Jump to content

9K31 Strela-1

From Wikipedia, the free encyclopedia
The printable version is no longer supported and may have rendering errors. Please update your browser bookmarks and please use the default browser print function instead.
"SA-9" redirects here. For the Apollo flight, see A-103 (SA-9).
9K31 Strela-1
(NATO reporting name: SA-9 Gaskin)
9K31 transporter erector launcher
TypeVehicle-mounted SAM system
Place of originSoviet Union
Service history
In service1968–present
Used bySee list of operators
WarsArab–Israeli wars, Western Sahara War, Yugoslav wars, South African Border War Lebanon wars, Iran–Iraq War, Gulf War, 2003 invasion of Iraq,[1] Syrian Civil War, Yemeni Civil War (2014–present)
Production history
DesignerOKB-16 design bureau (now the Moscow-based KB Tochmash Design Bureau of Precision Engineering)
ManufacturerSoviet state factories
Produced1966
Variants9K31, CA-95[2]
Specifications (9K31 Strela-1[2])
Mass7,000 kg (15,000 lb)
Length5.8 m (19 ft)
Width2.4 m (7.9 ft)
Height2.3 m (7.5 ft) (travelling)
Crew3 (commander, gunner and driver)
Armour5–14 mm (0.20–0.55 in)
Main
armament
4 × 9M31 (or 9M31M)
EngineGAZ 41 V-8 water-cooled petrol
140 hp at 3,400 rpm
Power/weight20 hp/t (15 kW/t)
Ground clearance0.43 m (1.4 ft)
Fuel capacity290 litres (77 US gal)
Operational
range
750 km (470 mi)
Maximum speed 100 km/h (62 mph) (road)
10 km/h (6.2 mph) (water)
Guidance
system
infrared homing

The 9K31 Strela-1 (Russian: 9К31 «Стрела-1»; English: arrow) is a highly mobile, short-range, low altitude infra-red guided surface-to-air missile system. Originally developed by the Soviet Union under the GRAU designation 9K31, it is commonly known by its NATO reporting name, SA-9 "Gaskin". The system consists of a BRDM-2 amphibious vehicle, mounting two pairs of ready-to-fire 9M31 missiles.

Development history

The missiles used in this system were developed alongside the ubiquitous Soviet MANPADS 9K32M "Strela-2" (NATO designation SA-7 "Grail") in the 1960s. At first, both missiles were intended to be man-portable systems, but as it became obvious that the Strela-2 would be far more compact, the development goals of Strela-1 were changed. Instead of a battalion-level man-portable system the new criteria called for a regimental vehicle-mounted SAM to support the ZSU-23-4.

As a result of the change in role and more relaxed weight limits of a vehicle-mounted SAM, the design team made the 9M31 a much heavier missile, which permitted fewer design compromises than in the case of Strela-2 to achieve acceptable kinematic performance. The most notable difference is the much larger diameter of the missile and a blunt seeker head spanning the full width of the missile. With all else being equal, the ability of an optical seeker to detect a target is directly proportional to its diameter, but on the other hand aerodynamic drag increases proportionally to the square of the diameter.

The Strela-1 also had a warhead more than twice as heavy as the Strela-2, a proximity fuze, and more effective control surface configuration to provide better maneuverability at the cost of increased drag. The result was a missile four times the weight of Strela-2, with only slightly longer reach, but otherwise much better performance.

Vehicle

Each TEL carries four ready-to fire missiles, but typically no missiles for reloading. Reloading is performed manually and usually takes approximately 5 minutes. The missile boxes are lowered for transport to lower the total height of the vehicle. The driver and commander have periscopes for viewing outside the vehicle when the hatches are closed.

Apart from the new turret, the other major change to the BRDM-2 chassis is the removal of the belly wheels (which are presumably to improve off-road performance). The driver and commander both have infra-red vision systems. The vehicle has standard NBC (Nuclear, Biological and Chemical) protection including overpressure. The missiles fold down to the sides of the turret which greatly reduces the height of the vehicle whilst travelling. Each vehicle weighs around 7 tonnes (7.7 short tons) and has a 104 kW (140 hp) engine and a central tire pressure control system.

Missiles and guidance

9M31

The 9M31 missile

According to a number of Russian sources,[who?] the original 9M31 (US DoD designation SA-9A "Gaskin-Mod0") had a zone of reliable target destruction from 900 to 4200 metres. Several western and also some Russian sources give much higher range estimates of 800 to 6500 m (0.5 to 4 miles); these may refer to maximum firing range against an approaching target and minimum against receding, which are obviously larger envelopes as the target only has to reach the intercept zone by the time the missile would reach it.

The missile is effective against targets receding at a maximum speed of 220 m/s, or approaching at 310 m/s.

