A helicopter has a main rotor with propeller blades which is driven by a rotor shaft and which is hinge-mounted to this rotor shaft. The angle between the surface of rotation of the main rotor and the rotor shaft may vary. A swinging manner on an oscillatory shaft is essentially transverse to the r
A helicopter has a main rotor with propeller blades which is driven by a rotor shaft and which is hinge-mounted to this rotor shaft. The angle between the surface of rotation of the main rotor and the rotor shaft may vary. A swinging manner on an oscillatory shaft is essentially transverse to the rotor shaft of the main rotor and is directed transversally to the longitudinal axis of the vanes. The main rotor and the auxiliary rotor are connected to each other by a mechanical link. The swinging motions of the auxiliary rotor controls the angle of incidence (A) of at least one of the propeller blades of the main rotor. There are wings from the body and a stabilizer at the tail.
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What is claimed is: 1. A remote control toy helicopter comprising a body with a tail; a motor and a battery for the motor, the motor being controllable by a controller remote from the helicopter body; a main rotor with propeller blades which is driven by a rotor shaft on which the blades are mounte
What is claimed is: 1. A remote control toy helicopter comprising a body with a tail; a motor and a battery for the motor, the motor being controllable by a controller remote from the helicopter body; a main rotor with propeller blades which is driven by a rotor shaft on which the blades are mounted; a tail rotor which is driven by a second rotor shaft directed transversally to the rotor shaft of the main rotor, an auxiliary rotor driven by the rotor shaft of the main rotor for rotation in the sense of rotation of the main rotor, the auxiliary rotor being mounted such that the generally longitudinal axis of the auxiliary rotor in the sense of rotation, is located at an angle relative to a generally longitudinal axis of one of the propeller blades of the main rotor, and wherein the generally longitudinal axis of the auxiliary rotor is along a center line of the auxiliary rotor passing to the rotor shaft, and the generally longitudinal axis of one of the propeller blades of the main rotor is determined from an end area of the blade to the rotor shaft, and the angle is less than about 25 degrees, and preferably about 10 degrees, and wherein the auxiliary rotor is mounted in a swinging relationship on an oscillatory shaft and the swinging motion being relatively upwardly and downwardly about the oscillatory shaft, and which oscillatory shaft is provided essentially transverse to the rotor shaft of the main rotor, such that the swinging motion of the auxiliary rotor controls the angle of incidence of at least one of the propeller blades of the main rotor, and a joint of the main rotor to the propeller blade formed of a spindle which is fixed to the rotor shaft of the main rotor, the spindle being directed substantially parallel to the generally longitudinal axis of at least one of the propeller blades of the main rotor, the blades being a relatively rigid structure essentially from the end area of one blade through an area adjacent to the rotor shaft to the end area of an opposite blade. 2. A remote control toy helicopter comprising a body with a tail; a motor and a battery for the motor, the motor being controllable by a controller remote from the helicopter body; a main rotor with propeller blades which is driven by a rotor shaft on which the blades are mounted; a tail rotor which is driven by a second rotor shaft directed transversally to the rotor shaft of the main rotor, an auxiliary rotor driven by the rotor shaft of the main rotor for rotation in the sense of rotation of the main rotor, the auxiliary rotor being mounted such that the generally longitudinal axis of the auxiliary rotor is located relative to a generally longitudinal axis of one of the propeller blades of the main rotor, and wherein the auxiliary rotor includes elongated members, the elongated members being directed in the plane defined by the rotation of the auxiliary rotor, and wherein each propeller blade has a profile wherein along the direction of its generally longitudinal axis of each blade includes a first longitudinal convex curve from a position towards the rotor shaft to a position towards an end area of the blade, and wherein the auxiliary rotor is mounted in a swinging relationship on an oscillatory shaft and the swinging motion being relatively upwardly and downwardly about the oscillatory shaft, and which oscillatory shaft is provided essentially transverse to the rotor shaft of the main rotor, such that the swinging motion of the auxiliary rotor controls the angle of incidence of at least one of the propeller blades of the main rotor, and a joint of the main rotor to the propeller blade formed of a spindle which is fixed to the rotor shaft of the main rotor, the spindle being directed substantially parallel to the generally longitudinal axis of at least one of the propeller blades of the main rotor, the blades being a relatively rigid structure essentially from the end area of one blade through an area adjacent to the rotor shaft to the end area of an opposite blade, and wherein each blade includes a second transverse convex curve in a profile on its top face from a position towards a leading edge towards a position towards a trailing edge, the second transverse convex curve preferably being present over a substantial portion of the generally longitudinal length of the blade. 