The Yak-130 combat trainer was selected as the winner of the trainer competition of the Voyenno Vozdushnyye Sily, Russian Federation Air Force, in April 2002. The aircraft is also actively marketed for export by Yakovlev, the Irkut company, and by Rosoboronexport.
The Russian Air Force has a future requirement for 300 Yak-130 aircraft that can be deployed as a light strike aircraft or as a trainer for a range of fourth or fifth-generation fighters. An order was placed for the first 12 aircraft to replace ageing Aero Vodochody L-39 Albatros in 2002. The aircraft entered service in the Russian Federation Air Force at the military pilot training academy in Krasnodar in July 2009 and was showcased in the MAKS 2009 air show.
The first Yak-130 ordered by the Russian Air Force completed its flight acceptance test at Sokol in August 2009. The Russian Air Force received the first four of 12 Yak-130s between February 2010 and April 2010. Another five aircraft were delivered in April 2011.
In December 2011, the Russian Ministry of Defence placed an order with Irkut for the delivery of 55 Yak-130 combat trainers by 2015.
The Yak-130 has a maximum g-loading of +8g to -3g and is capable of executing the flight manoeuvres specific to current operational and developmental combat aircraft, including Su-30, MiG-29, Mirage, F-15, F-16, Eurofighter, F-22 and F-35.
Other variants of the Yak-130 considered included a navalised carrier-based trainer aircraft, a lightweight reconnaissance aircraft and an unmanned strike aircraft.
The Yak-130 is of classical swept-wing and empennage monoplane design and light alloy construction with carbon-fibre control surfaces. Kevlar armour protection is fitted to the engines, cockpit and avionics compartment.
All-digital cockpit
The aircraft has an air-conditioned and pressurised two-seat tandem cockpit fitted with NPO Zvezda K-36LT 3.5 zero-zero ejection seats. The pilots have all-round view through a blister canopy. The forward pilot has a view over the nose to -16°. The rear pilot has a view to -6°.
K-36L-3,5YA (К-36Л-3,5Я)
Main specifications:
Ejection seat provides rescue crew member in Vi speed ranges (0 to 1050) km / h, Mach numbers up to 1.0 and the aircraft flight altitudes (from 0 to 13,000) m, including take-off, landing run, “H = 0 mode, V = 0 “and is applied with a set of protective equipment and oxygen RUC-15 type of equipment.
The installation weight of the chair is not more than 86 kg (with a survival kit)
Application:
Yak-130
Source zvezda-npp.ru
Oxygen system comprises the onboard oxygen generating system (OBOGS) designed to supply oxygen to the crew members in all flight modes at altitudes of up to 12,500 m, including emergency situations such as cockpit depressurization and crew ejection. Emergency oxygen system installed in the ejection seats is a source of oxygen for about 5 minutes in cases of the OBOGS failure and cockpit depressurization (automatically activated if over 8,000 m), ejection and subsequent parachute descent.
Air conditioning system is designed to ventilate and maintain the required air temperature and pressure in the cockpit, cool down electronic equipment compartments, pressurize external fuel tanks, supply air to the OBOGS, etc.
Protective equipment provides optimal working conditions for the flight crew and includes pilots’ anti-G suits and protective helmets with oxygen masks. Source redstar.gr
Oxygen System KS – 130
Purpose:
The KS-130 oxygen system is designed to provide one or two pilots of the front-line aircraft with oxygen during flights at the altitudes up to 12 km. The oxygen source is the BKDU-130 onboard oxygen-generating system, which produces oxygen from compressed air tapped from the aircraft gas turbine compressor.
Major advantages of the bottle-free oxygen system:
- There are no onboard oxygen bottles in the system and, correspondingly, there is no need in pre-flight charging of the system with oxygen;
- The mission duration is not limited with the onboard oxygen reserve;
- The system features less line maintenance man-hours than the system with the bottle oxygen source.
The KS-129 oxygen system is used onboard the Yak-130 aircraft.
Source zvezda-npp.ru
The production Yak-130 is the first Russian aircraft with an all-digital avionics suite. The avionics meets Mil Standard 1553 and can be adapted to the customer’s requirements.
