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Boeing C-17
Boeing C-17

Boeing C-17 Globemaster


Boeing C-17 Globemaster - Strategic American military transport aircraft. It should be in service with the US Air Force, Australia, Qatar, the UAE, Canada, Great Britain, India, Kuwait.

Designed for the transportation of personnel and cargo, and cargo dropping from a plane.

It was developed to replace the cargo version Lockheed c-141 Starlifter. The first flight made 15.09.1991.

DesignBoeing C-17 Globemaster

The aircraft was created using a typical aerodynamic scheme, consisting of a large-diameter fuselage with a T-shaped tail and a high wing. The glider material is mainly aluminum alloys, some of the composite materials are small - 10-15% (controls, wing end surfaces, fairings and bays). The glider provides warranty service life - 30 thousand flight hours. The wing has a supercritical profile, sweep - 25 °, elongation - 7,2. Dimensions of the terminal aerodynamic surfaces (KAP): height - 2,9 m, area - 3,33 m², sweep - 30 °, vertical inclination - 15 °.

Boeing C-17

The wing skin panels used 26,82 m long - the largest aluminum aircraft components end 1980-ies. The ailerons are made of composite materials. Each length is 6,4 m, area - 5,9 m², root chord - 1,32 m, end - 0,76 m.

The wing mechanism includes double-slotted flaps and slats, which are blown by the flow of gases from the engines. They are taken with prototype YC-15, cover an area of ​​the wing surface at 2 / 3. The position of the flaps can be changed depending on the flight mode. In the reclined position during the landing of the aircraft speed reduced by 46 km / h. On each wing flaps placed in front of the console spoilers in four sections.

The fuselage is made on semi-monocoque type has a beveled top of the tail with two aerodynamic ridges below. The cargo compartment has a rear cargo ramp, on which you can place a weight of up to 18 tons. The ramp is composed of four sections and is equipped with a hydraulic drive. The angle of its installation depends on being loaded into the plane technology. The load on the mooring sites - 11,3 ton. The nodes are placed in the cabin at a distance 0,61 m apart. As part of the handling equipment are roller conveyor and rails.

Boeing C-17

The volume of cargo cabin is designed to carry tanks M1A1, M2 / 3 infantry fighting vehicles, trucks weighing 45 t, SUVs (three in number), self-propelled artillery caliber 155 mm, and three attack helicopters AH-64 «Apache" to 18 463L cargo containers. In the airplane established 54 of fixed folding seat for the transport of military personnel and equipment provided more additional seats (48 pcs.), Which are stored on board. Holder 12 stretcher in the form of racks installed on the sides of the aircraft.

Boeing C-17 has armored the lower part of the fuselage, which provides protection against small arms. The aircraft is designed for non-stop landing cargo from putting the parachute device with extremely low altitudes or to 102 landing parachutists.

The crew consists of three people: the commander of the ship, the second pilot (sitting side by side in the control room) and the operator of loading and unloading equipment (located under the floor of the control cabin on the starboard side). There are places for two observers. Penetrate into the control room can be through the door with a built-in staircase, which is on the left side. The glazing of the cabin is thick enough to not be damaged from collision with oncoming birds. The rest room of the crew is presented completely by an autonomous module, similar to passenger aircraft, located immediately behind the control cabin.

Boeing C-17 cabin

T-tail has swept stabilizer and fin. stabilizer area - 79,2 m², swing - 19,81 m rudders and height of two sections.. elevator section length -. 4,45 m two-segment rudder has a height m 3,4.

The aircraft is equipped with a three-support retractable chassis with hydraulic drive and the possibility of its emergency release. The structure of the chassis elements is designed for landing, during which the speed of descent reaches 4,57 m / s, and operation with non-betonated and concreted runways. Front support two-wheeled, with retraction forward. The basic supports six-wheeled, have in structure two consistently located uniaxial three-wheeled carts, retracted on each side of a fuselage in fairings. The aircraft is equipped with a braking system that allows you to stop the car at a speed of 240 km / h, weight 228 t on a segment of the road 490 m in 14 seconds. Base chassis - 20,05 m, track - 10,27 m.