3. A helicopter according to claim 1 wherein the main rotor includes two propeller blades situated essentially in line with each other, and the auxiliary rotor includes two elongated members, selectively vanes, situated essentially in line with each other, preferably there being only the two blades and only the two elongated members, selectively vanes, respectively, and the center line is selectively a line from a radial end area of the auxiliary rotor passing to the rotor shaft. 4. A helicopter according to claim 2 wherein the main rotor includes two propeller blades situated essentially in line with each other, and the auxiliary rotor includes two elongated members, selectively vanes, situated essentially in line with each other, preferably there being only the two blades and only the two elongated members, selectively vanes, respectively, and the center line is selectively a line from a radial end area of the auxiliary rotor passing to the rotor shaft. 5. A helicopter according to claim 2 wherein the main rotor includes two propeller blades situated essentially in line with each other, and the elongated members are respectively two vanes situated essentially in line with each other, preferably there being only the two blades and only the two vanes respectively, and wherein each rotor blade includes a second transverse convex curve in a profile on its top face from a position towards a leading edge towards a position towards a trailing edge, the second transverse convex curve preferably being present over a substantial generally longitudinal length of the blade. 6. A helicopter according to claim 4 wherein the main rotor includes two propeller blades situated essentially in line with each other, and the elongated members are respectively two vanes situated essentially in line with each other, preferably there being only the two blades and only the two vanes respectively, and wherein each rotor blade includes a second transverse convex curve in a profile on its top face from a position towards a leading edge towards a position towards a trailing edge, the second transverse convex curve preferably being present over a substantial generally longitudinal length of the blade. 7. A helicopter according to claim 1 wherein the generally longitudinal axis of the auxiliary rotor is determined along a center line of the auxiliary rotor passing through the rotor shaft, and the generally longitudinal axis of one of the propeller blades of the main rotor is from an end area of the blade to the rotor shaft, and the angle is less than about 25 degrees, and preferably about 10 degrees, and wherein the main rotor includes two propeller blades situated essentially in line with each other, and the auxiliary rotor includes two elongated members, selectively vanes, situated essentially in line with each other, preferably there being only the two blades and only the two elongated members, selectively vanes, respectively, and the center line is selectively a line from a radial end area of the auxiliary rotor to the rotor shaft. 8. A helicopter according to claim 2 wherein the generally longitudinal axis of the auxiliary rotor is determined along a center line of the auxiliary rotor passing through the rotor shaft, and the generally longitudinal axis of one of the propeller blades of the main rotor is from an end area of the blade to the rotor shaft, and an angle between the generally longitudinal axis of the auxiliary rotor and the generally longitudinal axis of one of the propeller blades of the main rotor, in the sense of rotation, is less than about 25 degrees, and preferably about 10 degrees, and wherein the main rotor includes two propeller blades situated essentially in line with each other, and the auxiliary rotor includes two elongated members, selectively vanes, situated essentially in line with each other, preferably there being only the two blades and only the two elongated members, selectively vanes, respectively, and the center line is selectively a line from a radial end area of the auxiliary rotor to the rotor shaft. 9. A helicopter according to claim 1 wherein the propeller blades of the main rotor, and the auxiliary rotor respectively are connected to each other with a mechanical linkage that permits the relative movement between the blades of the propeller and the auxiliary rotor. 10. A helicopter according to claim 2 wherein the propeller blades of the main rotor, and the auxiliary rotor respectively are connected to each other with a mechanical linkage that permits the relative movement between the blades of the propeller and the auxiliary rotor. 11. A helicopter according to claim 1 wherein a fastening point of a rod situated on the main rotor is at a distance from the axis of the spindle of the propeller blades of the main rotor, and another fastening point of the rod is situated on the auxiliary rotor at a distance from the axis of an oscillatory shaft of the auxiliary rotor. 