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{{Infobox Weapon
{{Infobox weapon
|is_missile = yes
|is_missile = yes
|name = R-33<br><small>AA-9 Amos</small>
|name = R-33<br><small>AA-9 Amos</small>
|image = AA-9-Amos.png
|image = [[Image:MiG-31 gear and R-33.jpg|300px|[R-33 on MiG-31 at [[Zhukovsky, Moscow Oblast|Zhukovski]], 1999]]
|caption = R-33 on MiG-31 at Zhukovski, 1999
|caption = R-33
|type = Heavy air-to-air missile
|type = Long range air-to-air missile
|length = {{convert|13|ft|7|in|abbr=on|disp=flip}}
|origin = Soviet Union
|length = {{convert|13|ft|7|in|abbr=on|order=flip}}
|wingspan = {{convert|3|ft|8|in|abbr=on|disp=flip}}
|wingspan = {{convert|3|ft|8|in|abbr=on|order=flip}}
|diameter = {{convert|380|mm|abbr=on}}
|diameter = {{convert|380|mm|abbr=on}}
|weight = {{convert|490|kg|abbr=on}}
|weight = {{convert|490|kg|abbr=on}}
|filling = {{convert|47.5|kg|abbr=on}}
|filling = {{convert|47.5|kg|abbr=on}}
|engine = solid fuel rocket
|guidance = [[inertial guidance system|inertial]] and [[semi-active radar homing]]; terminal [[active radar homing]] (R-33E)<ref>{{cite web |url=http://www.deagel.com/Air-to-Air-Missiles/R-33E_a001031001.aspx |title=R-33E |author=<!--Staff writer(s); no by-line.--> |date= |website=Deagel |publisher= |accessdate=2015-01-29}}</ref>
|guidance = [[inertial guidance system|inertial]] and [[semi-active radar homing]]; terminal [[active radar homing]] (R-33S)<ref>{{cite web |url=http://www.deagel.com/Air-to-Air-Missiles/R-33E_a001031001.aspx |title=R-33E |author=<!--Staff writer(s); no by-line.--> |website=Deagel |access-date=2015-01-29}}</ref>
|speed = [[Mach number|Mach]] 4.5<ref name="FAS">https://fas.org/man/dod-101/sys/missile/row/aa-9.htm</ref>
|speed = [[Mach number|Mach]] 4.5 (R-37)<ref>{{Cite web|url=http://rbase.new-factoria.ru/missile/wobb/r33/r33.shtml|title=Управляемая ракета большой дальности Р-33 (К-33) {{!}} Ракетная техника|publisher=rbase.new-factoria.ru|access-date=2016-12-01}}</ref>
|vehicle_range = 120 km (1981), 160 km (1999),<ref name="FAS"/><ref>http://xn--80akhcovnjb1g.xn--p1ai/russia/vympel/r/33/r33_1.htm</ref> 304 km (2012).<ref>http://dokwar.ru/publ/vooruzhenie/aviacija_i_flot/mig_31bm_poluchat_novuju_raketu/15-1-0-583</ref>
|vehicle_range = {{cvt|120|km|mi|abbr=on}} - 1981<ref name="FAS">{{cite web|url=https://fas.org/man/dod-101/sys/missile/row/aa-9.htm|title=AA-9 AMOS}}</ref><br>{{cvt|160|km|mi|abbr=on}} - 1999<ref>{{cite web|url=http://xn--80akhcovnjb1g.xn--p1ai/russia/vympel/r/33/r33_1.htm|title=УР Р-33|url-status=dead|archive-url=https://web.archive.org/web/20141027092514/http://xn--80akhcovnjb1g.xn--p1ai/russia/vympel/r/33/r33_1.htm|archive-date=27 October 2014|df=dmy-all}}</ref><br>{{cvt|304|km|mi|abbr=on}} - 2012<ref>{{cite web|url=http://dokwar.ru/publ/vooruzhenie/aviacija_i_flot/mig_31bm_poluchat_novuju_raketu/15-1-0-583|title=МиГ-31БМ получат новую ракету}}</ref>
}}
}}
The '''R-33''' ({{lang-ru|Вымпел Р-33}}, [[NATO reporting name]]: '''AA-9 Amos''') is a long-range [[air-to-air missile]] developed by the [[Vympel NPO|Vympel]]. It is the primary armament of the [[Mikoyan MiG-31|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]].


The '''R-33''' ({{lang-ru|Вымпел Р-33}}, [[NATO reporting name]]: '''AA-9 Amos''') is a long-range [[air-to-air missile]] developed by [[Vympel NPO|Vympel]]. It is the primary armament of the [[Mikoyan MiG-31|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]].
Generally similar to the [[U.S. Navy]]'s [[AIM-54 Phoenix]], 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.

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 six missiles to be guided simultaneously at separate targets.


The R-33 AAM remains in service with the [[Commonwealth of Independent States|CIS]] and Russian forces (See [[Mikoyan MiG-31#Operators|MiG-31 operators]]).
The R-33 AAM remains in service with the [[Commonwealth of Independent States|CIS]] and Russian forces (See [[Mikoyan MiG-31#Operators|MiG-31 operators]]).


