1. Domestic J-5 jet fighter
The J-5 is a subsonic jet fighter produced by Shenyang Aircraft Manufacturing Company. It is the first jet fighter made in China. aircraft. Shenfei began to imitate the MiG-17Φ jet fighter prototype provided by the former Soviet Union in early 1955. On July 19, 1956, the J-5 prototype successfully made its first test flight. Production was discontinued in September of the same year, and 767 aircraft were produced. The aircraft is mainly used for day interceptions and air combat, and also has certain attack capabilities. Its improved J-5A is equipped with a radar on the nose and is used for night interception air combat.
The J-5 adopts a single-seat, single-engine, nose-intake, and swept-back mid-wing layout. The sweep angle of the swept-back monoplane is 45°, and it is a double-spar structure. There are angle-controllable setback flaps on the inside of the wing. The aileron deflection angle range is ±18°. The landing gear bay is at the root of the wing, and the main landing gear is retracted in two bays on the wing. The all-metal semi-monocoque structure fuselage is a streamlined body with a circular cross-section, and the air intake is at the nose. The rear fuselage is equipped with a maneuverable speed brake. The vertical tail is divided into upper and lower sections. The lower section is fixed on the load-bearing inclined frame of the rear fuselage, and the upper section is removable. The vertical tail sweep angle is 55°41′. The rudder can rotate 25°. The horizontal tail sweep angle is 45° and is installed on the top of the lower section of the vertical tail. The elevator can rotate 32° upward and 16° downward. The front tricycle landing gear is single wheel. The nose landing gear retracts into the wheel well at the lower part of the front fuselage, and the main landing gear retracts into the wings. The main landing gear is equipped with buffers, and the nose landing gear is equipped with shock absorbers and sway absorbers. The main wheel tire pressure is 8.34×105 Pa (8.5 kg/cm2). The sealed single-person cockpit can throw away the hatch cover in an emergency, and the ejection seat ensures that the pilot can quickly and safely escape the aircraft in an emergency. The control system is hard control. The aileron trim tabs and elevator trim tabs are electrically controlled. The hydraulic system is used to retract and retract the landing gear, flaps, speed brakes, adjustable nozzles and control ailerons. The air-conditioning system is used for braking, sealing the cockpit, emergency landing gear retraction and emergency braking, etc.
It uses a turbojet-5 centrifugal afterburning turbojet engine with a static thrust of 2,600 kg and an afterburning thrust of 3,380 kg. The engine is a copy of the VK-1F engine of the Soviet Klimov Design Bureau, which is the engine of the MiG-17. After the Aviation Industry Bureau was established in 1951, it began to organize engine production and learn the Soviet Union's new jet engine production process data. With the assistance of the Soviet Union, the patented manufacturing rights of the VK-1F were introduced. In June 1956, a team including my country's well-known engine designer Wu Daguan successfully copied the turbojet-5 at Shenyang Aviation Engine Factory (now "Shenyang Liming Machinery Company"). In 1964, the production task was transferred to Xi'an Hongqi Machinery Factory. In 1966, it was converted into a final product and put into mass production. The turbojet-5 has an afterburning thrust of 3380 kg, a maximum thrust of 2700 kg, a rated thrust of 2400 kg, and a cruise thrust of 2160 kg. The fuel consumption rate in different states ranges from 2 kg/kg/h to 1.05 kg/kg/h. There is 1,170 kilograms of fuel inside the machine, and two 400-liter auxiliary fuel tanks are mounted externally.
Airborne equipment includes ultrashort wave command radio, radio compass, radio altimeter, beacon receiver, identification friend or foe, tail guard, range finder, etc. Two 23mm cannons are installed under the left side of the nose, and a 37mm cannon is installed under the right side of the nose. The ammunition reserve is 200 rounds. The aircraft is equipped with optical semi-automatic sights and two camera guns. A 100-250kg bomb can be hung under each of the left and right wings.
The wing is a swept-back mid-wing, and the deflection angle of the aileron is ±18 degrees. Two 23-1 23mm cannons are installed under the left side of the nose, and one H-37 37mm cannon is installed under the right side of the nose. The ammunition capacity is 200 rounds. The 23-1 cannon has a muzzle velocity of 680 meters/second and a rate of fire of 800 rounds/min; the H-37 cannon has a muzzle velocity of 690 meters/second and a rate of fire of 400 rounds/min. Two 100-250kg bombs can be hung under the wings.
