☭History, Design & Performance of All Russian Air-to-Air Missiles (IR, SARH, ARH)☭

02ded · November 28, 2024, 8:17am

Property of @Blitzkrieg877, migrated from the old forums

In parallel with Iron_physik’s AIM-9 and AIM-7 threads, I decided to create a unique post of the same concept but on Russian AAMs.

This list includes IR, SARH and ARH, as well as beam-riding missiles. It includes every AAM developed by the USSR with the exception of a few as they have little known history on them such as the K-6V and K-7L.

If you have any suggestions feel free!

Vympel R-3S (NATO codename: “AA-2A Atoll”)

In 1958, yet another strait crises in Taiwan occurred. The US modified more than a hundred F-86F Sabres to be able to carry the new AIM-9B Sidewinder (also known as the GAR-8) and quickly sent them to Taiwan to combat the issue. Chinese MiG-17Fs from the mainland were scrambled to intercept a squad of Sabres, only to find themselves under missile fire. In one of those MiGs, a Sidewinder landed inside the VK-1F engine and the fuse did not detonate. The MiG-17 successfully landed and the missile was taken out of it for research. After some time of negotiating and wrangling with the Chinese, USSR diplomats finally persuaded them to take the missile back to the Union in order to study it. Where it was sent, was to the Vympel OKB, and at the time the head of the company was Gennady Sokolovsky. To quote his words on the GAR-8, “The Sidewinder missile has become a real university to us, offering a course in missile design that has raised our engineering background and updated our approach to creating future rockets.” and the USSR went on to reverse-engineer the weapon and improve upon it. It set the stone for Russian air-to-air missile development. The missile is also known as “K-13A”, “Object 310” and in Russian “P-3”. It entered service in 1962 and went on to serve for a long time and as a training weapon during its last years.

Unknown to many people, this is actually not the first variant of the series. In fact, the R-3 was the first and the reverse-engineered AIM-9B, while the R-3S (P-3C) is a slightly improved variant with higher lock-on range and longer flight time.

Loaded under APU-13 racks and guided by the TGS-13 seeker head.

Performance Vympel R-3S

Length: 2.832 m (111.5 in)
Finspan: 0.56 m (22 in)
Body Diameter: 127 mm (5 in)
Weight: 75.3 kg (166 lb)
Speed: Mach 1.7
Burn time: 2.4s
Flight time: 21s
Propulsion: DWP-80A single stage solid propellant rocket motor (thrust: 3,800 kgf)
Warhead: 11.3 kg (25 lb) HE
Guidance: Infrared-Homing
Seeker:
- FOV: 4°
- Gimbal limit: 28°
- Tracking rate: 10°/s
- Cooling: gas-cooled
Range: 7.5 km max (4.6 mi), 2 km effective (1.2 mi)
G overload (launch limit): 2G
G overload (target): 3G
G overload (Air): 12G
IRCM: No
ECCM: No
Aspect: Rear-Aspect
In service: MiG-19P, MiG-21F-13, MiG-21PF, MiG-21PFM, MiG-21M, MiG-21MF, MiG-21R, MiG-21S, MiG-21SM, MiG-21MT, MiG-21SMT, MiG-21bis, MiG-23S, MiG-23SM, MiG-23P, MiG-23bis, MiG-23B, MiG-23BN, MiG-23M, MiG-23MF, MiG-23ML, MiG-23MLA, Su-17M2, Su-17M3, Su-17M4, Su-20

Vympel R-3R (NATO codename: “AA-2B Atoll”)

(R-3R under the wing of a MiG-21bis)

In 1961, while the AIM-9B was being reverse-engineered, an order for a semi-active radar-homing (SARH) missile was ordered, for high altitude engagements and particularly against bombers as the threat of long-range Western strategic bombers was increasing at the time. The result was the R-3R, also known as “K-13R”, “Object 320” and “P-3P” in Russian. Entered service in 1966, most widely used on the MiG-21bis. Diminished from export models, such as the MiG-21M and MiG-21MF, as Soviet standards for export were simplicity and up-to-date technology was reserved for the USSR.

Performance Vympel R-3R

Length: 3.41 m (134.25 in)
Wingspan: 0.56 m (22 in)
Body Diameter: 127 mm (5 in)
Weight: 83.5 kg (184 lb)
Speed: Mach 1.7
Burn time: 2.4s
Flight time: 21s
Propulsion: DWP-80A single stage solid propellant rocket motor (thrust: 3,800 kgf)
Warhead: 11.3 kg (25 lb) HE
Guidance: Semi-Active Radar-Homing
Range: 8 km max (4.97 mi)
G overload (launch limit): 2G
G overload (target): 3G
G overload (Air): 12G
IRCM: No
ECCM: No
Aspect: All-Aspect
In service: MiG-21S, MiG-21SM, MiG-21SMT, MiG-21bis, MiG-23S, MiG-23SM

Kaliningrad RS-1U (NATO codename: “AA-1 Alkali”)

(A MiG-17PFU loaded with four RS-1U AAMs and two drop tanks in a Soviet-era publicity photo)

On the 18th of July, 1952, by order of the USSR Ministry of Aviation Industry, the Gorky branch of OKB-155 (MiG) was ordered to re-equip three MiG-17PF fighters into SP-6 missile carriers by the end of the summer of that year. In addition to the three Gorky SP-6s, two more aircraft were produced on time by plant # 153 in Novosibirsk. But missile tests began only in 1953. At the beginning of the summer of 1953, ground throw tests of prototypes of missiles “product ShM” - B-89 began. At the same time, static tests of the “CMM product” were completed. By the end of the summer of 1953, the production of prototypes of missiles “product ShM” for autonomous flight tests (without a guidance system) - B-140 was started. A group of Il-28 photographers has been prepared for flight tests. The first successful launch was performed on March 8, 1955. The carrier aircraft is a MiG-17P / SP-6, the target is the Tu-4 target aircraft. The tests also involved an Il-28 photographic aircraft and two MiG-15 fighters to destroy the target aircraft in the event of an unsuccessful missile attack. The target aircraft was hit. By the time the state tests of the system were completed - by the beginning of 1956 - more than 70 launches of the “CMM product” had already been completed.

These aircraft eventually became known as MiG-17PFU jets. The SP-6 derivative of the MiG-17PFU was usually fitted with four RS-1U missiles and one 23mm NR-23 cannon. The beam-riding missiles were operated in conjuction with the Izumrud RP-1U radar and were loaded under APU-3 racks.

In accordance with the December 1954 Decree of the USSR Council of Ministers in 1956, a series of MiG-17PFU / SP-15 (40 copies) interceptors were produced at the aircraft plant No. 21 in Gorky. During 1956, military tests of the RS-1U missiles were carried out on them, and in 1956 the S-1U weapon system was adopted by the air defense aviation. Also in 1956, the missile was adopted by the Yak-25K interceptor aircraft with a suspension of 2 missiles under the wing between the fuselage and the engine. Only one aviation unit was equipped with Yak-25K aircraft.

Serial production of RS-1U missiles was fully realized in 1956 at Plant No. 455 in Kaliningrad (Moscow region). Later, the RS-1U missiles were mass-produced at five factories of the USSR Ministry of Aviation Industry.

The missiles were capable of hitting targets traveling at up to 1,600 km/h, flying at up to 10,000 meters and could pull up to 9G in the air.

Performance RS-1U

Length: 2.35 m (92.75 in)
Wingspan: 0.549 m (21.61 in)
Body Diameter: 200 mm (5 in)
Weight: 74.25 kg (163.69 lb)
Speed: Mach 2.35
Burn time: ?
Flight time: 12s
Propulsion: U-19U / PRD-45 liquid-fuel rocket motor (thrust: ?)
Warhead: 11.35 kg (25 lb) HE
Guidance: Beam-Riding
Cooling: ?
Range: 2 - 3 km (1.24 - 1.86 mi)
G overload (launch limit): 2G
G overload (target): 2G
G overload (Air): 9G
IRCM: No
ECCM: No
Aspect: All-Aspect
In service: MiG-17PFU, MiG-19 (SM-17A), Yak-25K

Kaliningrad RS-2U / RS-2US (NATO codename: “AA-1 Alkali”)

Based on the previous RS-1U. Even though in the second half of the fifties it became clear that the system the RS-2U missile used was becoming obsolete, a basis formed on modifying it for use on interceptor-only aircraft. These weapons were meant to be used exclusively against bombers, using beam-riding guidance to steer the missile to its large, unmaneuverable target. This weapon became the basis of the Sukhoi Su-9’s offensive capability that matched its TsD-30 / RP-9 search and tracking radar. The first generation RS-2US was extremely sensitive to the illuminating beam-ride shape and the launch platform. It was also used on the short-lived MiG-17PFU, and the MiG-19PM which was a Farmer modified for the use of those weapons with the RP-5U radar. Entered service in 1961 first. These became the missiles to first arm a production aircraft in Europe, first on the MiG-17. In 1967, the RS-2US’ beam-riding head was replaced with the SARH compartment of the R-3R, in order to achieve compatibility with radars such as the RP-22SM on the MiG-21bis. This missile was designated R-55. It likely had an increase in maneuverability, but only slightly, and information on this is not conclusive.

The RS-2US can be differentiated from the RS-2U in having a revised fuse which had a longer body with better heat resistance and shorter time delay, as well as new tracers which could burn at higher altitudes.

On MiG-21 interceptors, APU-7 launchers were used in conjunction, while the Su-9 utilized the APU-19 and APU-20 for the outboard and inboard racks respectively (later replaced with the modernized APU-19D and APU-20D).

Its service lasted until the late 70s to the early 80s, when the MiG-23P began replacing the MiG-19PM, Su-9 and Su-11 interceptor fleet.

Most widely used on the MiG-19PM under APU-4 racks, four each. It had a hit probability of 0.7 - 0.8 at high altitudes (10 - 12 km), and its service ceiling was 20,300 meters. Furthermore, it was capable of pulling 18G in the air, and the recommended flight speed of the engaged target was 1,600 km/h max, as the missile could only reach 1,650 km/h.

(RS-2US missiles under the wing of an Su-9

Performance RS-2U / RS-2US

Length: 2.5 m (98.4 in)
Wingspan: 0.650 m (25.59 in) (RS-2U), 0.654 m (25.75 in) (RS-2US)
Body Diameter: 200 mm (5 in)
Weight: 82.7 kg (182.3lb) (RS-2U), 83.23 kg (183.49 lb) (RS-2US)
Speed: Mach 2.35
Burn time: 3.5 - 7s
Flight time: 13 - 21s (controlled flight: 12s)
Propulsion: U-19U liquid-fuel rocket motor / PRD-45 (thrust: ?)
Warhead: 13 kg (28.6 lb) HE (RS-2U), 15.8 kg (34.8 lb) HE (RS-2US)
Guidance: Beam-Riding (RS-2U / RS-2US)
Cooling: nitrogen-cooled (retrofit)
Range: 1.95 - 5.2 km max (1.21 - 3.2 mi) (RS-2U), 1.8 - 6.9 km (1.1 - 4.3 mi) (RS-2US), effective 2 - 5 km (1.24 - 3.1 mi)
G overload (launch limit): 2G
G overload (target): 2G
G overload (Air): 18G
IRCM: No
ECCM: No
Aspect: All-Aspect
In service (RS-2U): Su-9, MiG-17PFU, MiG-19PM, MiG-21PF, MiG-21PFM, MiG-21S, MiG-21SM, MiG-21SMT, MiG-21bis
In service (RS-2US): Su-9, MiG-17PFU, MiG-19PM, MiG-21PF, MiG-21PFM, MiG-21S, MiG-21SM, MiG-21SMT, MiG-21bis
In service (R-55): MiG-21bis

Kaliningrad R-55 / R-55M (NATO codename: “AA-1 Akali”)

The RS-2US was becoming a very old missile using outdated guidance techniques. On the other hand, the R-3S missile proved to be inadequate as more advanced Sidewinder missiles such as the AIM-9D and AIM-9E began appearing over Vietnam in the mid 60s. Specifically, in 1966, the Soviets managed to acquire a couple of AIM-9D missiles from aircraft wreckages and immediately began working on an improved K-13 missile based on the AIM-9D. However, it seemed like the new Object 380 missile under development (what would later become the R-13M) wasn’t going to enter production until a few years later. Using experience learned from the more advanced Sidewinders, Soviet engineers took to the decision to fill the void with a missile better than the R-3S using existing examples.

