AH-64 Apache is an advanced attack helicopter developed by mcdowell Company of the United States according to the advanced attack helicopter (AAH) plan proposed by the US Army. The aircraft can perform anti-tank tasks day and night in bad weather conditions, and has strong fighting, life-saving and survival capabilities. 1The prototype made its first flight in September 1975,1officially delivered in June 1984,1entered the war for the first time in Panama in February 1989. AH- was widely used in the June Gulf War of 19 1 and the NATO military attack on Yugoslavia in June of 438+0999. Existing types: AH-64A, Advanced Apache and MSIP; AH-64B is a modification of AH-64A, equipped with global positioning system (GPS) and capable of target handover. AH-64C is a modification of AH-64A; AH-64D "Longbow Apache" is equipped with "Longbow" radar and can carry "Herfa" missile with RF seeker. It is planned to refit the T700-GE-70 1C engine of General Dynamics Company with higher power, a new power distribution system, a large generator with double 70 KVA, and AN/ASN- 157 Doppler navigation system.
The overall layout is a four-blade fully articulated rotor system, which adopts steel belt laminated joint components and elastic shimmy dampers. The tail rotor is mounted on the same fork joint by two pairs of rotors with two blades. The fuselage is equipped with cantilever short wings with low aspect ratio, which can be disassembled, and there are two hanging points under each short wing. After the three-point wheeled landing gear, the landing gear strut can be folded backwards, and the tail wheel is an omnidirectional steering self-centering tail wheel.
Power plant: two T700-GE-70 1 turboshaft engines of American General Electric Company, with single power 1265kW and emergency power 1285kW. T700-GE-70 1C engine is installed from 100th AH-64A, with single emergency power 1C.
Weapons and equipment Hughes XM-230-E 1 30 mm machine gun, reserve 1200 rounds, and the normal firing rate is 652 rounds per minute. It can carry 16 "Helfa" missiles, and 70mm rockets are optional. Each hanging point can be hung with a 19 rocket launching nest.
Dimension data: rotor diameter14.63m, tail rotor diameter 2.77m, captain (rotor and tail rotor rotate)17.76m, machine height (to vertical tail) 3.52m, tail rotor diameter (to tail rotor) 4.30m and short wingspan 5.23m.. ..
Weight and load empty weight 5092 kg, maximum takeoff weight 9525 kg, maximum external load 77 1 kg, main task weight 6552 kg.
Performance data (take-off weight 6552kg, ISA): the maximum allowable speed is 365km/h, the maximum level flying speed and cruising speed are 293km/h, and the maximum climbing rate is (altitude 1220m, 35. C)4.32 m/s, service ceiling 6400 m, hovering height (with ground effect) 4570 m, range (internal combustion) 482 km, endurance time (height 1220 m, 35. C) 1 hour 50 minutes, maximum endurance (internal combustion) 3 hours and 9 minutes, ultimate overload (low altitude and speed of 304 km/h)+3.5/-0.5g. ..
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Zhi -8 is a medium-sized multi-purpose helicopter jointly developed by China Helicopter Research and Development Institute and China Changhe Aircraft Factory. The first test of the prototype was in198565438+February, and the second test was in198765438+1October. 1989 received the license on April 8. Zhi -8 is a single-rotor helicopter with tail rotor, which has a large power reserve under standard conditions. It has the characteristics of good flight performance, long service life, safe flight, simple operation, convenient use and maintenance, and can take off and land on water in an emergency. Zhi -8 helicopter is widely used. As a civil aircraft, the interior is spacious and comfortable, and it is an ideal civil airliner; After installing this equipment, it can serve all industries of the national economy, such as carrying out tasks such as geological exploration, surveying and mapping, building construction, forest fire fighting, and setting up high-voltage cables. It can also perform tasks such as border patrol, cargo transportation, communication and command in plateau areas, and can also be used as an ambulance. After adding (or changing) a complete set of equipment for submarine search, submarine attack, anti-submarine maneuver and combat liaison, it becomes an anti-submarine helicopter.
design feature
The rotor system consists of a hub and six rectangular bonded metal blades. The main hub is hinged and consists of upper and lower six-arm star plates, which are used to install six blades and form a whole with the rotor shaft of the main reducer. The hub is also equipped with flapping hinge, axial hinge and dragging hinge with hydraulic damper. The tail rotor consists of five all-metal blades.
