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 plane is created in a typical aerodynamic configuration, a part of the large-diameter fuselage with a T-tail and high wing settling down. The material of manufacture of the airframe - mainly aluminum alloys, composite materials of the small - 10-15% (controls, the end surface of the wing fairings and fairings). On glider provided the warranty period - 30 thousand. flight hours. The wing has a supercritical profile, sweep - 25 °, elongation - 7,2. Dimensions of the end of the aerodynamic surfaces (CAP): height - 2,9 m, area - 3,33 m² sweep - 30 °, inclination of the vertical - 15 °.
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.
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 next to the cab control) and the operator of cargo handling equipment (located under the floor on the right side the control room). There are places for two observers. Infiltrate into the control cabin can be built through the door with a ladder, which is located on the left side. cockpit glazing is thick enough not to be damaged by a collision with birds colliding. Crew Lounge is presented completely self-contained unit, the same passenger aircraft, it is just behind the control cab.
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 retractable tricycle landing gear with a hydraulic drive and the possibility of an emergency release. chassis design elements intended to land, during which the rate of descent reaches 4,57 m / s and operating with nebetonirovannyh and concreted runway. Front support two-wheeled, with retracting forward. Major support six-wheeled, are composed of two successive single-axle three-wheeled carts, retractable on the sides of the fuselage fairings. The aircraft is equipped with a braking system that allows to stop the car at a speed of 240 km / h, a mass m on 228 490 m stretch of road for 14 seconds. The 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.
The total capacity of the fuel tanks is 102 614 l. The aircraft is equipped with air refueling.
The structure of the on-board equipment includes a digital-wire control system with hydraulic drive from the aileron and rudder height and four-redundancy scheme. There is alarm system with manual control wiring. 17.10.1991 occurred if all the channels FBWCS, and put the unit was only thanks to the alarm system. The investigation revealed that the cause of the accident was the failure of the software. By the end of the year 1992 IN FBWCS changed, providing an opportunity to the loss of airspeed signal to switch to a fixed gain.
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.
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.
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|
|Dimensions & Weight|
|Aircraft Length m||53,04|
|Wing area, m2||353|
|Sweep the front edge of the wing||25 °|
|Dimensions of cargo cabin, m||length (including the length of the rear ramp 6,05 m)||20,79|
|height under the wing||3,76|
|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|
|number of engines||4|
|engine's type||Turbofan R117-PW-100|
|Engine thrust, kgf (kN)||4h 19000 (185.49)|
|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||2001-2003|
|m at an altitude of 7620||2001-2003|
|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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