Helicopters At War. Sikorsky H-34 And Bell UH-1 | Listen To Hero And Medal of Honor Patrick Brady

Major General, hero and medal of honor Patrick Henry Brady talks about the Sikorsky H-34 and Bell UH-1 helicopters.
The Sikorsky H-34 and Bell UH-1 are two iconic helicopters that have played an essential role in military and civilian applications over the years. They have contributed significantly to the evolution of helicopter technology and have set the standard for modern rotorcraft design.

Sikorsky H-34:
The Sikorsky H-34 is a medium-sized helicopter that was first introduced in 1954 as the Sikorsky S-58. It was initially designed for the U.S. Navy, which was looking for a replacement for its aging helicopter fleet. The H-34 was a significant improvement over the previous generation of helicopters, offering increased speed, range, and payload capacity.
The H-34 had a unique design, with a cockpit located at the front and a large, round fuselage that could accommodate up to 16 passengers or cargo. It was powered by a single Pratt & Whitney R-1820-84 radial engine, which produced 1,525 horsepower, giving the helicopter a top speed of 120 miles per hour and a range of over 300 miles.
The H-34 was used extensively during the Vietnam War, where it was known as the "Choctaw" by the U.S. Army and the "Seabat" by the U.S. Navy. It was used primarily for troop transport, medical evacuation, and search and rescue missions. The H-34 was also used by several other countries, including France, Germany, and the United Kingdom.

Bell UH-1:
The Bell UH-1, also known as the "Huey," is a legendary helicopter that has become synonymous with the Vietnam War. It was first introduced in 1959 and quickly became one of the most recognizable helicopters in the world. The UH-1 was designed primarily as a utility helicopter, capable of transporting troops, equipment, and supplies.
The UH-1 had a distinctive design, with a single main rotor and a tail rotor to counteract torque. It could accommodate up to 14 passengers or cargo and was powered by a single Lycoming T53-L-11 turboshaft engine, which produced 1,100 horsepower, giving the helicopter a top speed of 135 miles per hour and a range of over 300 miles.
The UH-1 was used extensively during the Vietnam War, where it was primarily used for troop transport and medical evacuation. It was also used for close air support and as a gunship, equipped with machine guns and rockets.
One of the most significant advantages of the UH-1 was its versatility. It could operate in a wide range of environments, from jungles to deserts, and was capable of performing a variety of missions. It was also relatively easy to maintain and repair, making it a popular choice for military and civilian organizations around the world.

H-34 General characteristics:
Crew: 2
Capacity: 12 troops (H-34A) / 18 troops (H-34C) / 8 stretchers
Length: 47 ft 2 in (14.38 m) fuselage
56 ft 8.5 in (17 m) rotors turning[citation needed]
Height: 14 ft 3.5 in (4.356 m)
Empty weight: 7,646 lb (3,468 kg)
Gross weight: 11,867 lb (5,383 kg)
Max takeoff weight: 13,300 lb (6,033 kg)
Fuel capacity: 198–307 US gal (165–256 imp gal; 750–1,160 l)
Powerplant: 1 × Wright R-1820-84 Cyclone , 1,525 hp (1,137 kW) for take-off
1,275 hp (951 kW) METO for 5 minutes
Main rotor diameter: 56 ft 0 in (17.07 m)
Main rotor area: 2,463 sq ft (228.8 m2) *Blade section: - NACA 0012[119]
Performance
Maximum speed: 122 mph (196 km/h, 106 kn) [120]
Cruise speed: 97 mph (156 km/h, 84 kn) [120]
Range: 190 mi (310 km, 170 nmi)
Service ceiling: 12,000 ft (3,700 m)
Hover ceiling IGE: 9,600 ft (2,926 m) (H-34A)
Hover ceiling OGE: 5,500 ft (1,676 m) (H-34A)
Rate of climb: 1,500 ft/min (7.6 m/s) at sea level
Vertical rate of climb: 600 ft/min (3.05 m/s) at sea level

UH-1 General characteristics:
Crew: 1–4
Capacity: 3,880 lb (1,760 kg) including 11-14 troops, 6 stretchers and attendant, or equivalent cargo
Length: 57 ft 9+5⁄8 in (17.618 m) with rotors
Width: 9 ft 6+1⁄2 in (2.908 m) (over skids)
Height: 14 ft 5+1⁄2 in (4.407 m) (tail rotor turning)
Empty weight: 5,210 lb (2,363 kg)
Gross weight: 9,039 lb (4,100 kg) (mission weight)
Max takeoff weight: 9,500 lb (4,309 kg)
Powerplant: 1 × Lycoming T53-L-13 turboshaft, 1,400 shp (1,000 kW) (limited to 1,100 shp (820 kW) by transmission)
Main rotor diameter: 48 ft 0 in (14.63 m)
Main rotor area: 1,809.56 sq ft (168.114 m2)
Performance
Maximum speed: 127 mph (204 km/h, 110 kn) (at maximum takeoff weight; also Vne at this weight)
Cruise speed: 127 mph (204 km/h, 110 kn) (at 5,700 ft (1,700 m) at maximum takeoff weight)
Range: 318 mi (511 km, 276 nmi) (with maximum fuel, no reserves, at sea level)
Service ceiling: 12,600 ft (3,800 m) (at maximum takeoff weight)
Rate of climb: 1,600 ft/min (8.1 m/s) at sea level (at maximum takeoff weight)
Disk loading: 5.25 lb/sq ft (25.6 kg/m2)
Power/mass: 0.1159 hp/lb (0.1905 kW/kg)

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