This question is a matter of personal opinion and wisdom.
In my opinion, I think they are F-16 and J-10.
The following is the brief introduction of the F16 fighter:
Wingspan: 9.45m
Total length: 15.09m
Height: 5.09m
Empty weight: 7,070kg
Maximum take-off weight: 16,057kg
Internal fuel capacity: 3,160kg (4,060L)
Maximum load capacity: 6,800kg
Engine: Pamp; one WF100-PW-200 turbofan engine.
Engine thrust: 11,350kg
Maximum level flight speed: 2483km/h
Maximum climb rate: 15,240m/min
Ceiling limit: 15,240m (46,250ft)
Maximum range: 3,890km
Electronic system
Fire control radar: WestinghouseAN/APG-66 (V)2A Maximum search distance: 185km (100nm) Navigation system: LittonLN-93 laser gyroscope
Edit this paragraph Electronic warfare system
Radar warning system (RWS): LittonAN /ALR-56M radar early warning system electronic countermeasures system (ECM): AN/ALE-47 infrared decoy, interference wire spreader, RaytheonAN/ALQ-184(v)2 electronic countermeasures pod
Weapons System
The aircraft is equipped with an M-61A1 aircraft cannon with 500 rounds of ammunition. ***9 weapon hardpoints: one at each end of the left and right wings, and 3 under each wing. The two wing end hardpoints can carry infrared-guided air-to-air missiles; the hardpoints under the belly can carry 1,000 kilograms of payload; the inner wing hardpoints can each carry 1,587 kilograms; and the center wing hardpoints can each carry 1,134 kilograms. Load; the two outer wing hardpoints and wing end hardpoints can each carry a load of 113 kg.
Structural details
Overall design
The F-16 fighter jet adopts slat wings, air combat flaps, wing-body fusion, relaxed static stability, New technologies such as fly-by-wire control and high-overload cockpit are used to improve the aircraft's air combat performance.
Materials
The structural materials of the F-16 are 80.6% aluminum alloy, 7.6% steel, 2.8% composite materials, 1.5% titanium alloy, and 7.5% other materials.
Layout
The overall layout of the F-16 adopts the "relaxed static stability" technology in the follow-up control layout. Compared with the conventional layout, the wing has been moved forward by 40.6 cm, thus moving the aerodynamic center forward. The static stability is slightly negative at Mach 0.9 and 8% at Mach 1.2. The aircraft relies on the "stability augmentation system" to automatically control the rudder surface and maintain stable flight. The benefits of this are to reduce the size of the tail, reduce the structural weight and resistance, improve the maneuverability of the aircraft, and increase the maneuverability.
Wing
The F-16 uses a cantilever mid-wing with a plane geometry of a tangent triangle. The leading edge sweep angle is 40°. The aspect ratio is about 3.0, the relative thickness is about 4%, and the basic airfoil is NACA64A-204. The leading edge of the wing has leading edge flaps that automatically deflect as the angle of attack and Mach number change to change the curvature of the wing, allowing the aircraft to maintain effective lift at high angles of attack. There is a full-span flaperon on the trailing edge of the wing, which can be used as a general flap to increase lift, and can be differentially operated left and right for lateral control. The large swept-back wing extending forward from the leading edge of the wing root along both sides of the fuselage can control vortices, increase lift at high angles of attack, improve maneuverability and stability, and reduce the wing area.
According to calculations, the use of slat wings reduces weight by 222 kilograms compared with conventional wings. The internal structure of the wing is composed of beams and ribs, and the upper and lower parts are covered with integral plate skins.
The body
adopts a semi-monocoque structure. The shape is short and thick, and it is connected to the wing in the form of a wing-body fusion body, so that the fuselage and the wing are smoothly combined, thereby reducing drag, improving lift-to-drag ratio, increasing stiffness, and increasing fuselage volume by 9%. And the body weight is reduced by 258 kilograms.
