The CH-46 helicopter is one of the U.S. Marine Corps' primary combat attack helicopters, which looks a bit like a bus*** car with twin propellers, and is used by the Marine Corps to transport troops from ship to shore, or from camp to combat forward positions. The U.S. Navy, on the other hand, uses this helicopter to transport equipment to the ship or to perform search and rescue missions.
The CH-46 helicopter was built by Boeing and entered service in 1964.
The helicopter was extremely useful during the Vietnam War, when it first entered service, and was initially used to transport troops and cargo from Navy ships to land, or from land to ship, as well as performing thousands of rescue missions for wounded Marines. Since the Vietnam War, the CH-46 has participated in virtually every major U.S. military operation, including the 2001 war in Afghanistan and the ongoing war against Iraq.
I. Mission
The mission of the CH-46 transport helicopter is to rapidly transport combat troops, support equipment, and supplies from amphibious assault landing ships and established airfields, which are improvised and have limited maintenance and logistical support capabilities, to forward bases. The Navy also uses CH-46D helicopters to attempt vertical resupply, intra-group logistics, medical evacuation, and search and rescue missions.
Second, data
Main contractor: Boeing Vitus
Crew: 4
Initial operational capability: 1964
Ownership: 324
Length: 13.7 meters
Rotor diameter: 15.31 meters
Take-off weight: 11032.2 kg
Maximum speed: 268.25 km/h
Range: 176 kilometers (one-way)
Endurance: 2 hours (CH-46D)
1.75 hours (CH-46E)
Weapons: 2 x MZ (25.4 mm) or M60 (70 mm) guns ( only equipped with CH-46E aircraft)
III. Applications
The 120 CH-46E transport helicopters of 10 U.S. Marine Corps transport squadrons (9 active and 1 reserve) and the 42 CH/HH-46D transport helicopters of 21 Navy transport detachments (with both types of transports) performed the mission of supporting the "Desert Shield and Desert Storm. These helicopters were used for missions such as transporting Marines, Soldiers, cargo, mail, ammunition, and medical evacuation and search and rescue missions
Design Features
Rotor System
Two three-bladed, longitudinal, counter-rotating rotor blades payable to New York Aviation and Kawasaki Heavy Industries, Japan, Boeing 107 IIs, with muzzle-type steel beams, glued aluminum-ribbed fiberglass (scored to aluminum) and aluminum-ribbed fiberglass (scored to aluminum), and aluminum-ribbed fiberglass (scored to aluminum). Glued aluminum rib fiberglass (engraved aluminum) skin trailing edge box structure, the trailing edge of the stainless steel bar, the paddle blade equipped with a force beam internal monitoring system, the system can be pointed out in the paddle beam 15 hours before the destruction of the beam cracks exist. Paddle refurbishment life force 5000 hours. The paddle hub is equipped with a pendulum vibration damper. Paddle Trail overhaul life is 2,000 hours. Rotor speed is 264 rpm. CH / UH a 46 have power to manipulate the paddle when the prayer folding system, including: a set of lights, to indicate the folding of the front paddle should be the angle of attack; a and the rear drive system is connected to the hydraulic motor, to rotate the rotor blades to the azimuth should be, and then lock the rotor blades; a set of electric motors mounted in the folding hinges, the gear reducer can be folded with a speed reduction ratio of 16,000 :1 paddles. The folding system utilizes bearings, requires no lubrication, and has a folding time of approximately 60 seconds. The system has been tested on a test rig for 5000 folding cycles without any damage.
Drivetrain
The power of each engine is fed into the reducer through a clutch and driven to the front and rear reducers and two rotors. Engine rotor speed ratios are 73.722:1 for the CH-46A and 73.770:1 for the CH-113.
Powerplant
Model 107 II: Two 932 kW (1,267 hp) General Electric CT-58-110-1 turboshaft engines are mounted side-by-side at the base of the rear rotor pylons; the HRp. 4 is equipped with two 932 kW (1,267 hp) turboshaft engines; the HRp. 4 is equipped with two 932 kW (1,267 hp) turboshaft engines; the HRp. 4 is equipped with two 932 kW (1,267 hp) turboshaft engines. HRp.4 with two 932 kW (1,267 shp) Brestol Siddeley "Nome" H.1200 turboshaft engines. 107 "A was modified with a newer 044 kW (1,419 shp) CT58-140-1 turboshaft engine. CH-46A is equipped with two 932 dry-watt (1,267 hp) General Electric T58-GE-8B turboshaft engines. The CH/UH-46D was fitted with two 1044 kW (1419 hp) turboshaft engines.