To this end, the RS-2US missile was used as the basis of the new “Object (izdeliye / product) 67” missile. A new infrared-homing seeker, designated TGS-59 was installed, along with a new Zarya optical fuse. The new missile had a new wing and rudders with an increased area and more powerful steering drives. Compared to its older brother, it retained only the PRD-45 engine. To maintain the alignment of the rocket, the volumes of the tail compartment freed from the equipment were occupied by an additional high-explosive fragmentation warhead.

In tests, the new AAM proved effective against targets maneuvering at 3G. It also retained the maximum 18G overload of its predecessor. In addition, due to the lower load on the missile’s “wings”, it significantly surpassed the R-3S in maneuverability and had a longer range. The missile was designated R-55, and was put into production in the year 1967, then put into service in 1969. Production last until 1976 at Kaliningrad’s plant. A MiG-21PFM numbered “3532” and a MiG-21bis “24” tested it.

It served as the main offensive platform of the Su-9 (late config), Su-11 and the early Su-24. As a matter of fact, it was the forefront of the MiG-21bis’ missile selection until the arrival of the Vympel R-60 in December 1973.

In 1971, there was a proposed upgrade to the R-55 called the R-55M. It introduced a new S-59M seeker with better/higher lock range. However since the R-13M1 and R-60 were close to entering production, there was little use seen in mass-producing it.

Performance R-55

Length: 2 m (78.7 in)
Wingspan: 3.1 m (122 in)
Body Diameter: 200 mm (7.87 in)
Weight: 92 kg (203 lb)
Speed: Mach 1.6
Burn time: 4.5 - 7s
Flight time: 30s
Propulsion: PRD-45 single stage solid rocket propellant motor (thrust: ?)
Warhead: 9.1 kg (20 lb)
Guidance: Infrared-Homing
Seeker:
- FOV: 2.5°
- Gimbal limit: 40°
- Tracking rate: 12°/s
- Cooling: nitrogen-cooled
Range: 10 km max (6.2 mi)
G overload (launch limit): 3G
G overload (target): 3G
G overload (Air): 18G
IRCM: No
ECCM: No
Aspect: Rear-Aspect
In service: MiG-21PFM, MiG-21bis, Su-9, Su-11, Su-24 sans suffix

Lavochkin izdeliye 275

During the inception of the Lavochkin La-250 “Anakonda” , it was decided to equip the upcoming interceptor with air-to-air missiles only. Much like every other interceptor designed in the mid and late 50s, the main idea was to intercept the threat of high-flying western aircraft, particularly US strategic bombers. Seeing as this was during Nikita Khrushchev’s era, which saw the missilization of the Soviet Union, interceptor aircraft designed during that time were envisioned to be strict missile carriers.

As such, the La-250 was to be armed with two AAMs. These AAMs did not receive an official service designation as the La-250 prototype failed, so they are still known by their in-house designation of “izdeliye 275” (product 275). Much like the previous RS-1U/RS-2U/S series of AAMs, they were beam-riding; utilizing the aircraft’s radar to point a beam at the targeted enemy. A primitive guidance system such as this one was mainly intended to be used against large, lumbering aircraft with little to no maneuvering capabilities, as it was not fast and efficient enough at updating the flight coordinates of a tightly maneuvering target. It was armed with a 125 kg warhead, guaranteed to be lethal within a radius of 50 m (161 ft).

The izdeliye 275 AAMs formed a part of the K-15 aerial intercept system which also included the K-15U radar. They were to be carried in a semi-recessed position under the fuselage, in the same fashion as the R-33 missiles of the MiG-31.

However, problems with the La-250 such as the unavailability of the intended engines led to an extensive redesign to incorporate new powerplants, which directly affected the izdeliye 275. The changes took some time to finish, therefore the missiles were not tested but made way to the later izdeliye 275A AAMs on the La-250A.

Performance izdeliye 275

Length: 6.6 m (259.8 in)
Wingspan: 1.7 m (67 in)
Body Diameter: 450 mm (17.71 in)
Weight: 870 kg (1918 lb)
Speed: Mach 3.7
Burn time: 23s
Flight time: ?
Propulsion: Single stage liquid-propelled rocket motor (unknown type, thrust: 2,830 kgf)
Warhead: 125 kg (275.5 lb) HE
Guidance: Beam-Riding
Range: 20 km max (12.4 mi)
G overload (launch limit): 2G
G overload (target): 2G
G overload (Air): 3G
IRCM: No
ECCM: No
Aspect: All-Aspect (20 km)
In service: Lavochkin La-250

Lavochkin izdeliye 275A

When the Klimov VK-9- powered La-250 failed, it was decided to equip the plane with Lyulka AL-7Fs instead, the powerplants used by the Su-7, Su-9 and Su-11. The changes resulted in a smaller aircraft design, and necessitated the need for a scaled-down version of the intended AAMs.

The new La-250A variant was equipped with the new izdeliye 275A air-to-air missiles, working in conjunction with the updated K-15M radar. The new radar had a maximum detection range of 30 - 40 km in the rear and frontal hemisphere as well as being able to track bomber-sized targets from 20 km at high altitude. This potentially allowed the La-250A to get into a good firing position and then wait until the target is within the izdeliye 275A’s launch envelope. Another update due to the necessary changes applied to the La-250 was the change from semi-recessed under-fuselage pylons to wing pylons.

The scaled-down izdeliye 275A was powered by a liquid-propellant rocket motor designed by Aleksei Isayev with up to 2,830 kgf of thrust at 14,000 m.

A total of nine launches were made, however in ballistic mode from ground launchers. It was actually never tested against aerial targets, so in every photograph of the Anakonda, the missiles seen are dummies. The total (experimental) production count is 106 izdeliye 275A missiles, produced by MMZ Kuiybishev. Ten of those were converted to “izdeliye 278” missiles; the same as the izdeliye 275As, but with solid propulsion instead of liquid.

Another project based on the izdeliye 275A was the izdeliye 279 air-to-air missile. In order to increase lethality, it was decided to test the izdeliye 275A with a nuclear warhead. This idea never passed the drawing board as the designers were getting ahead of themselves. Had the La-250 become a successful production aircraft, the izdeliye 279 AAM concept may have been realized.

Performance izdeliye 275A

Length: 6.6 m (259.8 in)
Wingspan: 1.7 m (67 in)
Body Diameter: 450 mm (17.71 in)
Weight: 600 kg (1323 lb)
Speed: Mach 3.4
Burn time: 23s
Flight time: ?
Propulsion: Single stage liquid-propelled rocket motor (solid-propellant rocket motor for the izdeliye 278) (unknown type, thrust: 2,830 kgf)
Warhead: 140 kg (309 lb) HE
Guidance: Beam-Riding
Range: 27 km max (16.7 mi)
G overload (launch limit): 2G
G overload (target): 2G
G overload (Air): 3G
IRCM: No
ECCM: No
Aspect: All-Aspect (27 km)
In service: Lavochkin La-250A

Lavochkin izdeliye 277

A project aimed at providing the izdeliye 275A with a more reliable seeker head. The new missile was designated “izdeliye 277”. This new seeker head was actually semi-active radar-homing, which is a feat considering the year of design (1958). It was built, bench-tested and ready to be fired aerially from the La-250.

However, the K-15M radar’s production was inefficient, which meant that it would be consistently unavailable most of the time, thus the Sokol-2 radar replaced it. The problem was, the new radar (speaking of which, it was used by the La-200B) had target tracking and detection capabilities lower than that of the izdeliye 277’s seeker target acquisition range. This necessitated the development of a derivative with a seeker range lower than that of the Sokol-2’s target tracking and detection ranges, which would end up with an active radar-homing seeker.

After the cancelation, work commenced the izdeliye 280, which is the ARH derivative.

Performance izdeliye 277

Length: 6.6 m (259.8 in)
Wingspan: 1.7 m (67 in)
Body Diameter: 450 mm (17.71 in)
Weight: 600 kg (1323 lb)
Speed: Mach 3.4
Burn time: 23s
Flight time: ?
Propulsion: Single stage liquid-propelled rocket motor (unknown type, thrust: 2,830 kgf)
Warhead: 140 kg (309 lb) HE
Guidance: Semi-Active Radar-Homing
Range: ?
G overload (launch limit): ?
G overload (target): ?
G overload (Air): ?
IRCM: No
ECCM: No
Aspect: All-Aspect (Range: ?)
In service: Lavochkin La-250A

Lavochkin izdeliye 280

When the Sokol-2 radar replaced the K-15M on the La-250A, it created a problem. It was indeed much more available and easier to produce, however it was less capable than the izdeliye 277’s seeker. To this end, a derivative with a seeker weaker than the Sokol-2’s capabilities was designed, and an active radar-homing seeker head was chosen. Other than that, its fate remains unknown.

Performance izdeliye 280

Length: 6.6 m (259.8 in)
Wingspan: 1.7 m (67 in)
Body Diameter: 450 mm (17.71 in)
Weight: 600 kg (1323 lb)
Speed: Mach 3.4
Burn time: 23s
Flight time: ?
Propulsion: Single stage liquid-propelled rocket motor (unknown type, thrust: 2,830 kgf)
Warhead: 140 kg (309 lb) HE
Guidance: Active Radar-Homing
Range: ?
G overload (launch limit): ?
G overload (target): ?
G overload (Air): ?
IRCM: No
ECCM: No
Aspect: All-Aspect (Range: ?)
In service: Lavochkin La-250A

Bisnovat / Molniya / Vympel R-4T / R-4R (NATO codename: “AA-5 Ash”)

In the late 1950s, the threat of US heavy strategic, nuclear-armed bombers was started to boom. At the time, the USSR’s air force inventory had capable interceptors, however they lacked the range to intercept the theoretic approach of bombers such as the B-47, B-52, etc in time. In response to the government order to design a high-altitude interceptor capable of reaching longer ranges, the Tupolev Tu-128 interceptor was developed. It was a huge aircraft, essentially a bomber airframe fitted with avionics and weapons for interception. The aircraft was larger than a B-17. The weapon systems that were installed for the Tu-128 were the Bisnovat (later Molniya then Vympel) R-4 air-to-air missiles; the R-4T infrared-homing model, and the first-designed R-4R semi-active radar-homing version. They were successful enough to ensure a kill on any bomber they are targeted on, however they were lacking against fighters. They were very heavy missiles, both in terms of weight and warhead weight, which in turn gave them slow flight speed in the air. Introduced in 1961. Interestingly, they were first designated R-80T and R-80R. The absolute maximum kill range was 25 km, and the seeker’s acquisition range for the R-4R capped at 30 km.

For a long time, the R-4s were one of the main interception weapons of the PVO against high-flying US aircraft. With the advent of the SR-71, that job was gradually being replaced in position by the R-40, and then the R-33 with the introduction of the B-1 Lancer in the late 70s. In the late 60s, they were modernized (see below) and they remained in service till 1990.