Tail
Fully moving horizontal tail, the plane geometry is similar to the wing, the dihedral angle is 25°, the rear of the horizontal tail root fairing is a cracked speed brake, the maximum opening 60°. The vertical tail is high, the stabilizer surface is large, the stability is good at large angles of attack, it can prevent spin, and it has a full-span rudder. The vertical stabilizer is a multi-beam and multi-rib aluminum alloy structure, and the skin is made of carbon fiber composite material. The dorsal fin in front of the vertical tail root fairing is fiberglass. The horizontal tail is composed of a carbon fiber composite cover plate, an aluminum honeycomb sandwich core, a titanium alloy beam and a steel leading edge. The ventral fin is an ordinary aluminum alloy structure.
Power Plant
The early F-16 was equipped with a Pratt & Whitney F100-PW-100 turbofan engine, with a maximum thrust of 7,400 kilometers. F-16 Fighter
catties, with an afterburner thrust of 11,340 kilograms. Starting in 1984, the U.S. Air Force required F-16s produced by General Dynamics to be installed with General Electric's F110-GE-100 turbofan engines, and required that the two engines be interchangeable. The F-16C "Block-50", which began production in 1991, was equipped with F-100-PW-229 and F110-GE-129 engines with a thrust of 13,163 kg. A fixed-geometry abdominal air inlet equipped with a boundary layer baffle is positioned for air combat in the Mach 0.8-1.0 speed range. Using a fixed air inlet saves 180 kilograms of weight compared to using an adjustable air inlet. The abdominal air inlet was chosen to minimize interference with the airflow during maneuvers and to avoid inhalation of cannon smoke. There is an air refueling port above the fuselage at the rear of the cockpit. The pylon under the fuselage can hang a 1136-liter auxiliary fuel tank, and the pylon on the inner wing can hang a 1400-liter auxiliary fuel tank.
Cockpit
The cockpit of the F-16A and F-16C is a single-person air-conditioned cockpit. In order to improve the driver's field of vision, a bubble-type canopy is used. This new type of canopy allows the driver's upper hemisphere field of vision to reach 360°, 260° from one side to the other, 195° from front to back, and 40° from side to side. The front and lower sides are 15°. Using Douglas's IE-2010 ejection seat, it can safely eject at zero altitude and within a speed range of 0-1100 km/h. The seat is tilted back 30° and the footrest position is raised, which can enable the driver's anti-overload capability to reach 8-9G in a short period of time. The F-16B and F-16D are tandem dual cockpits. The two cockpits are equipped with a complete set of control devices, display devices, instruments, electronic equipment and life-saving systems, which can be used for training and combat. The layout of the second cockpit is basically the same as that of the F-16A and F-16C, and has all system control functions. The front and rear cockpits are separated by two transparent glass panels, and both the front and rear cockpits have good visibility.
Edit this section of airborne equipment
The main equipment of the early F-16A was: APG-66 pulse Doppler radar, with a downward-looking range of 37-56 kilometers and an upward-looking range. 46-74 kilometers; F-16 fighter AN/ARN-108 instrument landing system; SKN-2400 inertial navigation system; radar photoelectric display equipment; central atmospheric data computer; flight control computer, etc. The F-16A is equipped with AN/APG-66 pulse Doppler fire control radar. There are four working states during air combat, namely, looking up to search and track, looking down to search and track, fighting to automatically intercept the target, and working automatically. For a target with a radar reflection area of ??5 meters, the detection distance of the APG-66 radar is 60-90 kilometers when looking up and 46-65 kilometers when looking down. For large targets such as the Tu-95 aircraft, its maximum detection distance can reach about 140 kilometers.
In the air-to-ground working state, the APG-66 radar has 7 working modes: air-to-ground ranging, real beam map mapping, extended real beam map mapping, Doppler wave speed sharpening, beacon, image freezing, and Sea search. The improved F-16C uses the AN/APG-68 fire control radar, which is developed from the APG-66. Mainly three components have been improved, namely the programmable signal processor, the transmitter and the low pulse repetition frequency component. It is said that the detection range of APG-68 is 40% greater than that of APG-66. This kind of radar has the capabilities of reprogramming as requirements and weapons change, high-resolution map surveying, and over-the-horizon target recognition. It can be used with "Sidewinder", "Sparrow", AIM-120 and other air-to-air missiles. It can track 10 targets at the same time in the air-to-air side scanning and side tracking state. When using the aircraft gun, you can first use the lead angle to calculate the optical display and fast hotline display mode. When performing ground missions, there are 8 working states available, namely continuous calculation of hit point, continuous calculation of throw point, throw, photoelectric guided weapon release, strafing, beacon, visual landmark point and manual method. In addition, compared with the F-16A, the F-16C also has night low-altitude navigation and targeting infrared pod systems, and the display device and computer have also been improved.