The Model 107II and 107 IIA have two self-sealing fuel tanks in pontoons on either side of the fuselage, made of crash-resistant material, with a total capacity of 325 liters. The CH-46/UH-46 fuel tanks have a total capacity of 438 liters, and the refueling ports are located in the upper part of the tanks. The total skidding capacity is 15.9 liters.
Fuselage
The rectangular-section semi-monocoque structure is mainly made of clad and non-clad high-strength aluminum alloys. The transverse bulkheads and reinforcing frames are the load-bearing members of the drive train, engines and landing gear. The upward sloping lower surface of the rear fuselage is formed by the rear skips on the multi-purpose and military types. The rear of the airliner fuselage consists of a baggage compartment instead of a loading and unloading skip. The fuselage is sealed to allow landing and takeoff over water, and can even be operated in moderate wave heights; the floatation system consists of nine sealed compartments, any one of which
fails to maintain the helicopter's buoyancy and stability over water.
Landing gear
Non-retractable front three-point landing gear. Each landing gear has two tubeless machine wheels measuring 8X5.5.5 with a tire pressure of 10.35X10 "Pa (10.55 kg/cm) and a disc brake mechanism. Landing gear fluids. There are two damping holes in the air damping struts. When the compression speed is less than 0.305 m/s, the larger damping hole is blocked by a spring and a fungus-shaped valve, and the oil passes through the small damping hole, thus ensuring that the helicopter has good ground *** vibration characteristics, and when the compression speed is greater than 0.305 m/s, the valve opens to ensure that the strut has good vibration damping.
Cockpit
Model 107 II: The standard cockpit layout is for two pilots, an onboard attendant and 25 passengers. The cockpit*** has 8 rows of seats, 2 pairs of seats in each row on the left side, a single seat on the right test, and 4 seats in the last row with an aisle in the center. The cabin has luggage racks and a rolled luggage compartment with 680 kg of cargo placed in the lower rear fuselage. The rear skips could be power-operated on the ground or in the air, and could be removed or opened completely for extra-long cargo.CH/UH I46: 3 crew; 25 soldiers
and 1 commander. There is an upper and lower split kneeling door in front of the upper soldier's hatch. The upper half of the hatch is received in the upper fuselage by a slide. The lower half is hinged to the bottom of the fuselage and opens outward with a boarding ladder attached to it. The loading skip and aft fuselage hatch can be opened in flight or over water. The central section of the floor has a carrying capacity of 14.36 dry N/m' (1,464.6 kg/m'), and is flanked on each side by rows of rollers for the transportation of standard military cargo flats or wire baskets. The outside of the floor was a driveway that could carry a tire load of 454 kg. The winch system for lifting cargo and personnel can be operated by one person and has a variable speed winch capable of lifting 907 kg of cargo at 9 m/min or 272 kg of personnel and other items at 30 m/min. The floor has an external lifting hook that can lift 4535 kg of cargo.
Systems
(CH/UH I46) The cockpit heater is combustion type. The hydraulic system used for the flight maneuvering booster has a pressure of 103X10'Pa (105 kg/cm'), and the other systems have a pressure of 206X10'Pa (210 kg/cm'). The electrical system consists of two 40 kVA alternators and a 200 amp DC generator. A Solar auxiliary power unit is fitted for starting the engine and checking the system.
Paddles
A 200-volt, 20-kVA electrical de-icing system was utilized, with six conductors flame-sprayed along the spread of the leading edge of the paddles, with the thickness and width of each conductor varying with the heating requirements of the spread of the paddles. These conductors are periodically heated for de-icing. The de-icing system is controlled by a radioactive ice thickness gauge. When the ice thickness on the rotor reaches 4.77 mm, de-icing is initiated by energizing the three blades of each rotor at the same time to ensure that it does not cause excessive: times/week vibration. The two rotor blades are not de-iced simultaneously. Electronics and Instrumentation Standard instrument flight equipment. The CH- 46 is equipped with a compound stabilization system, and an automatic leveling system. Early CH-46 had a sudden stall vibration of the rear rotor blade, which caused excessive stress on the upper maneuvering parts, and thus the helicopter's permissible gross weight, center of gravity range, speed and altitude had to be severely limited. For this reason, the helicopter was fitted with a cruise indicator that indicates the stress level of the rotor
maneuvering parts, thus relaxing the limitations and reducing the workload of the pilot when driving.