(Tu-128 loaded with 2 x R-4R + 2 x R-4T)

Performance R-4R

Length: 5.45 m (214.56 in)
Wingspan: 3.1 m (122 in)
Body Diameter: 310 mm (12.2 in)
Weight: 493 kg (1087 lb)
Speed: Mach 1.6
Burn time: 4.5 - 7s
Flight time: ?
Propulsion: PRD-84 single-stage solid rocket propellant motor (thrust: 24,500 kgf)
Warhead: 54 kg (119 lb) HE
Guidance: Semi-Active Radar-Homing
Range: 25 km max (15.5 mi)
G overload (launch limit): 2G
G overload (target): 4G
G overload (Air): 4G
IRCM: No
ECCM: No
Aspect: All-Aspect (30 km)
In service: Tu-128

Performance R-4T

Length: 5.2 m (214.56 in)
Wingspan: 3.1 m (122 in)
Body Diameter: 310 mm (12.2 in)
Weight: 480 kg (1058 lb)
Speed: Mach 1.6
Burn time: 4.5 - 7s
Flight time: ?
Propulsion: PRD-84 single-stage solid rocket propellant motor (thrust: 24,500 kgf)
Warhead: 54 kg (119 lb) HE
Guidance: Infrared-Homing
Seeker:
- FOV: 2.5°
- Gimbal limit: 20°
- Tracking rate: 8°/s
- Cooling: gas-cooled
Range: 15 km max (9.3 mi)
G overload (launch limit): 2G
G overload (target): 2G
G overload (Air): 4G
IRCM: No
ECCM: No
Aspect: Rear-Aspect
In service: Tu-128

Bisnovat / Molniya / Vympel R-4MT / R-4MR (NATO codename: “AA-5 Ash”)

In the late 60s, the R-4T and R-4R were modernized. As usual, the “M” suffix referred to “modifitserovani” (or Russian for “modified” or “improved”). Their maximum G overload in the air was increased from 4G to 5G. The new seeker for the R-4MR provided all-aspect engagement even in ground clutter and dense ECM environments (the seeker type is unknown, but with this information available and given their introduction date, a good guess would be an inverse-monopulse seeker). On the other hand, the R-4MT IR-homing model received a new combined radar/optical proximity fuse which also provided high ECM resistance. The decision to use that proximity fuse came as a result of positive experience gained from the R-40.

The new missiles also feature rudders with reduced area, due to the shorter root chord and reduced leading edge sweep.

With Soviet intelligence spotting the program of the B-1 Lancer in 1977, they quickly went on to develop the R-33 missiles for the MiG-31. With their introduction, the Tu-128 and the R-4MR/T missiles gained less and less popularity until their retirement in 1990.

(The upgraded R-4MR and R-4MT)

Performance R-4MR

Length: 5.45 m (214.56 in)
Wingspan: 3.1 m (122 in)
Body Diameter: 310 mm (12.2 in)
Weight: 493 kg (1087 lb)
Speed: Mach 1.6
Burn time: 4.5 - 7s
Flight time: ?
Propulsion: PRD-84 single-stage solid rocket propellant motor (thrust: 24,500 kgf)
Warhead: 54 kg (119 lb) HE
Guidance: Semi-Active Radar-Homing
Range: 25 km max (15.5 mi)
G overload (launch limit): 2G
G overload (target): 2G
G overload (Air): 5G
IRCM: No
ECCM: Limited
Aspect: All-Aspect
In service: Tu-128

Performance R-4MT

Length: 5.2 m (214.56 in)
Wingspan: 3.1 m (122 in)
Body Diameter: 310 mm (12.2 in)
Weight: 480 kg (1058 lb)
Speed: Mach 1.6
Burn time: 4.5 - 7s
Flight time: ?
Propulsion: PRD-84 single-stage solid rocket propellant motor (thrust: 24,500 kgf)
Warhead: 54 kg (119 lb) HE
Guidance: Infrared-Homing
Seeker:
- FOV: 2.5°
- Gimbal limit: 20°
- Tracking rate: 8°/s
- Cooling: gas-cooled
Range: 15 km max (9.3 mi)
G overload (launch limit): 2G
G overload (target): 2G
G overload (Air): 5G
IRCM: No
ECCM: Limited
Aspect: Rear-Aspect
In service: Tu-128

Kaliningrad R-8 / R-8MR / R-8MT / R-8MR1 / R-8MT1 (NATO codename: “AA-3A Anabi” / “AA-3B Anabi”)

Known previously as the R-8, the R-8MR and R-8MT are a development of the former from the 1950s. The “M” refers to “modifitseerovannaya” (modified), as they were modified for use by the Oryol (radar)-equipped aircraft. They were virtually the same as the previous R-8, sharing the exact same aerodynamical layout. They entered service in 1961, and were mostly used by the Sukhoi Su-11 interceptor. Both were under the project designation of “Object 24M”. The R-8MR was a semi-active radar-homing air-to-air missile, while the latter was a heat-seeker. The R-8 in general was first adopted in 1957 when it was first tested using a Yak-27K, then in 1962 it was made co mpatible with the Su-11. The configuration of these missiles is usually one SARH variant and one IR variant simultaneously.

On the other hand, the R-8MR1 and R-8MT1 are slightly more improved missiles of their respective versions. They saw an increased operational altitude envelope, to 300 m - 23,000 m and it is thanks to the improved autopilot and newer seeker heads; especially the R-8MT1, the new IR seeker head gave it round-the-clock capability. Changes have also been amde to the missiles’ airframes, featuring reinforced wings enabling them to turn tighter at low altitudes.

Developed exclusively to combat high-flying aircraft such as the B-52 Stratojet and the U-2 spyplane. The R-8MR was guided by the PARG-14 SARH seeker head, while the R-8MT had the TGS-14.

(The 10th production Su-11 carrying a pair of R-8MTs)

Performance R-8MR

Length: 4.18 m (164.56 in)
Wingspan: 1.22 m (48 in)
Body Diameter: 275 mm (12.2 in)
Weight: 285 kg (628 lb)
Speed: Mach 2
Burn time: 2.5 - 6s
Flight time: 40 - 60s
Propulsion: PRD-141 single-stage solid rocket propellant motor (thrust: 11,200 kgf)
Warhead: 40 kg (88 lb) HE
Guidance: Semi-Active Radar-Homing
Range: 20 km max (12.4 mi) (seeker lock range)
G overload (launch limit): 3G
G overload (target): 3G
G overload (Air): 14G
IRCM: No
ECCM: No
Aspect: All-Aspect
In service: Yak-28P, Yak-28PM, Su-11, all Su-15 models

Performance R-8MT

Length: 4.05 m (159 in)
Wingspan: 1.22 m (48 in)
Body Diameter: 275 mm (12.2 in)
Weight: 265 kg (584 lb)
Speed: Mach 2
Burn time: 2.5 - 6s
Flight time: 40 - 60s
Propulsion: PRD-141 single-stage solid rocket propellant motor (thrust: 11,200 kgf)
Warhead: 40 kg (88 lb) HE
Guidance: Infrared-Homing
Seeker:
- FOV: 2.5°
- Gimbal limit: 20°
- Tracking rate: 10°/s
- Cooling: liquid nitrogen-cooled
Range: 20 km max (12.4 mi)
G overload (launch limit): 3G
G overload (target): 3G
G overload (Air): 14G
IRCM: No
ECCM: No
Aspect: Rear-Aspect
In service: Yak-28P, Yak-28PM, Su-11, all Su-15 models

Kaliningrad R-98R / R-98T / R-98MR / R-98MT (NATO codename: “Advanced Anaab”)

In 1963, based on the older R-8, new models of each the IR and SARH deriatives were conceived. The objective was to improve on their reliability and nose immunity to countermeasures, as well as increasing their power supply. The changes that ocurred were promising; the IR version became all-aspect, featuring the new TGS-14T seeker-head, while the SARH version received the more reliable PARG-14-VV. The autopilot and fuse were also improved, and the rear-fairing was reshaped to become perfectly cylindrical instead of the tapered design. The new missiles were designated R-98R and R-98T.

As the Su-15 interceptor evolved, so did the R-98. A new PARG-16 semi-active radar-homing seeker head was installed in the R-98R which improved its reliability. Other than that however, not much changed. The new missiles were designated R-98MR and R-98MT (SARH and IR respectively). The main changes were to make the previous R-98s compatible with the Taifoon-M radar of the Su-15TM.

The R-98MR was capable of engaging targets from 2,000 - 21,000 m in head-on mode, and from 500 m - 24,000 m in pursuit mode, and its maximum kill range was 24 km in head-on and 16 km in pursuit.

These missiles were usually loaded under PU-2-8 racks.

(Su-15 with an R-98MR and R-98MT)

Performance R-98MR

Length: 4.18 m (164.56 in)
Wingspan: 1.22 m (48 in)
Body Diameter: 275 mm (12.2 in)
Weight: 285 kg (628 lb)
Speed: Mach 2
Burn time: 2.5 - 6s
Flight time: 40 - 60s
Propulsion: PRD-143 single-stage solid rocket propellant motor (thrust: 13,400 kgf)
Warhead: 40 kg (88 lb) HE
Guidance: Semi-Active Radar-Homing
Range: 24 km max (15 mi)
G overload (launch limit): 3G
G overload (target): 3G
G overload (Air): 14G
IRCM: No
ECCM: No
Aspect: All-Aspect
In service: Su-15TM

Performance R-98MT

Length: 4.05 m (159 in)
Wingspan: 1.22 m (48 in)
Body Diameter: 275 mm (12.2 in)
Weight: 265 kg (584 lb)
Speed: Mach 2
Burn time: 2.5 - 6s
Flight time: 40 - 60s
Propulsion: PRD-143 single-stage solid rocket propellant motor (thrust: 13,400 kgf)
Warhead: 40 kg (88 lb) HE
Guidance: Infrared-Homing
Seeker:
- FOV: 2.5°
- Gimbal limit: 20°
- Tracking rate: 10°/s
- Cooling: liquid nitrogen-cooled
Range: 20 km max (12.4 mi)
G overload (launch limit): 3G
G overload (target): 3G
G overload (Air): 14G
IRCM: No
ECCM: No
Aspect: All-Aspect
In service: Su-15TM

Raduga R-38 (AKA: K-9 / K-9-155) (NATO codename: “AA-4 Awl”)

During the development of the Mikoyan-Gurevich MiG Ye-152A, a high-speed, deadly missile was required in order to fulfill the aircraft’s pure interception role, considering it was an aircraft intended to climb to high altitudes and intercept quick NATO aircraft using immense speed from itself and from its intended missiles. A Russian aerospace company by the name of Raduga responded with the creation of the K-9 missile, which would have also been known as the R-38 in service. It used a semi-active radar-homing guidance mode using a pulse-action TsR-1 seeker guided by the TsP-1 radar’s beam, in addition to an APC-18 autopilot, a pulse radio fuse TsRV-1, high-explosive fragmentation warheads, an I-60 safety mechanism, and a PRD-56 single-chamber dual-mode powder engine. The thrust of its engine was 5,500 kgf at launch which was switched to 2,500 - 3,000 kgf during cruise mode, and the engine itself weighed 103 kg. In total, the missile weighed at 245 kg: 103 kg counted for the engine, 27 kg for the warhead, 15 kg for the seeker and the rest towards the airframe.