Edit this paragraph for electronic system details
Offensive system
AN/APG-66 pulse Doppler radar, with a maximum search range of 185 kilometers; AN/AAQ-14 "Blue Shield" navigation crane F-16 fighter cabin. "Pave Penny" laser tracking pod, "HAM" targeting system pod, AN/APX-101 identification friend or foe.
Defensive systems
AN/ALR-56M threat warning receiver, AN/ALR-69 radar early warning system, AN/ALE-74 radar early warning system (replaces ALR-69) ; AN/ALQ-119 electronic jamming pod, AN/ALQ-131 electronic jamming pod, AN/ALQ-178 internal electronic jamming system and AN/ALQ-184 electronic jamming pod; AN/ALE-40, AN/ALE -47 infrared bait and interference wire spreader.
Communication system
AN/ARC-164 or AN/ARC-126 VHF radio, KY-58 secure voice communication system
Navigation system
p>LN-93 laser gyroscope, AN/APN-132 radar altimeter, AN/ARN-108 instrument landing system, AN/ARN-118 TACAN system, AN/AAQ-20 "Explorer" navigation system, global positioning system.
Edit the detailed description of weapons and equipment in this paragraph
Aircraft gun
The F-16 aircraft is equipped with an M61A1 6-barreled aircraft gun with 515 rounds of ammunition. It can be used with radar and computer to calculate the lead angle, and the effective range is about 1,000 meters.
External contact points
The F-16A has 9 external contact points: 1 on the left and right wing tips, 3 under the left and right wings, and 1 on the belly of the fuselage. The wingtip and outer wing pylons can only carry Sidewinder missiles. The wingtip pylons can withstand a maximum overload of 9g, and the outer wing pylons have an overload limit of 5.5g. The center rack of the wing can be mounted with combat missiles or various air-to-ground weapons. The inner wing rack can be mounted with guided bombs, nuclear bombs and conventional bombs, air-to-ground missiles, sub-munition boxes and rockets or a 1400-liter For the auxiliary fuel tank, the maximum overload capacity of these two pairs of pylons is 5.5g. The belly rack of the fuselage can hold bombs or a 1135-liter auxiliary fuel tank. The maximum external load of the F-16A is 4760 kg (engine oil) and 6890 kg (internal minus).
Air-to-air missiles
The main weapon of the F-16A is the "Sidewinder" air combat weapon. "The air-to-air missile has the model number AIM-9L, and there is also an export version numbered AIM-9P-3.
The maximum range of AIM-9L is about 7 kilometers, the maximum overload is 26-35g, and the off-axis launch angle is plus or minus 30 degrees. It has a certain omnidirectional attack capability and has good actual combat results. AIM-9P-3 is composed of AIM-9 or Improved from AIM-9J, its performance is not as good as AIM-9L. Compared with the F-16A, the number of external contacts of the improved F-16C has not changed, but it can mount the "Sparrow" medium-range air-to-air missile. The more advanced AIM-120 advanced medium-range air-to-air missile has now become the standard weapon of the F-16C/D, and the F-16A/B cannot be loaded. After the F-16C is equipped with the "Blue Shield" nacelle, the aircraft can perform laser irradiation when launching laser-guided bombs. The newly produced F-16C can also use ground attack weapons such as air-to-ship missiles, anti-radar missiles, and "Baby" AGM-65 air-to-surface missiles.
