Matra M.04

Matra M.04
Type	Air-to-air missile
Place of origin	France
Production history
Designed	1948
Manufacturer	Matra
Specifications
Weight	460 kilograms (1,000 lb)
Length	4.6 metres (15 ft)
Diameter	0.25 metres (9.8 in)
Engine	Solid-fuel rocket 1,250 kg thrust for 14 seconds
Wingspan	1.8 metres (5 ft 11 in)
Propellant	Acid/Aniline rocket
Launch platform	Halifax (testing)

The Matra M.04 was a French missile project that began development in Societe Matra in 1948. Intended either as an air-to-air missile or a surface-to-air missile it was never adopted in service, although it was tested over the Sahara in 1952.

Development

The missile was first test-fired in flight from a Halifax bomber in May 1950 at Colomb-Bechar. The missile was large for an air to air missile, with two pairs of curciform swept wings, with the smaller rear pair being moved using pneumatic actuation to provide steering. A SEPR acid/aniline rocket containing 110 kg of propellent provided 1,250 kg of thrust for 14 seconds, taking it to a speed of 490 meters per second.

The surface-to-air version was intended to have an additional tandem booster stage, and was designated the R.042 - and work continued on it until 1955.

References

• Flight magazine, 28 January 1955
• Gunston, Bill (1979). The Illustrated Encyclopedia of the World's Rockets & Missiles. London: Salamander Books. ISBN 0-817-26870-1.