A total of 26 K-9 / K-155 / R-38 missiles were manufactured in 1961, before being canceled. It was tested in three “versions”; to conduct flight tests, the K-9 rocket was developed in the following versions:

Battle version (Vol. 90) - what was going to enter production
Ballistic (Vol. 91) - is designed to determine the aerodynamic and ballistic characteristics of a rocket when flying with fixed wings, to check the safety of separation from the carrier, and also to check engine performance
Software (Vol. 92) - designed to determine the aerodynamic and ballistic characteristics of a rocket in a program-controlled flight, as well as to test the autopilot, power unit and pneumatic system in flight conditions
Telemetry (Vol. 93) - designed to assess the fulfillment of requirements for a rocket in a closed system (carrier-rocket-target) with a GOS and a radio fuse, without undermining the warhead of the rocket when it flies near the target

A version designated K-9M with a new seeker head modified to work with derivatives of the Smerch radar was developed, but it faired no better than the K-9.

Performance R-38

Length: 4.3 m (14.1 in)
Wingspan: 1.6 m (63 in)
Body Diameter: 250 mm (9.8 in)
Weight: 245 kg (540 lb)
Speed: Mach 4
Burn time: ?
Flight time: ?
Propulsion: PRD-56 single-chamber dual-mode powder rocket motor (thrust: 5,500 kgf intial impulse mode, 2,500 - 3,000 kgf in cruise mode)
Warhead: 27 kg (59.5 lb) HE fragmentation
Guidance: Semi-Active Radar-Homing
Range: 9 km max (5.59 mi)
G overload (launch limit): 3G
G overload (target): 3G
G overload (Air): 10G (?)
IRCM: No
ECCM: No
Aspect: All-Aspect
In service: Ye-150, Ye-152A, Ye-152M

Vympel R-13M (NATO codename: “AA-2C Atoll”)

In 1974, a new missile based on the older R-3S was developed and introduced under the project name of “Object 380”. Previously during the start of the Vietnam War, the USSR had managed to obtain AIM-9D examples from U.S aircraft wreckages between October 1965 and 1967. The missile received the K-13M designation and its development officially commenced on the 28th of November, 1967. It had a better and new proximity fuse, a propellant for longer ranges, better maneuverability, sharper, wider lock angles and a more sensitive nitrogen-cooled seeker homing head. It’s a heavy development of the previous R-3S, and the end result was a heat-seeker that although was maneuverable, it wasn’t quite the dogfight-type of missile, but its range was significant for an IR guided weapon, higher than that of the radar-homing R-3R. It is considered the Russian equivalent to the AIM-9D to a certain extent, and more accurately the equivalent of the AIM-9G.

After its introduction, the R-13M was immediately retrofitted to many existing MiG-21 and MiG-23 models. The first and earliest aircraft to have received this missile was the MiG-21PFM, followed by the MiG-21SM, MiG-21SMT, MiG-23M and so on. It was usually loaded under APU-13MT racks, either in a pair or two. On the MiG-23, it was possible to load two of them in the fuselage section and install R-23R/T missiles under the wing racks.

The first stage of tests for the R-13M commenced in 1969, while the second stage started in 1972 and concluded the 8th of January, 1973. The missile was adopted for service the next year. The first stage of tests had up to 36 launches, with the aircraft being used for testing as follows: one MiG-21S, two MiG-21SMTs and three MiG-23s. In some cases, Tu-16s on runways with their engines turned on were used as target dummies.

The R-13M enjoyed an official production from lasting from 1971 till 1988. It didn’t see much service within the USSR; the MiG-23M and MiG-23BM/MiG-27 sans suffix were its largest users. Outside of the USSR however, it was the main export weapon to Warsaw Pact nations receiving MiG-21 and MiG-23 aircraft until 1981 when the Soviets officially began exporting the R-60 AAM, which was declared operational years prior on the 18th of December, 1973.

Performance R-13M

Length: 2.875 m (113.18 in)
Wingspan: 0.528 m (22 in)
Body Diameter: 127 mm (5 in)
Weight: 87.7 kg (193.3 lb)
Speed: Mach 2.5
Burn time: 3.3 - 5.4s
Flight time: 55s
Propulsion: DWP-240 single stage solid propellant rocket motor (thrust: 6,000 kgf)
Warhead: 11.3 kg (25 lb) HE
Guidance: Infrared-Homing
Seeker:
- FOV: 2.8°
- Gimbal limit: 40°
- Tracking rate: 12°/s
- Cooling: nitrogen-cooled
Range: 15 km max (9.3 mi), 3 km effective (1.86 mi)
G overload (launch limit): 3.7G
G overload (target): 5G
G overload (Air): 15G
IRCM: No
ECCM: No
Aspect: Rear-Aspect
In service: MiG-21M, MiG-21MF, MiG-21R, MiG-21S, MiG-21SM, MiG-21MT, MiG-21SMT, MiG-21bis, MiG-23S, MiG-23SM, MiG-23P, MiG-23bis, MiG-23B, MiG-23BN, MiG-23M, MiG-23MF, MiG-23ML, MiG-23MLA

Vympel R-13MK (NATO codename: “AA-2C Atoll”?)

Development of the new R-13M missile, first under the internal designation of “Object 380” (or “Product 380”/“izdeliye 380”) commenced shortly after acquiring AIM-9D Sidewinders from aircraft wreckages over Vietnam in 1966. November 1967 marked the beginning of a new series of Soviet missiles with uncaged seekers, wider FOVs and increased maneuverability. The R-13M would go onto the testings stage first in 1969, then the second stage in 1972, to being introduced in 1974.

In 1968, a year after the development of the R-13M began, a decree by the party and government was issued to develop a missile based on the one in development with a thermal radar seeker; a seeker which combined both infrared-homing and semi-active radar guidance. Unsurprisingly, creating such a seeker for a light missile was complicated. The components of the PARG-50VV thermal radar seeker and missile would not be constructed until 1972, but the combined seeker would not be realized until 1974.

Only in 1975, the missile was fully completed and received the designation R-13MK. A total of nine launches were made, some at parachute targets and others at aircraft. The MiG-21S was its carrier, and seemingly the variant the R-13MK was specifically designed for.

Performance R-13MK

Length: ?
Wingspan: ?
Body Diameter: ?
Weight: ?
Speed: Mach 2.5
Burn time: 3.3 - 5.4s
Flight time: 55s
Propulsion: DWP-240 single stage solid propellant rocket motor (thrust: 6,000 kgf)
Warhead: 11.3 kg (25 lb) HE
Guidance: Thermal Radar-Homing
Seeker:
- FOV: 2.8° (?)
- Gimbal limit: 40° (?)
- Tracking rate: 12°/s (?)
- Cooling: nitrogen-cooled (?)
Range: 15 km max (9.3 mi), 3 km effective (1.86 mi)
G overload (launch limit): 3.7G (?)
G overload (target): 5G (?)
G overload (Air): 15G (?)
IRCM: No
ECCM: No
Aspect: All-Aspect
In service: MiG-21S

Vympel R-13M1 (NATO codename: “AA-2D Atoll”)

Two years after the introduction of the base R-13M, a new variant was designed on the goal of increasing the maneuverability of the missile and study missile development in general. Under the project designation of “Object 380M”, the newly derived R-13M1 missile from the R-13M had the new “INEY-M” seeker head with 40* of view instead of 28* as on the R-13M’s INEY-70 and new canards for increased maneuverability, which were similar to those of the AIM-9P and AIM-9J. The USSR had captured some examples of the AIM-9J/P and AIM-9H from the Vietnam War, which inspired the canard design, specifically some AIM-9Js were stolen from a South Korean base in the 1970s. The missile went into three years of testing, from 1973 till 1976 and entered service in that year, however its use was limited due to more promising missiles being under development at that time. It was not used outside of the USSR at all, and its main users were the MiG-21bis (it’s possible that the earlier MiG-21SM/SMT used it but that’s not confirmed), later MiG-23 models (MiG-23M, MiG-23ML, MiG-23MLA) and some ground-attack versions of the MiG-23.

The new seeker and canards offered a great deal of performance improvement over the R-13M. Its predecessor’s launch limit was only 3.7G, meaning if its carrier was pulling more than 3.7G it was off limits, and it could only be fired at targets pulling 5G; while the R-13M1 improved on those with 6G and 7G respectively. The R-13M1 enjoyed a production run of four years, from 1977 till 1981, and remained in service till 1988.

This is the Russian equivalent of the AIM-9H.

Performance R-13M1

Length: 2.876 m (113.3 in)
Wingspan: 0.528 m (22 in)
Body Diameter: 127 mm (5 in)
Weight: 90.6 kg (199.74 lb)
Speed: Mach 2.5
Burn time: 3.3 - 5.4s
Flight time: 55s
Propulsion: DWP-240 single stage solid propellant rocket motor (thrust: 6,000 kgf)
Warhead: 11.3 kg (25 lb) HE
Guidance: Infrared-Homing
Seeker:
- FOV: 4.0°
- Gimbal limit: 40°
- Tracking rate: 18°/s
- Cooling: nitrogen-cooled
Range: 15 km max (9.3 mi), 3 km effective (1.86 mi)
G overload (launch limit): 6G
G overload (target): 7G
G overload (Air): 21G
IRCM: No
ECCM: No
Aspect: Rear-Aspect
In service: MiG-21SM (?), MiG-21bis, MiG-23M, MiG-23ML, MiG-23P, MiG-23MLA, MiG-23MLD, MiG-23BN, MiG-23BM, MiG-27D, MiG-27M

Vympel R-14 (NATO codename: “AA-2(E?) Atoll”)

While work was underway on fourth generation jet fighters such as the MiG-29 and Su-27 in the late 70s, in 1974 Vympel OKB proposed yet another new missile based on the K-13 series to replace the R-13M and R-13M1 for those new jet fighters. At that time, the R-13M1 was about to enter service and was in the shadow of the R-60/R-60M. However, this did not stop them from improving on the series even more. They were considered as the cheap alternatives to more advanced missiles. The plan was to replace the R-13M1 with the K-14 / R-14, and the R-60/R-60M with the upcoming R-73 missile.

The company begun developing the new missile, while in the meantime they were also working on the R-73. Results have shown that with an increase in mass, the R-73 became all aspect and thus became a direct competitor to the R-14, threatening its future.

The R-14 was elongated enough to have caused a reduction in aerodynamic drag, but at the same time it required a higher moment of intertia and so they developed the “duck” scheme to increase its control forces for maneuvering. This was however problematic still, as the missile had limited angles of deflection for its rudders, which meant that at high AoA they lost their effectiveness due to stalling. A possible solution was the use of aerodynamic rudders on a feathered base to reduce the effective angle of attack. With this scheme, it was determined only by the rudder deflection angle, and not the sum of this value with the angle of attack of the rocket body. Despite this, the proposal of GosNIIAS, as well as another recommendation of the specialists of this institute, proposed to abandon the “pilotless” control scheme as it was not accepted by the designers of Vympel. To increase the efficiency of rudders at high angles of attack, destabilizers were used to straighten the flow.

The missile officially entered testing in 1978. A MiG-23ML no.123 was used as its carrier, and a total of five launches were made.

Despite being characteristically similar to its competitors (the R-60M and R-73), work on it was halted in favor of the more promising R-73. The program was officially concluded on the 14th of June, 1979.