The power plant is equipped with three turboshaft 6 engines. Two sets are in front of the main reducer, and 1 set is behind the main reducer. The power of the three engines is transmitted from the main reducer to the rotor and tail rotor. The maximum takeoff power of a single engine is1128 kw (1535 axle horsepower). The main fuel tank in the aircraft consists of three groups of eight soft fuel tanks with a total effective volume of 3900 liters, which is located in the sealed fuel tank cabin under the cargo hold floor. Both the fuel tank and the auxiliary fuel tank have ventilation systems, and each group of fuel tanks has a gravity refueling port located on the left side of the fuselage.
The fuselage and cockpit fuselage are semi-hard shell watertight riveted structures, and the bottom is boat-shaped. The fuselage includes six parts: cockpit, engine room, tail beam, transmission platform, hull and horizontal safety surface.
The cockpit has pilot and co-pilot seats, which can be adjusted up and down. There is 1 piece of large-area electrically heated frost-proof laminated silicate glass in front of the cockpit, which has a good view. There are 1 emergency jettisonable doors on the left and right sides, and there are 1 sliding windows on them for pilots to observe when landing in complex terrain.
The engine room is located in the middle of the fuselage and can carry all kinds of goods. There is a sliding door at the right front of the engine room, with a height of 1.5m and a width of1.2m.. There is an emergency jettison door with a height of 1. 12 m and a width of 0.58 m on the side, which is used to evacuate the crew from the plane quickly in case of emergency. There are eight throwing windows on both sides. There is a 1 tailgate at the rear of the fuselage, which is operated by a hydraulic actuator and hinged on the floor as a loading springboard from which goods or 1600kg vehicles can enter the cargo hold. When flying in the air, it can be operated by hydraulic solenoid valve, actuated by left and right hydraulic actuators, and the tailgate can be opened to a horizontal position for airdrop. There is a 1m× 0.8m/cargo hold on the cargo hold floor, which is used for hanging steel cables and anti-submarine sonar. The external lifting capacity is 500 kg. When the engine room is used as a cabin, it can carry 27 passengers, with 3 seats in 5 rows on the left and 3 seats in 4 rows on the right. According to the needs of the task, 12 movable seats can be installed to carry 39 passengers. During the rescue mission, the seat can be folded along the inside of the fuselage, and 15 stretcher can be placed to transport 15 patients. There are 1 folding seats for flight mechanics in the passage between the cockpit and the engine room. There is sound insulation equipment in the cargo hold, which can reduce the noise level in the cabin.
Landing gear consists of landing gear, tail strut, amphibious short wing and buoy. The nose landing gear can turn, and is equipped with a direction locking mechanism and an anti-swing device. Both the front landing gear and the main landing gear are equipped with dual-cavity oil-gas shock absorbers, and two wheels with the same specifications are installed under each shock absorber, using low-pressure tires. The wheels of the main landing gear are equipped with hydraulic disc brakes. A tail brace for protecting the tail beam during landing is installed at the lower part of the tail beam.
The bottom of the fuselage is in the shape of a boat. There are 1 amphibious short-wing buoys near the left and right landing gears of the fuselage, which are composed of rectifying short wings and buoys with hull, aerodynamic and hydrodynamic shape seals. The volume of each buoy is 1.425m3 to ensure the floating capacity and water surface stability of the helicopter. For sea use, when the sliding door of the aircraft is opened, a door baffle is installed to prevent water from entering the cockpit. Planes can take off and land on the water, hover on the water, save people and slide on the water.
The system machine is equipped with two independent main hydraulic systems, namely the left and right main hydraulic systems, and the working pressure is176.5x105pa (180kg/cm2). Each has a booster pump with a rated flow of 2 1 liter/minute. There are also 1 set of auxiliary hydraulic system and 1 set of emergency hydraulic system, and the working pressure is112.8 ~137.3x105pa (11). The 8.9-liter hydraulic oil tank supplies oil for the above four hydraulic systems.
When the outside air temperature is 0℃, the ventilation and heating system can maintain 20℃ in the engine room and 15℃ in the cockpit. When the outside air temperature is -30℃, the cabin and cockpit are kept at 0℃. Hot air is pumped from the engine compressor.
The fire protection system consists of three independent systems to protect the three engine compartments. Each system has 1 fire detection system and 1 fire extinguishing system.
The power supply has two power generation systems, namely the AC -DC hybrid power supply system: the 28.5-volt DC power generation system is powered by three 9-kilowatt starters/generators; 1 15/200 V and 400 Hz three-phase AC power generation system is powered by a 9 KVA alternator and a 1 2.7 KVA converter.
