Xian JH-7
| Xian JH-7 | |
|---|---|
 A JH-7A "Flounder" of the Chinese Navy |
|
| Type: | Fighter bomber |
| Design country: | |
| Manufacturer: | |
| First flight: |
December 14, 1988 |
| Commissioning: |
1992 |
| Number of pieces: |
114 (2011) |
The Xian JH-7 ( NATO code name : "Flounder" ) is a twin-engine Chinese fighter-bomber manufactured by Xi'an Aircraft . It was the first Chinese fighter aircraft that was not based on a Soviet model. The JH-7 is also known as the FBC-1 Flying Leopard .
history
In the mid-1980s, China was looking for a replacement for the Harbin H-5 and Nanchang Q-5 . So the JH-7 was developed, which flew for the first time on December 14, 1988. The aircraft was designed as a multi-role combat aircraft and should meet the requirements of both naval aviators and the air force. Since the machine did not meet the requirements of the Luftwaffe, only about 40 of this first version were built for the Navy. After the success of the Super Étendard in the Falklands War , the naval version was preferred and the air force version was postponed. This was later developed in the form of the significantly revised, lighter and more modern JH-7A. In 1983 the WS-9, a license for the Rolls-Royce RB.168 Spey Mk202, was chosen as the engine . The first flight of the JH-7A took place on July 1, 2002. The cockpit is equipped with multifunction screens (MFD) and the pulse Doppler radar allows the use of laser, TV and radar-guided precision weapons. Between 2004 and 2009 around 100 machines were delivered to the Navy and Air Force. A total of 114 machines were built.
Technical specifications
The JH-7A is a two-seat, twin-engine shoulder -wing aircraft with side air intakes and tandem arrangement of the crew. The wings are swept between 55 ° (in the inner area) and 45 ° and had a boundary layer fence , which was omitted on the JH-7A. At the end of the fuselage there are four air brakes, below each of the two engines a stabilizing fin (JH-7A / EloKa: a central false keel ) and a container for the braking parachute. The main and nose landing gear are equipped with twin wheels, suggesting the possibility of operating from unpaved runways. The main landing gear is retracted forwards. The machine is controlled by a fly-by-wire system of the type KF-1, which has been further improved in the JH-7A.
| Parameter | Dates of the JH-7 |
|---|---|
| crew | 2 |
| length | 21.02 m (22.32 m with pitot tube ) |
| span | 12.80 m |
| height | 6.22 m |
| Empty mass | 14,500 kg |
| Max. Takeoff mass | 28,475 kg |
| Top speed | 1,808 km / h (at an altitude of 10,975 m) |
| Service ceiling | 16,000 m |
| Use radius | 1,759 km |
| Range | approx. 3,700 km |
| Engines | two XAE WS-9 Qingling turbofan engines |
| Thrust |
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| Armament |
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See also
Web links
Individual evidence
- ^ A b Adam Baddeley: The AMR Regional Air Force Directory 2011, pp. 24-25
- ↑ Jefim Gordon , Dmitri Komissarow: Chinese Aircraft . Polygon Press, 2008, ISBN 978-1-902109-04-6 .
- ↑ FliegerRevue February 2009, p. 67, data sheet JH-7A