Boeing CH-47 "Chinook" (English. Boeing CH-47 Chinook) - American heavy military-transport helicopter longitudinal scheme. Developed based on the CH-46 and is widely exploited since the early 1960s. He succeeded in U.S. Army H-37 helicopter, later - and CH-54. Is in service with more than 20 countries of the world. In addition to the US, produced from 1970 g. in Italy (more 200 helicopters) and Japan (firm "Kawasaki" is produced 54 helicopter).
Helicopter CH-47 Chinook – video
AT 1956 g. under contract with the US Army company "Boeing-Vertol" started the development of medium-sized military transport helicopter twin-screw longitudinal scheme with two GTE. Army helicopter following requirements have been set: transported load 2725 kg under static ceiling out of ground effect 1850 m, and air temperature surrounding 35'S, Maximum cruising speed 240 kmh, tactical range 185 km from the carriage on the way back, half load (1363 kg).
The first of five experienced YCH-47A helicopter with two P D Laykoning T55-L-5 capacity of 1640 kW / 2200 liters. from. It made its first flight 21 September 1961 g, and mass production of helicopters SP-47 began in 1962 g. Total "Boeing-Vertol" was delivered by 752 military transport helicopter SP-47 of all modifications for the US Army, and 136 military helicopters for other countries, including 5 helicopters for Argentina, 12 Australia, 41 UK, 19 for Spain, 9 Canada, 6 for the Netherlands, 6 for Singapore, 6 for Thailand, 5 Taiwan and 2 for Japan. additionally supplied 13 civil helicopters.
CH-47 helicopters manufactured with 1970 g. under license in Italy's Agusta and "Meridionali" firms, which produced more than 200 helicopters, including 41 Italian army helicopter, 68 Iran, 15 Egypt, 10 Greece, 20 Libya, 9 Morocco, and 11 helicopters for the US Army National Guard. Besides, 43 helicopter manufactured under license in Japan by "Kawasaki".
Design
Helicopter longitudinal twin-screw scheme with two gas turbine engines and chassis Four.
Fuselage
all-metal, semi-monocoque design, with a rectangular cross section with rounded corners; It has a two-seat cockpit, on each side of which there are resettable emergency doors, and cargo compartment volume 41,7 m³ , wherein the set 44 seat (33 main and 11 additional, along the central passage), with the back of the cargo hatch, Flap valve which forms a loading ramp, provided with three hinged sections, and compartments pylons rotors. The cargo compartment with the dimensions 9,19 x 2,29 x x 1,98 m and floor area 21 m² is on the right side of a large sliding door to the size 1,68 x 0,9 m, and further an emergency escape hatches cab. Cargo cabin crew cabin and connected to a passage. The sanitary embodiment may be located in the cab 24 wounded on a stretcher, and 2 accompanying medic, seats are installed in the passenger variant for 44 passengers, by 4 in line with the central passage. For transportation of cargo on external sling has a central load hook under the fuselage, designed for effort 11 970 kg, and front and rear load hooks on 7140 kg each.
rotors
trilobate, with hinged blades mounted, rotating in opposite directions. The blades of the rectangular planform area 7,43 and each chord m² 0,81 m. D-shaped blade spar is formed of fiberglass epoxy, with fittings of the sock of titanium and nickel alloys, tail compartments are also made of fiberglass with a filler Nomex. The wear blade installed counterweights, a longitudinal member as set replaceable counterweights from tungsten - to adjust the taper. The blades have an improved aerodynamic profile VR-7 (and on the front part, where the flow rate is achieved, corresponding to the number M = 0.85, - Profile VR-8) and, linear twist -12 °. The installation of the anti-icing system on the blades. The circumferential speed of the blade tips 215 m / s.
Power point
Engines mounted on each side of the main rotor pylon rear, have an axial air inlets, tightened mesh screen. Auxiliary Power Unit Comp T-62T-capacity 2B 71 kW / l 95. from. It is used for driving auxiliary units, but on the ground provides the electrical work, gidrousilyteley management system, chassis, hydraulic pumps and other aggregates.
Transmission
It consists of a central gear, gear rotors, Gear motors and connecting shafts. The gear ratio from the engine to the rotor 1: 67.
Cooling and lubrication gearboxes
improved: cooling air is fed from inlet, located in the nose of the rear pylon. Maslosistema dublirovana. The transmission is designed for maximum power 5590 kW / 7500 liters. from. and 330 min run without oil. Oil tank capacity 14 l.
Fuel system
It includes six self-sealing, refillable pressurized fuel tanks (three in the side fairings) total capacity 3900 l. Can be installed in the cargo three additional fuel tanks for 3025 l each.
Chassis
FIXED GEAR, Four, with oil-pneumatic shock absorbers. The front supports dual wheels. Wheels rear legs swiveling, manageable. All wheels are pneumatic with pressure 0,45 MPa / 4.6 kg / cm² and disc brakes with hydraulic drive. The installation of the wheels removable ski. The base chassis 6,86 m, track 3,2 m.