12. A helicopter according to claim 2 wherein a fastening point of a rod situated on the main rotor is at a distance from the axis of the spindle of the propeller blades of the main rotor, and another fastening point of the rod is situated on the auxiliary rotor at a distance from the axis of an oscillatory shaft of the auxiliary rotor. 13. A helicopter according to claim 1 wherein the auxiliary rotor is provided with stabilizing weights which are fixed respectively to elongated members of the auxiliary rotor, the elongated members being directed in the plane of rotation of the auxiliary rotor. 14. A helicopter according to claim 1 wherein the auxiliary rotor is mounted for relative oscillating movement about the rotor shaft so that when one elongated member of the rotor moves relatively upwardly the other elongated arm moves relatively downwardly and being such that for different relative positions, the auxiliary rotor causes the angle of incidence of the main rotor to be different. 15. A helicopter according to claim 2 wherein the auxiliary rotor is mounted for relative oscillating movement about the rotor shaft so that when one elongated member of the rotor moves relatively upwardly the other elongated arm moves relatively downwardly and being such that for different relative positions, the auxiliary rotor causes the angle of incidence of the main rotor to be different. 16. A helicopter according to claim 4 wherein the auxiliary rotor is mounted for relative oscillating movement about the rotor shaft so that when one elongated member of the rotor moves relatively upwardly the other elongated arm moves relatively downwardly and being such that for different relative positions, the auxiliary rotor causes the angle of incidence of the main rotor to be different. 17. A rotor assembly for a remote control toy helicopter, comprising a motor and a battery for the motor, the motor being controllable by a controller remote from the helicopter body; a main rotor having two propeller blades mounted on a rotor shaft for rotation with the rotor shaft, an auxiliary rotor mounted on the rotor shaft for rotation in the sense of rotation of the main rotor, the auxiliary rotor being mounted in a swinging relationship on an oscillatory shaft provided essentially transverse to the rotor shaft of the main rotor and the swinging motion being relatively upwardly and downwardly about the oscillatory shaft, the main rotor and the auxiliary rotor having planes of rotation spaced from each other and being linked with each other by a mechanical linkage, such that the swinging motion of the auxiliary rotor controls an angle of incidence of the propeller blades of the main rotor, and wherein at least one propeller blade of the main rotor is for pivotably mounting on a spindle which is fixed on the rotor shaft, a longitudinal axis of the main rotor being from an end of one blade towards the rotor shaft, and wherein each propeller blade has a profile wherein along the direction of it generally longitudinal axis of each blade includes a first longitudinal convex curve from a position towards the rotor shaft to a position towards an end area of the blade, the convex curve extending over a portion of the length of the blade, and wherein each blade includes a second transverse convex curve in a profile on its top face from a position towards a leading edge towards a position towards a trailing edge, the second transverse convex curve preferably being present over a substantial portion of the generally longitudinal length of the blade. 18. A rotor assembly according to claim 17, wherein the upper surface of each propeller blade is convex along a significant portion of an axis of the blade, and the lower surface is concave along the same portion of the axis of the blade, the upper and lower surfaces being parallel along the axis, wherein the axis passes through the center of rotation of the blade and to the tips of the blades. 19. A rotor assembly according to claim 17, wherein the top surface of each propeller blade along the leading edge of each blade is a convex curve along a significant portion of its length, oriented with the peak uppermost, in a plane perpendicular to the plane of rotation of each blade. 20. A rotor assembly according to claim 17, wherein the bottom surface of each propeller blade along the leading edge of each blade is a concave curve along a significant portion of its length, oriented with the peak uppermost, in a plane perpendicular to the plane of rotation of each blade.
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이 특허에 인용된 특허 (95)
Kastan Howard (Northridge CA), Advanced control system for a rotor and/or a compound or rotary wing vehicle.
Vuillet Alain E. (Bouc Belair FRX) Philippe Jean J. (Versailles FRX) Desopper Andr (Garches FRX), Blade with curved end for a rotary airfoil of an aircraft.
Sims Anson (Granada Hills CA) Jones Lawrence T. (Playa Del Rey CA) Howden Ashley G. (Los Angeles CA) Lee Robert S. (West Lake Village CA), Insect simulating mobile toy having flappable wings.
Eickmann Karl (2420 Isshiki Hayama-machi ; Kanagawa-ken JPX), Vehicle for traveling in the air and on the ground equipped with hydraulically driven propellers.
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