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R-33 (missile)

January 09, 2023

The R-33 (Russian: Вымпел Р-33, NATO reporting name: AA-9 Amos) is a long-range air-to-air missile developed by Vympel. It is the primary armament of the MiG-31 interceptor, intended to attack large high-speed targets such as the SR-71 Blackbird, the B-1 Lancer bomber, and the B-52 Stratofortress.

R-33
AA-9 Amos
R-33 on MiG-31 at Zhukovski, 1999
TypeLong range air-to-air missile
Specifications
Mass490 kg (1,080 lb)
Length4.14 m (13 ft 7 in)
Diameter380 mm (15 in)
Warhead47.5 kg (105 lb)
Wingspan1.12 m (3 ft 8 in)
Operational
range
120 km (1981), 160 km (1999),[1][2] 304 km (2012).[3]
Maximum speed Mach 4.5 (R-37)[4]
Guidance
system
inertial and semi-active radar homing; terminal active radar homing (R-33S)[5]

It uses a combination of semi-active radar homing for initial acquisition and mid-course updates, and inertial navigation to reach the target at extreme range. The Zaslon phased array radar of MiG-31 allows four missiles to be guided simultaneously at separate targets.

The R-33 AAM remains in service with the CIS and Russian forces (See MiG-31 operators).

Development

The history of the R-33 missile is tightly bound to the story of its launcher, the MiG-31. The development of the modernized MiG-25, E-155MP, was authorized by a governmental decision of 24 May 1968. There was a competition for future missiles for the E-155MP. Izdeliye 410 by "Vympel" of A.L.Lyapin won, while the K-50 by PKPK of M.R.Bisnovat lost. The missile was assigned the development name K-33, continuing the series of K-13 and K-23 missiles. The development was headed by vice-chief designer V.V.Zhuravlev and leading designer Y.K.Zakharov.

The R-33/MiG-31 missile/interceptor combination is similar to the earlier Bisnovat R-40/MiG-25 combination, although it is much more versatile and modern in that the MiG-25 was very heavily specialized for the interception of large supersonic targets such as the cancelled North American XB-70 Valkyrie bomber, and thus lacks maneuverability and is not suitable for air combat maneuvering. The MiG-31 is a much more versatile and capable aircraft and is still able to employ the older R-40.

Two prototypes were built in 1968, featuring nose-mounted manoeuvring fins and intended for carriage on underwing pylons, similar to the Bisnovat R-40 on board the MiG-25.

The draft project was completed in 1970 and progressed to testing using testbed aircraft. One of these was a converted early-production MiG-25 (aircraft P-10), and was used in 1972 for autonomous test launches from the upgraded APU-40 pylon. A MiG-21 (serial 76211524) was converted into the LL-21 testbed to test the missile seekers, while a Tu-104 jetliner (serial 42324) was converted into LL-104-518 (also known as LL-2) by NTK "Vzlet" to test the MFBU-410/"Zaslon" radar along with missile homing heads mounted on GVM-410 mockups. The space on board the passenger aircraft-based testbed allowed for the carriage of extensive diagnostic and support equipment.

The K-33 was evaluated with the RGS-33 SARH seeker and the TGS-33 IR seeker. Other candidates included active radar homing and dual IR/radar homing seekers. The final decision was made in favor of semi-active radar homing with an inertial initial stage. The homing device, designated MFBU-410 was developed by B.I.Ermakov under the supervision of Akopyan.

The missile design was significantly altered later in 1972. The seeker and warhead were enlarged, the span of the control fins was reduced from 1100 mm to 900 mm. Further, the mounting system was revised to include new under-fuselage slipper pylons, akin to the Phoenix mount on the American F-14, and the missile was reoriented, so it mounted with the fins cruciform rather than diagonal; the fins on the mounting (dorsal) side were made to fold to the side, to lie flush against the belly of the carrying aircraft. Consequently, the missile launch method also needed to be changed. Rather than launching directly from the mounting pylon, the redesigned missile used drop-launch, with the missile being jettisoned from the pylon on launch, and its rocket motor igniting on a time-delay.

A small run of one dummy (for launch system testing), 5 'programmed' (guidance and propulsion only, no warhead) and 8 fully functional trial missiles were built to the new design before the end of 1972. Of those 14, three were launched from the MiG-25P-10 testbed in 1973. Different warhead types (high explosive fragmentation and continuous-rod warhead) were evaluated, and tests of the radar and seeker systems were conducted on the LL-2. 1974 saw 11 more test launches from the MiG-25P-10, and the production of another 40 trial missiles. The first AKU-33 launchers and B-410 warheads were built. "Zaslon" tests continued at Akhtubinsk using the LL-2.

