Helicopter

Abstract

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.

1 . A helicopter comprising a body with a tail; a main rotor with propeller blades which is driven by a rotor shaft and which is hinge mounted on this rotor shaft, such that the angle between the plane of rotation of the main rotor and the rotor shaft may vary; 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 and provided with two vanes extending essentially in a line with their longitudinal axis in the sense of rotation of the main rotor is essentially parallel to the longitudinal axis of at least one of the propeller blades of the main rotor or is at a relatively small acute angle relative to the axis, the auxiliary rotor being mounted in a swinging relationship on an oscillatory shaft which is provided essentially transversally to the rotor shaft of the main rotor and being directed essentially transversally to the longitudinal axis of the vanes, and the main rotor and the auxiliary rotor are connected to each other by a mechanical link, 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. 
   
   
       2 . A helicopter according to  claim 1 , wherein the main rotor includes two propeller blades situated essentially in line with each other. 
   
   
       3 . A helicopter according to  claim 1  or  2 , wherein the propeller blades of the main rotor, the vanes of the auxiliary rotor respectively, are substantially rigidly connected to each other and the joint of the main rotor is formed of a spindle which is fixed transversally to the rotor shaft of the main rotor and which is directed essentially transversally to the axis of the oscillatory shaft of the auxiliary rotor. 
   
   
       4 . A helicopter according to  claim 3 , wherein the spindle of the main rotor extends essentially in the longitudinal direction of the propeller blade of the main rotor which is parallel to one of the vanes or is located at an acute angle relative to the longitudinal direction. 
   
   
       5 . A helicopter according to  claim 1  wherein the mechanical link includes a rod hinge mounted to a vane of the auxiliary rotor with one fastening point and is hinge-mounted with another fastening point to the propeller blade of the main rotor which is parallel to one of the vanes or is at an acute angle relative to the blade. 
   
   
       6 . A helicopter according to  claim 5 , wherein the fastening point of the rod is situated on the main rotor at a distance from the axis of the spindle of the propeller blades of the main rotor, and the other fastening point of the rod is situated on the auxiliary rotor at a distance from the axis of the oscillatory shaft of the auxiliary rotor. 
   
   
       7 . A helicopter according to  claim 6  wherein the distance between the fastening point of the rod on the main rotor and the axis of the spindle of the propeller blades of the main rotor is larger than the distance between the fastening point of the rod on the auxiliary rotor and the axis of the oscillatory shaft of the auxiliary rotor. 
   
   
       8 . A helicopter according to  claim 6  or  7  wherein the distance between the fastening point of the rod on the main rotor and the axis of the spindle of the propeller blades of the main rotor is about the double the distance between the other fastening point on the auxiliary rotor and the axis of the oscillatory shaft of the auxiliary rotor. 
   
   
       9 . A helicopter according to  claim 5  wherein the rod is fixed to lever arms with its fastening point respectively part of the main rotor and of the auxiliary rotor. 
   
   
       10 . A helicopter according to  claim 1  wherein the longitudinal axis of the vanes of the auxiliary rotor in the sense of rotation is located within an angle of about 10 degrees with the longitudinal axis of one of the propeller blades of the main rotor 
   
   
       11 . A helicopter according to  claim 1  wherein the longitudinal axis of one of the propeller blades of the main rotor in the sense of rotation, is located at an acute angle with the axis of the spindle of these propeller blades. 
   
   
       12 . A helicopter according to  claim 1  wherein the diameter of the auxiliary rotor is smaller than the diameter of the main rotor. 
   
   
       13 . A helicopter according to  claim 1  wherein the auxiliary rotor is provided with stabilizing weights which are fixed respectively to a vane. 
   
   
       14 . A helicopter according to  claim 1  wherein the tail rotor is supported by a swing with its rotor shaft which can rotate round a swinging shaft which essentially extends according to the longitudinal direction of the body of the helicopter. 
   
   
       15 . A helicopter according to  claim 14  wherein a sensor determines the relative angular displacement of the swing round the swinging shaft, and this angular displacement is used as an input signal for a microprocessor which controls the drives of the main rotor and of the tail rotor as a function of a stabilizer algorithm. 
   
   
       16 . A helicopter according to  claim 15  wherein the sensor includes a magnet fixed to the swing and of a magnetic sensor which is fixed opposite the pendulum path of the magnet on the tail of the helicopter. 
   
   
       17 . A helicopter according to any one of  claims 14  to  16  wherein between the swing and the tail there is provided a spring which keeps the swing in rest in a central position. 
   
   
       18 . A helicopter comprising a body with a tail; a rotor with propeller blades which is driven by a rotor shaft and which is mounted on this rotor shaft, such that the angle between the plane of rotation of the rotor and the rotor shaft may vary; a tail rotor which is driven by a second rotor shaft directed transversally to the rotor shaft of the main rotor, wherein the tail rotor is supported by a swing with its rotor shaft which can rotate round a swinging shaft which essentially extends according to the longitudinal direction of the body of the helicopter. 
   
   
       19 . A helicopter according to  claim 18  wherein a sensor determines the relative angular displacement of the swing round the swinging shaft, and this angular displacement is used as an input signal for a microprocessor which controls the drives of the main rotor and of the tail rotor as a function of a stabilizer algorithm. 
   
   
       20 . A helicopter according to  claim 19  wherein the sensor includes a magnet fixed to the swing and of a magnetic sensor which is fixed opposite the pendulum path of the magnet on the tail of the helicopter. 
   
   
       21 . A helicopter according to any one of  claims 18  to  20  wherein between the swing and the tail there is provided a spring which keeps the swing in rest in a central position. 
   
   
       22 . A helicopter comprising a body with a tail; a main rotor with propeller blades which is driven by a rotor shaft and which is mounted on this rotor shaft, such that the angle between the plane of rotation of the main rotor and the rotor shaft may vary; 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 and provided with two vanes, and the main rotor and the auxiliary rotor being connected to each other by a mechanical link, such that the motion of the auxiliary rotor controls the angle of′ incidence of at least one of the propeller blades of the main rotor.