The aircraft has an all-glass cockpit. Both pilot positions are night vision goggle compatible and equipped with three multi-function 6in x 8in color liquid crystal displays. The pilot in the forward cockpit can use the helmet-mounted sight for target designation. The cockpit is fitted with an MS internal and external communication and voice warning system supplied by AA.S. Popov GZAS Joint Stock Company.
The Avionica fly-by-wire flight control system is used to adjust the stability and controllability characteristics and flight safety systems to simulate a number of aircraft such as the MiG-29, Su-27, Su-30, F-15, F-16, F-18, Mirage 2000, Rafale, Typhoon and future fighters such as the F-35. The pilot selects the software model of the simulated aircraft’s control system on the Yak-130 onboard computer. The pilot can select the model during flight. The system can be forgiving to allow cadet pilots the easy acquisition of piloting skills.
The open architecture avionics suite includes two computers and a three-channel information exchange multiplexer. The navigation suite includes laser gyroscopes and GLONASS/NAVSTAR global positioning.
WEAPONS
The Yak-130 combat trainer can simulate the tactics of different combat aircraft. There is one centerline fuselage hardpoint and the number of wing hardpoints for the suspension of weapons payloads has been increased to eight with six underwing and two wingtip points, increasing the combat payload weight to 3,000kg. The aircraft can carry weapons, suspended fuel tanks, reconnaissance pods and a range of electronic warfare pods including radar jammers and infrared countermeasures.
An open architecture avionics suite installed on the Yak-130 allows a wide range of western weapon systems and guided missiles to be integrated including the AIM-9L Sidewinder, Magic 2 and the AGM-65 Maverick. Weapons fits include the Vikhr laser-guided missile, R-73 infrared-guided air-to-air missiles (NATO designation AA-11 Archer) and the Kh-25 ML (NATO designation AS-10 Karen) air-to-surface laser-guided missile. A Platan electro-optical guidance pod is installed under the fuselage for deployment of the KAB-500Kr guided bomb.
AIM-9L Sidewinder
AIM-9L Sidewinder
The Sidewinder is the most widespread Air-to-Air missile in the world; its first version, the AIM-9B, entered service in 1953 and since then it has been continuously updated up to the latest versions AIM-9L and AIM-9M and it boasts many imitation attempts, like the Russian AA-2 “Atoll” or the Israeli Rafael “Shafrir 2”.
It features four detachable double-delta control surfaces behind the nose and a roll stabilizing rear wing/rolleron assembly. The main components of the missiles are an infrared homing guidance system with “all aspect” capability, an explosive/fragmentation warhead weighting about 10 Kg and an active optical target detector. According to the avionic system of the carrier aircraft, the missile can be fired in two modes:
- “Boresight Mode”: IR seeker slaved to the aircraft weapon aiming system
- “Scan Mode”: IR seeker performs autonomous scanning
| LENGTH: | 2.87 m |
|---|---|
| DIAMETER: | 127 mm |
| WING SPAN: | 0.64 m |
| WEIGHT: | 87 Kg |
| WARHEAD: | 9.5 Kg HE/fragmentation |
| FUZE: | Active Laser |
| GUIDANCE: | IR |
| PROPULSION SYS.: | Rocket motor, solid propellant |
| RANGE: | 8 Km |
Source nibbio14.altervista.org
Magic 2 (R-550)
Magic 2 missile
Magic R550 -“All aspect” medium-range missile, developed in 1967 by Matra and entered service in 1974. Advanced aerodynamic characteristics, thanks to moving control fins near the nozzle, in combination with four aerodynamic vanes which serve to stabilize the flow for better control.