The aircraft is equipped with an M-61A1 aircraft cannon with 500 rounds of ammunition. Weapon hardpoints: one at the left and right wing ends, three under each wing, and one on the belly, for a total of nine hardpoints. The mounting points on both wings can carry infrared-guided air-to-air missiles. The underbelly hardpoints can hold 1,000 kilograms of load, each of the inner wing hardpoints can hang 1,587 kilograms of load, and the center wing hardpoints can each hang 1,134 kilograms; the two outer wing hardpoints and the two wing end hardpoints can each hang a load of 1,000 kilograms. 113 kg. The weapons that can be carried include: AIM-9 "Sidewinder" (2 pieces), AIM-120 missiles (up to 6 pieces), AGM-65 "Maverick" air-to-surface missiles (2 pieces), AGM-88 "Ham" High-speed anti-radar missiles (2 pieces), Mk-82 (6 pieces), Mk-84 (2 pieces), CBU-87 (4 pieces), CBU-89 (4 pieces), CBU-97 (4 pieces), CBU -103 (4 pieces), GBU-10 (2 pieces), GBU-12 (6 pieces), GBU-31 (4 pieces).
Development background
In the mid-1960s, the Vietnam War broke out, and the United States' second-generation fighter jets, such as the F-4, were put into actual combat. The characteristics of this generation of aircraft are strong emphasis on high-altitude, high-speed performance and multi-purpose capabilities, while not paying enough attention to maneuverability. Judging from the actual combat effects, the development of the second-generation fighter jet was not very successful; it can even be said that it took a detour. This is not to say that its technical level and performance have not improved, nor is it that there is a problem with the development work itself, but that the prediction of the combat method is inconsistent with the actual situation. As a result, the United States began to consider developing third-generation fighter jets in the mid-to-late 1960s. In January 1972, the U.S. Air Force officially proposed a "light fighter" development plan. The purpose was to verify the use of new technologies on fighter jets, and it was not determined to develop a production model. In April 1972, the U.S. Air Force selected General Dynamics' 401 and Northrop's P-600 from the five companies that submitted bids for the "Light Fighter Program" and signed a contract requiring each company to Build two prototypes and compete in test flights. The military designation of General Dynamics' 401 program is YF-16; the military designation of Northrop's P600 is YF-17.
The third-generation fighter has the following main design features:
(l) Excellent flight performance, emphasizing mid- and low-altitude transonic maneuverability and long-range combat capabilities;
(2) The airborne electronic equipment is advanced, it has good all-weather combat capabilities, and the downward shooting capability is greatly improved;
(3) The airborne weapons have strong damage power. It has quite strong close-combat firepower, and is generally equipped with medium- and long-range omnidirectional and full-height interceptor missiles; (4) It has outstanding air combat capabilities, but many also have good ground attack capabilities;
(5) The aircraft has good reliability and maintainability, and has great potential for improvement and development.
At the beginning of its design and manufacturing, the F-16 adopted many new technologies, which were very advanced at the time. These new technologies mainly include: edge wings. A wing with a large sweep angle and a sharp leading edge is installed along the front fuselage to provide controllable vortices at the connection between the wing and the fuselage, thus keeping the boundary layer from separating even at high angles of attack, improving Lift and stability. Leading edge maneuverable flaps.