Performance R-14

Length: ?
Wingspan: ?
Body Diameter: ?
Weight: ?
Speed: Mach 2.5
Burn time: 3.3 - 5.4s
Flight time: 55s
Propulsion: DWP-240 single stage solid propellant rocket motor (thrust: 6,000 kgf)
Warhead: 11.3 kg (25 lb) HE
Guidance: Infrared-Homing
Seeker:
- FOV: 4.0°
- Gimbal limit: 40°
- Tracking rate: ?
- Cooling: nitrogen-cooled
Range: 15 km max (9.3 mi), 3 km effective (1.86 mi)
G overload (launch limit): ?
G overload (target): ?
G overload (Air): 21G (?)
IRCM: No
ECCM: No
Aspect: All-Aspect
In service: MiG-23ML

Vympel R-23R / R-23T (NATO codename: “AA-7A Apex” / “AA-7B Apex”)

The origins of the R-23 date back to 1961, when the MiG-23’s idea was first conceived. The Soviets needed a supersonic, long-range interceptor to deter the threat of high-flying westen aircraft and thus the MiG-23 and R-23 were developed. Six years after the idea’s conception, the R-23 became a reality and was test-fired multiple times in the summer of 1967. In 1971, it entered service with the MiG-23 1971.

The R-23R was meant to be the Russian equivalent of the AIM-7E Sparrow, however it was deemed slightly worse in terms of range and maneuverability, meanwhile an IR seeker model was being developed which was more or less the equivalent of the AIM-9J in terms of maximum G load, but better-fitting in a comparison with the AIM-9G and AIM-9D in terms of G limits and track rate. The R-23T’s seeker was designated TGS-23, while the latter had the RGS-23. The job of the R-23R was to intercept bomber-sized targets between altitudes of 40 - 25,000 m. Target acquisition is made in 0.5 seconds and after around 2 seconds post-launch, it captures its target and begins tracking. The R-23T on the other hand could capture targets before launch and thus had a lower minimum launch range. The autopilot of the R-23 allowed it to gradually reach 20g in the air. The R-23 could be launched from a MiG-23 overloaded at 4g and was best at tracking targets pulling 5g.

Both of those missiles were only used on the MiG-23, since the requirement of using them stated that they needed the MiG-23’s Sapphire RP-23 radar deriatives in order to utilize them. However, the first production (pre-production at that) MiG-23S lacked that capability, as its radar was the RP-22SM, taken from the MiG-21bis. It was first included on the MiG-23L (MiG-23SM or Edition 1971), which was a slightly faster and more capable model, since it had the newer Sapfir-23E radar to fire the R-23, but it still had the abysmal wing limit of 5G.

The R-23R can be differentiated from the R-23T by the length of the nose and the glass tip.

It was an effective medium-range missile, boasting a range of 27 km max for the radar-homing model and 11 km for the latter. It was maneuverable, well-ranged, fast (capable of mach 3), and possessed a large warhead. Moreover, in terms of nose immunity, the west had no analogue until the arrival of the AIM-7M in the late 80s.

Usually loaded in a pair (2 x R-23R or T) alongside four R-60 / R-60M, totalling a six missile loadout that made the MiG-23 versatile; the capability of the plane being used in missions that require short and medium ranged hostile encounters. However, starting with the MiG-23ML, it was possible to load both the IR and SARH models simultaneously. Loaded under APU-23-11 launch rails (later replaced with the APU-23M).

(R-23T and R-23R under a MiG-23ML’s wing glove pylons)

Performance R-23R

Length: 4.46 m (175.6 in)
Wingspan: 1 m (39.37 in)
Body Diameter: 223 mm (8.78 in)
Weight: 222 kg (489 lb)
Speed: Mach 3
Burn time: 5s
Flight time: 35s
Propulsion: PRD-194 two stage solid propellant rocket motor (thrust: ?)
Warhead: 25 kg (55.1 lb) HE
Guidance: Semi-Active Radar-Homing
Range: 25 km max (15.5 mi) (forward quarter)
G overload (launch limit): 4G
G overload (target): 5G
G overload (Air): 20G
IRCM: No
ECCM: Yes
Aspect: All-Aspect
In service: MiG-23P, MiG-23bis, MiG-23M, MiG-23MF, MiG-23ML, MiG-23MLA, MiG-23MLD

Performance R-23T

Length: 4.16 m (164 in)
Wingspan: 1 m (39.37 in)
Body Diameter: 223 mm (8.78 in)
Weight: 215 kg (474 lb)
Speed: Mach 3
Burn time: 5s
Flight time: 35s
Propulsion: PRD-194 two stage solid propellant rocket motor (thrust: ?)
Warhead: 25 kg (55.1 lb) HE
Guidance: Infrared-Homing
Seeker:
- FOV: 2.6°
- Gimbal limit: 60°
- Tracking rate: 12°/s
- Cooling: nitrogen-cooled
Range: 11 km max (6.8 mi)
G overload (launch limit): 4G
G overload (target): 5G
G overload (Air): 20G
IRCM: No
ECCM: No
Aspect: All-Aspect (3 km non-afterburning @ sea level)
In service: MiG-23SM, MiG-23P, MiG-23bis, MiG-23M, MiG-23MF, MiG-23ML, MiG-23MLA, MiG-23MLD

Vympel R-24R / R-24T (NATO codename: “AA-7C Apex” / “AA-7D Apex”)

The ultimate development of the R-23 series, the R-24 increased the range on the R-23, as well as warhead weight, G overload and tracking. The number of internal compartments was changed from eight to five, and the most noticeable external difference between the missile and its predecessor was the use of wings with reverse sweep along the trailing edge. The seekers were changed to the RGS-24 and the TGS-23T4 (SARH and IR respectively), and the rocket motor was replaced with the more powerful PRD-287. Moreover, the rear fins were redesigned, a deadlier warhead was installed and new airfoils for the rudders and wings. These changes improved the maneuverability of the missile from 20G to 24G, and the tracking rate from 12°/s to 20°/s. The new battery also allowed the missile to be guided for 45 seconds; 10 more seconds than the R-23, as well as a more powerful rocket motor; both of which helped increase the aerodynamic range from 27 km to 50 km. Had it not been for the limited battery however, the R-24R would have had more aerodynamic range. The R-24T on the other hand had a very powerful IR seeker; it could actually lock an SR-71 from 123 km from an aspect of 180° at an altitude of 20,000 m! As well as being able to lock an F-15 from 80 - 90 km at an altitude of 5,000 m between an aspect of 60° to 90°.

Thanks to the new, yet simplified INS (intertial navigation guidance system), the minimum launch range was decreased from 1,500 - 2,000 m to 500 - 600 m. The R-24R used a simplified analogue of the INS without the gyroscopes, as opposed to the fully integrated version on the next R-27R.

The R-24 missiles were successfully used from MiG-23ML “late” aircraft during the armed conflict in southern Lebanon in 1982 during which, according to the Syrian side, these fighters managed to shoot down three F-15s and one F-4 with a dry count. Two models were developed; the R-24R SARH model under the project designation of “Object 140” and its IR brethren, the R-24T under the project designation of “Object 160”.

In general, the R-23 and R-24 were stopgaps for the R-27 Alamo, developments and contemporaries of the AIM-7. The R-23R was considered to be comparable to the AIM-7E though slightly worse, while the R-24R was considered superior and more fitting in a comparison with the AIM-7F. Furthermore, due to the improvements, the R-24T is considered superior to the AIM-9J / AIM-9P-3 in almost every aspect.

The R-24R/T were usually loaded in a pair (2 x R-24R or T) under APU-23M1 pylons, alongside 4 x R-60 / R-60M in APU-60-2 dual racks. Compared to the R-23s, they have larger wingspan and longer bodies.

On the 17th of January, 1991, an Iraqi MiG-23 fired an R-24 and damaged an F-111 Aardvark.

Performance R-24R

Length: 4.46 m (175.6 in)
Wingspan: 1 m (39.37 in)
Body Diameter: 200 mm (7.8 in)
Weight: 243 kg (535.7 lb)
Speed: Mach 3.5
Burn time: 5s
Flight time: 45s
Propulsion: PRD-287 two stage solid propellant rocket motor (thrust: ?)
Warhead: 35 kg (77 lb) HE
Guidance: Semi-Active Radar-Homing
Range: 50 km max (15.5 mi) (forward quarter)
G overload (launch limit): 5G
G overload (target): 7G
G overload (Air): 24G
Aspect: All-Aspect
IRCM: No
ECCM: Yes
In service: MiG-23P, MiG-23MLA, MiG-23MLD

Performance R-24T

Length: 4.16 m (164 in)
Wingspan: 1 m (39.37 in)
Body Diameter: 200 mm (7.8 in)
Weight: 235 kg (518 lb)
Speed: Mach 3.5
Burn time: 5s
Flight time: 45s
Propulsion: PRD-287 two stage solid propellant rocket motor (thrust: ?)
Warhead: 35 kg (77 lb) HE
Guidance: Infrared-Homing
Seeker:
- FOV: 2.6°
- Gimbal limit: 60°
- Tracking rate: 20°/s
- Cooling: nitrogen-cooled
Range: 50 km max (15.5 mi)
G overload (launch limit): 5G
G overload (target): 7G
G overload (Air): 24G
IRCM: No
ECCM: No
Aspect: All-Aspect (3 km non-afterburning, 5 - 6 km afterburning @ sea level, 9 km afterburning @ 5,000 m), (or even up to 90, 100 or 123 km, depending on the target and altitude)
In service: MiG-23P (1980s retrofit), MiG-23bis (1980s retrofit), MiG-23MLA, MiG-23MLD

Vympel R-40R / R-40T (NATO codename: “AA-6 Acrid”)

Exclusively used by the MiG-25 and MiG-31, the R-40 missile models are the largest and heaviest AAMs to have ever been in service. Both SARH and IR models existed, usually the MiG-25 carried two of each, making the count four in total. On the MiG-25PD and MiG-25PDS, it was possible to load two of the SARH models alongside four R-60s, making it six missiles in total for the Foxbat. This was not possible on the MiG-25P, the first production model, as the R-60s were ommitted. It was also possible to equip the MiG-31 with two R-40Rs alongside three R-33s.

Under the project name of “Object 46”, the R-40 in general was first conceived in 1959 and went on to serve the next year until 1995, as a weapon designed to intercept the SR-71 Blackbird. They were made compatible with the Smerch-A, RP-25M Sapfir and RP-31 Zaslon radars. They were capable of destroying targets flying up to 3,000 km/h, from 500 m to 27,000 m.

The R-40R used the PARG-14 seeker head. Both variants are loaded under APU-84-6 launch rails.

In 1991, an R-40 scored a successful kill on a USN F/A-18 Hornet, and on the 30th of January the same year, an Iraqi MiG-25 scored a hit with an R-40 on an F-15C.

