R.511

From Wikipedia, the free encyclopedia
R.511
Type Air-to-air missile
Place of origin  France
Service history
In service 1952–1976
Used by Armee de l'Air
Aeronavale
Production history
Manufacturer Matra
Number built 1,500
Specifications
Weight 184 kilograms (406 lb)
Length 3.09 metres (10.1 ft)
Diameter 0.26 metres (10 in)
Warhead Blast-frag high explosive
Warhead weight 30 kilograms (66 lb)
Engine Hotchkiss-Brandt solid cast two stage motor
1,600 kg / 200 kg
Wingspan 1 metre (3 ft 3 in)
Operational
range
 7 kilometres (4.3 mi)
Flight ceiling 18,000 metres (59,000 ft)
Flight altitude 3,000 metres (9,800 ft) to 18,000 metres (59,000 ft)
Guidance
system
 Semi-active Radar Homing (R.511)
Steering
system
 Twist and steer
Launch
platform
 Vautour IIN
Mirage IIIC

The R.511 was a French air-to-air missile, developed by Matra, based on their work with the Matra M.04 (R.042) and R.05. The first version of the missile, the R.510, was infra-red guided, and while accurate had very limited operating parameters.[1] The missile was superseded by the far more capable R.530 in French service, although continued to be used in training units until 1976.

Description

View of the radar homing head of the R511.

The R.510 was optically guided by a PbS infra-red photocell with a 20 degree field of view. Testing of the R.510 began at Hammaguir in October 1952, and a limited production run of 100 missiles were ordered. However the PbS seeker was insensitive and could only effectively track targets at night. However The R.511 entered service in 1957, replacing the R.510. The R.511 used a Thompson-CSF radar homing head which was tuned to home on reflections of the launch aircraft's radar, its antenna scanned conically 8 degrees off the boresight of the missile at a rate of 225 revolutions per second.[1] For longer range firing guidance commands were transmitted directly to the missile via an antenna on the trailing edge of the missiles wing. Limitations of the launch aircraft's radar restricted operation to above 3,000 meters.

The missile could pull 12g's while travelling at Mach 1 at 33,000 feet (10,000 m) [1]

References

  1. ↑ 1.0 1.1 1.2 Flight, 6 November 1959
Bibliography
  • Gunston, Bill (1979). The Illustrated Encyclopedia of the World's Rockets & Missiles. London: Salamander Books. ISBN 0-5172-6870-1. 
  • Taylor, Michael; Taylor, John. Missiles of the World. ISBN 0-7110-0712-8. 
This article is issued from Wikipedia. The text is available under the Creative Commons Attribution/Share Alike; additional terms may apply for the media files.