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CH-53E Sikorsky is developed by the three heavy-duty multi-purpose helicopter, nicknamed children almost all the important parts were made to repair it. In order to improve flight performance, using the seven new main rotor blades, blade Yeda Liang made by the titanium alloy, to increase transmission power to 11,570 shaft horsepower.
CH-53E
R & D R & D performance characteristics of configuration data structure CH-53E in 1971 started to develop, March 1974 The first prototype first flight, in December 1975 the first production aircraft test the prototype's 1978 20 CH-53E has been put into batch production approval, in June 1981 began to pay for use of key U.S. Marine Corps. Marine Corps CH-53E used in amphibious warfare, which can carry 55 fully armed soldiers, heavy equipment and weapons, and recovery of aircraft damaged in combat. Navy put the CH-53E for vertical replenishment, transport combat equipment, and lifting from the deck of an aircraft carrier damaged aircraft. MH-53 for mine type, number the Navy RH-53D, is mainly used to remove the mines. Constructed a fully articulated CH-53E rotor blades seven, blades from titanium beams, Nomex honeycomb and glass fiber epoxy composite skin composition. Propeller hub from the titanium and steel. Hydraulic folding rotor blades can be. Aluminum tail rotor blades from the four components, installed in the left tail ramp inclined 20 degrees beam soil. Semi-monocoque fuselage was watertight light alloy, titanium structure. Hydraulic tail boom can be folded to starboard. Cockpit can accommodate three crew members. Main cabin can accommodate 55 soldiers. Retractable landing gear for the three-point landing gear. Configuration information is powered by three General Dynamics T64-GE-416 turboshaft engine single engine maximum power of 10 minutes 4380 shaft horsepower, 30-minute average power 4145 hp maximum continuous power of 3696 shp. Dimension Data rotor diameter 24.08 m, tail rotor diameter 6.10 m, the captain (rotor turning) 30.19 m, (rotor and tail folding inclined beams) 18.44 m, body length of 22.48 m, Height (tail rotor turning) 8.66 m, (rotor and tail folded) 5.66 m, 2.69 m wide fuselage, the cabin length × width × height 14 m × 2.29 米 × 1.98 meters. Empty weight 15,070 kilograms of weight data, the maximum takeoff weight of 33,300 kg payload (internal loading, activity radius of 185 km) 13,6 l0 kg (plug-in, the activities of the radius of 185 km) 14,520 kilograms. Performance data (international standard atmosphere, take-off weight of 25,400 kg) maximum level flight speed (sea level) 315 km / h, cruising speed (sea level) 278 km / h, the maximum rate of climb (sea level) 13.96 m / s, practical l limit (maximum continuous power) 5640 meters, hover height (with ground effect, the maximum power) 3520 m (without ground effect, the maximum power) 2895 surgery, a range of (economic cruise more degrees) 2080 km. Features ① engine power, carrying ability. Machine executable amphibious assault mission,[link widoczny dla zalogowanych], carrying 55 fully armed soldiers, transport heavy equipment and ammunition. ② a variety of tasks to be completed. U.S. Navy ship to use it for vertical replenishment, can be removed the damaged aircraft on aircraft carriers. ③ advanced airborne equipment can be carried out in adverse weather conditions at night at low altitude. Main modifications: CH-53E Super Stallion. Basic type. U.S. Marines used the summer of 1983, CH-53E began combat operations in the Mediterranean region, CH-53E's total requirements for the 177. RH-53E Sea Dragon. Naval Air mine type. June 1986 began by the troops, to June 1991 have been equipped with 29 U.S. Navy MH-53E. Another CH-53E's export-oriented S-80E and MH-53E's export-oriented S-80M. Japan has purchased CH-53E11 aircraft. Basic data (CH-53E): Crew 3 3 sets of power plant T64-GE-416 turboshaft engine fuel capacity 3,849 liters (inside), 12,[link widoczny dla zalogowanych],113 liters (MH-53E) maximum speed 315 km / h cruising speed of 278 km / h Service ceiling 5640 m Ferry range 2075 km rotation hover height of 3520 m (with ground effect), 2895 m (no ground effect) Captain Height 8.97 m 30.19 m 24.08 m rotor diameter maximum takeoff weight 31,640 kg (internal load), 33,340 kg (external load) the main compartment can carry 37 fully armed soldiers, airborne automatic flight control system, two digital onboard computer and a four-channel autopilot. Operational Application: April 1980, the Iranian hostage crisis, the U.S. Navy on April 24 sent eight RH-53D in conjunction with C-130 transport planes, carrying commandos implementation of the hostage rescue mission, due to mechanical failure and the plane collision incident, action fails, RH-53D aircraft lost, abandoned 5. During the Gulf War, CH-53E helicopters from the amphibious ships and major logistic support ship equipped with its main task is to vertical landing, vertical replenishment, and mine in the Persian Gulf. War in Bosnia and Kosovo during the war, CH-53E carrying commandos successfully rescued the downed F-16 aircraft, F-117 pilot. Identifying characteristics: ① body flat, front right side of the cockpit door. Fuselage on both sides have large wingtip floats. ② all articulated rotor blades 7, 4 tail rotor blades installed in the 20 degree tilt to the left end of oblique beam. Single set of high level of security in the tail surface of the right oblique beams, with pole support. ③ 3 engine, (non-E type fitted two engines, the fuselage sub-placed shoulder) 3 made more unique configuration, in addition to the installation of a shoulder, respectively, its left side, after launching a short tank top, with the third engine, front-end to launch a network-shaped hood, exhaust after the exhaust pipe was flared laterally. Retractable tricycle landing gear. More Atlas Atlas entry Open Category: aircraft carriers

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