Description:
The J-10 is a lightweight, single-engine, multi-role fighter developed by Chengdu Aircraft Industry Corporation (CAC) and 611 Institute for the People's Liberation Army Air Force (PLAAF). The high-performance J-10 aircraft has been designed as an air superiority fighter with air-to-surface capability. The aircraft's development started in the mid-1980s based upon the cancelled Israeli Air Force Lavi lightweight fighter. In the 1990s, the Russians joined the J-10 project providing the AL-31FN as the replacement engine for Chinese incapable WS-10 turbofan. The first J-10 prototype made its maiden flight in March 1998 and the aircraft achieved initial operational capability (IOC) with PLAAF by late 2003/early 2004.
The J-10 aerodynamic configuration is based on a delta-wing with canard foreplanes design with a single ventral air intake. All in, the J-10 is very similar to Eurofighter/Typhoon multi-role aircraft being procured by European countries. The J-10 aircraft is made of composite materials resulting in a high thrust-to-weight ratio with enhanced maneuverability and low drag thanks to its advanced aerodynamics. The flight control system is based on a 4-channel fly-by-wire (FBW) system. An engine digital control system provides for fuel consumption efficiency. The J-10 has been fitted with a glass cockpit and pulse-Doppler radar system capable of tracking 10 targets at ranges of up 100 km while engaging four of them simultaneously.
The J-10 aircraft has 11 external stations for weapons and auxiliary fuel tanks. For air-to-air engagements the aircraft can be equipped with PL-8 (a version of Israel's Python 3) infrared-guided short-range and PL-12 radar active medium-range missiles. Laser guided bombs, free fall bombs and rockets are provided for the air-to-ground attack role. In addition, the J-10 is provided with a single-barrel 23mm internal gun. Future plans call for the installation of the improved Chinese-built WS-10A turbofan in lieu of AL-31FN. The J-10 might be fitted with a detachable air refueling probe to extend its radius of operation or carrying a greater load of weapons. A pilot's helmet-mounted sight system is under study.
The tandem two-seat J-10S aircraft was developed to provide training to PLAAF J-10 equipped regiments. The maiden flight was carried out in December 2003 and achieved IOC in early 2006. The J-10S advanced trainer keeps all the equipment, avionics and weaponry provided to the J-10A air superiority fighter as well as its performance thus being a fully operational combat aircraft. The PLAAF may be evaluating potential derivatives of the J-10S aircraft such as a suppression of enemy air defenses (SEAD) and electronic attack aircraft. J-10AS and J-10BS designations refers to tandem two-seat variants based upon the J-10A and J-10B aircraft respectively.
Specifications Accommodation: Crew 2
Guns: Main Gun Caliber 23 mm
Dimensions: Length 15.5 m, Wing Area 39 square meter, Wingspan 9.7 m
Weights: Fuel Load 4,500 kg (9,921 lb), Max Weight 18,000 kg (39,683 lb), Min Weight 8,300 kg (18,298 lb), Operational Weight 13,200 kg (29,101 lb)
Engine/s Performance: Thrust 27,557 lb (12,500 kg) with afterburning
Performance: Radius of Operation 1,100 km (594 nm), Take Off Run Distance 500 m (1,640 ft), Top Speed Mach 2.20 (2,629 kph), Top Speed at Sea Level Mach 1.20 (1,434 kph)
G Loads: Max Maneuvering Load Factor 9 g, Min Maneuvering Load Factor -3 g
Other: External Stations 11, Number of Engines 1
Operators
China
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Notes (*) lead contractor
IOC: Initial Operating Capability
FOC: Full Operating Capability
CEP: Circular Error Probable
Comm: Commissioning Date
Meters (m) Kilometers (km) Nautic Miles (nm) Inch (in) Yard (yd) Foot (ft) Millimeter (mm)
Pound (lb) Kilogram (kg) kN (KiloNewton) Ton (t)
Meters per Second (mps) Kilometers per Hour (kph) Knot (kt) Miles per Hour (mph)
Liter (l) Galon (gl)
Year (yr) Minutes (min) Second (sec)
Shaft-Horse-Power (shp)
China