The first flight of the future MiG-31 (aircraft No.831) took place on 16 September 1975, with 12 more flights by the end of the year. The MiG-25P-10 testbed launched 20 more test missiles before being sent for its launchers to be upgraded, and the first telemetric missile launches from the LL-2 were carried out that year.

Development continued in 1976, including launches at PRM-2 parachute targets in April. Factory tests were completed in 1977 with 32 launches from the MiG-31 prototype, the first launch being against a MiG-17 drone on 26 March 1977). The guidance systems were improved during 1978, and the radar/missile combination performed a simultaneous launch at 4 targets in August.

State trials started in March 1979 using MiG-31 No.83210. They were successfully completed in 1980. A government decision on 6 May 1981 recommended R-33 into service.

Variants

[6]

R-33 R-33S R-33E
Maximum launch range, km 120 160 160
Maximum flight speed, Mach 4.5 — 4.5
Length, mm 4250 — 4150
Maximum diameter of the missile body, mm 380 — 380
Wingspan, mm 900 — 900
Rudders span, mm 1180 — 1180
Launch mass, kg 491 — 490
Warhead mass, kg 55 — 47
Maximum overload of targets hit 8g — —
Maximum speed of the target, km / h 3700 — —
R-33
Standard type.
R-33S
Improved version.
R-33E
Export version.
R-37
Further development of the R-33.

References

  1. ^ "AA-9 AMOS".
  2. ^ . Archived from the original on 27 October 2014.
  3. ^ "МиГ-31БМ получат новую ракету".
  4. ^ "Управляемая ракета большой дальности Р-33 (К-33) | Ракетная техника". rbase.new-factoria.ru. Retrieved 1 December 2016.
  5. ^ "R-33E". Deagel. Retrieved 29 January 2015.
  6. ^ "Управляемая ракета большой дальности Р-33 (К-33) | Ракетная техника". rbase.new-factoria.ru. Retrieved 1 December 2016.

Sources

  • Gordon, Yefim (2004). Soviet/Russian Aircraft Weapons Since World War Two. Hinckley, England: Midland Publishing. ISBN 1-85780-188-1.

External links

  • GlobalSecurity.org page
  • Federation of American Scientists page 28 August 2016 at the Wayback Machine