9M31
TypeSurface-to-air missile
Place of originSoviet Union
Production history
Variants9M31, 9M31M
Specifications (9M31[2])
Mass30 kg (66 lb)
Length1.803 m (5.92 ft)
Diameter120 mm (4.7 in)
Wingspan36 mm (1.4 in)
WarheadFrag-HE
Warhead weight3 kg (6.6 lb)
Detonation
mechanism
RF Proximity
Propellantsingle-stage Solid-fuel rocket motor
Operational
range
4,200 metres (2.6 mi)[3] (sometimes reported also as 6.5 kilometres (4.0 mi) for 9M31, 8 kilometres (5.0 mi) for the 9M31M.)
Flight altitude3,500 metres (11,500 ft) (some sources give also higher figures)
Maximum speed Mach 1.8
Guidance
system
photocontrast Lead(II) sulfide infrared homing seeker.[3] (sometimes reported also as IR seeker of 1–3 μm and/or 1–5 μm wavelength);

The warhead was primarily intended to impact the target directly, and had contact and magnetic fuzes, but also contained a back-up optical proximity fuze to detonate the warhead in case of a near miss. The missile also had an unusual safety mechanism in case of a miss; rather than a self-destruct fuze, if the optical fuze didn't detect a target within 13–16 seconds, the warhead safety mechanism would be engaged to prevent its detonation upon impact.

The missile is propelled by a single-stage solid-fuel rocket motor, which is ignited a few meters from the launch tube. As the throw-out charge ejects the missile from its canister, it trails a wire from its rear The main rocket ignites when the missile reaches the wire's end at a few metres distance, and is cut off from it. To achieve roll stabilization, the rollerons on the tailfins are used. In contrast with the rollerons used on some IR guided air-to-air missiles which are spun by the airflow, 9M31 missile uses four wires which are wound on the rollerons' discs, with other end connected to the launch tube. On launch their wires crank the discs to speed.[4]

The seeker head is an unusual construction, using uncooled lead sulphide (PbS) detector elements but with an unusual tracking mechanism. Uncooled PbS elements are commonly used to detect radiation at only short wavelengths of less than 2 micrometers. Only very hot objects emit strongly at such short wavelengths, limiting heat-seeking systems using uncooled PbS detector elements to rear-hemisphere engagements against jet targets, although propeller-driven aircraft and helicopters can of course be engaged from any direction from which the exhaust or other very hot parts of the engine are visible.

The seeker head of 9M31, however, utilizes the PbS elements differently from usual. Taking advantage of the fact that the clear sky gives strong and constant background emission at below 2 micrometer range, peaking at visual light (0.4 to 0.7 micrometer) wavelengths at which PbS at a temperature of 295 kelvins still provides a response, the seeker head is used to track the absence of radiation when the target blocks the background. The method is called optical photocontrast homing (Rus.: фотоконтрастное наведение). The advantage of photocontrast homing method over traditional heat-seeking homing heads using PbS elements is that it negates the most serious drawback of early-generation IR-homing missiles: complete lack of front-aspect engagement capability against approaching jets. Even early cooled seeker heads had usually only limited forward hemisphere engagement abilities, often reducing to zero in case of jets approaching exactly towards the shooter.

The new photo-contrast seeker also had serious limits, which came in the form of rather strict meteorological conditions that had to be met to enable the seeker to detect and track the target. It could only engage targets against background conditions of either clear sky or solid overcast, at least 20 degrees away from the sun, and at least 2 degrees above horizon. Nevertheless, following a study of battlefield conditions and aircraft tactics in past conflicts where short-range air defences had been used, it was concluded that conditions allowing the use of such a homing system were common enough to make it a cost-effective design choice and a better trade-off than the only practical alternative available at the time, which was infrared homing restricted to rear-hemisphere engagements.

The fact that Strela-1 would be supplemented by IR-homing Strela-2 and radar-controlled ZSU-23-4 self-propelled AA gun system may have influenced the decision in favour of such an unusual homing system. The main advantage of the choice was that it made Strela-1 the only ADA system in the Soviet tank or motor rifle regiment that could engage approaching targets out to a range of several kilometers – the ZSU being hampered by very short range, and Strela-2 by its limitation to tail-chase engagements of ground attack jets, after the jet had already delivered its attack.

9M31M

While the 9M31 was accepted to service after state trials in 1968, the trials committee also suggested improvements that should be incorporated into the weapon as soon as possible. As a result of these improvements, the 9M31M "Strela-1M" (US DoD designation SA-9B "Gaskin-Mod1") entered service in 1970.

The new version introduced many incremental improvements in the performance characteristics of the missile: it had a slightly heavier warhead (increased from 2.6 kg to 3 kg), a more accurate guidance system to increase the probability of a hit, and extended range. Range is again reported to be as high as 8000 m (0.35 to 5 miles) in a number of western and also a few Russian sources, whereas for example Petukhov & Shestov, Lappi, and a number Russian web sources give much more modest performance figures; considering the performance of similar systems, at least an intercept range of 8,000 m seems unlikely for such a small, high-drag missile design.

