Mil V-16
| V-16 | |
|---|---|
| General information | |
| Manufacturer | Mil |
The Mil V-16 was a Soviet heavy cargo/transport helicopter project of the late 1960s. The Mil V-16 was designed by Mil Design Bureau, a Moscow helicopter plant. The original scheme described a heavy side-by-side twin-rotor aircraft with two soloviev D-25VF gas turbine engines[1] below six-bladed rotors at the tips of heavily supported wings on each side of the fuselage and tricycle-type landing gear, with both rear landing wheels mounted below the wings while the front wheel was located below the cockpit, as well as located directly under the wings.
Designed to be capable for transporting large numbers of combat units, the V-16 was also intended as a Soviet military vehicle transportation aircraft.[2] This aircraft was one of the first for the USSR to begin using operational based algorithms within its controlling systems.[3]
A sample of V-16 has been on show at the Le Bourget-Paris "Salon de l'Aviation" in June, 1971. After attention two more shows in France, the aircraft was not shown again until the project shifted towards the V-12.
This helicopter and its later versions, would go on to influence other countries' military designs. Most noteable, the United States developed a similar design called the CH-47 Chinook, following the Soviet V-16. This Boeing aircraft, took the long fuselage of the V-16 (and its related projects) as well as its cargo capacity, and engineered the rotary wings on top.
Variants
- V-12
- Designed by the USSR during the Mil V aircraft projects to lift and transport. Aircrafts design originating from the Mil V-16 prototype which toured Europe displaying the Soviets latest aviation advances.
- V-16
- Proposed ultra-heavy version of the V-12, intended to lift 40,000 to 50,000 kg (88,000 to 110,000 lb). Originally envisaged in a three rotor layout, powered by six Soloviev D-25VF engines, but reverted to a two-rotor system similar to the V-12 powered by two large gas generators supplying a single large low pressure free-turbine driving a main gearbox each.[4]
- Mi-16
- The proposed VVS designation for the production V-16.[4]
Specifications (V-16)
General characteristics (Planned)
- Length: 37 m (121 ft 5 in)
- Wingspan: 67 m (219 ft 10 in) across rotors
- Height: 12.5 m (41 ft)
- Empty Weight: 69,100 kg
- Gross Weight: 97,000 kg
- Max Takeoff Weight: 105,000 kg
- Freight compartment: 28.15×4.4×4.4 m (92.4×14.4×14.4 ft)
- ^ "Soviet helicopters (Development and testing of Soviet helicopters)". Army Foreign Science and Technology Center. 1: 12. 1969 – via ProQuest SciTech Collection.
- ^ JWR, Taylor (1977). "Trends in Soviet aircraft design". Aerospace (UK). 4: 21.
- ^ Minshnev, B.F. (1977). "Optimal control of helicopter longitudinal motion on the basis of an operational algorithm". Soviet Aeronautics. 20: 107 – via ProQuest SciTech Collection.
- ^ a b Gordon, Yefim; Dimitriy and Sergey Komissarov (2005). Mil's heavylift helicopters : Mi-6, Mi-10, V-12 and Mi-26. Red Star. Vol. 22 (2nd ed.). Hinckley: Midland Publishing. ISBN 1-85780-206-3.