Airborne equipment consists of H- X- 1 heading and attitude system, air data calculation system, engine instrument, other auxiliary instruments, signal display and alarm device, etc. Instruments and equipment can display the flight course, attitude, speed, driving and engine working conditions of the aircraft in day and night and under various complex meteorological conditions, as well as within the flight envelope. KT-8A four-channel autopilot is installed to control the stability of flight attitude. Communication equipment includes 53# walkie-talkie, 506 VHF dual-band radio and TDT- 1 shortwave single sideband radio. Navigation equipment includes WL-7 radio compass, 264 radio altimeter and XS-6 beacon receiver.
engineering data
outline dimension
Rotor diameter18.9m.
The tail rotor is 4m in diameter.
Captain (rotor and tail rotor rotation) 23.05 meters
The height of the machine (rotor and tail rotor rotation) is 6.66m.
The fuselage is 20.27 meters long.
The fuselage width (with buoy) is 5.2m
The lateral tread is 4.30m.
The longitudinal tread is 6.567m.
Cargo hold width (on the floor)1.90m.
Cargo hold height (in the plane of symmetry)1.83m.
inside measurement
The total volume of engine room is 28.9 cubic meters.
zone
Rotor disk 280.48 square meters
Tail rotor disc12.57m2.
Weight and load
Empty weight is 7095 kg.
Maximum takeoff weight 13000kg.
The maximum commercial load is 3000 kg.
The maximum fuel weight is 3 120kg.
Maximum hovering weight (ground effect) 12480 kg
Performance data (standard atmosphere, three engine hours)
Maximum horizontal flight speed
(total weight 9000kg) 3 15km/h
(total weight 13000kg) 275km/h
Economic cruising speed
(Total weight 9000 kg) 255 km/h
(total weight 13000kg) 232km/h
Maximum cruising speed
(Total weight 9000 kg) 266 km/h
(gross weight13000kg) 248km/h
Climbing rate (15.5 total distance)
(total weight 9000 kg) 1 1.5 m/s
(total weight13000kg) 6.6m/s
Dynamic lifting limit
(total weight 9000 kg) 6000 meters
(total weight13000kg) 3050m
Effective hovering height
(total weight 9000 kg) 5500 meters
(total weight 13000kg) 1900m
Non-ground effect hovering height
(total weight 9000 kg) 4400 meters
(gross weight 13000kg, maximum hovering weight) 1248m.
navigate by water/air
(Total weight 9000 kg) 430 km
(total weight 13000kg) 800km
keep patience
(Maximum standard fuel, one engine stopped, no fuel left)
(total weight 9000 kg) 2 hours 3 1 min
(total weight 13000kg) 4 hours 13 minutes.
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SA34 1/342 "Little Antelope" light helicopter was jointly developed by the former French Aerospace Company (now the French branch of Eurocopter) and the British westland Helicopter Company. In order to deal with the threat of the powerful Soviet armored cluster, China began to seek the possibility of importing advanced anti-tank helicopters from foreign countries in the late 1970s. Soon the PLA selected the "Little Antelope" helicopter, which was not the most advanced at that time. At that time, the French aerospace company thought it had met a big customer and was very involved. It is predicted that China will order 24 "small antelopes" in the first batch. I don't want the PLA to order a batch of eight SA342L 1 "Gazelle" in the early 1980s and deliver them in 1988, which surprised the west. Since then, the PLA has never purchased "Little Antelope". 1986 After the formation of the Army Air Force, all the "Little Antelopes" were incorporated into the Army Air Force.
The "Little Antelope" development plan was originally proposed by France to replace the "Lark" II helicopter. Development started at 1964. "Lark" II transmission system of Tubomeka Company, "Aste Resistance" III engine and rotor jointly developed with Bokov Company are adopted. 1967, France and Britain began to develop together. The first prototype was called SA340 340,/KLOC-0, which made its first flight on April 7, 1967. The second prototype was named SA34 1, 1968, and the first pre-production made its first flight on August 6th, 197 1.
The flying performance of "Little Antelope" is excellent. 1971may 13 and 14, SA34 1-0 1 set three E 1C world records at Easter: the flight speed of the 3-kilometer direct flight reached 3/kloc. 15/25km flight speed reaches 312km/h; The flight speed reached 296 km/h on the closed route of 100 km, so a large number of military and civilian customers from all over the world soon ordered the "Little Antelope" helicopter, which was widely used in fields from anti-tank to traffic surveillance.