This flap is intended to allow the wing airfoil to have variable camber, which can improve the lift-to-drag ratio during sustained high-g-turns. Wing-body fusion. The shape of the F-16 is said to have been selected from more than 50 proposals. It is characterized by careful rectification of the joints of the wing and fuselage to make them smooth and integrated. The main advantages are to reduce wave resistance, improve lift-to-drag ratio and transonic flutter boundary, and enhance stiffness, so that the aircraft has good maneuverability. And increase the interior volume and reduce the weight of the aircraft. High overload cockpit. Ordinary seats are tilted back 12 to 13 degrees, while the F-16 uses a high-overload cockpit with seats tilted back 30 degrees and the footrests are raised. This posture can improve the pilot's ability to withstand overload by at least 0.6-1G, and can generally withstand up to 9G, exceeding the original allowable 7.3g. In addition, the pilot's visual function can be maintained. The fly-by-wire control system is mainly composed of signal conversion device, flight control computer, cables and action devices. This control system is a system that converts the control signals sent by the pilot into electrical signals through a converter, and then directly transmits them to the autonomous steering gear through cables. It has the advantages of simple structure, small size, light weight, easy installation and maintenance. , improves the aircraft control quality, increases the reliability of the control system, and reduces the workload of flight demonstrations. Relax static stability. The use of relaxed static stability technology means that the strict restrictions on static stability are relaxed. The aerodynamic center can be very close to the center of gravity, or coincide with it, or even in front of the center of gravity. The static stability of the aircraft becomes extremely small or unstable. Therefore, the static stability of the aircraft is negative when flying at low speeds. During flight, it mainly relies on the "stability augmentation system" to automatically control the rudder surface to ensure stable flight; when flying at high speed, The aircraft's static stability is positive. The advantage of this is that it can reduce the size of the tail, reduce the structural weight and resistance, and improve the maneuverability and maneuverability of the aircraft. Use composite materials. The tail of the F-16 aircraft is made of composite materials, which is 30% lighter than the tail made of aluminum alloy. The cockpit of the F-16 aircraft uses a bubble canopy. The pilot's field of view is very wide. The field of view in the upper hemisphere reaches 36O degrees, 260 degrees sideways, 195 degrees front and rear, 40 degrees sideways and lower, and 15 degrees front and lower. The pilot's seat can be tilted back 30 degrees. This is conducive to improving the pilot's ability to withstand overload. It is said that its ability to withstand overload in a short period of time can reach 8-9g. In order to facilitate the pilot to control the aircraft while leaning back, the F-16 adopts an unprecedented "side stick" solution, that is, the control stick is mounted on the armrest of the seat. This also improves the pilot's ability to control the aircraft in a high-mobility environment. This gives the F-16 the characteristics of light structural weight, large external load, and relatively good air and ground combat capabilities. Due to the advanced aerodynamic layout of the F-16 aircraft and the high thrust-to-weight ratio of the engine, its flight performance, especially maneuverability, is quite good. The maximum flight speed of the F-16 is not much different from that of most second-generation fighter jets, about M2; but its maximum flight speed is high, reaching 1,480 kilometers per hour. Due to the large thrust-to-weight ratio and low wing load of the F-16 aircraft, its maneuverability is quite good. The horizontal speed increase performance of the F-16 before M1.5 is quite good. At an altitude of 6,000 meters, it only takes 19 seconds to increase the speed from M0.9 to M1.2, and 48 seconds to increase the speed to M1.5. The F-16 has a large available lift coefficient and low wing load, so the instantaneous hovering angular velocity is large. When flying at ultra-low altitude and low speed, its instantaneous hovering angular speed can reach 25.5 degrees/second. The stable hovering performance is also good. When the flight speed is M0.7, its hovering radius is only 650 meters. When the flight altitude exceeds 11,000 meters, especially when flying at supersonic speeds, its hovering performance decreases significantly. The ceiling of the F-16 is not very high, about 18,000 meters, but its climbing performance is very good. At sea level, its maximum climb rate is about 305 meters/second; at an altitude of 6,000 meters, the climb rate is 183 meters/second; at an altitude of 9,000 meters, its climb rate is still 120 meters/second. When the speed exceeds M1.5 and the altitude is greater than I1000 meters, the climbing performance declines rapidly. The F-16 aircraft has better aerodynamic performance, higher internal fuel load coefficient, and lower engine fuel consumption, so the aircraft has a longer range. Its range without auxiliary fuel tanks is 1,825 kilometers, and its maximum transition range when three external auxiliary fuel tanks are connected is about 3,800 kilometers.
When performing interception missions, the combat radius can exceed 900 kilometers; when performing air patrols, the combat radius is about 700 kilometers; when performing ground attack missions, its combat radius is about 440-1,400 kilometers depending on the external connection and flight profile.
