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Aviolanda AT-21

Dutch pulsejet target drone From Wikipedia, the free encyclopedia

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The Aviolanda AT-21 was a target drone developed in the Netherlands by Aviolanda. Powered by a pulsejet engine, it was the Netherlands' first drone to be successfully developed, and saw limited use in the late 1950s and early 1960s.

Quick Facts AT-21, Role ...
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Design and development

Developed in 1955,[1] the AT-21 was of conventional aircraft design,[2] with a high-mounted, constant-chord monoplane wing and a twin tail empennage. Power was provided by a SNECMA AS-11 Ecrevisse pulsejet, mounted in a fairing underneath the aircraft's fuselage; the construction of the airframe made extensive use of plastic in the nose and tail, with the center-section being of metal construction, and the wings and tail were made of foam-filled plastic with metal stabilizers and rudders.[1]

Launch was by JATO-type booster rockets from a zero-length launch ramp; a trolley for conventional takeoff from a runway was also available. Control was by radio commands from a remote guidance station, set up like an aircraft cockpit; if radio contact was lost, the parachute recovery system would automatically deploy. The parachutes could also be manually released at the end of a mission; the wing and tail would be separated by explosive bolts upon landing to simplify recovery and reduce the risk of damage during the process.[1] Endurance was up to one hour, and it was possible to fit a payload of cameras for aerial reconnaissance duties.[3]

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Operational history

The first flight of the AT-21 took place in late 1955.[1] The first Dutch drone to successfully complete development,[3] it entered service with the Royal Dutch Navy.[4] Production of the AT-21 continued through 1958.[5]

Specifications

Data from Ordway and Wakeford,[3] Jane's All the World's Aircraft 1958-59[6]

General characteristics

  • Length: 5.5 m (18 ft 1 in)
  • Wingspan: 3.6 m (11 ft 10 in)
  • Height: 1 m (3 ft 3 in)
  • Wing area: 1.44 m2 (15.5 sq ft)
  • Empty weight: 155 kg (342 lb)
  • Gross weight: 300 kg (661 lb)
  • Fuel capacity: 120 L (31.7 US gal; 26.4 imp gal)
  • Powerplant: 1 × SNECMA AS.11 pulsejet, 0.85 kN (190 lbf) thrust

Performance

  • Maximum speed: 330 km/h (210 mph, 180 kn) at sea level
346 km/h (215 mph; 187 kn) at 3,000 m (9,800 ft)
  • Cruise speed: 285 km/h (177 mph, 154 kn) at 1,500–3,000 m (4,900–9,800 ft)
  • Endurance: 60-70 minutes
  • Rate of climb: 6.17 m/s (1,215 ft/min) at sea level
3.17 m/s (10 ft/s) at 3,000 m (9,800 ft)

See also

Aircraft of comparable role, configuration, and era

Related lists

References

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