RSD 58
 | This article includes a list of general references, but it lacks sufficient corresponding inline citations. (August 2012) |
| Contraves-Oerlikon RSD-58 | |
|---|---|
| Type | Surface-to-air missile |
| Place of origin |  Switzerland |
| Service history | |
| Used by | Switzerland, Italy and Japan[1] |
| Production history | |
| Designed | From 1947[1] |
| Manufacturer | Contraves-Oerlikon[1] |
| Produced | ca 1950[1] |
| Variants | Contraves-Oerlikon RSC-57 parachute recoverable training round[1] |
| Specifications | |
| Mass | 467 kg (1,030 lb) firing weight[1] |
| Length | 6.1 m (20 ft)*[1] |
| Diameter | body 0.4 m (1.3 ft)*[1] |
| Wingspan | 1.34 m (4.4 ft)*[1] |
| Warhead | High explosive[1] |
| Warhead weight | 40 kg (88 lb)[1] |
Detonation mechanism | Radio signal[1] |
| Engine | Liquid propellant rocket motor[1] Approx. 2,200 lbf (9.79 kN) for 45 seconds in RSD-58 and 30 seconds in RSC-57[1] |
| Propellant | RFNA and Kerosene[1] |
Operational range | 30 km (18.64 mi)[1] |
| Flight ceiling | 24,500 m (80,400 ft)* maximum, 3,000 m (9,800 ft)* minimum[1] |
| Maximum speed | Mach 2.4 at burn-out[1] |
Guidance system | Beam-riding[1] |
Steering system | controllable tail fins and vectoring motor combustion chamber[1] |
Launch platform | Transportable ground launcher.[1] |
The RSD 58 is an early production surface-to-air missile system developed by Contraves Oerlikon in Switzerland from 1947. Test firings were first made in 1950 with production starting in 1952 for the armed forces of Switzerland, Italy and Japan.[1]
Design and development
Design work on the RSD-58 commenced in 1947, resulting in a liquid-fuelled rocket powered missile guided to its target by riding a radar beam. The complete system includes a battery command post, target tracking radar, guidance beam transmitter and six twin railed trainable launchers. The entire system including the static launchers is readily transported to new locations with mobility claimed to be similar to that of a heavy anti-aircraft gun system.[1]
Test firings commenced in Switzerland during 1950-51, with a batch of 25 pre-production missiles being evaluated at Holloman air force base in New Mexico USA in 1953.[1]
Targetting is by search radar and beam transmitter with targets tracked by a search radar until a beam riding transmitter locks on, at which point the missile can be fired, riding the beam until impact, proximity fuze or radio signal detonation. Launchers, slaved to the beam transmitter can launch missiles at any angle form 10° to 90°. Control of the missiles is by vectoring rocket motor combustion chamber at low speeds and controllable rear fins at higher speeds.[1]
A parachute recoverable training round, the RSC-57, has been developed which is powered by a reduced burn time rocket motor with the recovery parachute replacing the warhead.[1]
Operational history
This missile system has seen active service in Switzerland, Italy and Japan.[1]
References
Notes
Bibliography
- Taylor, John W.R. FRHistS. ARAeS (1962). Jane's All the World's Aircraft 1962-63. London: Sampson, Low, Marston & Co Ltd.
- Hogg, Ian: Tykistö- ja ohjusaseet, Karisto, 2011, Hämeenlinna (Translated by: Petri Kortesuo) ISBN 978-951-23-5456-6 (s.209)