In the early 1990s, the Soviet government asked the industry to develop a new aircraft to replace the Czech-made Aero L-29 Delfín and Aero L-39 Albatros jet trainers. Five design bureaus put forward proposals. Among them were Sukhoi's S-54, Myasischev's M-200, Mikoyan's MiG-AT, and Yakovlev's Yak-UTS. In 1991, the other proposals were dropped and only the MiG-AT and Yak-UTS remained.
Development of Yak-UTS started in 1991 and the design was completed in September 1993. The same year, Yakovlev entered an agreement with the Italian company Aermacchi to work together on the plane, which now became Yak/AEM-130. The Yak-130 version was to be offered for the Russian and the M-346 version for the Italian market. On 10 April 2002, it was announced that Yak-130 had been chosen as the winner of the tender for trainer aircraft for basic and advanced pilot training, beating the MiG-AT.
Yak-130 completed its maiden flight, registered as RA-431130, on 25 April 1996 at Zhukovsky. The plane was put on display for the first time at the Paris Air Show in June, 2005. The same year, the Russian Air Force made its first order for 12 Yak-130 planes. In May 2005, the first serially produced Yak-130, assembled at the SOKOL plant in Nizhny Novgorod, performed its maiden flight. In 2009, the Russian Air Force received its first 3 planes, and is expected to receive rest from the initial batch of 12 planes during 2010. The Russian airforce intends to buy at least 72 Yak-130s, enough to equip four training regiments.
The Yak-130 aircraft is a swept mid-wing monoplane of a classical configuration with two-seat tandem cockpit and two turbofan engines with 2500 kg thrust each.
Each cockpit of the aircraft is equipped with three multifunctional colored 6x8 inches LCD displays without electromechanical
instruments, as well as collimator aviation indicator and helmet-mounted target designation system in forward cabin.
The aircraft aerodynamic configuration and flight and power plant controls performance make it possible to operate the aircraft essentially at all flight conditions, typical of modern and advanced combat aircraft. The aircraft leading edge extensions and air intakes layout enable a steady controllable flight at angles of attack up to 40 deg.
High thrust/weight ratio provides high sustained maneuvering load factors, takeoff performance and rate of climb.
The air intakes and landing gear design with high take-off/landing performance make it possible to operate the aircraft from unpaved runways small unprepared airfields.
The aircraft is equipped with complex fly-by-wire control system that functions as automatic flight control system, active flight safety system and provides in training stability and controllability characteristics change depending on the aircraft being simulated.
The aircraft combat training system provides simulation of:
•air combat with tracing, detection, identification, locking-in, and tracking of air targets, with launching of air-to-air missiles fitted with radar and IR homing heads, with imitation of enemy missiles and jamming launching and with application of airborne defensive aids system;
•interaction with other aircraft in group and with ground and air control units;
•air-to-ground attacks with launching of air-to-surface missiles fitted with radar, TV, IR and laser homing heads, with bombs and rockets releasing, gun firing, with imitation of enemy surface-to-air missiles and jamming launching and with application of airborne defensive aids system.
Simplicity of the structure, high reliability of the airframe, power plant and aircraft systems, long service life and full self-sufficiency of the aircraft as well as high maintainability together with a low cost of the life cycle and high flight performance provide high-quality training of the pilots in the shortest possible time and meet efficiently different military challenge.
- takeoff, maximum 9 000 kg
- takeoff, normal 5 700 kg
- fuel, maximum:
- in internal tanks 1 750 kg
- in external tanks 2 ? 450 kg
- armament, maximum 3 000 kg
Power plant 2 turbofance
Takeoff thrust, ISA 2 ? 2 500 kg
Maximum thrust/weight ratio 0,9
- 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
- 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