J-10 parameters
Power:
AL-31FN turbofan engine
The first batch of production models of the J-10 will use The proven Russian-made AL-31FN turbofan engine. The Su-27 family also uses the AL-31 series engines, but the FN version adds a completely redesigned access compartment. The setting of this inspection cabin is a standard Russian style. In the original AL-31 model, it was located above the engine and also included part of the outer side of the upper compressor casing. However, the FN type's inspection cabin was adjusted to match that of Western fighter engines. The inspection compartment is in the same position, located outside the lower casing of the engine and compressor. In addition to the engines used in J-10 prototypes and pre-production models, Russia is said to have provided 54 AL-31FN units to China at one time in 2001 (other sources reported that it was 100 units). These engines are used in the first batch of production J-10s. However, Russia refused to provide China with a production license for this type of engine. For this reason, China is developing a domestic engine that can replace the AL-31FN. However, even if all J-10s will use the AL-31FN, China will also seek a more advanced variant. Its most important technical requirement is to be equipped with an axial 360-degree vector nozzle to improve the maneuverability of the aircraft. And the propulsion efficiency brought about by the effective cooperation between the engine and the fuselage. This engine made its first appearance at the Zhuhai Air Show in 1998. Russia clearly understood China's potential interest in the engine. In fact, engine vector control technology, strangely ignored by the West, has gained wide popularity in Asia, first adopted by fighter jets equipped by the Indian Air Force, then Malaysia, and now probably China.
Looking to the future, China may eventually adopt the AL-41 engine of the "Saturn" company. Currently, this type of engine is being developed for Russia's next-generation fighter jets. The volume of AL-41 may be the same as AL-31, but the thrust will be increased by 30 to 40%. Therefore, the AL-41 may become a potential choice for future J-10 models, giving it the same combat capabilities as the F-16 Block 60, which is also in the proof-of-concept stage.
At present, the powerful and fuel-efficient AL-31FN provides strong support for the J-10's superb performance in air combat, making it capable of flying at high speeds, with high climb rates, and during large overload maneuvers. No need to worry about engine shutdown. Due to its extremely high fuel efficiency, this type of engine enables the fighter aircraft to perform exceptionally well when performing long-range penetration missions. In addition, the J-10 has a built-in fuel tank with a capacity of 5,000 liters. Although this is 700 liters less than the F-16 with two conformal fuel tanks, the fighter can still achieve an ideal combat radius while carrying a larger load. The J-10 can also carry three auxiliary fuel tanks and has the ability to receive fuel in the air. However, since Russia refuses to provide a production license for the AL-31FN, and considering that China has been working hard to achieve the localization rate of equipment procurement, it is very likely that the J-10 will use a domestic engine in the future, such as that produced by Liming Engine Company. WS-10A. But the information currently known only includes the thrust level (similar to the AL-31) and layout of the WS-10A (a two-shaft turbofan engine with a small bypass ratio and an afterburner), and Dawn Company has planned to develop this engine. Install vector nozzles.
Parameters
J-10 fighter structure diagram
Considering that China clearly regards U.S. fighter jets as its main air threat, and the design of U.S. fighter jets has always emphasized The ability to seize air superiority, so it is not difficult to understand that China regards air-to-air combat capabilities (including offense and defense) as the main need for the development of its fighter jets.
In the same way, the structural design of the J-10 emphasizes that the maneuvering overload must reach 9G (a goal pursued by all the latest fighter jets). This undoubtedly reflects the Chinese Air Force’s requirement that this new multi-functional fighter jet must be superior to others in air superiority operations. At least the performance of the latest model of F-16 must be achieved.
The J-10 is designed to relax static stability and adopts a four-degree fly-by-wire flight control system. This is the first time that a Chinese fighter jet has adopted this most advanced flight control system. The Chinese Air Force used a specially modified J-8II technology demonstrator to test the redesigned fly-by-wire flight control system, which shows that the J-10's fly-by-wire flight control system should be a product independently developed by China.
The J-10 is most likely to adopt a quadruple digital fly-by-wire flight control system like other fourth-generation fighter jets. The advantage of using a quadruple system instead of a triple system is that it allows the fighter to malfunction twice while performing its mission. If a second failure occurs, for the triple system, there will be a situation of good and bad. If the good system wants to turn left and the bad system wants to fly right, the aircraft will be at a loss. But if it is a quadruple digital fly-by-wire flight control system, the ratio of good to bad systems is still 2:1. According to the principle of the minority obeying the majority, the aircraft can still fly normally. If the multiple independent wings of the J-10 are all controlled by a quadruple digital fly-by-wire flight control system, then when these control surfaces coordinate to complete the fuselage steering, the aircraft can be moved up, down, left, and right without pitching or tilting. Switch direction.
