A three-stage helicopter transmission of split torque type is shown to offer advances in a configuration that allows the engine axes to be widely separated and parallel.
Three variants of the configuration are examined; one design with separated drive paths and four final-drive pinions is discussed in detail. This design offers 26 per cent less weight and 9 per cent lower losses than current production transmissions.
Comparison is made with epicyclic type transmissions of similar rating that have been developed in the past decade.
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References
1.
LastineJ. L.WhiteG.Advanced technology VTOL drive train configuration study. USA AVLABS Technical Report 69–69, January 1970.
2.
SolovievP. A.Mechanical drive with angle power transmission. US Patent No. 3 564937, February 1971.
3.
WhiteG.Design of a light-weight split power transmission for a 4000 hp helicopter. Mechanisms Conference 1972, 123–132. (Instn Mech. Engrs, London).
4.
WhiteG.New family of high ratio reduction gears with multiple drive paths. Proc. Instn Mech. Engrs, 1974, 188, 281–288.
5.
WhiteG.Helicopter transmission arrangements with split torque gear trains. Proceedings First European Rotorcraft and Powered Lift Aircraft Forum, Southampton University, September 1975, 36.1–36.11. See also: Advanced power transmission technology, NASA Conference Publication 2210, 141–150, June 1981.
6.
WatsonK.Helicopter power transmission systems. US Patent 3 977 632, August 1976.
7.
WhiteG.A light-weight split torque transmission for a 330 kW helicopter. Proc. Instn Mech. Engrs, 1982, 196(2), 11–22.
8.
WhiteG.Design study of split torque helicopter transmissions. NASA Technical Report NAS-3-22528, August 1982.
9.
WhiteG.Design study of a 375 kW helicopter transmission with split torque epicyclic and bevel drive stages. Proc. Instn Mech. Engrs, Part C, 1983, 197, 213–224.