| LAUNCH-PLATFORM | Mirage 2000, Rafale, F-16, Sea Harrier, Mirage 5, Super Etendard, Mirage F1, Mirage III |
| DESIGNER | Marta, MBDA |
| COUNTRY | France |
| IN SERVICE | 1975 (Magic)
1986 (Magic II) |
| TYPE | Short-range air-to-air missile |
| POWER PLANT | Rocket motor |
| Thrust, kN | – |
| DIMENSIONS | |
| Length, mm | 2750 |
| Diameter, mm | 160 |
| Wing span, mm | 470 |
| WEIGHT | |
| Weight, kg | 89 |
| Warhead weight, kg | 30 |
| Warhead type | Fragmentation |
| GUIDANCE SYSTEM | IR |
| PERFORMANCE | |
| Speed, (Mach) | 4 |
| Range, km | 15 |
Source redstar.gr
AGM-65 Maverick
AGM-65 Maverick
Vikhr laser-guided missile
Vikhr laser-guided missile
The 9A4172 Vikhr is a Russian long-range anti-tank guided missile. It is known in the West as the AT-16 Scallion. It was developed in the Soviet Union during the 1980s. At the time Soviets needed a new missiles, to replace the 9K114 Shturm (AT-6 Spiral) system, that could penetrate contemporary Western main battle tanks with composite and explosive reactive armor, such as the American M1 Abrams, German Leopard 2, and British Challenger. Prototypes were tested by the Soviet armed forces in 1989. First production missiles were delivered in 1992. During the same year the Vikhr was first publicly revealed. Since its introduction sales of the Vikhr missile have been slow, partly because Russia also uses Ataka missile, developed by another manufacturer, which is similar in function, but uses different guidance. In 2013 Russian MoD ordered over 6 000 Vikhr-1 missiles in order to prevent the manufacturer from going bankrupt. Delivery was completed in 2016. The Vikhr has been exported to Egypt, and possibly some countries.
Launchers with the Vikhr missiles can be mounted on helicopters, vehicles and watercraft. This missile is typically used on Russian helicopters, such as the Ka-52, and Su-25T ground attack aircraft. However much more numerous Russian Mil attack helicopters, such as the Mi-24 and Mi-28 are typically equipped with broadly similar Ataka anti-tank missiles.
The Vikhr missiles are used in conjunction with APU-6 and APU-8 aviation launchers. The APU-6 launcher carries 6 missiles and is used on the Ka-50 helicopters. The APU-8 launcher carries 8 missiles and is used on the Su-25T ground attack aircraft.
| Country of origin | Russia |
| Entered service | 1992 |
| Missile | |
| Armor penetration | 1 000 mm behind ERA |
| Missile length | 2.75 m |
| Missile diameter | 0.13 m |
| Fin span | 0.38 m |
| Missile launch weight | 45 kg |
| Warhead weight | 10 – 12 kg |
| Warhead type | Tandem HEAT |
| Range of fire | up to 10 km |
| Guidance | Laser-guided |
Source military-today.com
R-73 infrared-guided air-to-air missiles (NATO designation AA-11 Archer)
R-73 infrared-guided air-to-air missiles
The R-73 short-range air-to-air missile was developed by “Molniya” (recently the special design bureau Nr.4) design bureau. It’s team at the beginning of the 1970s developed the R-60 missile and the R-73 was intended to replace it. It is known as the AA-11 “Archer” with NATO countries.
Missile features a wide angle infrared seeker and extreme maneuverability.
The R-73 is completed with a vectored trust system to makevery tight turns. It’s minimum range of fire is 0.3 km and missile is intended as a dogfight weapon in close air combats. Furthermore the R-73 is considered to be the most dangerous weapon system in close visual combat.
There were developed later variants of the R-73 missile:
– The R-73E missile features extended range;
– The R-73M1 (sometimes designated as R-73 RDM-1) features improved overall performance;
– The R-73M2 (R-73 RDM-2) has even better performance characteristics than it’s predecessor – the R-73M1;
– The K-74ME.
All these missiles have the same AA-11 “Archer” NATO designation.
| Model | R-73E | R-73M1 | R-73M2 |
| Entered service in | ? | 1982 | ? |
| Range against closing target | < 30 km | 30 km | 40 km |
| Range against receding target | < 15 km | 15 km | ? |
| Weight | 115 kg | 105 kg | 110 kg |
| Weight of warhead | 7.4 kg | 8 kg | ? |
| Type of warhead |
expanding rod |
||
| Speed |
Mach 2.5 |
||
| Guidance |
infrared |
||
| Kill probability | ? | 0.6 | ? |
| Length |
2.9 m |
||
| Diameter |
0.17 m |
||
| Fin span |
0.51 m |
||
| Carried by | Ka-50, Ka-52, MiG-29, MiG-31, Su-25, Su-27, Su-30, Su-33, Su-34, Su-35, Su-37, Su-39, Yak-141 | ||
Source enemyforces.net
Kh-25 ML (NATO designation AS-10 Karen) air-to-surface laser-guided missile
The Kh-25/Kh-25M (Russian: Х-25; NATO:AS-10 ‘Karen‘) is a family of Soviet lightweight air-to-ground missiles with a modular range of guidance systems and a range of 10 km. The anti-radar variant (Kh-25MP) is known to NATO as the AS-12 ‘Kegler‘ and has a range up to 40 km.Designed by Zvezda-Strela, the Kh-25 is derived from the laser-guided version of their Kh-23 Grom (AS-7 ‘Kerry’). It has now been succeeded by the Kh-38 family, but the Kh-25 remains in widespread use.