(R-40T on the left, R-40R on the right)

Performance R-40R

Length: 6.376 m (251 in)
Wingspan: 1.45 m (57.01 in)
Body Diameter: 300 mm (11.81 in)
Weight: 469 kg (1034 lb)
Speed: Mach 4.5
Burn time: ?
Flight time: ?
Propulsion: P1D-134 single stage solid propellant rocket motor (thrust: ?)
Warhead: 38 kg (83.77 lb) HE
Guidance: Semi-Active Radar-Homing
Range: 36 km max (22.37 mi)
G overload (launch limit): 8G
G overload (target): 2.5G
G overload (Air): 24G
Aspect: All-Aspect
IRCM: No
ECCM: Yes
In service: MiG-25P, MiG-25PD, MiG-25PDS, all MiG-31 models

Performance R-40T

Length: 6.376 m (251 in)
Wingspan: 1.45 m (57.01 in)
Body Diameter: 300 mm (11.81 in)
Weight: 469 kg (1034 lb)
Speed: Mach 4.5
Burn time: ?
Flight time: ?
Propulsion: P1D-134 single stage solid propellant rocket motor (thrust: ?)
Warhead: 38 kg (83.77 lb) HE
Guidance: Infrared-Homing
Seeker:
- FOV: 2.5°
- Gimbal limit: 60°
- Tracking rate: 18-20°/s
- Cooling: gas-cooled
Range: 30 km max (18.6 mi)
G overload (launch limit): 8G
G overload (target): 2.5G
G overload (Air): 24G
Aspect: Rear-Aspect
IRCM: Yes
ECCM: No
In service: MiG-25P, MiG-25PD, MiG-25PDS, MiG-31, MiG-31B

Vympel R-40RD / R-40TD (NATO codename “AA-6 Acrid”)

On the 6th of September, 1976, Lt. Viktor Belenko flew a MiG-25P from Tchuguevka (Sokolovka) Airfield, 200 km from Vladivostok in Russia’s Far East (where the 531st IAP was home-based), to Hakodate, Japan, on the 6th of September, 1976. The defector pilot provided the US and Japanese intelligence with detailed information about the USSR’s most up-to-date fighter interceptor. Belenko revealed that by the time of his defection, the IA PVO had a fleet of around 400 MiG-25Ps, and that the aircraft he had brought to Japan had been produced three years earlier. US intelligence began examining the aircraft, and when the Union’s government got ahold of this, they immediately demanded that the MiG-25P’s capabilities be hidden from the west by designing a better variant. The new MiG-25s were the MiG-25PD and PDS, with improved RP-25M radar alongside other electronics and better weapon loadout options. Those loadouts include the new and improved R-40RD-1 and R-40TD-1 air-to-air missiles, whose range, G overload and warhead weight were significantly improved. The IR model in particular received a new 35T1 seeker that had a nitrogen-cooled detector which was sensitive enough to enable head-on engagements (previously, on the R-40T, only tail-on / rear attacks were possible). The changes also resulted in a silght increase of weight. On the other hand, the R-40RD received the RGS-24 from the R-24R missile.

Lastly, their tracking ceiling was heightened to 30,000 m, compared to the previous models’ baseline of from 500 - 27,000 m. They can be differentiated from the older R-40T and R-40R by the thick and short tailcone which replaced the long and pointed one.

(R-40RD and R-40TD seen under the wing port of a MiG-25PD, notice the rocket motor nozzles and the short yet thick tail sections as opposed to the long and pointed tailcone of the R-40R/T)

When exported, they were designated R-40RD-1 and R-40TD-1. Nations such as Libya and Iraq received them with MiG-25PD aircraft, however the exported MiG-25PD (izdeliye 84DE) received the Smerch-A2 radar instead of the Sapfir RP-25M to guide them.

Performance R-40RD

Length: 6.376 m (251 in)
Wingspan: 1.45 m (57.01 in)
Body Diameter: 300 mm (11.81 in)
Weight: 471 kg (1038 lb)
Speed: Mach 4.5
Burn time: ?
Flight time: ?
Propulsion: P1D-134 single stage solid propellant rocket motor (thrust: ?)
Warhead: 55 kg (121.25 lb) HE
Guidance: Semi-Active Radar-Homing
Range: 60 km max (37.28 mi)
G overload (launch limit): 8G
G overload (target): 4G (minimum) - 8G (best conditions)
G overload (Air): 24G
Aspect: All-Aspect
IRCM: No
ECCM: Yes
In service: MiG-25PD, MiG-25PDS, all MiG-31 models

Performance R-40TD

Length: 6.376 m (251 in)
Wingspan: 1.45 m (57.01 in)
Body Diameter: 300 mm (11.81 in)
Weight: 471 kg (1038 lb)
Speed: Mach 4.5
Burn time: ?
Flight time: ?
Propulsion: P1D-134 single stage solid propellant rocket motor (thrust: ?)
Warhead: 55 kg (121.25 lb) HE
Guidance: Infrared-Homing
Seeker:
- FOV: 2.5°
- Gimbal limit: 60°
- Tracking rate: 18-20°/s
- Cooling: nitrogen-cooled
Range: 50 km max (31 mi)
G overload (launch limit): 8G
G overload (target): 4G (minimum) - 8G (best conditions)
G overload (Air): 24G
Aspect: All-Aspect
IRCM: Yes
ECCM: No
In service: MiG-25PD, MiG-25PDS, MiG-31, MiG-31B

Vympel R-33 / R-33S (NATO codename: “AA-9 Amos”)

Developed as a replacement for the previous R-40 models and for the MiG-31 exclusively, the R-33 is an active radar-homing, long range air-to-air missile, lock-on-after-launch weapon which uses intertial guidance in the initial stage of flight to extend range (with mid-course correction provided by the launch platform. It was developed under the project name of “Object 410”. The main improvement over the older R-40 was range, from 60 km to 120 - 130 km at high altitude, head on. The tests of this missile were conducted between 1975 and 1980, and in 1981 it was adopted for the MiG-31 and entered mass production. The tests proved to be successful; the vision for a future and upgraded MiG-25 came to be. A newly developed version is the R-33S, a model with 40 km more range and a higher g limit of the target; where the base version should only be fired when the target is pulling 4g or less, the R-33S is capable of tracking a target pulling up to 8g. The MiG-31 usually carried four R-33 missiles using AKU-410 ejector racks under the belly, coupled with four more missiles of the R-60/R-60M IR type.

(Firing sequence demonstrated during the R-33’s trials)

After launch, it initially flies towards the assigned target by following a lofting trajectory in a bid to extend range (climbing to 30,000 meters / 98,400 ft and then diving towards the target on a ballistic curve). Then, it uitlizes intertial guidance (10-20% of the total range to target) and switches to the semi-active homing mode. This guidance mode also enabled the missile to be re-targeted during flight (before the SARH seeker’s activation) in case more dangerous targets popped on the radar, made possible by the TGS-33 seeker head of the R-33. The probability of a hit when employed to shoot down maneuvering targets, turning up to 4g, was advertised to be between 0.6 and 0.8. It is capable of destroying targets traveling at up to 3,700 km/h and reaching altitudes of 28,000 - 30,000 meters.

The primary mission of the R-33 remains the same: intercept high-flying and high-speed aircraft such as the SR-71 and B-1 Lancer.

(MiG-31B seen carrying four R-33 + two R-40RD)

Performance R-33 / R-33S

Length: 4.15 m (163.38 in)
Wingspan: 0.9 m (57.01 in)
Body Diameter: 380 mm (15 in)
Weight: 490 kg (1080 lb)
Speed: Mach 4.5
Burn time: ?
Flight time: ?
Propulsion: Single stage solid propellant rocket motor (unknown type and thrust)
Warhead: 55 kg (121.25 lb) HE fragmentation
Guidance: Active Radar-Homing
Range: 120 km max (74.56 mi), 160 km (99 mi) (R-33S)
G overload (launch limit): 8G
G overload (target): 4G (R-33), 8G (R-33S)
G overload (Air): 21~25G
Aspect: All-Aspect
In service: All MiG-31 models

Vympel R-37 / R-37M (NATO codename: “AA-13 Axehead”)

The R-37 is a further improvement on the R-33 and R-40, featuring immense range and speed, and SARH tracking. Its main task is to shoot down high-flying aircraft, such as AWACS and spy planes. There are two models: the R-37 with a range of 280 km, and the latter being the R-37M that has a jettisonable rocket which increases the range to 300 - 400 km. They utilize the 9B-1103M-350 seeker head, which is active radar-homing during the terminal phase. Compared to the R-33, it differs in having a totally different control system which is designed to be statically unstable in flight in order to enhance its maneuverability.

Currently quite a new missile, it entered service in 2019. Its development was protracted due to the instability in the USSR and then economic recovery after the dissolution. First conceived in the early 1980s, then first produced in 1985. Not much is known about it, but it is known to be more maneuverable than the previous R-33.

Performance R-37 / R-37M

Length: 4.2 m (165.35 in)
Wingspan: 0.7 m (27.56 in)
Body Diameter: 380 mm (15 in)
Weight: 600 kg (1322 lb)
Speed: Mach 6
Burn time: ?
Flight time: ?
Propulsion: Dual stage solid propellant rocket motor (unknown type and thrust)
Warhead: 60 kg (132.27 lb) HE fragmentation
Guidance: Semi-Active Radar-Homing
Range: 280 km max (174 mi), 300 - 380 - 400 km (661 - 837.7 - 882 mi) (R-37M)
G overload (launch limit): ?
G overload (target): 8G (?)
G overload (Air): ?
Aspect: All-Aspect
In service: ?

Vympel R-60 (NATO codename: (“AA-8 Aphid-A”)

Originally, the R-60 was developed for the MiG-23. Development commenced in the 1960s, and in 1971 tests began. Two years later, the R-60 was put into mass production and was officially declared operational on the 18th of December, 1973. It utilizes a small, 3 kg expanding-rod warhead to damage enemy aircraft. At the time of its introduction, it was one of the most maneuverable air-to-air missiles in the world, until the arrival of thrust-vectoring missiles such as the newer Vympel R-73. It is also the first ever dogfight missile in the world, thanks to its light weight, distinctive design and the seeker head. It is guided by the OGS-60TI Komar homing-head, which gives it an off-boresight capability of 12 degrees.

The inert one (used for training) was guided by the UZR-60T head. When exported, it’s sometimes called the R-60K (though that designation is more used for the model with the Kolibri active fuse).

Official introductory date was the 18th of December, 1973. The first nation other than the USSR to receive the R-60 was East Germany inside the Iron Curtain; in 1982.

(Training version)

Performance R-60

Length: 2.08 m (81.9 in)
Wingspan: 0.39 m (15.3 in)
Body Diameter: 130 mm (5.1 in)
Weight: 43.5 kg (96 lb)
Speed: Mach 2.5
Burn time: 3 - 5s
Flight time: 23 - 25s
Propulsion: PRD-259 single stage solid propellant rocket motor (thrust: 582 kgf - variable)
Warhead: 3 kg (6.61 lb) HE
Guidance: Infrared-Homing
Seeker:
- FOV: 5.0°
- Gimbal limit: 45°
- Tracking rate: 35°/s
- Cooling: gas-cooled
Range: 7 km max (4.34 mi), 4 km (2.48 mi) practical
G overload (launch limit): 7G
G overload (target): 8G
G overload (Air): 30G (47G structural limit)
IRCM: No
ECCM: No
Aspect: Rear-Aspect
In service: All MiG-21 models beyond the MiG-21SM, all MiG-23 models beyond the MiG-23M, MiG-25PD, MiG-25PDS, all MiG-27 models, all MiG-29 models, all MiG-31 models, all Su-15 models, Su-17M2, Su-17M3, Su-17M4, Su-20, Su-22, all Su-24 models, all Su-25 models, Yak-38, Yak-141

Vympel R-60M (NATO codename: “AA-8 Aphid-B”)

An upgraded R-60 emerged, the R-60M. The new model featured more immunity to countermeasures, as well as a more sensitive OGS-75 Komar-M seeker, however it was not enough to give it the full aspect capability; it is classified as a limited-aspect missile due to the seeker’s size and other limitations. However, it was still capable of frontal locks like the R-73 from at least 2 km.

The new and more sensitive seeker increased its off-boresight capability by 5 degrees (from 12 to 17*), and increased its range. With the higher off-boresight capability, it could see targets better and perform tighter initial pulls upon firing. It was also fitted with a continuous rod warhead instead of the older expanding rod, which had a warhead weight of 3.5 kg. As a result of the changes, the missile’s weight increased slightly.

A variant with the more reliable Kolibri active radar proximity fuse was designated R-60MK.

(R-60K/R-60MK, obvious from the Kolibri fuse in the nose section)

The missile proved itself as an efficient air-to-air weapon and a cheaper alternative to the R-73; on the 17th of January, a MiG-29A (9-12) of the Iraqi Air Force damaged an F-111 with an R-60M. It was inducted into Soviet service in 1977, and in the mid 80s it was introduced to Warsaw Pact customers who bought the MiG-29A izdeliye 9-12A.

