The early F- 16 of the power plant was equipped with Pratt? Whitney's F 100-PW- 100 turbofan engine has a maximum thrust of 72.5 kn (7400 kg) and afterburner thrust of11.1kn (11). The 50th batch of F- 199 16c, which started production in the year of F-65438 1965438, was replaced by F-129KN (13163kg) with maximum thrust.
F- 16 "combat falcon"
General dynamics company
general situation
F- 16 is a single-engine single-seat light fighter developed by General Dynamics for the US Air Force. Mainly used in air combat and close air support, it is one of the main models of the US Air Force.
1972, 1 In June, the US Air Force formally put forward the "Light Fighter Prototype Plan" to develop and verify new technologies that can be used for light fighters, but did not decide to develop a fighter that was put into production. At that time, the main requirements of the US Air Force for light fighters were: ceiling18000m; The maximum flight speed m 2.0 accelerates from M0.9 to M 1.5 at an altitude of 9000m for less than one minute; At the height of 12000m, it can hover rapidly at the speed of M 1.5 (overload 3 ~ 4g); Small size and light weight (no more than 9 tons); Cheap price (no better than similar active aircraft); We should try our best to adopt new design methods and advanced technologies to improve air combat capability.
1In April, 1972, the US Air Force selected 40 1 of General Dynamics and P.600 of Norrop from five companies bidding for the "light fighter prototype plan", and signed a contract for the two companies to manufacture two prototypes for test flight competition. The military number of 40 1 scheme of general dynamics company is YF-16; Northrop's P.600 military number is YF- 17. YF- 16 and YF- 17 started from 1974 and conducted a 300-hour competitive flight test lasting 12 months. 1974 In April, the U.S. government decided to choose one of the two planes YF- 16 and YF- 17 for further development, so as to make it a small, simple and cheap light air combat fighter to be used with heavy fighter F- 15 to make up for the complexity and high cost of the latter. 1975,65438+10, in October, the US Air Force announced that General Dynamics had obtained YF- 16, and signed a contract with General Dynamics to manufacture 15 aircraft (later changed to eight) for engineering development. It is planned to start equipping troops on 1978.
The first YF- 16 prototype was delivered in1973,65438+February, and 1974 made its first flight. The pre-production of F- 16 was first tested in 1976. F- 16 began to equip the US Air Force at the end of 1978. The US Air Force originally planned to order a total of 650 aircraft, which was later increased to 2,384.
In addition, the US Navy also ordered 26 F- 16 aircraft. By the end of 1992, the countries and regions that ordered F- 16 were Belgian, Danish, Greek, Turkish, Pakistani, Korean, Thai, Indonesian, Singaporean, Bahrain, Venezuelan and Taiwan Province Province of China. The Netherlands, Belgium, Turkey, Israel and South Korea also introduced the F- 16 production line and produced some F- 16 in China. Japan introduced the production patent of F- 16, and developed its next-generation fighter/attack aircraft FS-X on this basis.
By the spring of 1993, F- 16 * * had ordered 3,835 aircraft, of which 2,203 were ordered by the US Air Force. By July 1992, General Dynamics Company * * * had produced 2,466 F- 16 aircraft of various types, and the 6 15 aircraft was patented by other countries. The order of the US Air Force was completed by 1995. In order to meet the needs of domestic and foreign users, the F- 16 production line will last until 2005.
After the end of the cold war, the demand for military aircraft by the US Air Force dropped sharply. Because the market demand can no longer maintain the scale of military aircraft production in the Cold War era, it is the development trend of military aircraft production at this stage to transfer capital and production power to other industries. Although the production prospect of F- 16 is still promising, General Dynamics announced that it would sell its F- 16 production line to Lockheed in February 1992 at a transaction price of15.25 million US dollars.
From 1972 to 1978, the first F- 16 was put into use, and the development cost was about 870 million US dollars. The unit price of F- 16 199 1 is190,000 USD, and that of 1992 is $23.97 million USD.