==Development==
==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 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 Aviation]] [[XB-70 Valkyrie|XB-70]] 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.
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 [[Wing#Artificial wings|underwing]] pylons, similar to the Bisnovat R-40 on board the MiG-25.
Two prototypes were built in 1968, featuring nose-mounted manoeuvring fins and intended for carriage on [[Wing#Artificial wings|underwing]] pylons, similar to the Bisnovat R-40 on board the MiG-25.
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The K-33 was evaluated with the RGS-33 [[semi-active radar homing|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 guidance system|inertial]] initial stage. The homing device, designated MFBU-410 was developed by B.I.Ermakov under the supervision of Akopyan.
The K-33 was evaluated with the RGS-33 [[semi-active radar homing|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 guidance system|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&nbsp;mm to 900&nbsp;mm. Further, the mounting system was revised to include new under-fuselage slipper pylons, akin to the [[AIM-54 Phoenix|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. One dummy, 5 programmed, and 8 trial missiles were built in 1972 for the new design.
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&nbsp;mm to 900&nbsp;mm. Further, the mounting system was revised to include new under-fuselage slipper pylons, akin to the [[AIM-54 Phoenix|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 build 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 ([[Fragmentation (weaponry)|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.
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 ([[Fragmentation (weaponry)|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.
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.
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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.
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.

==R-37==
{{main|AA-13 Arrow}}
A governmental decision of 8 April 1983 authorized the development of '''[[Vympel R-37|K-37]]''' ('''izdeliye 610''', upgraded version of R-33) for the '''MiG-31M'''. The first flight of MiG-31M №0151 was on 21 December 1985. The first launches of K-37 were performed from MiG-31M in 1988. The tests were continued up to 1997.


==Variants==
==Variants==
<ref>{{Cite web|url=http://rbase.new-factoria.ru/missile/wobb/r33/r33.shtml|title=Управляемая ракета большой дальности Р-33 (К-33) {{!}} Ракетная техника|publisher=rbase.new-factoria.ru|access-date=2016-12-01}}</ref>
{| class="wikitable"
!
!R-33
!<strong>R-33S</strong>
!<strong>R-33E</strong>
|-
|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-33:Standard type.
;R-33E:Export version.
;R-33S:Improved version.
;R-33S:Improved version.
;[[AA-13 Arrow|R-37]] Developed version.
;R-33E:Export version.
;[[R-37 (missile)|R-37]]:Further development of the R-33.


==References==
==References==
;Citations
{{Reflist|2}}
{{Reflist|2}}
==Sources==
;Bibliography
{{refbegin}}
{{refbegin}}
* {{cite book|last=Gordon|first=Yefim|title=Soviet/Russian Aircraft Weapons Since World War Two|year=2004|location=Hinckley, England|publisher=Midland Publishing|isbn=1-85780-188-1}}
* {{cite book|last=Gordon|first=Yefim|title=Soviet/Russian Aircraft Weapons Since World War Two|year=2004|location=Hinckley, England|publisher=Midland Publishing|isbn=1-85780-188-1}}
Line 61: Line 116:
== External links ==
== External links ==
* [http://www.globalsecurity.org/military/world/russia/aa-9.htm GlobalSecurity.org page]
* [http://www.globalsecurity.org/military/world/russia/aa-9.htm GlobalSecurity.org page]
* [https://fas.org/man/dod-101/sys/missile/row/aa-9.htm Federation of American Scientists page]
* [https://fas.org/man/dod-101/sys/missile/row/aa-9.htm Federation of American Scientists page] {{Webarchive|url=https://web.archive.org/web/20160828095659/http://fas.org/man/dod-101/sys/missile/row/aa-9.htm |date=28 August 2016 }}


{{Russian and Soviet Aircraft Ordnance}}
{{Russian and Soviet Aircraft Ordnance}}
{{Russian and Soviet missiles|AAM}}
{{Russian and Soviet missiles|AAM}}
{{Russian and Soviet military designation sequences}}
{{Russian and Soviet military designation sequences}}

{{Use dmy dates|date=June 2017}}


{{DEFAULTSORT:R033 (Missile)}}
{{DEFAULTSORT:R033 (Missile)}}
[[Category:Air-to-air missiles of Russia]]
[[Category:Air-to-air missiles of the Soviet Union]]
[[Category:Air-to-air missiles of the Soviet Union]]
[[Category:Cold War air-to-air missiles of the Soviet Union]]
[[Category:Cold War air-to-air missiles of the Soviet Union]]
[[Category:Vympel NPO products]]
[[Category:Military equipment introduced in the 1980s]]

Revision as of 04:39, 13 July 2024

R-33
AA-9 Amos
R-33
TypeLong range air-to-air missile
Place of originSoviet Union
Specifications
Mass490 kg (1,080 lb)
Length4.14 m (13 ft 7 in)
Diameter380 mm (15 in)
Wingspan1.12 m (3 ft 8 in)
Warhead47.5 kg (105 lb)

Enginesolid fuel rocket
Operational
range
120 km (75 mi) - 1981[1]
160 km (99 mi) - 1999[2]
304 km (189 mi) - 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]

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.

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 six 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. ^ "УР Р-33". 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.