The prototype of fighter MiG-17 is 歼 5.
Mi-17 is a medium-sized transport helicopter with single rotor and tail rotor, which was developed by Miri Design Bureau of the former Soviet Union. It was nicknamed "Hippocampus" -H(Hip-H) by the North Atlantic Treaty Organization.
Mi-17 was first exhibited at Paris Air Show on 198 1, and 1983 exit. The machine adopts Mi -8 machine body and Mi-14 power plant with increased power. The prototype (SSSR- 177 18) exhibited in Bourget, France, flew from Moscow to Paris by Mi -26.
Mi-17 is an improved version based on Mi -8, which is almost the same as Mi -8, but the tail of Mi-17 is independently calculated on the left side of the vertical stabilizer, which is the same as Mi-14. From the appearance, the engine nacelle of Mi-17 is short, but the air inlet above the midpoint of the left door in front of the cockpit is in front, and the small nozzles in front of each nozzle have been redesigned. Mi-/KOOC-0/7 is equipped with two TV3-/KOOC-0//KOOC-0/7mt turboshaft engines with single takeoff power/KOOC-0/454kW (/KOOC-0/977 shaft horsepower). Compared with Mi -8, the performance has been greatly improved. The output of the two engines is synchronous, which can automatically keep the rotor speed. If one engine loses power, the output of the other engine will increase and automatically compensate. If one engine stops working, the power output of the other engine is increased to emergency power of 1640 kW (2230 shaft horsepower) to keep the helicopter flying. The auxiliary power unit starts the turboshaft engine by compressed air. If necessary, the air inlet of the engine can be equipped with a deflector to avoid inhaling foreign objects such as dust when landing at an accidental landing site. The cockpit layout and payload have not changed much compared with Mi -8. Mi-17 mainly has passenger and cargo transportation type. It can transport vehicles, engineering facilities and various goods, and can carry 24 passengers or 12 stretchers. In addition, there are two modifications of Mi-17;
Mi-17P "Haima" K communication jammer. At 1990, we saw two planes of the Hungarian army. The antenna array on board is much better than the Mi -8 Hippo K, and the large array of 32 yuan is installed on the vertical partition wall behind the main landing gear on both sides. 4 yuan arrays are installed on both sides of the tail beam. There are large radomes under the nozzles on both sides of the engine room.
Mi-17- 1VA "Hippocampus" H 1989 Paris Air Show was exhibited for the first time. This type is used as an aviation hospital in Russia. There are three stretchers, an operating table, various surgical and medical equipment, 1 surgeon and 3 nursing staff. This model is equipped with two more powerful TV3-/KOOC-0//KOOC-0/7VM turboshaft engines, with a single power of/KOOC-0/678 kW (2280 shaft horsepower). The climb rate and hovering ceiling have been improved, but the weight and performance have not changed.
The armed forces of the former Soviet Union used a large number of Mi -8 and Mi-17 helicopters. It was also widely used in the war in Afghanistan. Mi-17 delivered 16 aircraft to Cuba in 1983. Subsequently, Angola, North Korea, Nicaragua, Poland, India and Peru also purchased the aircraft. Mi-17 is still in production. The unit price of civilian export type is $5.5 million.
Rotor system: 5 all-metal rectangular blade rotors and 3 blade tail rotors.
Armored plates are installed on both sides of the military cockpit of the fuselage. AS0-2 artificial radar jamming chaff bomb dispenser is installed under the tail beam, and "Holt? Brick "infrared jammer.
Power plant: two TV3-/KOOC-0//KOOC-0/7mt turboshaft engines of kerimov Design Bureau, with takeoff power of 2×/KOOC-0/454kW (2×/KOOC-0/977 shaft horsepower).
The weapon system is equipped with a 23mm GSH-23 machine gun.
(Except for the following data, the rest are the same as Mi -8)
outline dimension
Rotor diameter is 2 1.29 m.
The tail rotor is 3.90 meters in diameter.
The center distance between rotor and tail rotor is 12.338+0m.
Captain (rotor and tail rotor rotation) 25.352m.
The length of the fuselage (excluding the tail rotor) is18.424 m.
The width of the machine is 2.50m..
The height of the machine (to the top of the rotor hub) is 4.757m.
The main wheel rail is 4.5 10/0m.
The front main wheel rail is 4.281m.
The cabin volume is 23m3.
Weight and load
Empty weight (with equipment) 7 100 kg
Maximum payload
4000 kilograms in the plane
Hanging outside 3000 Jin
Normal takeoff weight 1 1 100 kg.
Maximum takeoff weight 13000kg.
The maximum blade load is 0.358kN/m2 (36.5kg/m2).
operating characteristic
The maximum horizontal flight speed (maximum takeoff weight) is 250km/h.
Maximum cruising speed (maximum takeoff weight) 240 km/h
The upper service limit (normal takeoff weight) is 5000m.
(Maximum takeoff weight) 3600 meters
Hover height (no ground effect, normal takeoff weight) 1760m.
Range (maximum standard fuel, 5% residual oil)
(Normal takeoff weight) 495km
(Maximum takeoff weight) 465km
The voyage (with auxiliary fuel tank and normal takeoff weight) is 950km.