F- 16 development type:
YF- 16 prototype, * * * produced two.
F- 16A, the first mass production model, 1976 made its first flight in February. It is mainly used for theater air defense and also for close air support. 1985 In March, all the F- 16A produced for the US Air Force were delivered, but the aircraft was still produced abroad. At present, F- 16A has been improved many times. The F- 16A at the exit after 1988 is equipped with an F- 100-PW-220 engine and an /APG-66 radar, which adopts a lot of technologies on F- 16C, including ring laser inertial navigation. In addition to the early F- 16A weapons, it can also carry AIM-9P close combat missiles and a new generation of over-the-horizon attack missiles, which have the ability to attack the ground. 199 1 On May 3, 2008, the US government and relevant countries approved the mid-term improvement plan of F- 16. According to this plan, 533 F- 16A/B aircraft from the United States, Denmark, the Netherlands, Belgium and Norway will be improved. The improved F- 16 will be equipped with a cockpit similar to F- 16C/D, equipped with a wide-angle head-up display and night vision goggles, and equipped with an /APG-66(V2A) fire control radar, GPS system, automatic target processing system and microwave landing system, and will also have the ability to mount forward-looking infrared pods. At present, the research work of modification has started, and it is planned to deliver 1996.
F- 16B is a two-seat fighter/trainer developed by F- 16A. Due to the installation of the second cockpit, the internal fuel is reduced by 17%. The first F- 16B was tested in August 1977.
F- 16C single-seat light fighter is an improved version of F- 16A. 1982 first flew in February and delivered to the US Air Force in July. The aircraft is equipped with AN/APG-68 pulse Doppler radar, wide-angle head-up display of GEC company, AN/ALQ- 165 airborne self-defense jamming system, GPS system, etc. The improved F- 16C is equipped with MIL-STD- 1760 weapon interface unit, which has the ability to launch AIM- 120 missiles. In the test of F- 16C launching AIM- 120, * * launched 30 missiles, of which 25 hit and 5 missed the target. The experiment was carried out under the conditions of electronic interference and target maneuvering. 1992 On February 27th, an American F- 16C fighter shot down an Iraqi MIG -29 with an AIM- 120 missile in the no-fly zone in southern Iraq, which was the first time that the AIM- 120 missile was used in actual combat. The F- 16C can be equipped with F 100-PW-220 and f110-ge-100 engines. The 50th batch of F- 16C delivered on 199 1 was replaced with an enhanced F 100-PW-229 or f1/kloc-0-ge-129 engine. According to the plan, F- 16C will also have the ability to launch Ham and Kuzu missiles, and perform the suppression task of air defense system.
F- 16D is a two-seat fighter/trainer developed by F- 16C. The first F- 16D was delivered to the US Air Force on September 1984.
NF- 16D Variable Stability Flight Simulator was ordered in February 1988 and modified from the 30th batch of F- 16D.
The F- 16N supersonic imaginary enemy aircraft selected by the US Navy is used for air combat training. It is modified from F- 16C, and only the airborne equipment is changed. Replace APG-68 radar with APG-66 radar; ALR-99 replaces ALR-74 radar early warning system; Add an ARC- 164 VHF radio communication station; Dismantled the machine gun and An /ALR-69 radar early warning system, installed the engine F110-GE-100, and only hung the AIM-9 training bomb on the wing tip. The US Navy ordered 26 aircraft, which were delivered at 1987 and 1988 respectively.
F- 16R F- 16 reconnaissance type. To replace the active RF-4C of the US Air Force. Carrying a reconnaissance pod equipped with a camera system can transmit images to users in near real time. It can perform reconnaissance tasks at night and under any meteorological conditions, and has the ability to fly at low altitude and high speed.
