Turkey's Anka UAS enters new test phase

2011-11-16

Turkey's Anka UAS enters new test phase

Ankara's ambitions to field an indigenous medium-altitude, long-endurance unmanned aircraft system (UAS) have been advanced, with flight tests of Turkish Aerospace Industries' (TAI) Anka having entered a new phase.

The company has announced that its Anka prototype completed its fifth flight on 22 October, "marking the beginning of the envelope expansion process". This will demonstrate the aircraft's performance at various altitudes, speeds and weights, TAI said.

First flown on 30 December 2010, the Anka reached an altitude of 10,000ft (3,050m) during its latest sortie, which tested the design's autopilot.

"Over the next few flights, the expansion will be completed and the test campaign will continue with demonstrations of a series of systems improvements, including the automatic take-off and landing system," the Turkish company said.

Previous information released about the Anka ("Phoenix") has described it as having a maximum take-off weight of 1,600kg (3,530lb), including a 200kg payload. It is designed to stay aloft for up to 24 hours, and to fly at an altitude of up to 30,000ft.

Craig HoyleLondon / Flight International

Region:  Europe
Contry:  Turkey
Category:  UAV
Company:  TAI-TUSAS



Turkey TAI-TUSAS UAV
Name:  Anka   Region:  Middle East    Country:  Turkey    Category:  UAV    Company:  TAI-TUSAS   
Anka

Use(s): MALE ISTAR Manufacturer: TAI-TUSAS Aerospace Industries Inc Powerplant: single heavy-fuel piston-prop engine, pusher configuration Dimensions: length: 8m, wingspan: 17m Weight: empty: 1,368kg, MTOW: 1,750kg, max payload: 200kg Performance: endurance: 24hr, ceiling: 30,000ft, mission radius: (LOS) 200km; endurance speed: 110kt Payload: ASELSAN ASELFLIR-300T EO/IR, LRF and LD as the primary payload; as the secondary payload, currently a SAR/ GMTI radar or alternatively any customer payload which meets the weight and volume restrictions Data Link: dual redundant Ku/C-band LoS data link Guidance/Tracking: full autonomous navigation and real time telemetry and telecommand; stability augmentation, fail-safe modes; redundant flight critical systems Launch: conventional wheeled; dual thread automatic take-off and landing system Recovery: conventional wheeled automatic or manual; dual thread automatic take-off and landing system Structure Material: full composite airframe System Components: 4-5 aircraft, mission payloads, 1 x GCS, 2xGDT, 1x Transportable Image Exploitation System, 1x Remote Video Terminal, 1 set of GSE Electrical Power: 28V DC, dual redundant power bus GCS: NATO ACE III shelterised GCS, two redundant consoles for piloting, mission planning and diagnostics



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