Due to the large number of airfoils that need to be controlled, it is no longer possible to use human power and mechanical transmission systems to control the airfoil. The J-10 may also adopt advanced four-degree fly-by-wire control to sense the hand movements through sensors. The pressure on the joystick is converted into an electrical signal and sent to the control computer. The computer calculates the optimal control amount based on the real-time situation of the aircraft, and sends the control signal to the rudder control system to adjust the attitude of the aircraft. This not only reduces the pilot's burden, but also gives full play to the maneuverability of the canard aircraft and ensures the redundancy and survivability of the control system.
Airframe parameters:
Length 16.43 meters (excluding pitot tube)
Height 5.43 meters
Wingspan 9.75 meters
The empty weight of the entire aircraft is 8840kg
Engine thrust 132KN
Normal takeoff weight 12400kg
Maximum takeoff weight 19277kg
Maximum speed Mach 2.2 (high altitude) Mach 1 (low altitude)
Maximum surface speed 1250 km/h (low altitude)
Maximum overload 9G
Minimum overload-3G
Takeoff distance 350 meters
Landing distance 450 meters
Combat radius 1,600 kilometers (confirmed)
The maximum range is 3,500 kilometers
The bomb load is 7,000 kilograms
Navigation
The single-seat cockpit of the J-10 provides the pilot with a good omnidirectional vision. It has made a lot of progress compared to previous Chinese fighter jets that inherited the design style of the former Soviet Union. The aircraft's avionics equipment adopts a design combination that conforms to Western engineering principles: a large-screen head-up display, three LCD multi-function heads-up displays, throttle and pushrod control systems, data storage systems, advanced automatic navigation and weather data computers and Helmet sights.
Although the suppliers of these products have not been determined yet, it is basically confirmed that the helmet sights will be domestic models, designed and produced by Luoyang Aviation Design Institute. The J-10 uses the domestic JL-10 pulse Doppler radar, with a search range of 100 kilometers to 130 kilometers and an attack range of 80 kilometers to 90 kilometers. It can track 6 targets at the same time and select 4 to lock and destroy. ; In the long term, domestic phased array radar or Russian "Beetle" and "Pearl" radars will be used.
China's J-11 (Su-27) is equipped with a high-performance infrared search and tracking and laser ranging integrated system, which provides the fighter with completely passive search and tracking capabilities.
Naturally, the J-10 may be equipped with the same or similar system. However, the spherical structure used to accommodate the infrared search and tracking system cannot be seen on the J-10 prototype and pre-production aircraft, and there seems to be no other fuselage window showing such a system built-in.
Weapons
J-10 fighter weapons and equipment
The J-10 is equipped with a semi-submerged double-barreled 23mm cannon (Russian-made Gsh- The Chinese version of the Type 23 cannon), located on the left side of the nose landing gear below the air inlet. There are 11 pylons designed under the fuselage of the J-10: six under the wings, one on the central axis under the belly, and the remaining four are semi-automatic tandem pylons on both sides of the belly (similar to the Phantom). -2000, Rafale and F-15E have similar belly pylon configurations). Chinese officials have not announced the external load capacity of the J-10, but it is estimated to be 5,500 kilograms. According to the photos, it can be seen that most of the J-10 prototypes and pre-production aircraft are equipped with two PL-8 (to prepare "Strange Snake" III) short-range infrared guided missiles. The J-10's weapon system will also include Russian-made air-to-air missiles (R-73 short-range and R-77 medium-range active guided missiles) already used on the J-11, as well as China's PL-12 medium-range radar-guided air-to-air missiles . When performing ground attack missions, the J-10 can also carry domestic and Russian-made air-to-surface missiles and laser-guided bombs (including YJ-8K anti-ship missiles and new YJ-9 anti-radiation missiles), as well as unguided bombs and Aviation rockets.
It is reported that navigation and target designation pods for the J-10 are under development, and these devices may be placed symmetrically with the cannon