F- 16XL supersonic cruise fighter. It is a modification of the F- 16 proposed by General Dynamics as a multi-role fighter to the US Air Force in the 1990s. * * * Made two prototypes, 1982, and started the test flight in July, and later renamed it F- 16E. They participated in the US Air Force's multi-role fighter competition in the 1990s, and lost to F- 15E in the competition, so it is planned to be held in June of 1985+065438+ 10. 1989 In March, an F- 16XL was used by NASA as a supersonic drag reduction demonstrator.
AFTI/F- 16 advanced technology testing machine.
F- 16/J79 performance export fighter. Install a J79-GE- 1 19 turbojet engine. I was going to export it because no one ordered it. 198 1 stopped.
F-16A DF-16A improved air defense fighter, * * * improved 270. The modified equipment includes: adding advanced medium-range air-to-air missile data link and improved electronic anti-jamming equipment to APG-66 radar; Update high frequency radio stations, IFF transponders, flight data recorders, etc.
The modification scheme of F- 16 "Sensitive Hayabusa" F- 16 is to increase the wing area by 25%, replace it with "IPE" of F 100 or F 10, and replace it with new electronic equipment. 1989 complete the first phase of the project and stop funding.
design feature
The shape scheme of F- 16 was selected through wind tunnel tests of more than 50 layouts in 1200 hours. New technologies such as strake wing, air combat flap, wing-body fusion, relaxation of static stability, fly-by-wire control and high acceleration cockpit are selected to improve the air combat performance of the aircraft. The structural materials of F- 16 are 80.6% aluminum alloy, 7.6% steel, 2.8% composite material, 1.5% titanium alloy and 7.5% other materials. When the F- 16 is fully loaded with internal fuel, all shells and two external missiles, the maneuvering overload at low altitude is 9.0g.
Relaxing Static Stability F- 16 adopts the technology of "relaxing static stability" in the overall layout. Compared with the conventional layout, the wing moves forward by 40.6 cm, which makes the aerodynamic center move forward. Its static stability is slightly negative at M0.9, but it is 8% at M 1.2. The aircraft relies on the "stability augmentation system" to automatically control the rudder surface and maintain a stable flight. The advantage of this is to reduce the size of the tail, reduce the weight and resistance of the structure, and improve the maneuverability of the aircraft.
The cantilever wing is a single wing, and its plane geometry is a tangent triangle. The leading edge sweepback angle is 40. The aspect ratio is about 3.0, the relative thickness is about 4%, and the basic airfoil is NACA64A-204. There is a leading edge flap at the leading edge of the wing, which can automatically deflect with the change of angle of attack and M number, and change the camber of the wing, so that the aircraft can still maintain effective lift coefficient at high angle of attack and improve the maneuverability of the aircraft. There is a full-length aileron at the trailing edge of the wing, which can be used as a general flap to increase lift and also for differential lateral control. The large swept-back strakes extending forward from the leading edge of the wing root along the two sides of the fuselage can control the vortex, improve the lift at high angle of attack, improve the maneuverability and stability, and reduce the wing area. According to the calculation, the weight of the strake wing is 222kg lighter than that of the conventional wing. The internal structure of the wing is composed of beams and ribs, and the upper and lower parts are covered with integral plates.
Semi-monocoque structure of fuselage. The shape is short and thick, and it is connected with the wing in the form of wing-body fusion, so that the fuselage and the wing are smoothly combined together, thus reducing the resistance, improving the lift-drag ratio, increasing the stiffness, increasing the fuselage volume by 9% and reducing the fuselage weight by 258 kg.
The tail is a full-motion flat tail with a plane geometry similar to that of a wing, and the dihedral angle is 25. The rear part of the tail root fairing is a differential brake with a maximum opening of 60. High vertical tail, large stabilizer and good stability at high angle of attack, which can prevent spin and full extension of rudder. The vertical tail is multi-beam and multi-rib aluminum alloy structure, and the skin is carbon fiber composite material. The dorsal fin in front of the vertical tail root fairing is made of glass fiber. The flat tail consists of carbon fiber composite cover plate, aluminum honeycomb sandwich, titanium alloy beam and steel front edge. The ventral fin is a common aluminum alloy structure.
