fuselage
It is mainly an all-metal semi-hard shell structure, and a large number of parts are numerically controlled or chemically milled. The cross section of the fuselage is basically oval. The maximum design overload of the airframe structure is+12g and -6.4g, and the service life is 10000 hours.
tail
Cantilever all-metal structure, similar to wing structure. The sweepback angle of the leading edge of the vertical tail is 45. The sweepback angle of the leading edge of the flat tail is 30. There is a rear fairing between the cockpit and the vertical tail. Full-motion horizontal tail, with adjustable artificial force sensing system controlled by table speed. The rudder driven by the double-body hydraulic servo motor also has an adjustable artificial force sensing system.
undercarriage
The first three points are retracted, and the main landing gear is below the side of the engine inlet. The front and rear wheels are single-wheel low-pressure tires, and the tire pressure at normal takeoff weight is 4.04×105pa (4.1kg/cm2). The main tire size is 6 15×255- 10. The front tire size is 380× 150-4. The main landing gear has steel disc brakes and anti-skid devices. There is an emergency braking system. There are hydraulic front wheel steering mechanism and landing hook on the tight support type. In order to make the guns in the gun cabin shoot to the ground, the installation position of the front landing gear deviates from the center line of the fuselage to the right.
powerplant
The fuselage is equipped with two "Razak" 40 C6 turbofan engines from Sigma/Tubomeka, with a single static thrust 13.24 kN .. Each air inlet on both sides has a diverter plate. The outer wing has two integral fuel tanks, the middle wing has one fuel tank, and the fuselage has three fuel tanks, carrying 1900 liters or 2040 liters of oil. A 450-liter or 625-liter auxiliary fuel tank can also be hung on each internal hanger under the wing.
passenger cabin
Series two-seat supercharged type, two cockpits open backwards and upwards, and two-seat control is standard. The coach-type rear seat is slightly higher. The prototype and French coach models adopt the AJRM4 ejection seat of Martin-Baker Company, which can eject at zero height (including ejection through the hood) at a speed of167 km/h. ..
Belgium adopts Martin-Baker B 10N zero zero ejection seat. Egypt and Cadal are equipped with F 10N seats. NGEA is an American S-III-S3AJ zero-zero ejection seat manufactured by German patent. The luggage compartment is in the tail cone and the door is on the right.
system
There is air conditioning and anti-fog equipment in the cockpit. Two independent redundant hydraulic systems with the pressure of 207×105pa (211kg/cm2) are used to drive the control surface, landing gear, speed brake, flaps, brakes and front wheel steering mechanism.
The main power supply is two 28V 9KW starters/generators. There is also a 36-amp-hour nickel-cadmium battery for the engine to start by itself. Two static converters provide 1 15 volts 400 Hz AC to the accessory system. The air conditioning system is provided with compressed air by the engine, which is used for cabin pressurization, air conditioning, pilot's anti-load suit and fuel tank pressurization.
airborne equipment
There is a large electronic cabin in the rear fuselage, in which most radio and navigation equipment are installed. Standard equipment includes VHF and UHF radio stations, IFF/code selection and identification devices, VHF omnidirectional radio beacon/instrument landing system beacon, TACAN system, gyro platform and intercom device.
The attack type is equipped with KM808 head-up display, radar altimeter, LSI6000E attitude and heading reference system, Doppler navigation system with LR- 14 16 navigation electronic computer, aerial judgment control device for bombing effect, speed sensor and electronic countermeasure equipment.