Russian Weapons

Planes > Weapons

AIR TO AIR

	R-73E

	The R-73E (R-73EL) small-range air-to-air missile is designed to engage in a dogfight various types of air targets, such as fighters, bombers, attack and military cargo aircraft, approaching from any direction, by day and night, in conditions of ground clutter and ECM. The missile is intended for arming fighters, attack aircraft and helicopters. It features all-aspect IR passive homing. The “fire-and-forget” principle is realized. The missile is powered by a fixed-thrust solid-fuel rocket engine. The R-73E missile modification is equipped with a radar proximity fuse/target sensor, while the R-73EL - with a laser proximity target sensor. The warhead is of a rod type. The missiles’ high agility is achieved due to the use of a unique combined gas/aerodynamic control system. The missile is suspended from the carrier aircraft, energized in a captive flight, launched in combat or jettisoned in emergency by means of the P-72-1D/P-72-1DB2 air rail launcher. The missile can be adapted for employment from foreign-made carriers in accordance with the technology, developed by the designer.

	Launch range, km:
	in the front hemisphere, max	30
	in the aft hemisphere, min	0.3
	Target designation angle, deg	± 45
	Target engagement altitudes, km	0.02 - 20
	Max target g-load	up to 12
	Launch weight, kg	105
	Warhead type	rod
	Warhead weight, kg	8
	Missile dimensions, m:
	length	2.9
	body diameter	0.17
	wing span	0.51
	fin span	0.38

	RW-AE

	The RVV-AE medium-range air-to-air guided missile is intended for round-the-clock all-aspect engagement of various air targets such as fighters, bombers, attack aircraft, helicopters, military cargo aircraft and cruise missiles, against ground and water surface background, in harsh ECM environment. The missile features multi-target and “fire-and-forget” capabilities. The missile can be carried on MiG/Su-type aircraft. The missile guidance is combined: inertial with radiocorrection datalink at the initial leg and active radar homing at the terminal leg. It is powered with a fixed-thrust solid-fuel rocket engine. The warhead is of a multi-shaped charge rod type. It is fitted with a laser proximity target sensor. Folding lattice (electrically driven) fins is a missile’s distinctive design feature, which has no matches in the World.

	Launch range, km:
	max, in the frond hemisphere	80
	min, in the aft hemisphere	0.3
	Target engagement altitude, km	0.02 - 25
	Launch weight, kg	175
	Warhead weight, kg	22.5
	Missile dimensions, m:
	length	3.6
	body diameter	0.2
	wing span	0.4
	fin span	0.7

	RVV-MD

	RVV-MD, a small-range air-to-air guided missile for a close-in dogfight, can engage helicopters and aircraft of different types on a round-the-clock basis, from all aspects, against ground surface, under severe countermeasures. The missile has high maneuverability, (optical) jamming immunity. It is intended for arming fighters, attack aircraft and combat helicopters. The missile features all-aspect passive IR guidance (two-color IR seeker) with combined aerogasdynamic control, a fixed-thrust solid fuel motor, a laser proximity fuse (for RVV-MDL) or a radar proximity fuse (for RVV-MD). The warhead is of rod type. Aircraft rail launcher P-72-1D (P-72-1BD2) is responsible for missile suspension, energization during captive flight, combat launch and emergency jettisoning. The missile may be adapted for foreign-made Carriers.

	Launch Range: - max, at the front hemisphere, km - 0.3 - min, at the aft hemisphere, km - up to 40 Targeting angles, degrees - ± 60 Target altitude, km - 0,02 - 20 Targets g-factor, g - up to 12 Launch weight, kg - 106 Warhead weight, kg - 8 Missile dimensions, m - length - 2. 92 - diameter - 0.17 - wing span - 0.51 - fin span - 0.385

	RVV-SD

	RVV-SD is a highly effective medium-range missile used for engaging air targets (fighters, attack aircraft, helicopters, cruise missiles, etc.) on a round-the-clock basis, from all aspects, under severe countermeasures, against ground or water surface, in a multi-channel firing mode in accordance with “fire-and-forget” principle. It is intended for arming aircraft of MiG and Su type. The missile features inertial guidance system with radio correction and an active radar seeker, a fixed-thrust solid fuel motor and a laser proximity fuse. The warhead is a rod type, multiple hollow charge one. Aircraft catapult launcher AKU-170E is used for suspension. The missile may be adapted for deployment on foreign carriers.