Landing gear hydraulically retracts the front three-point landing gear. The main wheel is retracted forward, and the front wheel is retracted backward into the fuselage. The nose landing gear is installed behind the air intake to prevent foreign bodies flying into the air intake when taxiing. When put away, the front wheel rotates 90 degrees and lies flat on the lower side of the air inlet. Most parts of the left and right main landing gears are interchangeable. Use telex braking system and install anti-skid device. A landing hook is installed between two ventral fins at the lower part of the rear fuselage.
The early F- 16 of the power plant was equipped with Pratt? Whitney's F 100-PW- 100 turbofan engine has a maximum thrust of 72.5 kn (7400 kg) and afterburner thrust of11.1kn (11). The 50th batch of F- 199 16c, which started production in the year of F-65438 1965438, was replaced by F-129KN (13163kg) with maximum thrust. The abdominal inlet with fixed geometry is equipped with boundary layer baffle, and its position is suitable for air combat in the speed range of M0.8 ~ 1.0. Weight loss of fixed inlet ratio adjustable inlet 180 kg. The purpose of choosing the abdominal air inlet is to minimize the interference of the air inlet and avoid inhaling the smoke from the machine gun during maneuvering flight. At the high angle of attack of 30, no adverse effects were found. The internal fuel tanks in the wing and fuselage can carry 3 162kg of internal fuel, and there is an air refueling port above the fuselage at the rear of the cockpit. 1 136-liter auxiliary fuel tank can be hung on the hanger below the fuselage, and 1400-liter auxiliary fuel tank can be hung on the hanger inside the wing.
Cockpits F- 16A and F- 16C are single air-conditioned cabins. In order to improve the driver's vision, a bubble canopy is adopted, and the driver's seat is arranged higher, so that the driver's upper body is exposed above the cockpit frame. The canopy is made of polycarbonate plastic. The windshield is integrated with the front section of the cockpit cover, and there is no support frame. It is connected with the rear hatch cover through a simple support frame, and the support frame is provided with a hinge point, so that the front hatch cover can be opened backwards and upwards. This new canopy can make the driver's vision of the upper hemisphere reach 360, from one side to the other 260, from front to back195, from the lower side 40 and from the lower front side15. In case of emergency, the cover can be thrown by hydraulic pressure, explosive bolt and manual unlocking. Using the IE-2 zero-zero ejection seat of Douglas Company, it can safely eject in the zero altitude and speed range of 0 ~1100 km/h. The seat leans back 30 degrees and the pedal position is improved, which can improve the driver's anti-overload ability by 0.6 ~ 1.0g, and make its short-term anti-overload ability reach 8 ~ 9g. In order to facilitate the pilot to control the plane when he leans back, the so-called "force-sensitive lateral steering handle" installed on the armrest of the seat is adopted. F- 16B and F- 16D are tandem double cabins. 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 F- 16A and F- 16C, and it has all system control functions. The front and rear cabins are separated by two polycarbonate transparent glass plates, and the front and rear cabins have a good view.
The system uses a four-redundancy fly-by-wire control system to replace the conventional mechanical control system, which is composed of signal conversion device, flight control computer, cable and actuating device, and there is no mechanical emergency control system. The fly-by-wire control system is used to control the full-motion horizontal tail, flaperon, rudder and leading edge flap (automatic control). Landing gear retraction, canopy opening and closing, and landing hook retraction are all hydraulically operated.