Boeing C-17 Globemaster

The structure of the power plant Boeing C-17 includes four engines, which are located in nacelles on the pylons under the wings. Modular turbofan F117-PW-100, which is mounted on a plane - this version of the engine for civil aircraft PW2040. This engine is equipped with a single-stage fan, four-stage LP compressor, 12-HP stage compressor, two-stage HP turbine and turbo five-ND.

Present devices reverse thrust in flight and on the ground. Gaza during the reverse flow upwards to prevent the penetration of foreign objects inside the engine, which can cause damage to the structure. The power plant is equipped with electronic engine management and control system of the active radial clearances. The engine has a length of 3,729 m, dry weight - 3220 kg. Auxiliary Power Unit "Garrett» GTCP331 placed in the compartment right main landing gear.

Boeing C-17 Salon

The total capacity of the fuel tanks is 102 614 l. The aircraft is equipped with air refueling.

The onboard equipment includes an electric remote digital control system with a hydraulic drive from the ailerons of rudders of direction and height and a four-channel redundancy scheme. There is an emergency control system with mechanical wiring. 17.10.1991, there was a case of failure of all channels of the EMF, and the device was able to land only thanks to the emergency system. The investigation showed that the cause of the accident was the software failure. By the end of 1992, the EMF software has been changed, allowing the possibility, with loss of the airspeed signal, to pass to fixed gain factors.

On-board equipment received a new type of control knob. It is fully rejected for pitch control and partly to the top of the roll control.

Boeing C-17

The aircraft is equipped with improved handling and stability. Experienced checking on flights with a large angle of attack showed the need to set the angle of attack limiter. Also proved insufficient level departure warning signs of dangerous options stall with flaps. The problem persists installation shaker lever.

EquipmentBoeing C-17 Globemaster

The structure of instrumentation includes two ILS, four multifunctional color display, it is possible to use night vision goggles.

Boeing C-17

The equipment presented onboard autonomous system of neutral gas generating OBIGGS, weather radar, "Bendix» AN / APS-133 (V), satellite navigation receiver system.

Boeing C-17 Globemaster characteristics:

developer McDonnell Duglas - Boeing
designation C-17A «Globemaster III»
A type heavy military transport aircraft
First flight 17 September 1991 of
Crew 3
Dimensions & Weight
Aircraft Length m 53,04
Wingspan, m 50,29
Wing area, m2 353
Sweep the front edge of the wing 25 °
Height, m 16,79
Dimensions of cargo cabin, m length (including the length of the rear ramp 6,05 m) 20,79
maximum width 5,49
height under the wing 3,76
maximum height 4,11
The volume of cargo cabin, m3 592
Maximum Takeoff Weight, kg 263083
Empty weight, kg 122016
Maximum payload Overload 2,25, kg 78108
Normal payload transportation: kg between the theaters of military action in case of overload 2,5 56245
heavy loads Overload 2,25 69535
Fuel capacity, l 102614
Power point
number of engines 4
engine's type Turbofan R117-PW-100
Engine thrust, kgf (kN) 4h 19000 (185.49)
flight data
Flight speed, km / h (M =) cruising at an altitude of 8535 m -0,77
Maximum cruising (terrestrial indicator) in flight at low altitude 648
Speed ​​when dropped loads (earth indicator), km / h near the ground 2713934-4
m at an altitude of 7620 2713934-4
Approach speed with a maximum transported load, km / h 213
Practical ceiling, m 13700
Flight distance without refueling in flight with a load, km 72575 2,25 kg Overload 4445
71895 2,25 kg Overload 5000
56245 2,5 kg Overload 5190
Ferry range, km 9430
Radius without in-flight refueling, km the load 36785 3,0 kg Overload 925
the load 56245 2,25 kg Overload during the flight back and unloaded during the flight back 3520
Required runway length, m. take-off with a load of 75750 kg 2286
landing with a load 75750 kg using reverse thrust 915




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