Mil Mi-40: Difference between revisions
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The '''Mil Mi-40''' was a projected utility version of the [[Mil Mi-28]], first initiated in [[1983]], announced in [[1992]] and shown at the [[Moscow]] Airshow in [[1993]]. It was primarily intended for the "Aerial [[Infantry Fighting Vehicle]]" category as a successor to the [[Mil Mi-24]] and [[Mil Mi-8|Mi-8]] assault helicopters. |
The '''Mil Mi-40''' was a projected utility version of the [[Mil Mi-28]], first initiated in [[1983]], announced in [[1992]] and shown at the [[Moscow]] Airshow in [[1993]]. It was primarily intended for the "Aerial [[Infantry Fighting Vehicle]]" category as a successor to the [[Mil Mi-24]] and [[Mil Mi-8|Mi-8]] assault helicopters. |
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It was planned to use two 1,863kW [[Kilmov TV-117VMA]] turboshaft engines, four-bladed main rotor, four-bladed Delta H tail rotor (both from the Mi-28), and retractable tricycle-type landing gear. It was expected to weigh 11-12, |
It was planned to use two 1,863kW [[Kilmov TV-117VMA]] turboshaft engines, four-bladed main rotor, four-bladed Delta H tail rotor (both from the Mi-28), and retractable tricycle-type landing gear. It was expected to weigh 11-12,000 kg and estimated to attain a 3300 m ceiling, a 314 km/h maximum speed and a 260 km/h cruise speed. |
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Specifications required the functioning in day, night and poor weather as well as carrying eight soldiers (the design achieved seven in practice), eight stretchers or large external loads. An emphasis was placed on survivability with a focus on redundancy, IR suppression and special shock absorbers for the crew to increase the maximum "safe" crash velocity. |
Specifications required the functioning in day, night and poor weather as well as carrying eight soldiers (the design achieved seven in practice), eight stretchers or large external loads. An emphasis was placed on survivability with a focus on redundancy, IR suppression and special shock absorbers for the crew to increase the maximum "safe" crash velocity. |
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Revision as of 19:20, 29 March 2009
 | This article includes a list of references, related reading, or external links, but its sources remain unclear because it lacks inline citations. (August 2008) |
The Mil Mi-40 was a projected utility version of the Mil Mi-28, first initiated in 1983, announced in 1992 and shown at the Moscow Airshow in 1993. It was primarily intended for the "Aerial Infantry Fighting Vehicle" category as a successor to the Mil Mi-24 and Mi-8 assault helicopters.
It was planned to use two 1,863kW Kilmov TV-117VMA turboshaft engines, four-bladed main rotor, four-bladed Delta H tail rotor (both from the Mi-28), and retractable tricycle-type landing gear. It was expected to weigh 11-12,000 kg and estimated to attain a 3300 m ceiling, a 314 km/h maximum speed and a 260 km/h cruise speed.
Specifications required the functioning in day, night and poor weather as well as carrying eight soldiers (the design achieved seven in practice), eight stretchers or large external loads. An emphasis was placed on survivability with a focus on redundancy, IR suppression and special shock absorbers for the crew to increase the maximum "safe" crash velocity.
The design incorporated a 23mm cannon (most likely GSh-23L) for defense in the forward hemisphere and a 12.7mm machine gun (most likely Yak-B) for defense in the rear. Fuselage fairings containing fuel would replace stub wings with missiles mounted above on special hardpoints.
Its design borrowed much from the Mil Mi-36 developed over the previous two years, and would itself be replaced after a year by the Mil Mi-42 project. Although the Mi-40 design would be resurrected for a short period in the 1990s, with optimization studies being completed, it did not reach the prototype stage.
See also
Related development
Aircraft of comparable role, configuration, and era
References
Mil Mi-40 (Russian) at www.aviastar.org