Deployment

The Strela-1 was deployed in short-range air defense batteries of Soviet motor rifle and tank regiments. The battery consisted of a gun platoon of four ZSU-23-4 Shilkas, and a SAM platoon with four Strela-1 vehicles.

The Strela-1 platoon contains, in addition to a command vehicle, one TEL fitted with a passive radar detection system similar to a Radar Warning Receiver, and several more (usually three) without any radar system. The radar detection system is the 9S16 "Flat Box" and consists of four sensors mounted around the BRDM vehicle giving it 360 degree coverage. This system emits no radar energy but can detect radio waves emitted from aircraft, giving the vehicle warning about incoming aircraft and aiding in the acquisition of the target aircraft with the optical system. Typical tactics call for the launch of two missiles against each target to improve the chance of destroying it.

In Russia, the 9K31 Strela-1 system was superseded by the 9K35 Strela-10.

Operators

Operators
  Current
  Former
Croatian 9K31.
Angolan 9K31 captured by South African troops during Operation Askari.
Missile launch of a Romanian CA-95 (licensed built 9K31 Strela-1 using a TABC-79 vehicle instead of a BRDM-2).

Current

Former

See also

Bibliography

  • Cooper, Tom (2017). Hot Skies Over Yemen, Volume 1: Aerial Warfare Over the South Arabian Peninsula, 1962-1994. Solihull, UK: Helion & Company Publishing. ISBN 978-1-912174-23-2.
  • Cooper, Tom (2018). Hot Skies Over Yemen, Volume 2: Aerial Warfare Over the South Arabian Peninsula, 1994-2017. Warwick, UK: Helion & Company Publishing. ISBN 978-1-911628-18-7.
  • Cullen, Tony; Foss, Christopher F. (1992). Jane's Land-based Air Defence 1992-93 (5th ed.). Jane's Information Group. ISBN 978-0710609793.
  • International Institute for Strategic Studies (1989). The Military Balance 1989-1990. London: Brassey's. ISBN 978-0080375694.
  • International Institute for Strategic Studies (1991). The Military Balance 1991-1992. London: Brassey's. ISBN 978-0080413259.
  • International Institute for Strategic Studies (2011). The Military Balance 2011. London: Routledge. p. 321. ISBN 978-1857436068.
  • International Institute for Strategic Studies (2024). The Military Balance 2024. Taylor & Francis. ISBN 978-1-040-05115-3.
  • Lappi, Ahti: Ilmatorjunta kylmässä sodassa
  • O'Halloran, James C.; Foss, Christopher F., eds. (2002). Jane's Land-Based Air Defense 2002-2003 (15th ed.). Janes Information Group. ISBN 978-0-7106-2437-6.
  • Petukhov, Sergei I., Shestov I.V.: Istorija sozdanija i razvitija vooruzhenija i vojennoi theniki PVO suhoputnyh voisk Rossii

References

  1. ^ Cordesman, Anthony H. (7 February 2003). Iraqi Armed Forces on the Edge of War (PDF) (Report). Center for Strategic and International Studies. p. 9. Archived from the original (PDF) on 9 February 2010. Retrieved 16 July 2015.
  2. ^ a b c d e f g h i j k l m n o p q r s t u v w x y O'Halloran & Foss 2002, p. 147.
  3. ^ a b "«Стрела-1» (9К31, SA-9, Gaskin), зенитный ракетный комплекс — ОРУЖИЕ РОССИИ, Федеральный электронный справочник вооружения и военной техники". Archived from the original on 2008-08-01. Retrieved 2008-08-01.
  4. ^ "Anti-aircraft missile system Strela-1".
  5. ^ IISS 2024, p. 343.
  6. ^ IISS 2024, p. 472.
  7. ^ IISS 2024, p. 428.
  8. ^ IISS 2024, p. 80.
  9. ^ IISS 2024, p. 267.
  10. ^ IISS 2024, p. 372.
  11. ^ O'Halloran & Foss 2002, p. 138.
  12. ^ IISS 2024, p. 131.
  13. ^ IISS 2024, pp. 198−199.
  14. ^ Francesco Palmas (2012). "Il contenzioso del sahara occidentale fra passato e presente" (PDF). Informazioni della Difesa (in Italian). No. 4. pp. 50–59. Archived (PDF) from the original on 2018-06-12. Retrieved 2018-06-12.
  15. ^ IISS 2024, p. 133.
  16. ^ IISS 2024, p. 386.
  17. ^ a b c Cullen & Foss 1992, pp. 134−136.
  18. ^ IISS 1989, p. 47.
  19. ^ a b c Cullen & Foss 1992, p. 136.
  20. ^ IISS 2011, p. 321.
  21. ^ Cullen & Foss 1992, p. 122.
  22. ^ Cooper 2017, p. 41
  23. ^ IISS 1991, p. 38.
  24. ^ Cooper 2018, p. 16
Wikimedia Commons has media related to 9K31 Strela-1.
Retrieved from "https://en.wikipedia.org/w/index.php?title=9K31_Strela-1&oldid=1254758516"