Control system
Busternaya, upgraded, firm “Khanuiell”, ensures maintaining the position and velocity, helicopter flight, as well as the selection and maintaining course and altitude of flight; It includes the hydraulic actuators and the stabilization system.
Hydraulic system
Modular construction provides operation of servo control system, Brake system chassis and rotor. Pressure in the hydraulic control system is 20 MPa / 207 kg / cm² mixture flow velocity 53 l / min, It has a spherical tank capacity 5,32 l with pressure 0,17 MPa / 1.72 kg / cm² . The general-purpose hydraulic system pressure is 23 mPa / 230 kg / cm² , mixture flow velocity 51,5 l / min, hydraulic piston, reservoirs has a volume of about 7 l with pressure 0,39 MPa / 3.86 kg / cm² .
Electrical
It consists of two independent circuits, power which is provided by two alternators (40 kVA) air-cooled, driven from the main gearbox.
avionics
standard, It includes FM- station ARS-164 UHF with AM; SPU C-6533; system identification “friend or foe” Bendix ARH-100, VHF omnidirectional beacon ARN-123, altimeter ARN-209, finder ARN-89B; standard flight instruments include a pointer to the horizontal position AQV-Ba.
modifications
SN-47A – basic version.
BUT-47A – Ganşip, version with reinforced armor and weapons.
SN-47V – version with new engines and lopastyami.SN-47C – new engine modifications.
CH-47D – Modification to increase the resource, payload and other characteristics.
СН-47D International Chinook (Model 414—100) – first export version of the CH-47DNS.
Mk.1 and Mk.1V – version of the CH-47 for the Air Force in England
MH-47D – option for special operations with the possibility of in-flight refueling, landing system by descent on the rope with the trigger roller type, and other updates. Six helicopters MH-47D converted from CH-47A, six - of the CH-47C.
C / MH-47E – a multi-purpose version with extended range and refueling in flight, weapons and new equipment.
CH-47F – development of CH-47D with new engines, avionics and airframe.
MH-47G – option for special operations on the basis of MH-47E with new avionics.
HH-47 – rescue modification MH-47G.
SN-47J – option for the Japanese Self-Defense Forces.
CH-47SD (Great) – further modernization of the CH-47D, increased fuel tanks, improved digital control.
The performance characteristics of the CH-47 Chinook
– Getting Started: December 1962 of the year
– units produced: 1 200+ (on 2012)
StoimostCH-47 Chinook
– US$ 28,9 million (2012)
The crew of a CH-47 Chinook
– 2-3 man (2 pilot, borttehnik or commander of the operation)
Capacity of the CH-47 Chinook
– 33-55 the soldiers or 24 bedridden patients 2 the accompanying
Overall dimensions of the CH-47 Chinook
– Length: 30,14 m
– fuselage length: 15,87 m (without refueling boom)
– The diameter of the rotor: 18,29 m (each)
– Height: 5,59 m
– Area, swept rotor: 525,3 m²
– The base chassis: 7,87 m
Dimensions of cargo cabin
– Length: 9,19 m
– Width: 2,51 m
– Height: 1,98 m
– floorage: 21,0 m²
– Useful volume: 41,7 m³
Weight CH-47 Chinook
– empty weight: 12210 kg
– Normal takeoff weight: 22680 kg
– Maximum takeoff weight: 24494 kg
Payload CH-47 Chinook
– Payload weight: 12284 kg
Volume of tanks CH-47 Chinook
– Volume of fuel tanks: 7828 l (+3 × 3028 l additional tank in the cargo hold)
– Mass fuel in internal tanks: 6815 kg
Engines CH-47 Chinook
– Power point: 2 × турбовальных Honeywell T55-L-714
– engine power: 2 × 4168 HP. (2 × 3108 kW)
– thrust-to-weight ratio: 229,4 W / kg (for transmission at maximum takeoff weight)
CH-47 Chinook speed
– full speed: 285 kmh
– Cruising speed: 259 kmh
– Skoropodъёmnost: 9,35 m / s
Flight range CH-47 Chinook
– combat radius: 935 km
– Ferry range: 2333 km
Practical ceiling CH-47 Chinook
– 3090 m
Static ceiling of the CH-47 Chinook
– Static ceiling using ground effect: 1675 m
– Static ceiling without the use of ground effect: 2985 m
Armament CH-47 Chinook
– Small-pushechnoe: 3 × 7,62 mm machine gun (2 in the doorway 1 the ramp)
Photo CH-47 Chinook
Downed CH-47 Chinook
Cabin CH-47 Chinook
Cab CH-47F Chinook
Cab CH-47D Chinook
Inside the CH-47 Chinook
CH-47С Chinook
CH-47D Chinook
CH-47J Chinook
