| 摘要 |
The present invention relates to a lightweight helicopter, comprising of a rotary wing ( 1 ) unit and a frame assembly ( 2 ), the rotary wing consists of an engine ( 3 ) with a primary gear box ( 7 ), mounted below a keel post ( 8 ) and the keel post attached to a triangular control frame ( 28 ), the base of which forms the control bar ( 29 ), and is also provided with a tail plane ( 12 ) having one or more vertical articulable flaps ( 34 ). A secondary gearbox is provided with means capable of transmitting the rotary movement of the said engine to two horizontal rotors ( 9, 10 ) capable of pitch change. The rotary wing unit is suspended by means to a frame assembly having means ( 47 ) for pilot seating, landing gear ( 46 ) and provided with means for control of the engine, rotors, tailplane and landing gear.
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