Performance R-60M

Length: 2.08 m (81.9 in)
Wingspan: 0.39 m (15.3 in)
Body Diameter: 130 mm (5.1 in)
Weight: 44 kg (97 lb)
Speed: Mach 2.7
Burn time: 3 - 5s
Flight time: 23s
Propulsion: PRD-259 single stage solid propellant rocket motor (thrust: 582 kgf - variable)
Warhead: 3.5 kg (6.61 lb) HE
Guidance: Infrared-Homing
Seeker:
- FOV: 5.0°
- Gimbal limit: 45°
- Tracking rate: 35°/s
- Cooling: nitrogen-cooled
Range: 10 km max (6.21 mi), 7 km (4.35 mi) practical
G overload (launch limit): 8.5G
G overload (target): 12G
G overload (Air): 30G (42G structural limit)
IRCM: No
ECCM: No
Aspect: Limited-Aspect (2 - 3 km frontal lock)
In service: All MiG-21 models beyond the MiG-21SM, all MiG-23 models beyond the MiG-23M, MiG-25PD, MiG-25PDS, all MiG-27 models, all MiG-29 models, all MiG-31 models, all Su-15 models, Su-17M2, Su-17M3, Su-17M4, Su-20, Su-22, all Su-24 models, all Su-25 models, Yak-38, Yak-38M, Yak-141

Vympel R-73A / R-73M / R-74M (NATO codename: “AA-11 Archer”)

In 1973, a project was envisioned to replace the older Vympel R-60/M air-to-air missile. The R-73 is a thrust-vectoring missile with a sensitive, cryogenic cooled MK-80 seeker with a substantial off-boresight capability of 45 °, giving it fantastic capabilities of tracking, even from very sharp angles.

In the mid 1990s, GMKB Vympel was completing the design of a thoroughly upgraded missile based on the first production model of the R-73, the R-73M. The resulting missile was designated R-73M (“M” for “modernizeerovannaya” - updated / modernized) and was due to be included in the Russian Air Force by 1996.

The R-73M is a further improvement on the base model, with 60° gimbal limit, built-in ECM resistance, a new multi-facet IR seeker with an improved digital signal processor featuring two operating frequencies and more range. The new seeker allowed the missile to frontally lock on targets within 180 degrees of FOV!

Unlike like the previous R-73A which has a combined aerodynamic/reaction control system, the R-73M uses a vectoring nozzle instead, allowing it to solidly reach 50Gs in a maneuver with more ease, while the R-73A was slightly less maneuverable; since it used a less efficient system, its maneuverability varies between 40 and 50Gs.

Structurally, the R-73M has shorter span fins, a feature which minimizes the missile’s oscillations after leaving the launch rail.

In comparison with the R-73A, the R-73M’s kinetic energy is doubled, and is superior to the BAe ASRAAM in turning speed.

All base R-73s were converted to the R-73M standard.

(Two dummy R-73s under the wing of the Su-27SMK prototype “305-Grey”)

The R-74M increases the gimbal limit to 75° and further improves the seeker’s range to 40 km instead of 30 km on the R-73M, thanks to the new Impuls-90 seeker which also increased the off-boresight capability to 120°. This is currently the standard short range air-to-air missile of the VVS.

The first R-73s to enter service date back to 1984. In 1988, the R-73E model had its production commenced for exporting. The R-73M entered service in 1996 with the Su-27 first, and the R-74M was first demonstrated in 1997.

Performance R-73A

Length: 2.90 m (111.17 in)
Wingspan: 0.51 m (20 in)
Body Diameter: 170 mm (6.7 in)
Weight: 110 kg (242.5 lb)
Speed: Mach 2.5
Burn time: 6s
Flight time: 26s
Propulsion: RTTD-295 single stage solid propellant rocket motor (thrust: 1,428 kgf)
Warhead: 7.4 kg (16.3 lb) HE
Guidance: Infrared-Homing
Seeker:
- FOV: 5.0°
- Gimbal limit: 45°
- Tracking rate: 60°/s
- Cooling: cryogenic-cooled
Range: 2.2 km tail-on at sea level, 12 km at high altitude
G overload (launch limit): 12G
G overload (target): 12G
G overload (Air): 40~50G
IRCM: Yes
ECCM: No
Aspect: All-Aspect (10 - 12 km at low altitude, 30 km at high altitude)
In service: MiG-23MLD, MiG-23BN-98, MiG-23BN-99, MiG-27M-99, MiG-21-93, MiG-23-98, all modern Russian jets except for the MiG-31

Performance R-73M

Length: 2.90 m (111.17 in)
Wingspan: 0.51 m (20 in)
Body Diameter: 170 mm (6.7 in)
Weight: 110 kg (242.5 lb)
Speed: Mach 2.5
Burn time: 6s
Flight time: 26s
Propulsion: RTTD-295 single stage solid propellant rocket motor (thrust: 1,428 kgf)
Warhead: 7.4 kg (16.3 lb) HE
Guidance: Infrared-Homing
Seeker:
- FOV: 5.0°
- Gimbal limit: 60°
- Tracking rate: 60°/s
- Cooling: cryogenic-cooled
Range: 2.2 km tail-on at sea level, 12 km at high altitude
G overload (launch limit): 12G
G overload (target): 12G
G overload (Air): 50G
IRCM: Yes
ECCM: No
Aspect: All-Aspect (15 - 20 km at low altitude, 30 km at high altitude)
In service: MiG-21-93, MiG-23-98, all modern Russian jets except for the MiG-31

Performance R-74M

Length: 2.90 m (111.17 in)
Wingspan: 0.51 m (20 in)
Body Diameter: 170 mm (6.7 in)
Weight: 110 kg (242.5 lb)
Speed: Mach 2.5
Burn time: 6s
Flight time: 26s
Propulsion: RTTD-295 single stage solid propellant rocket motor (thrust: 1,428 kgf)
Warhead: 7.4 kg (16.3 lb) HE
Guidance: Infrared-Homing
Seeker:
- FOV: 5.0°
- Gimbal limit: 75°
- Tracking rate: 60°/s
- Cooling: cryogenic-cooled
Range: 40 km max (24.85 mi)
G overload (launch limit): 12G
G overload (target): 12G
IRCM: Yes
ECCM: No
G overload (Air): 50G
Aspect: All-Aspect (15 - 20 km at low altitude, 30 km at high altitude)
In service: MiG-21-93, MiG-23-98, all modern Russian jets except for the MiG-31

Vympel R-27R / R-27T / R-27P (NATO codename: “AA-10 Alamo-A” / “AA-10 Alamo-B” / “AA-10 Alamo-E”)

The Vympel R-27 is the standard high-speed high-tracking BVR missile that was widely used in the USSR and is now in use by the Russian Air Force. It comes in different models, the oldest and base ones being the R-27R which has a SARH head, and the R-27T, the IR brethren. They’re characterized by long range and impressive tracking, maneuvering and being able to operate in dense ECM envrionments. While the previous R-24 air-to-air missiles had low minimum launch ranges, the R-27s are the first Soviet BVR missiles truly classified as “dogfight missiles”; seeing as their minimum launch range(s) measured at 200 m as opposed to 500 - 600 m on the R-24.

(R-27 during trials, photograph from a movie)

The R-27R uses inertial navigation system (INS), which, in combination with other factors, provides a minimum launch range of about 400 m. Its aerial maneuverability is similar to that of the R-24, with a slight edge in maneuverability (about 25-30g). It is the first dogfight BVR missile in the Soviet Air Force’s inventory.

Currently, they are the standard and lethal modern BVR weapons the Russian Air Force possesses. They are directed by the TGS-27 IR homing-head for the heat-seeking derivative of the R-27 (R-27T), and the RGS-27 for the semi-active radar-homing model (R-27R). The RGS-27 provided a maximum acquisition range of 40 km, but the aerodynamic range exceeded (maximum in-flight range) that number, typically around 60 km. To compensate for the acquisition range whenever launch is required at greater distances, the developers of the missile made sure it was possible to fire the missile before lock, and when it comes within lock range, it would capture the target and start tracking. To achieve this, the missile receives mid-course guidance via a special command-link system until it receives lock-on.

The range is achieved with the that guidance system, the missile’s aerodynamic layout as well as its motor’s burn time of about 8.6 - 11 seconds (typically 10). The TGS-27 on the other hand could reliably lock onto targets from 80 - 90 km, depending on the flight conditions such as altitude and lock aspect. The main targets of the R-27 are fighters and medium-sized bombers.

Other developments of the R-27 include the R-27P and R-27EP passive-homing missiles, with the 9B1032K seekers. Exported models of the R-27 usually have the number “1” added to the designation as a suffix; for example the export R-27R is called the “R-27R1”. They are loaded under AKU-470 racks (a universal designation however; the R-27R was used in conjunction with the APU-27, and the R-27T with the AKU-27 specifically).

Adopted into service in 1983 with the MiG-29A and Su-27.

Performance R-27R

Length: 4 m (157.5 in)
Wingspan: 0.80 m (31.49 in)
Body Diameter: 230 mm (9.05 in)
Weight: 253 kg (557.7 lb)
Speed: Mach 4.5
Burn time: 11s
Flight time: 60s
Propulsion: Single stage solid propellant rocket motor (unknown type, thrust: 5,000 kgf)
Warhead: 39 kg (86 lb) HE
Guidance: Semi-Active Radar-Homing
Range: 60 km max (37.3 mi)
G overload (launch limit): 7G
G overload (target): 8G
G overload (Air): 25-30G (74G structural)
IRCM: No
ECCM: Yes
Aspect: All-Aspect
In service: All models of: Su-27, Su-33, Su-35, MiG-29, Yak-141, MiG-21-93, MiG-23-98

Performance R-27T

Length: 3.79 m (149 in)
Wingspan: 0.77 m (30.31 in)
Body Diameter: 230 mm (9.05 in)
Weight: 245 kg (540 lb)
Speed: Mach 4.5
Burn time: 11s
Flight time: 60s
Propulsion: Single stage solid propellant rocket motor (unknown type, thrust: 5,000 kgf)
Warhead: 39 kg (86 lb) HE
Guidance: Infrared-Homing
Seeker:
- FOV: 5.0°
- Gimbal limit: 40°
- Tracking rate: 14.5°/s
- Cooling: nitrogen-cooled
Range: 50 km max (31 mi)
G overload (launch limit): 7G
G overload (target): 8G
G overload (Air): 25-30G (74G structural)
IRCM: Yes
ECCM: No
Aspect: All-Aspect
In service: All models of: Su-27, Su-33, Su-35, MiG-29, Yak-141, MiG-21-93, MiG-23-98

Performance R-27P

Length: 4.7 m (185 in)
Wingspan: 0.77 m (30.31 in)
Body Diameter: 230 mm (9.05 in)
Weight: 245 kg (540 lb)
Speed: Mach 4.5
Burn time: 11s
Flight time: 60s
Propulsion: Single stage solid propellant rocket motor (unknown type, thrust: 5,000 kgf)
Warhead: 39 kg (86 lb) HE
Guidance: Passive-Homing
Seeker:
- FOV: 5.0°
- Gimbal limit: 40°
- Tracking rate: 14.5°/s
- Cooling: nitrogen-cooled
Range: 78 km max (48.46 mi)
G overload (launch limit): 5G
G overload (target): 5G
IRCM: ?
ECCM: ?
G overload (Air): 25G-30G (74G structural)
Aspect: All-Aspect
In service: All models of: Su-27, Su-33, Su-35, MiG-29, Yak-141, MiG-21-93, MiG-23-98

Vympel R-27ER / R-27ET / R-27EP (NATO codename: “AA-10 Alamo-C” / “AA-10 Alamo-D” / “AA-10 Alamo-F”)

In order to increase the effective range of the previous R-27 missile, it was decided to equip it with a much more powerful rocket motor, albeit with the same duration of burn. The new motor not only increased the maximum range by more than 30 km, but also increased the weight of the missile by about 100 kg. As a result, the range of the new R-27ER (“E” for “energovo’oroozhon”, Russian for “high-powered”) was 90 km: this was achieved by flying at an altitude of 14,000 m at Mach 1.2. With such conditions in place, the maximum flight duration was 90 seconds.

