and relay UAV. | Video camera; EO/IR sensor or others. | Pneumatic launcher, wheeled take-off or wheeled dolly. | Wheeled or skid landing. Parafoil precision approach and landing system optional, enabling recovery in small or unimproved landing area. | E-band or G-band | One 25.5 Herbrandson dyad 290cc two-cylinder two-stroke engine. | Two-blade prop. Dia=0.74/ | 3.35 | 2.84/ 2.911 | 1.65/ | 0.76/ | 59.0 | 27.2 (37.9 liters) | 27.2 | 113.4 | 95 | 80-85 | 65-75 | 28/ | 15,000 | 200 | 8 | Army | |||||||
| since 1989 | since 1991 for US Army | |||||||||||||||||||||||||||||||||
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Sentry HP
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Complete |
Complete |
Deployed |
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3.90 | 2.44/ 2.571 |
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81.6 | 32.7 (45.4 liters) | 34.0 | 147.4 | 110 | 80 | 60 |
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16,000 |
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Northrop Grumman
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Starbird
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Complete | Lightweight tactical UAV. | TV/FLIR | Autonomous ground launch by Westinghouse -designed WHEC550N pneumatic launcher. | Autonomous recovery by ram-airparafoil to belly skid landing. (area 20 m × 20 m) | Two personnel. | 4 AVs, 2 ground vehicle, two GCSs (one mobile, one revote), two generators, engine starter, launcher, fuel transfer/ storage tanks. | One 38 hp UEL AR 741 rotary engine. | Two-blade pusher propeller. | 5.28 | 2.29 | 0.81 | 17.3 | 68 | 13.6/ 27.2 (19/ 38 liters) | 22.7/ 36.3 | 172 | 130 | 100 | 55 | 17,000 | 2,500 | 108 | 4.0/ >9 | |||||||||
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BQM-74C
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Complete | Complete | Deployed | Turbojet | 30,000 | 200 | 1.0 | |||||||||||||||||||||||||||
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Sea Ferret
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Complete | Turbojet | 20,000 | 160 | 3.0 | |||||||||||||||||||||||||||||
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NRL (US Naval Research Laboratory, Washington, DC.)
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Extender
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Underway | Air-launched deployable mini-UAV. | Surveillance sensors. | Hand-launched. | Belly landing. | One piston engine. | Two-blade pusher. | 3.10 | 0.76 | 2.25 | 13.2 | 73 | 39 | 87 | 2.3 | ||||||||||||||||||