Airborne equipment An /APG-66 or An /APG-68 pulse Doppler radar, An /APN- 132 radar altimeter, An /ARN- 108 instrument landing system, An /ARN- 165438 TACAN, An/APX-. An /ALR-69 or An /ALR-56M radar warning receiver, An /ALQ- 13 1 or An /ALQ- 184 electronic jamming pod, An /ARC- 164 or An/ARC-/KLOC. LN-39, LN-39 of Litton Company or H-523 inertial navigation system of Honeywell Company, wide-angle head-up display of GEC Company, GPS system, external management computer and multifunctional display of Honeywell Company. The cockpit and main airborne equipment are connected by two sets of MIL-STD- 1553B data buses. F- 16C can hang the "LANTIRN" pod and carry out ground attack missions at night.
The weapons are M-M-6 1A 1 20 20mm multi-barrel guns and rapid-fire sights, with a reserve of 5 1 1 round. Air-to-air missiles with infrared guidance can be installed at the top of the two wings. There is a hanging point under the fuselage and six hanging points under the wing. The lower hanging point of the fuselage can hang 1000kg load, the inner hanging point of the wing can hang 1587kg load, and the middle hanging point can hang 1 134kg load (the above overload limit is 5.5g); Two external wing attachment points and two wing tip attachment points can each be attached 1 13kg (overload limit 9g). The maximum bomb load is 6894 kg (reducing internal fuel), and the bomb load is 4763 kg when the internal fuel tank is full of oil. External weapons include: AIM-9J/L/M/P rattlesnake, AIM-7F sparrow, Sky Flash, Magic 2 and AIM- 120 air-to-air missile, AGM-65A/B/D/G air-to-surface missile.
engineering data
outline dimension
Wingspan 9.45 meters
(missile with wingtip)10.00m
Captain15.03m.
The height of the machine is 5.09 meters.
The wing area is 27.87 square meters.
The wing leading edge sweepback angle is 40.
The aspect ratio of the wing is about 3.0.
The tail span is 5.58 meters.
The flat tail area is 5.92m2..
The vertical tail area is 5.09 square meters.
Elevator area 1.08 m2
The main track is 2.36 meters.
The front main wheel track is 4.00m.
Weight and load
Empty weight f-16c (f100-pw-220) 8273kg.
(f 1 10)8627 kg
8494 kg
(f110-ge-100) 8853 kg.
Maximum internal fuel F- 16C3 104kg.
F- 16D2567kg
The maximum external fuel is 3066 kg.
The maximum bomb load is 4763 kg.
Typical combat weight f-16c (f110)10780kg.
The maximum takeoff weight is 19 187kg.
Wing loading (gross takeoff weight19187kg) is 6.75kn/m2 (688kg/m2).
Thrust-to-weight ratio (without external stores) 1 ~ 1. 1
operating characteristic
Maximum horizontal flight speed (altitude12200m) M2.0
Service limit17200m
The maximum climb rate is 330m/s.
Maximum sustained hovering angular velocity (2×AIM-9+2×AIM-7, 50% engine fuel, maximum thrust state)
(height 1524m, m 0.9) 18/ sec.
(Height 4572m, m 0.9)23/ s
(height 9 144m, m 0.9)7/ sec.
Acceleration time (height 1524m, M0.4 to 1.0) 2 1 sec.
(Height 4572m, M0.5 to1.2) 35s..
(Height 9 144m, M0.6 to 1.6) 59 seconds.
Transition voyage (with auxiliary fuel tank) 3890 km
Operational radius: 370 ~ 1320 km.
Interception (with 2×AIM-9L+2×AIM-7F, maximum external oil quantity) 1440 km.
Ground attack (with 2× AIM-9L+2× 907kg bomb, maximum external oil quantity) 1 184km.
Limit overload +9g
F- 16 Hawk Fighter Weapon System
I. Overview of Aircraft Development and Service
F- 16 was originally a low-cost single-seat light fighter developed by General Dynamics. 1 production type entered active service on 1979+0. After several improvements, there are 1 1 models, such as A, B, C, D, N, R, XL, ADF and AFTI/F- 16, F- 16/J79, NF-/kloc-0. Some types are the best. By the end of 1996, more than 3,500 aircraft had been produced and equipped with air forces and navies of 17 countries.