Under the most favorable conditions, the aerodynamic range was 130 km. However, the seeker’s model remained unchanged, so the maximum acquisition range remained 40 km, but it could still be fired without lock, guided by a mid-course navigation system until it receives lock-on. The lock-on range for the R-27ET remained the same as the R-27T, the same applies to the R-27EP in comparison to the R-27P.

There is a special upgraded version of the R-27ER under the designation of “R-27EM”, which features an upgraded seeker capable of capturing and tracking targets as low as 3 meters.

(Inert R-27ER with a protective cap)

Performance R-27ER

Length: 4.7 m (157.5 in)
Wingspan: 0.77 m (30.31 in)
Body Diameter: 230 mm (9.05 in)
Weight: 350 kg (771.6 lb)
Speed: Mach 4.5
Burn time: 11s
Flight time: 90s
Propulsion: Single stage solid propellant rocket motor (unknown type, thrust: ? kgf)
Warhead: 39 kg (86 lb) HE
Guidance: Semi-Active Radar-Homing
Range: 93 km max (57.78 mi)
G overload (launch limit): 7G
G overload (target): 8G
G overload (Air): 25-30G (74G structural)
IRCM: No
ECCM: Yes
Aspect: All-Aspect
In service: All models of: Su-27, Su-33, Su-35, MiG-29, Yak-141, MiG-21-93, MiG-23-98

Performance R-27ET

Length: 4.49 m (176.77 in)
Wingspan: 0.80 m (31.49 in)
Body Diameter: 230 mm (9.05 in)
Weight: 343 kg (756 lb)
Speed: Mach 4.5
Burn time: 11s
Flight time: 90s
Propulsion: Single stage solid propellant rocket motor (unknown type, thrust: ? kgf)
Warhead: 39 kg (86 lb) HE
Guidance: Passive-Homing
Seeker:
- FOV: 5.0°
- Gimbal limit: 40°
- Tracking rate: 14.5°/s
- Cooling: nitrogen-cooled
Range: 84 km max (52.2 mi)
G overload (launch limit): 7G
G overload (target): 8G
G overload (Air): 25-30G (74G structural)
IRCM: Yes
ECCM: No
Aspect: All-Aspect
In service: All models of: Su-27, Su-33, Su-35, MiG-29, Yak-141, MiG-21-93, MiG-23-98

Vympel R-27EA (NATO codename: “AA-10 Alamo-E”)

With further advancements in missile technology, it was decided to equip the R-27ER with an active radar-homing seeker by the designation of ARGS-27. A true “wish them dead” weapon, the R-27EA is the first missile in Russian inventory with an ARH seeker, followed by the deadly R-77 (hence the “A” suffix in the missile and seeker designation, referring to the active seeker). With the new seeker, target illumination was only required before launch.

Outwardly, it can only be differentiated from the R-27ER by the conically-shaped radome instead of the usual ogival shape.

(R-27EA, R-77 and Kh-29TE missiles)

Performance R-27EA

Length: 4.7 m (157.5 in)
Wingspan: 0.77 m (30.31 in)
Body Diameter: 230 mm (9.05 in)
Weight: 350 kg (771.6 lb)
Speed: Mach 4.5
Burn time: 11s
Flight time: 60s
Propulsion: Single stage solid propellant rocket motor (unknown type, thrust: 5,000 kgf)
Warhead: 39 kg (86 lb) HE
Guidance: Active Radar-Homing
Range: 130 km max (81 mi)
G overload (launch limit): 7G
G overload (target): 8G
G overload (Air): 25-30G (74G structural)
IRCM: No
ECCM: Yes
Aspect: All-Aspect
In service: All models of: Su-27, Su-33, Su-35, MiG-29, Yak-141, MiG-21-93, MiG-23-98

Vympel R-77 / R-77-1 (NATO codename: “AA-12 Adder”)

The ultimate Russian BVR air-to-air missile. It is touted as the Russian AMRAAM, with an active radar-homing seeker and up to 100 km of range.

Under the project name of Izdeliye 170, the development of the R-77 had initially begun in 1982 in order for Soviet fourth gen aircraft to utilize it, such as the MiG-29 and Su-27. This was also around the same time the USA had begun developing the AIM-120A AMRAAM, which gave the Soviets more incentive to begin a race in technology for superior BVR missiles. The experimental design development of the missile was carried out by the joint team of Vympel and Molniya designers, headed by G.A. Sokolovsky under the direct supervision of V.A. Pustovoitova, and the work’s completion under the leadership of V.G. Bogatsky, currently the chief designer.

(R-77 during its trials, fired by one of the original MiG-29 prototypes; the izdeliye 9-19)

The missile was launched into production during 1984, and state acceptance trials were fully completed in 1991, and on the 23rd of February, 1994, the missile was fully adopted into service. The R-77 is guided by a 9B-1348 seeker head. Furthermore, it’s capable of hitting targets traveling at 30,000 meters in addition to maneuvering at up to 12G overload and 40 degrees of AoA. Its 9B-1348 seeker is capable of locking on targets from 16 km; much like the R-27, it can be launched without lock and guide itself using a special command-link system until the seeker finds its target. The max kill range against a maneuvering target is 25 - 40 km and the minimum launch range is 300 m.

The R-77-1 is a further improved model of the R-77, with new tail fins and a 9B-1248 seeker head. These changes resulted in a range increase by 30 km, and a higher seeker lock-on range of 25 km.

Performance R-77

Length: 3.5 m (138 in)
Wingspan: 0.4 m (15.7 in)
Body Diameter: 200 mm (7.87 in)
Weight: 175 kg (386 lb)
Speed: Mach 4
Burn time: 8s
Flight time: ?
Propulsion: Single stage solid propellant rocket motor (unknown type and thrust)
Warhead: 22 kg (48.5 lb) HE expanding rod
Guidance: Active Radar-Homing (+ inertial + ARLSN)
Range: 100 km max (62 mi)
G overload (launch limit): 8G
G overload (target): 12G
G overload (Air): 30G
IRCM: No
ECCM: Yes
Aspect: All-Aspect
In service: All Russian generation 4 jets (and higher) (except for the MiG-29A and Su-27S)

Performance R-77-1

Length: 3.5 m (138 in)
Wingspan: 0.4 m (15.7 in)
Body Diameter: 200 mm (7.87 in)
Weight: 175 kg (386 lb)
Speed: Mach 4
Burn time: 8s
Flight time: ?
Propulsion: Single stage solid propellant rocket motor (unknown type and thrust)
Warhead: 22 kg (48.5 lb) HE expanding rod
Guidance: Active Radar-Homing (+ inertial + ARLSN)
Range: 140 km max (87 mi)
G overload (launch limit): 8G
G overload (target): 12G
G overload (Air): 30G
IRCM: No
ECCM: Yes
Aspect: All-Aspect
In service: All Russian generation 4 jets (and higher) (except for the MiG-29A and Su-27S)

Believe it or not, even simple history books contain information on Russian missiles. For example, in the MiG-23 chapter from “Soviet Cold War Fighters”, there is a large table with G loads and every statistic for each missile used by the MiG-23.

References:

Soviet Cold War Fighters - Alexander Mladenov
Mikoyan-Gurevich MiG-21 - Alexander Mladenov
Mikoyan-Gurevich MiG-21: The Most Produced Supersonic Fighter - Yefim Gordon
Mikoyan-Gurevich MiG-21: Famous Russian Aircraft
Mikoyan-Gurevich MiG-23/27 Flogger: Soviet Swing-Wing Jet Fighter / Strike Aircraft - Yefim Gordon
Sukhoi Interceptors: The Su-9, Su-11, and Su-15: Unsung Soviet Cold War Heroes - Yefim Gordon
Soviet Aircraft Weapons Since WW2 - Yefim Gordon
MiG-25 Foxbat: Guardian of the Soviet Borders - Yefim Gordon
Mikoyan MiG-31- Yefim Gordon
History of the Electro-Optical Guided Missiles
Советские авиационные ракеты “Воздух-воздух” - Виктор Марковский, Константин Перов
Техника и вооружение 2005 09

Along with other books…

From others, private websites mainly but very resourceful…

https://ruslet.webnode.cz/technika/ruska-technika/letecka-vyzbroj/protiletadlove-rs/r-13m1-aa-2e-atoll-e-/

Some manuals were also used for some missiles, like the MiG-23 manual for the R-23 and R-24, and employment characteristics translated from Russian.

BBCRF · November 28, 2024, 8:53am

R-27 G overload-35
R-73/74-60G
R-77/77-1 50G

MaMoran20 · November 28, 2024, 9:44pm

Performance R-40

Speed: Mach 4.5, +540 m/s to 740 m/s to the launch velocity depending on conditions
Burn time: 4 - 6.7 seconds
Flight time: 40 seconds
Guidance: CW Semi-Active Radar-Homing
G overload (launch limit): 3G
G overload (target): 4G (max)
G overload (Air): 15G

Performance R-40T

Speed: Mach 4.5, +540 m/s to 740 m/s to the launch velocity depending on conditions
Burn time: 4 - 6.7 seconds
Flight time: 40 seconds
Warhead: 55 kg (This value seems to be the standard 38 kg warhead of the R + 17kg)
Seeker:
- FOV: 1.6° or 2°
- Cooling: nitrogen-cooled
G overload (launch limit): 3G
G overload (target): 4G (max)
G overload (Air): 15G
Aspect: ALL-Aspect

Performance R-40RD

Speed: Mach 4.5, +540 m/s to 740 m/s to the launch velocity depending on conditions
Burn time: 4 - 6.7 seconds
Flight time: 40 seconds
Warhead: 38 kg
Guidance: CW Semi-Active Radar-Homing
G overload (launch limit): 3G
G overload (target): 4G (max)
G overload (Air): 15G

Performance R-40TD

Speed: Mach 4.5, +540 m/s to 740 m/s to the launch velocity depending on conditions
Burn time: 4 - 6.7 seconds
Flight time: 40 seconds
Warhead: 55 kg (This value seems to be the standard 38 kg warhead of the R + 17kg)
Seeker:
- FOV: 0.94°
G overload (launch limit): 3G
G overload (target): 4G (max)
G overload (Air): 15G

These are the corrections I have for the R40s.

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Extra things to note

The CW illuminator is a fixed horn antenna. ±20°. Anything in that huge cone is getting illuminated. You cannot also beam more than that as you’ll no longer be illuminating the target, trashing the missile.

When launching, the target must be in a ±45° cone.

Min altitude is 50m due to the fuze going off.

Max relative closure rate between target-missile is 2000m/s (~6.7 Mach at a high alt)

Minimum closure rate for fuse activation is 200 m/s

speedgate for the R/RD is ± 7m/s

The fuze activates between 10-20m for large target and 6-7m to small targets, target size selected by pilot.

the frequency of the CW for R/RD is 16 GHz

Maximum fin deflection is 20°

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And some range suff

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WalletWorrier · November 29, 2024, 12:16am

MiG-31s are only capable of carrying IR R-40s and not radar ones
Also, the TD-1 featured a new fuze and was still used domestically
The R-33 and R-33S are both SARH