The Kh-25 is very similar to the later version of the Kh-23, with cruciform canards and fins.
The Kh-25MP has two versions of its homing head, 1VP and 2VP, sensitive to different frequencies.
The original Kh-25 entered service with the Soviet Air Force between 1973-5, equipping the Mikoyan-Gurevich MiG-23, MiG-27 and Sukhoi Su-17M. Since then it has been cleared for use on the MiG-21, MiG-29, Sukhoi Su-17/20/22 family, Sukhoi Su-24, Su-25 and Su-27. It can also be carried by attack helicopters such as the Kamov Ka-50.
Kh-25ML – semi-active laser guidance with tandem warhead that can penetrate 1 metre (39 in) of concrete.
|
Specifications |
|
| Weight | Kh-25ML :299 kg (659 lb)
Kh-25MP :315 kg (694 lb) |
| Length | Kh-25ML :370.5 cm (12 ft 2 in)
Kh-25MP 1VP :425.5 cm (167.5 in) Kh-25MP 2VP :435.5 cm (171.5 in) |
| Diameter | 27.5 cm (10.8 in) |
| Warhead | High explosive, shell-forming |
| Warhead weight | Kh-25MP :89.6 kg (198 lb), Kh-25MR :140 kg (309 lb) |
| Wingspan | 75.5 cm (29.7 in) |
| Operational
range |
Kh-25ML :11 km (5.9 nmi)
Kh-25MP :up to 60 km (32 nmi) Kh-25MTP : 20 km (11 nmi) |
| Speed | Kh-25ML :1,370–2,410 km/h (850–1,500 mph)
Kh-25MP :1,080–1,620 km/h (670–1,000 mph) |
| Guidance
system |
Laser guidance, passive radar, TV guidance, IIR, Satellite guidance,active radar homing depending on variant |
| Launch
platform |
MiG-21, MiG-23/27, MiG-29, Ka-52 , Su-17/20/22, Su-24,Su-25, Su-27, Yakovlev Yak-130
Kh-25MP : MiG-23/27, Su-17/22, Su-24, Su-25 |
Source wikipedia.org
KAB-500Kr guided bomb
The KAB-500Kr corrected air bomb is designed to engage stationary ground/surface small-sized hardened targets, such as reinforced concrete shelters, runways, railway and highway bridges, military industrial installations, warships, and transport vessels.
KAB-500Kr
| Weights: total/warhead/HE, kg | 520/380/100 |
| Dimensions: | |
| length, m | 3,05 |
| diameter, m | 0,35 |
| empennage, m | 0,75 |
| Bomb drop altitude, km | 0,5-5 |
| Carrier speed, km/h | 550…1100 |
| Root mean square deviation, m | 4…7 |
| Warhead type | concrete-piercing |
| (high explosive penetrator) | |
The aircraft is fitted with a 30mm GSh-301 cannon or a podded GSh-23 cannon installed under the fuselage. It can also deploy unguided B-8M and B-18 rockets, 250kg and 50kg bombs and cluster bombs.
KAB-500Kr guided bomb and B-18 Rocket pod
30mm GSh-301 cannon
30mm GSh-301 cannon
The GSh-301 is a modern Soviet single barrel autocannon with a high rate of fire. It arms the two most common types of Soviet multirole fighters, the MiG-29 and the larger Su-27.