Technical performance:
Wingspan 9.60 meters
Aircraft length 11.36 meters
Aircraft height 3.80 meters
Wing area 22.6 square meters
Main wheelbase 3.85 meters
Front main wheelbase 3.37 meters
Maximum take-off weight (with auxiliary fuel tank) 6000 kg
Normal takeoff weight 5340kg
Normal landing weight 4164kg
Empty weight 3939kg
Maximum fuel weight (inside the aircraft) 1170kg
p>(with auxiliary fuel tank) 1834 kg
Maximum level flight speed (height 3000 meters) 1145 km/h
(height 11000 meters) M0.994
Cruise speed 800 km/h
Stall speed 190~210 km/h
Practical ceiling (no plug-in, afterburner) 16,000 meters
Dynamic ceiling 17,500 meters
Climb time (0~10,000 meters) 3.7 minutes
Maximum climb rate 4,548 meters/minute
Maximum overload 8g
Maximum range (with auxiliary fuel tank) 1560 kilometers
Maximum range (in-plane fuel) 1020 kilometers
Endurance time (with auxiliary fuel tank) 2 hours and 50 minutes
Takeoff ground speed 235 km/h
Landing speed 170~190 km/h
Takeoff roll distance 590 meters
The landing roll distance is 825 meters
2. Domestic J-6 jet fighter
The main fighter of the Chinese Air Force is used for homeland air defense and to seize frontline air supremacy. It can also perform ground operations Attack mission. The J-6 is imitated and developed based on the Soviet MiG-19. Trial production began in early 1958, and the prototype flew for the first time on December 17 of the same year. In April 1959, the prototype was approved and mass production began.
The J-6 was first developed by the Shenyang Aircraft Factory (now the Shenyang Aircraft Corporation), which began developing it in 1953 based on the former Soviet Union's MiG-19 Wave (Л) and Ace fighters. The factory called it "Dongfeng 102" and the first flight was successful on September 23, 1959. The test pilot was Wu Keming. On September 30, it was officially announced that the first flight was successful. This is the prototype of the J-6 daytime version. Later, due to quality problems with the first batch of aircraft, the MiG-19 Ace aircraft was re-imited in 1961. The new aircraft was delivered to the troops on September 23, 1964, and was officially named J-6.
The J-6 aircraft is small in size, light in weight, has a large thrust-to-weight ratio, and has good maneuverability, making it suitable for close-range air combat. The F-6 aircraft has a simple structure, is easy to use and maintain, and is cheap. In addition to equipping the Chinese Air Force and Navy, it is also exported abroad. By the time production ceased in 1986, more than 4,000 aircraft of various models had been produced.
The main types of J-6 are:
J-6I: a high-altitude interception type modified in 1966. The deceleration parachute warehouse is modified from the belly of the aircraft to the root of the vertical tail.
J-6II: The J-6II is a further modification based on the J-6I. It first flew on March 25, 1969. An adjustable rectifying cone is added to the center of the inlet, and 8 intake valves are added to the outer wall of the inlet. A 30mm cannon and a 23mm cannon are installed under the nose, and there are no wing cannons.
J-6III: A supersonic day fighter modified on the basis of the prototype. The main improvement is to install a WP-6A engine and add a 2-stage adjustable rectifier cone in the center of the inlet. The wing chord length is shortened, the wingspan is shortened, air-to-air missiles are added, and three cannons are installed, thereby improving the air combat capability, increasing the level flight speed, and shortening the take-off and landing distance. First flight took place on August 5, 1969.
J-6IV: an all-weather supersonic fighter aircraft that first flew on September 24, 1970. The fuselage is lengthened, a domestic radar is installed on the nose, the air inlet lip adopts a thin structure, and the J-6III wing is selected, leaving only two cannons at the root of the wing, which can carry missiles.
J-6A: Also known as Dongfeng 103, it is an all-weather supersonic fighter modeled after the former Soviet MiG-19N aircraft. It first flew on December 21, 1975 and was manufactured by Guizhou Aircraft Company.
J-6B: Also known as Dongfeng 105, it is a copy of the former Soviet MiG-19NM all-weather missile interceptor. It is China's first all-weather missile interceptor. It first flew in 1963 and was manufactured by Nanchang Aircraft Company. .
JJ-6: The trainer type of J-6.