	Launch Range: - max, at the front hemisphere, km - up to 110 - min, at the aft hemisphere, km - 0.3 Target altitude, km - 0,02 - 25 Launch weight, kg - not more than 190 Missile dimensions, m - length - 3.71 - diameter - 0.2 - wing span - 0.42 - fin span - 0.68

R-27P1

The R-27P1 and R-27EP1 unified medium-range air-to-air missiles with passive radar homing heads are intended for round-the-clock engagement of radio-emitting air targets in fair and adverse weather conditions, in the front hemisphere, against diverse underlying backgrounds and in cases when the enemy targets protect their aircraft with anti-radar active jamming. Both missiles are intended for arming MiG/Su-type combat aircraft. They feature “fire-and-forget” covert attack capability. The R-27P1 missile is powered with a fixed-thrust solid-fuel engine, the R-27EP1 - with a dual-thrust solid-fuel engine. The fusing system includes a radar fuse and an impact target sensor. The warhead is of a load-carrying rod type. The missile layouts are characterized by modular design.

	R-27P1	R-27EP1
Max launch range, km:
in the front hemisphere	72	110
Target engagement altitude, km	0.02 - 20	0.02 - 20
Launch weight, kg	248	346
Warhead weight, kg	39	39
Missile dimensions, m:
length	4.047	4.742
body diameter:
at control unit section	0.23	0.23
at solid-fuel rocket section	0.23	0.26
wing span	0.7736	0.8033
control plane span	0.972	0.972

R-27R1 / R-27ER1

The R-27T1 and R-27ET1 medium-range air-to-air missiles with semi-active radar homing heads are designed to engage air targets by day and night, in fair and adverse weather conditions, in the front and rear hemispheres, also against diverse underlying surfaces with enemy’s active evasive maneuvering and intensive jamming. The missiles pursue their targets in accordance with an updated proportional navigation method both in the inertial/radio-corrected flight trajectory phase and in the semi-active homing phase after locking on target en route. The missiles’ fusing systems are based on radar proximity and impact target sensors. The missile layouts are characterized by modular design. Both missiles are intended for arming MiG/Su-type combat aircraft.

	R-27R1	R-27ER1
Launch range, km:
against fighter-type targets	50 - 60	60 - 62.5
against some other targets	up to 75	up to 100 (90)
Missile dimensions, m:
length	4.08	4.775
body diameter
at control unit section	0.23	0.23
at solid-fuel rocket section	0.23	0.26
wing span	0.7736	0.8033
control plane span	0.972	0.972
Warhead type	rod-type load-carrying	rod-type load-carrying
Warhead weight, kg	39	39
Launch weight, kg	253	350
Engine type	one-mode solid rocket	two-modesolid rocket

R-27T1 / R-27ET1

The R-27T1 and R-27ET1 medium-range air-to-air missiles with IR seekers are designed to engage various air targets, such as highly maneuverable aircraft, helicopters and the like, in the front and rear hemispheres, by day and night, under natural clutter and organized jamming, against ground and water surface. The missiles feature “fire-and-forget” principle. They are intended for arming MiG/Su-type combat aircraft. The missile guidance system features an updated proportional guidance algorithm when the target lock-on is accomplished in a captive flight. The R-27T1 missile is powered with a fixed-thrust solid-fuel engine, the R-27ET1 - with a dual-thrust solid-fuel engine. The fusing system includes a radar fuse and an impact target sensor. The warhead is of a load-carrying rod type. The missile layouts are characterized by modular design.

	R-27T1	R-27ET1
Max launch range, km:
max, at the front hemisphere	65	80
Launch weight, kg	245.5	343
Warhead weight, kg	39	39
Missile dimensions, m:
length	3.795	4.49
body diameter
at control unit section	0.23	0.23
at solid-fuel rocket section	0.23	0.26
wing span	0.773	0.803
control plane span	0.972	0.972

	R-33E

	The R-33E long-range air-to-air guided missile is intended for all-aspect round-the-clock interception of air targets, including cruise missiles, against various background surfaces, in fair and adverse weather conditions, under natural clutter and enemy-organized interference. The R-33E missile is the basic weapon of the MiG-31E interceptor. Missile control system as a part of the MiG-31E weapon system ensures autonomous guidance of missiles launched from one or several aircraft against one or several air targets that may fly at different altitudes and speeds. The R-33E missile features inertial guidance at the initial leg and semi-active radar homing at the terminal leg. The missile is powered with a fixed-thrust solid-fuel engine. It is equipped with an active pulse-type proximity target sensor effective at the range of up to 20 m. Warhead is of HE fragmentation type.

	Launch range, km	120
	Target engagement altitudes, km	0.05 - 25
	Engaged target flight speed, km/h	3,000
	Target g-load	4
	Launch weight, kg	490
	Warhead weight, kg	47
	Missile dimensions, m:
	length	4.15
	body diameter	0.38
	wing span	0.90
	control plane span	1.10