See table 1. 1 for the proportion of ordnance and avionics in the procurement cost of each aircraft.
Table 1. 1 Proportion of F- 16 fighters purchased in each fiscal year.
What is the total number of racks from 1979 1980 before FY78 to the end of procurement? Average value of
Aircraft fuselage 51.64 45.98 47.48 46.338+07 46.83
Engine 21.07 27.42 28.72 27.40 26.98
Avionics18.6218.615.6718.3618.08.
Military equipment 2.54 4.29 4.50 5.33 4.87
System/plan management 6. 13 3.70 3.63 2.74 3.25
Total100100100100.
Only two prototypes YF- 16 were produced. 1 The prototype made its first flight on February 2, 1974.
F- 16A/B is a 1 production aircraft, Type A is a single-seat combat aircraft, and Type B is a two-seat coach aircraft. Eight aircraft (two of which are two-seaters) were pre-manufactured, and Type A made its first flight in February 1976. Type B made its first flight in August 1977. 1977 10 10. In October, the US government approved the F- 16 fighter to be put into mass production. These two types include 1 (43 aircraft), 5 (126 aircraft), 10( 170 aircraft) and 15(457 aircraft). 15 aircraft were produced according to the requirements of F- 16 fighter multi-country and multi-stage improvement plan 1 stage (MSIPⅰ I). Among them, 270 aircraft were modified into F-16DF air defense interceptors, and guided AIM-7 "Sparrow" missiles and APG-66 fire control radar were added. 1988 delivery.
F- 16C/D is the main model of F- 16 fighter. Type C is an improved type A, and Type D is a coach type C. The aircraft produced from the 25th batch belong to these two types. Type C was tested on 1982 12 and delivered to the Air Force on 1984. The weapon system includes an /APG-68 multi-function radar, wide-angle head-up display, mission computer and other fire control equipment, 20mm 616 cannon, AIM-7 sparrow and AIM-9 rattlesnake air-to-air missile, AIM- 120 advanced medium-range air-to-air missile and AIM-65 cub. Type D is a type C instructor, which made its first flight in 1983 and was delivered to the Air Force in September/984. At present, about 65,438+0,680 C and D have been produced, which belong to the 25th batch (365,438+09), 30th batch, 32nd batch (* * 5,065,438+0), 40th batch and 42nd batch (* * 7,365) respectively. The main differences between different batches of aircraft are the local changes of aircraft structure, the differences of engines and the improvement of weapon systems.
F- 16N is a target aircraft selected by the US Navy for air combat training, which is modified from a C-type aircraft. The radar was replaced by APG-66, the machine gun was removed, only the training bomb of AIM-9 rattlesnake missile was hung on the wing tip, and the electronic warfare equipment was also changed a little. * * * 1987 was modified and delivered to the navy with 26 aircraft.
F- 16R is a reconnaissance plane replacing RF-4C.
F- 16XL The United States Air Force only produced two prototypes for the multi-role fighter in the 1990s, but the development stopped in June1985165438+1October due to the failure of competition. Among them, the 1 aircraft was converted into a NASA verification machine in March 1989.
F- 16ADF is an air defense fighter modified from Type A. See F- 16A/B fighter weapon system for details.
AFTI/F- 16 is an advanced comprehensive verification machine, and the automatic mobile attack system (AMAS) with integrated fire/flight control technology has been verified in the weapon system.
Second, the F- 16 fighter's weapons and firepower configuration
(1) fixed machine gun
On the left side of the front fuselage of the F- 16 fighter, there are120mmmM61Vulcan 6 guns, and the ammunition box is installed behind the cockpit on the fuselage, with a reserve capacity of 5 12rds. A large number of reinforced fiber plastics are used in the spoon-shaped disc and spiral parts of the ammunition supply system, which reduces the weight of the gun system. Its ammunition supply system can be connected with two loaders in ground equipment, and the adoption of the navy's chainless ammunition loading system can reduce the preparation time for the plane to take off again. The main features of the fixed gun system are as follows:
key property
Mounted fixed machine gun
Weighing 377kg, of which
Machine gun114kg
Ammunition130kg
Other 133kg (ammunition supply system, etc. )
Supply form of chainless ammunition with closed ends
Transmission hydraulic motor
The working speed is 98.4 liters/minute.