Jianzhan-6: The reconnaissance version of the J-6
The Jianjiao-6 has a special modification in recent years, namely the BW-1 stabilized aircraft. BW-1 is China's first fly-by-wire control and stable aerial testing machine. It is actually a testing machine for the fly-by-wire system. It provides a reliable aerial test method for my country's fighter aircraft to transform from mechanical control to electronic control. The front cabin of the aircraft was modified into a review test pilot cabin, and the rear cabin using a fly-by-wire control system was used as a safety cockpit, retaining the original mechanical control system. The small tie rod between the two cabin control sticks coordinates the disengagement and engagement of the front and rear levers of the fly-by-wire control and mechanical control via an electromagnetic clutch. When fly-by-wire control is implemented, the rear control column is linked to the mechanical lever. Once the fly-by-wire control fails, the rear control column can immediately take over the control of the aircraft through the emergency cut-off switch. During the modification, the BW-1 stabilization machine was equipped with a digital pneumatic stabilization system, an analog electro-hydraulic servo human sensing system, a digital target tracking and display system, an airborne data collection and recording and telemetry transmission system, a test signal amplifier, There are 136 items including atmospheric turbulence signal generators, various sensors, converters, electrical and hydraulic accessories, etc. In order to increase the installation space, in addition to dismantling and replacing relevant accessories of the original aircraft, a ventral equipment compartment and dorsal fin bulge were also installed. On November 5, 1988, the BW-1 first flight was reviewed and approved; on December 25, 1988, the ground taxied 3 times; from April 22 to 26, 1989, the modification flew 5 times; on June 21, 1989, the fly-by-wire control was carried out The system performed 2 closed-loop taxis; from June 27 to July 21, 1989, the human-sensing system tested 10 times; from August 8 to September 28, 1989, the fly-by-wire system performed 26 closed-loop tests. On September 28, the aircraft successfully completed all closed-loop test flights, creating a new field of research on flight quality and flight control technology in my country. The test flight implemented all design features. This machine won the first prize of the National Science and Technology Progress Award.
Main airborne equipment:
Communication radio, radar range finder, radio altimeter, and identification friend or foe.
Power plant:
Equipped with two WP-6 turbojet engines, with a maximum thrust of 2×25.5 kN and an afterburning thrust of 2×31.87 kN.
Weapons and equipment:
Three 23mm aircraft cannons, and air-to-air missiles, rockets, bombs and auxiliary fuel tanks can be mounted under the wings.
Dimensional data:
Wingspan is 9.04 meters, aircraft length (including pitot tube) is 14.64 meters, aircraft height is 3.89 meters, wing area is 25.0 square meters, sweep angle (1 /4 string) 55 degrees.
Weight:
The maximum take-off weight is 8820 kg, the normal take-off weight is 7400 kg, the fuel weight (inside the aircraft) is 1180 kg, the normal load is 1950 kg, and the external load is 500 kg.
Performance data:
Maximum level flight speed: M1.35/1450 km/h (altitude 11,000 meters)
Cruising speed: 960 km/h
Practical ceiling: 17500~17900 meters
Maximum climb rate: 180 meters/second (height 5000 meters)
Maximum range: (without auxiliary fuel tank) 1390 Kilometers / (with auxiliary fuel tank) 2200 kilometers
Endurance time: (with auxiliary fuel tank) 2 hours and 38 minutes / (without auxiliary fuel tank) 1 hour and 43 minutes
Takeoff roll distance: 515 meters
Landing roll distance: 610 meters
Maximum operational overload: 8g
3. Domestic J-7 jet fighter
1966 In August, the first J-7 made its maiden flight at the Shenyang Aircraft Factory, and the test pilot was Ge Wenyong. In 1964 and 1965, the Ministry of Aviation Industry determined that Chengdu Aircraft Factory and Guizhou Aircraft Factory would also produce J-7. Later, about a dozen basic J-7s were produced.
The J-7 base model is equipped with a 30mm aerial cannon and can be mounted with 2 PL-2 air-to-air missiles or 38 rockets. The intake cone of the air intake can be adjusted in three levels. The engine is a turbojet-7 turbojet engine with a thrust of 38.245 kN and an afterburner of 56.388 kN. The turbojet-7 was started by Liming Engine Manufacturing Company in 1963 based on the former Soviet Union's Р11-Ф-300 engine. It was accepted by the state in December 1966 and was produced in small batches in 1967. In 1968, it was transferred to Liyang Company for trial production, and mass production began in 1970. The first turning period is 100 hours, and the total life is 300 hours. After 1980, the turbojet-basic type was basically discontinued. In the early stages of use, many structural problems occurred that affected reliability, durability and maintainability. By changing the structure, replacing materials and improving processes, the faults were basically eliminated. Improvements include turbine blades and some important components manufactured with new processes, and redesigned afterburners and compressors. The turbine blades of the later Turbojet-7 were reduced from 31 to 24, which greatly improved reliability and reduced the engine's susceptibility to surge and stall flutter.