The GSh-301 fires the 30x165mm round at a rate of fire of 1.500 to 1.800 rpm. Short bursts are fired. A 100 round burst destroys the barrel. Effective range is quoted as 200 to 800 m against aerial targets and 1.200 to 1.800 m against ground targets. Combined with targeting computer and laser range finder accuracy is reported to be good.
| Type | Autocannon |
| Caliber | 30x165mm Soviet |
| Mechanism | Short recoil operated |
| Barrel | 1.500 m barrel |
| Dimensions | 1.978 m long, 156 mm wide, 185 mm tall |
| Weight | 46 kg |
| Feeding | Single belt feed |
| Rate of fire | 1.500 – 1.800 rpm |
| Muzzle velocity | 860 m/s |
| Recoil | ? |
| Remarks | 2.000 round barrel life |
Source weaponsystems.net
GSh-23 cannon gun pod
GSh-23 cannon
The GSh-23 functions on the Gast principle. In this twin barrel setup the recoil from one barrel cycles the action of the other, allowing for an instant high rate of fire. The GSh-23 is belt fed from a single belt. The GSh-23L adds a muzzle brake that helps reduce recoil. Both GSh-23 and GSh-23L are solenoid fired.
The GSh-23 fires the 23x115mm round that is also widely used in other Soviet aircraft cannon. The rate of fire is 3.000 to 3.400 rpm and is instantly achieved as opposed to Gatling type weapons. The muzzle velocity of 715 m/s is low compared to other modern aircraft cannon.
Image: Makarov Aleksey
| Type | Autocannon |
| Caliber | 23x115mm AM-23 |
| Mechanism | Gas operated, Gast principle |
| Barrel | Twin barrel, 1.000 m, rifled, 10 grooves, 575 mm right hand twist |
| Dimensions | 1.387 m long, 165 mm wide, 168 mm tall |
| Weight | 50 kg |
| Feeding | Single belt feed |
| Rate of fire | 3.000 – 3.400 rpm |
| Muzzle velocity | 700 – 730 m/s |
| Recoil | 2.900 kg recoil force |
| Remarks | Muzzle brake |
Source weaponsystems.net
Image @danielrychcik.com
RADAR
The Yak-130 is fitted with the 8GHz to 12.5GHz Osa or Oca (Wasp) radar developed by NIIP Zhukovsky. The radar has the capacity to track eight airborne targets simultaneously, simultaneously engage four targets at all angles and simultaneously track two ground targets. The detection range against 5m² cross section targets is 40km in the rear direction and 85km in the forward direction. The lock-on range for operation in automatic tracking mode is 65km.
Osa or Oca (Wasp) radar
Osa or Oca (Wasp) radar developed by NIIP Zhukovsky @vitalykuzmin.net
| General data: | |
|---|---|
| Type: Radar | Altitude Max: 0 m |
| Range Max: 83.3 km | Altitude Min: 0 m |
| Range Min: 0.2 km | Generation: Late 1980s |
| Properties: Identification Friend or Foe (IFF) [Side Info], Pulse Doppler Radar (Full LDSD Capability), Continuous Wave Illumination |
| Sensors / EW: |
|---|
| Oca – (Yak-130, Osa) Radar Role: Radar, FCR, Air-to-Air, Short-Range Max Range: 83.3 km |
Source cmano-db.com
COUNTERMEASURES
The electronic warfare suite includes a chaff and flare dispenser, a radar warning receiver and active jammers.
Image @info-aviation.com
Image @sputniknews.com
ENGINES
Yak taxing with air intakes closed to keep out foreign objects the air instead are from a series of vents that open above the air intakes
The aircraft has a high thrust to weight ratio of about 0.85. The demonstrator is powered by two Slovakian Povazske Strojarne DV-2SM turbofan engines, each rated at 2,200kg thrust.
Production aircraft are fitted with two powerful high economy AI-222-25 turbofan engines, each rated at 2,500kg thrust and developed under a Russian and Ukrainian program by Motor Sich, Zaporozh’e Progress Design Bureau and the Moscow Salyut Motor Building Production Enterprise. The export variant of the Yak-130 can be fitted with the DV-2SM engines.