(126.5 kg/cm2)
Ammunition reserve 5 12rd
Shooting position 10 o'clock position (viewed from the front)
The service life of the system is 65438+500,000 rds.
Figure 2. Fixed gun system of1F-16 fighter.
(2) Configuration scheme of external pylon, external weapon and firepower.
1, external pylon
The number of external weapon pylons of F- 16 fighters varies from 9 to 14 in different production batches.
The F- 16 fighter before the (1) 15 batch had nine external stores:
There are 1 (N0. 1 and N0.9) special pylons for rattlesnake missiles at the tips of the left and right wings. The maximum mounting capacity of each pylon is 1 13kg(250lb), and the overload limit is 9g.
There are three external racks under the left and right wings:
The maximum loading capacity of each pylon (No.2 and No.8) is 1 13kg(250lb), and the overload limit is 9g;
The maximum loading capacity of each intermediate pylon (No.3 and No.7) is1130kg (2,500 lb), with a limit of 5.5g；;
The maximum mounting capacity of each internal hanger (No.4 and No.6) is 1588kg(3500lb), and the overload limit is 5.5g:
The maximum loading capacity of the center pylon (No.5) under the fuselage is 998 kg (2,200 lb), and the overload limit is 5.5g.
(2) The production F- 16 fighter in batch 15 has 10 external weapon pylons, of which 9 pylons have the same position and mounting capacity as the aircraft before batch15, and only the 1 N0.5P pylon is added on the right side of the fuselage, with the maximum mounting capacity of 45 kg (.
(3) The F- 16 fighters after the 25th batch (including the 25th batch) have at most 14 external pylons, and the five additional pylons are N0.3A, N0.5T, N0.5E, N0.5P and N0.7A respectively, and the mounting capacity of the original pylons has also been improved. The location of each tower is shown in Figure 2.2, and the installation capacity and overload limit are as follows:
The maximum loading capacity of N0. 1 and N0.9 wingtip pylons is 193kg(425lb), and the overload limit is 9g;
The maximum loading capacity of pylon on the outer side of wings 2 and 8 is 204kg(450lb), and the overload limit is 9 g;
The maximum mounting capacity of the middle pylon of wings 3 and 7 is 1588kg(3500lb), and the overload limit is 5.5g Only 907kg (2000lb) can be hoisted under the maximum lifting force.
The maximum mounting capacity of the auxiliary pylon between wings 3A and 7A is 204kg(450lb), and the overload limit is 9 g;
The maximum mounting capacity of the inner hangers of wings 4 and 6 is 2040kg(4500lb), and the overload limit is 5.5; Only 907 kg (2000 lbs) can be loaded under the maximum lifting force; The maximum loading capacity of the N0.5P sub-pylon is 45kg( 100lb), and the overload limit is 9g.
The maximum mounting capacity of the N0.5E sub-pylon is 250kg(550lb), and the overload limit is 9g.
The maximum loading capacity of the central pylon under No.5 fuselage is 998 kg (2,200 lb), and the overload limit is 5.5g: only 544 kg (1200 lb) can be hoisted under the maximum lift;
The maximum loading capacity of 0.5T sub-pylon 136kg(300lb) and the overload limit of 9g.
