The present invention relates to a lightweight helicopter with features of coaxial, contra-rotating rotors and weight shift control. It has a rotary wing unit attached to a tricycle assembly through a hang bolt. The rotary wing unit has an engine mounted below a keel post, which drives a pair of co
The present invention relates to a lightweight helicopter with features of coaxial, contra-rotating rotors and weight shift control. It has a rotary wing unit attached to a tricycle assembly through a hang bolt. The rotary wing unit has an engine mounted below a keel post, which drives a pair of contra-rotating coaxial rotors through a primary gearbox and a secondary gear box. The keel post is attached to a triangular control frame, the base of which forms the control bar. The keel post also supports a fuel tank connected to the engine and a tail plane having one or more articulated vertical flaps actuated by cables. The secondary gearbox is provided with a free-wheeling clutch, a pinion gear and bevel gears for transmitting the rotary movement of the engine to the counter rotating coaxial vertical shafts each carrying two rotor blades of airfoil cross section fixed by pitch bearing on teetering plates and teetering hinges to form horizontal rotors. The tricycle assembly has a pilot seat and landing gear as well as controls for operation of the engine, rotors, tail plane and landing gear. The directional control of the helicopter is achieved through the weight shift principle by manipulating the control bar, thereby causing a tilt of the contra-rotating rotors, which cause a corresponding tilt in the aerodynamic thrust of the rotors, propelling the helicopter in the required direction.
대표청구항▼
What is claimed is: 1. A light weight helicopter comprising: a rotary wing unit having an engine with a primary gearbox being connected through a flexible coupling and a centrifugal clutch to a secondary gear box, said engine, said primary gearbox and said secondary gearbox being mounted below a ho
What is claimed is: 1. A light weight helicopter comprising: a rotary wing unit having an engine with a primary gearbox being connected through a flexible coupling and a centrifugal clutch to a secondary gear box, said engine, said primary gearbox and said secondary gearbox being mounted below a horizontal keel post using mounting means, said keel post being rigidly attached to a triangular control frame, a base portion of which forms a control bar, said keel post being fixed to a fuel tank and being connected to said engine, said keel post being also provided with a tail plane having one or more articulated vertical flaps capable of being articulated by cable means, said secondary gearbox being provided with a freewheeling clutch, pinion gear and bevel gears capable of transmitting the rotary movement of said engine to two contra-rotating vertical concentric shafts each of which being fixed by a pitch bearing on teetering plates and teetering hinges to horizontal rotors, said horizontal rotors having at least two rotor blades of airfoil cross section capable of pitch change through rotary movement of a pitch horn, said pitch horn on each rotor blade being connected to a star and turnbuckle mechanism and a stationary control fork, said rotary wing unit being attached to a tricycle assembly through a landing gear and provided with means for control of the said engine, rotors, tail plane and landing gear, said tricycle assembly having a triangular frame composed of a rear beam, a horizontal beam and a front tube, said horizontal beam supporting a front fork in a pivot, said front fork being provided with footrest for the pilot, said front fork being attached to cables linking to said articulated vertical flap, such that the rotation of said front fork results in the hinge movement of said articulated vertical flap, said horizontal tube also supporting a plurality of landing gear tubes, which are kept in position through tensioned cables, said landing tubes and the front fork supporting landing gear, the pilot being seated in a seat fixed on the said horizontal beam and secured firmly to the seat through seat belts. 2. The lightweight helicopter of claim 1 wherein said engine is selected from a group consisting of a two-stroke reciprocating petrol engine and a Wankel rotary engine. 3. The lightweight helicopter of claim 1 wherein said triangular control frame articulates said rotary wing unit through a control bar held by the pilot. 4. The lightweight helicopter of claim 1 wherein said means for activating the change in rotor blade mean pitch is a rotatable twist grip located on the control bar and controlled by the pilot. 5. The lightweight helicopter of claim 1 wherein said landing gear is selected from a group consisting of tired wheels, skids and floats. 6. A light weight helicopter comprising: a rotary wing unit having an engine with a primary gearbox being connected through a flexible coupling and a centrifugal clutch to a secondary gear box; a horizontal keel post mounted above said engine, said primary gearbox and said secondary gearbox, said keel post being rigidly attached to a triangular control frame; a base portion of said triangular control frame forms a control bar; a tail plane coupled to said keel post having one or more articulated vertical flaps selectively articulated by cable means; a freewheeling clutch coupling said engine to two contra-rotating vertical concentric shafts; horizontal rotors having at least two rotor blades, said horizontal rotors; teetering plates and teetering hinges coupling said horizontal rotors to said two contra-rotating vertical concentric shafts; and a tricycle assembly having a triangular frame composed of a rear beam, a horizontal beam and a front tube, said horizontal beam supporting a front fork in a pivot, said front fork being provided with footrest for the pilot, said tricycle assembly coupled to said rotary wing unit, said front fork coupled to said articulated vertical flap, such that the rotation of said front fork results in the hinge movement of said articulated vertical flap.
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이 특허에 인용된 특허 (7)
Yanagisawa Gennai,JPX, Coaxial twin-rotor type helicopter.
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