"Little Antelope" adopts three semi-articulated NACA00 12 wing rotors, which can be folded manually. The ducted tail rotor, which is common in French helicopters, is adopted with blade brakes. The cockpit frame is a light alloy welded structure, which is installed on the common semi-hard shell bottom mechanism. The bottom structure is mainly composed of light alloy honeycomb sandwich plate and longitudinal box body. Sandwich plate structure is widely used in automobile body. Steel tube skid landing gear can be used, and wheels, buoys and sledges can be added. The power of SA342 is a 640 kW "Aste resistance”XIVM turboshaft engine. The L 1 model of our army also uses the "Asnai" XIVM engine. There are two fuel tanks on board, with a total capacity of 545 liters, and the other 200-liter transit fuel tank is located at the back of the cockpit. The machine is equipped with a 4 kW DC generator driven by an engine and a 40 Amp-hour battery to supply power to the 28 Volt DC system. You can also choose a 26V DC system.
The "Little Antelope" adopts a parallel two-seat drive mechanism, and the cockpit has two rows of five seats. There is only one control system, but the dual drive system is optional. The rear seats can be folded to the floor and equipped with fixing rings and other facilities for loading goods in the rear compartment. There is also a luggage compartment behind the cockpit. Vehicle communication equipment can be equipped with UHF radio, VHF radio, HF radio, intercom system and non-directional beacon. Navigation equipment includes radio compass, radio altimeter, VHF omnidirectional beacon, blind flying equipment and autopilot. You can choose a hanging system with a load of 700 kg, a winch with a load of 135 kg, one or two stretchers or photographic observation equipment. At the end of 1980s, the electronic equipment of "Little Antelope" in Britain and France was generally upgraded, including adding omnidirectional warning devices.
In addition to Britain and France, Egypt and Yugoslavia also produced a certain number of Gazelle helicopters under patent license. By June 30th, 199 1, customers from 4 1 countries were using *** 1254 "Little Antelope" helicopter, including Britain, France, China, Iraq, Ireland, Morocco, Angola, Yugoslavia and Egypt. Among them, Britain has 282 aircraft, France has more than 357 aircraft, Egypt has 190 aircraft, and Iraq has 8/kloc-0 aircraft. "Little antelope" has rich practical experience. The British "Little Antelope" participated in the Falklands War, France participated in the Gulf War, and Iraq participated in the Iran-Iraq War.
The main weapons of foreign "Little Antelope" include120mm machine gun or two 7.62mm machine guns, which can carry four "hot" anti-tank missiles developed by European missile companies (joint venture between France's Matra Company and Germany's DaimlerChrysler Space Company) or two 70mm or 68mm rocket silos. In order to guide anti-tank missiles, APXM397 gyro stabilized aiming device, or its all-weather improvement, or AF532 advanced aiming device is usually installed at the top of the engine room. China's "Little Antelope" usually has four "Holt" missiles, but there is no news of switching to domestic "Red Arrow" missiles. The army often uses "Gazelle" to simulate enemy helicopter gunships, which not only plays the role of western helicopters, but also plays the role of Soviet helicopters.
There are many models of "Little Antelope", including:
SA34 1B British model, equipped with "Aste Resistance" Iin engine, numbered "Little Antelope". Mk 1。
SA34 1C Royal Navy model, numbered "Little Antelope" HT. Mk2
SA34 1D RAF instructor type, numbered "Little Antelope" HT. Mk3
SA34 1E RAF contact type, numbering "Little Antelope" HCC. Mk4
SA34 1F French army model, equipped with "Aste resistance" III C engine, produced 166 aircraft.
SA34 1G civil vehicle, equipped with "Aste resistance" iiia engine.
Military model of SA34 1H "Aste Nai" IIB engine.
Sa 342j 1977 Civil model delivered.
The military model of SA342K with "Aste resistance”XIVH engine.
SA342L is a military model similar to SA342J.
The basic military model of SA342L 1 with "Aste resistance”XIVM engine.
The advanced model of SA342M SA342F is equipped with advanced radar, navigation and night vision systems, and the French army is equipped with 188 aircraft.
Captain11.97m.
The height of the machine is 3.19m.
Rotor diameter10.5m.
Empty weight 99 1 kg
Maximum takeoff weight 1900kg.
The maximum horizontal flight speed is 260 km/h.
The maximum range is 7 10 km.
Service limit is 4 100 meter.
The maximum suspension load is 700kg.