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| Country | Prime Manu. | UAV Designation | Productionstatus | 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) | ||||
| USA | US AF College of Aerospace Doctrine | StrikeStar 2025 concept requirement | conceptual requirement | 400 | 85,000 | 1,700 | 24 | ||||||||||||||||||||||||||||
| DARPA & US AF / Boeing | X-45 Black UCAV ATD | Underway | Will be Deployed from 2008 for SEAD mission. | UCAV for AF SEAD mission. | JDAM (Joint Direct Attack Munition), GPS guided bomb, 6 LOCAAS (Low-Cost Autonomous Attack System) | Black1: UHF (control) / L-band (telemetry), Black2: UHF SAT link / 16 fighter's data link | Allied Signal F124 turbo-fan | 34 ft | 1,350 (3,000 lbs) | 8,000 lbs | 500 - 1000 | Storage container 15×6×20ft / 4.4×1.8×6.1 | |||||||||||||||||||||||
| Two prototype X-45A (Black1) were produced and first test flight was done in 2001 and prototype X-45B (Black2) will be produced and tested in 2003. |
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| DARPA & US Navy / Northrop Grumann / Boeing | X-47 Pegasus UCAV-N ATP | Underway | Shipboard precision strike, SEAD & surveilance. | SAR | P&WC JT15D-5C high bypass turbo-fan | 8.44 / >18 (future) | 389 sq.ft. | 8.46 | 3,835 lbs | 1,580 lbs | 1,000 lbs / 2,000 lbs (future) | 5,500 lbs | 36,000 | 12 | |||||||||||||||||||||
| First prototype X-47A was displayed on 26 Feb, 2001. 12 Test flight in Naval Weapons Center. |
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| US Army / Boeing | CRW UAAV | Underway | CRW(canard rotor wing) type | 780 km/h | |||||||||||||||||||||||||||||||
| DoD / Lochheed Martin | UCAV | Underway | UCAV | ||||||||||||||||||||||||||||||||
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| EADS | |||||||||||||||||||||||||||||||||||
| Country | Prime Manu. | UAV Designation | Productionstatus | 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) | ||||
| Sweden | NFFP / Saab Aerospace, Ericsson, Saab Avionics, Saab Dynamics | SHARC (Swedish Highly Advanced Research Configuration) | Underway | Attack UAV | Internally mounted weapons. | wheeled take-off | wheeled landing | Turbojet or turbofan engine | 8.0 | 10.0 | 5,000 | ||||||||||||||||||||||||
| Design study | NFFP 272 UAV Configuration |
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| France | Dassault | French Star UCAV | Underway | AVE (areon devalidation experinmental) stealth robotic combat aircraft | 8 | 10 | |||||||||||||||||||||||||||||
| 1998 - |
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| Israel | IAI | ||||||||||||||||||||||||||||||||||
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