Engine automatic control system
Engines operation is managed by a duplex all-mode electronic hydromechanical automatic control system built around an electronic digital full authority controller of FADEC type with a redundant hydromechanical control loop. The automatic control system monitors engines technical status, service life reserve and working parameters, and manages power plant modes of operation, surge protection, starting. Source redstar.gr
AI-222-25 turbofan engine
AI-222-25 turbofan engines @ivchenko-progress.com
|
Maximum power (SLS, ISA σin=1) |
|
| Thrust, kgf (flat rated to ISA =+30 °С) | 2,500 |
| Specific fuel consumption, kg/kgf/h | 0.64 |
| Maximum power (H = 5,000 m; M = 0.6; ISA; σin=0.97) | |
| Thrust, kgf | 1,450 |
| Cruise power (H = 10,000 m; M = 0.6; ISA; σin=0.97) | |
| Thrust, kgf | 300 |
| Specific fuel consumption, kg/kgf/h | 0.875 |
| Dimensions, mm | 2,238 х 860 х 1,102 |
| Weight, dry (without propfan), kg | 440 |
| Specified service life, h | 3,000 |
Al-225-25 engine specification ivchenko-progress.com
DV-2SM engine
| Take-off thrust (kN) | 21,58 |
| Specific fuel consumption (kg/kN/hour) | 61 |
| Weight, dry (kg) | 474 |
| Engine Control System | Supervisor + Stand-by + Back-up |
| Time between Overhauls (hour) | 750 |
| Service Life (hour) | 3750 |
| Inlet mass flow (kg/sec) | 49,3 |
| Overall compressor pressure (-) | 13,6 |
| Turbine Inlet Temperature (K) | 1440 |
| Bypass ratio (-) | 1,4 |
DV2 engine specification htc-aed.sk
TA-14-130 APU
TA-14-130 is a contemporary auxiliary gas-turbine engine with the equivalent power up to 106 kW. This engine is designed for APU of Jak-130 aircraft. It is used for air turbine start of the main aircraft engines, supplying on-board AC electric power (200/115 V, power up to 20 kWA) and providing air conditioning for cockpit and cabins.
The engine is equipped with a highly efficient turbo compressor and integrated system of oil cooling. As a result, fuel consumption and the weight is reduced.
The engine is compliant with the contemporary market requirements and is equipped with a full-authority electronic digital control system that provides regulation, control and error detection as well as operation time counter.
APPLICATION: Jak-130
Closeup APU exhaust – Image: Makarov Aleksey
Technical features:
| Absorbed electric power of AC, kVA |
20 |
| Bleed air consumption, kg/s |
0,55 |
| Bleed air pressure, kgf/sm2 |
3,65 |
| Bleed air temperature, °C |
210 |
| Start and operation altitude, m |
9000 |
| Environmental temperature, °С |
± 60 |
| Weight (without generator), kg |
63 |
| Overall dimensions, mm |
835х507х440 |
Source aerosila.ru
Operators: Here
Russian Aerospace Forces to Receive 30 Yak-130 Aircraft By End of 2018: Here
General characteristics
| Type |
| Combat trainer |
| Country user |
| Russia, Algeria, Vietnam |
| Country producer |
| Russia |
| Crew |
| 2 |
| Engine |
| 2 × Progress AI-222-25 turbofan, 21.58 kN (4,852 lbf) each |
Yak-130 specification airrecognition.com
Basic Data:
| Mass: | |
| – takeoff, maximum | 9 000 kg |
| – takeoff, normal | 5 700 kg |
| – fuel, maximum: | |
| – in internal tanks | 1 750 kg |
| – in external tanks | 2 х 450 kg |
| – armament, maximum | 3 000 kg |
| Power plant | 2 turbofance |
| Takeoff thrust, ISA | 2 х 2 500 kg |
| Maximum thrust/weight ratio | 0,9 |
| Speed: | |
| – level flight, maximum | 1 050 km/h |
| – takeoff (full fuel load) | 200 km/h |
| – landing | 195 km/h |
| Maximum flight altitude | 12 500 m |
| Flight angles of attack | < 40° |
| Service range with maximum internal fuel | 2.000 km |
| Load factor:: | |
| – sustained at 4 572 m altitude (15 000 ft | 5,2 g |
| – maneuvering load factor limits | +8 g; -3 g |
| Airfield runway length | 1 000 m |
| Service life | 10 000 hours |
Basic data yak.ru
Updated Aug 08, 2017
Main material source: Wiki/Sputnik/foromilitar.com.ar/Air Force Technology, Aironautical World Trainers
