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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.

AT-21
Role	Target drone Type of aircraft
National origin	Netherlands
Manufacturer	Aviolanda
First flight	1955
Primary user	Royal Netherlands Navy

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]

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 (9,843 ft)

• Cruise speed: 285 km/h (177 mph, 154 kn) at 1,500–3,000 m (4,921–9,843 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 (9,843 ft)

See also

Aircraft of comparable role, configuration, and era

• GAF Jindivik
• Ryan Firebee
• Martin KDM Plover

Related lists

• List of unmanned aerial vehicles

References

Citations

Bibliography

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