Hanger number 1
2 6 AIM-9 rattlesnake air-to-air missiles
3 2 AIM-7 sparrow air-to-air missiles
4 8 AIM- 120 advanced medium-range air-to-air missiles
5 ECM box/photoelectric sensor box
6 19 MK82 bombs (3 for pylons 0.3 and 0.7, 6 for pylons 0.4 and 0.6, 1 for the lower center of the fuselage)
7 4 MK84 bombs
8 4 guided bombs
9 13 submunitions (2 for pylons 0.3 and 0.7, 4 for pylons 0.4 and 0.6, 1 for the lower center of the fuselage).
10 6 air-to-surface missiles
1 1 two 1400L(370 gallons) auxiliary fuel tanks.
1211135 liter (300 gallon) auxiliary fuel tank.
13 2 2270 liters (600 gallons) secondary splash stage
2. External weapons
F- 16 fighter has many kinds of weapons, and different types of aircraft are different. The most common ones are: AIM-9L/M/P/X Sidewinder air-to-air missile, AIM-7 Sparrow air-to-air missile, AIM- 120 advanced medium-range air-to-air missile, AGM-65 cub air-to-surface missile, AGM-45/-78/-80. -7 1 submunition bomb, CBU-87 and CBU-89 combined effect ammunition, MK.82/83/84 general bomb, MK.20 "Shiyan" anti-tank submunition bomb, BL 755 incendiary bomb, LAU-3A rocket launcher (30mm4), GPU-5 machine gun bay (equipped with 60.
3. Firepower distribution scheme
The typical fire configuration scheme of the F- 16 fighter is as follows ((4) the scheme actually used in the Gulf War):
(1) In air combat, 20mmM6 1 machine gun (500rds shell) +4 AIM-9 rattlesnake air-to-air missiles.
(2) air interception scheme 1: 20mmmm6 1 machine gun (500rds shell) +2 AIM-9 air-to-air missiles +6 MK.82 general bombs +2 1400L auxiliary fuel tanks (Figure 2.3 (1));
(3) air interception scheme 2: 20mmmm6 1 machine gun (500rds shell) +2 AIM-9 air-to-air missiles +2 MK.84 general bombs +2 1400L auxiliary fuel tanks (Figure 2.3 (2));
(4) When searching for Scud missiles at night, the firepower configuration is as follows:
M6 1 machine gun +2 rattlesnake air-to-air missiles +6 CBU-87 composite effect ammunition +2 1400L(370 gallons) auxiliary fuel tank+1Alq-131ECM pod (lower center of fuselage).
(5) When searching for Scud missiles during the day, the firepower configuration is as follows:
M6 1 machine gun +2 rattlesnake air-to-air missiles +6 CBU-87 composite effect ammunition +2 1400L(370 gallons) auxiliary fuel tank+1Alq-131ECM pod (lower center of fuselage).
(6) During air defense suppression (SEAD), the firepower of the 7740th temporary composite wing F- 16C (batch 30) is:
M6 1 machine gun +2 AGM-45 Kuzu or AGM-88 Ham anti-radiation missiles +4 Sidewinder air-to-air missiles+1ALQ-131ECM pods;
(7) In close air support, the firepower configuration of F- 16A (batch number 10) fighters of 174 squadron (four-aircraft formation) is as follows:
The two planes are 1 M6 1 machine gun +2 rattlesnakes +6 MK82 general bombs (3 under the left and right central pylons) +2w 1400L auxiliary fuel tank+1ALQ-119e.
The two planes are 1 M6 1 machine gun +2 rattlesnakes +6 (3 on the left and right wings) MK20 stone eye anti-tank submunitions+1ALQ-19ECM pod;
(8) In close air support, the F-/KOOC-0/6A (batch/KOOC-0/0) fighter of/KOOC-0/74 squadron has the following firepower configuration:/KOOC-0/20mmmM6/KOOC-0/cannon +2 rattlesnake+/KOOC-0/air-to-air missile.
3. F- 16C/D Hayabusa fighter fire control system
(a) system overview
Formerly known as fire protection system
The fire control system of F- 16C/D fighter is an improvement of the fire control system of F- 16A fighter, and its main components include six bases.