January 09, 2023
missile, russian, Вымпел, nato, reporting, name, amos, long, range, missile, developed, vympel, primary, armament, interceptor, intended, attack, large, high, speed, targets, such, blackbird, lancer, bomber, stratofortress, 33aa, amosr, zhukovski, 1999typelong. The R 33 Russian Vympel R 33 NATO reporting name AA 9 Amos is a long range air to air missile developed by Vympel It is the primary armament of the MiG 31 interceptor intended to attack large high speed targets such as the SR 71 Blackbird the B 1 Lancer bomber and the B 52 Stratofortress R 33AA 9 AmosR 33 on MiG 31 at Zhukovski 1999TypeLong range air to air missileSpecificationsMass490 kg 1 080 lb Length4 14 m 13 ft 7 in Diameter380 mm 15 in Warhead47 5 kg 105 lb Wingspan1 12 m 3 ft 8 in Operationalrange120 km 1981 160 km 1999 1 2 304 km 2012 3 Maximum speedMach 4 5 R 37 4 Guidancesysteminertial and semi active radar homing terminal active radar homing R 33S 5 It uses a combination of semi active radar homing for initial acquisition and mid course updates and inertial navigation to reach the target at extreme range The Zaslon phased array radar of MiG 31 allows four missiles to be guided simultaneously at separate targets The R 33 AAM remains in service with the CIS and Russian forces See MiG 31 operators Contents 1 Development 2 Variants 3 References 4 Sources 5 External linksDevelopment EditThe history of the R 33 missile is tightly bound to the story of its launcher the MiG 31 The development of the modernized MiG 25 E 155MP was authorized by a governmental decision of 24 May 1968 There was a competition for future missiles for the E 155MP Izdeliye 410 by Vympel of A L Lyapin won while the K 50 by PKPK of M R Bisnovat lost The missile was assigned the development name K 33 continuing the series of K 13 and K 23 missiles The development was headed by vice chief designer V V Zhuravlev and leading designer Y K Zakharov The R 33 MiG 31 missile interceptor combination is similar to the earlier Bisnovat R 40 MiG 25 combination although it is much more versatile and modern in that the MiG 25 was very heavily specialized for the interception of large supersonic targets such as the cancelled North American XB 70 Valkyrie bomber and thus lacks maneuverability and is not suitable for air combat maneuvering The MiG 31 is a much more versatile and capable aircraft and is still able to employ the older R 40 Two prototypes were built in 1968 featuring nose mounted manoeuvring fins and intended for carriage on underwing pylons similar to the Bisnovat R 40 on board the MiG 25 The draft project was completed in 1970 and progressed to testing using testbed aircraft One of these was a converted early production MiG 25 aircraft P 10 and was used in 1972 for autonomous test launches from the upgraded APU 40 pylon A MiG 21 serial 76211524 was converted into the LL 21 testbed to test the missile seekers while a Tu 104 jetliner serial 42324 was converted into LL 104 518 also known as LL 2 by NTK Vzlet to test the MFBU 410 Zaslon radar along with missile homing heads mounted on GVM 410 mockups The space on board the passenger aircraft based testbed allowed for the carriage of extensive diagnostic and support equipment The K 33 was evaluated with the RGS 33 SARH seeker and the TGS 33 IR seeker Other candidates included active radar homing and dual IR radar homing seekers The final decision was made in favor of semi active radar homing with an inertial initial stage The homing device designated MFBU 410 was developed by B I Ermakov under the supervision of Akopyan The missile design was significantly altered later in 1972 The seeker and warhead were enlarged the span of the control fins was reduced from 1100 mm to 900 mm Further the mounting system was revised to include new under fuselage slipper pylons akin to the Phoenix mount on the American F 14 and the missile was reoriented so it mounted with the fins cruciform rather than diagonal the fins on the mounting dorsal side were made to fold to the side to lie flush against the belly of the carrying aircraft Consequently the missile launch method also needed to be changed Rather than launching directly from the mounting pylon the redesigned missile used drop launch with the missile being jettisoned from the pylon on launch and its rocket motor igniting on a time delay A small run of one dummy for launch system testing 5 programmed guidance and propulsion only no warhead and 8 fully functional trial missiles were built to the new design before the end of 1972 Of those 14 three were launched from the MiG 25P 10 testbed in 1973 Different warhead types high explosive fragmentation and continuous rod warhead were evaluated and tests of the radar and seeker systems were conducted on the LL 2 1974 saw 11 more test launches from the MiG 25P 10 and the production of another 40 trial missiles The first AKU 33 launchers and B 410 warheads were built Zaslon tests continued at Akhtubinsk using the LL 2 The first flight of the future MiG 31 aircraft No 831 took place on 16 September 1975 with 12 more flights by the end of the year The MiG 25P 10 testbed launched 20 more test missiles before being sent for its launchers to be upgraded and the first telemetric missile launches from the LL 2 were carried out that year Development continued in 1976 including launches at PRM 2 parachute targets in April Factory tests were completed in 1977 with 32 launches from the MiG 31 prototype the first launch being against a MiG 17 drone on 26 March 1977 The guidance systems were improved during 1978 and the radar missile combination performed a simultaneous launch at 4 targets in August State trials started in March 1979 using MiG 31 No 83210 They were successfully completed in 1980 A government decision on 6 May 1981 recommended R 33 into service Variants Edit 6 R 33 R 33S R 33EMaximum launch range km 120 160 160Maximum flight speed Mach 4 5 4 5Length mm 4250 4150Maximum diameter of the missile body mm 380 380Wingspan mm 900 900Rudders span mm 1180 1180Launch mass kg 491 490Warhead mass kg 55 47Maximum overload of targets hit 8g Maximum speed of the target km h 3700 R 33 Standard type R 33S Improved version R 33E Export version R 37 Further development of the R 33 References Edit AA 9 AMOS UR R 33 Archived from the original on 27 October 2014 MiG 31BM poluchat novuyu raketu Upravlyaemaya raketa bolshoj dalnosti R 33 K 33 Raketnaya tehnika rbase new factoria ru Retrieved 1 December 2016 R 33E Deagel Retrieved 29 January 2015 Upravlyaemaya raketa bolshoj dalnosti R 33 K 33 Raketnaya tehnika rbase new factoria ru Retrieved 1 December 2016 Sources EditGordon Yefim 2004 Soviet Russian Aircraft Weapons Since World War Two Hinckley England Midland Publishing ISBN 1 85780 188 1 External links EditGlobalSecurity org page Federation of American Scientists page Archived 28 August 2016 at the Wayback Machine Retrieved from https en wikipedia org w index php title R 33 missile amp oldid 1129515528, wikipedia, wiki, book, books, library,

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