Helicopter

Information

  • Patent Grant
  • 7494397
  • Patent Number
    7,494,397
  • Date Filed
    Thursday, June 14, 2007
    17 years ago
  • Date Issued
    Tuesday, February 24, 2009
    15 years ago
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 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.
Description
BACKGROUND

The present disclosure concerns an improved helicopter.


The disclosure concerns a helicopter generally. In particular, but not exclusively, it is related to a toy helicopter and in particular to a remote-controlled model helicopter or a toy helicopter.


SUMMARY

It known that a helicopter is a complex machine which is unstable and as a result difficult to control, so that much experience is required to safely operate such helicopters without mishaps.


Typically, a helicopter includes a body, a main rotor and a tail rotor.


The main rotor provides an upward force to keep the helicopter in the air, as well as a lateral or forward or backward force to steer the helicopter in required directions. This can be by making the angle of incidence of the propeller blades of the main rotor vary cyclically at every revolution of the main rotor.


The main rotor has a natural tendency to deviate from its position, which may lead to uncontrolled movements and to a crash of the helicopter if the pilot loses control over the steering of the helicopter.


Solutions to slow down the effect have already been provided up to now, including the application of stabilizing rods and weights at the tips of the propeller blades.


All these solutions make use of the known phenomenon of gyroscopic precession caused by the Coreolis force and the centrifugal forces to obtain the desired effect.


The tail rotor is not at all insensitive to this phenomenon, since it has to prevent the body to turn round the drive shaft of the rotor as a result of the resistance torque of the rotor on the body.


To this end, the tail rotor is erected such that it develops a lateral thrust which has to counteract the above-mentioned resistance torque of the rotor and the helicopter is provided with means which have to enable the pilot to control the lateral thrust so as to determine the flight position round the vertical axis.


Since the tail of the helicopter tends to turn round the drive shaft of the main rotor, even in case of small variations in the drive torque of the main rotor, most helicopters are provided with a separate and autonomous mechanical or electromechanical system such as a gyroscope or the like which automatically compensates the thrust of the tail rotor for the unwanted rotations.


In general, the stability of a helicopter includes the result of the interaction between:


the rotation of the rotor blades; the movements of any possible stabilizing rods; compensation of the resistance torque of the main rotor by means of the tail rotor;


the system such as a gyroscope or the like to compensate for small undesired variations in the resistance torque of the main rotor; and control of the helicopter which controls the rotational speed of the main rotor and of the tail rotor.


When these elements are essentially in balance, the pilot should be able to steer the helicopter as desired.


This does not mean, however, that the helicopter can fly by itself and can thus maintain a certain flight position or maneuver, for example, hovering or making slow movements without the intervention of a pilot.


Moreover, flying a helicopter usually requires intensive training and much experience of the pilot, for both a full size operational real helicopter as well as a toy helicopter or a remote-controlled model helicopter.


The present disclosure aims to minimize one or several of the above-mentioned and other disadvantages by providing a simple and cheap solution to auto stabilize the helicopter, such that operating the helicopter becomes simpler and possibly reduces the need for long-standing experience of the pilot.


The helicopter should meet the following requirements to a greater or lesser degree:


(a) it can return to a stable hovering position, in case of an unwanted disturbance of the flight conditions. Such disturbance may occur in the form of a gust of wind, turbulences, a mechanical load change of the body or the rotors, a change of position of the body as a result of an adjustment to the cyclic variation of the pitch or angle of incidence of the propeller blades of the main rotor or a steering of the tail rotor or the like with a similar effect; and


(b) the time required to return to the stable position should be relatively short and the movement of the helicopter should be relatively small.


To this end, the disclosure concerns an improved helicopter including a body with a tail; a main rotor with propeller blades which are driven by a rotor shaft and which are hinge-mounted to the rotor shaft by means of a joint. The angle between the surface of rotation of the main rotor and the rotor shaft may vary. A tail rotor is driven by a second rotor shaft which is directed transversal to the rotor shaft of the main rotor.


The helicopter is provided with an auxiliary rotor which is driven by the shaft of the main rotor and which is provided with two vanes extending essentially in line with their longitudinal axis. The ‘longitudinal’ axis is seen in the sense of rotation of the main rotor, and is essentially parallel to the longitudinal axis of at least one of the propeller blades of the main rotor or is located within a relatively small acute angle with the latter propeller blade axis. This auxiliary rotor is provided in a swinging manner on an oscillatory shaft which is provided essentially transversal to the rotor shaft of the main rotor. This is directed essentially transverse to the longitudinal axis of the vanes. The main rotor and the auxiliary rotor are connected to each other through a mechanical link, such that the swinging motions of the auxiliary rotor control the angle of incidence of at least one of the propeller blades of the main rotor.


In practice, it appears that such an improved helicopter is more stable and stabilizes itself relatively quickly with or without a restricted intervention of the user.


According to different aspect of the disclosure, the helicopter is made more stable by suspending the tail rotor with its rotor shaft in a swing which can rotate round a swing shaft. The swing shaft essentially extends in the longitudinal direction relative to the body of the helicopter.


In case of malfunction or the like, whereby the helicopter starts to turn round the rotor shaft of the main rotor in an unwanted manner, the tail rotor, as a result of the gyroscopic precession acting on the rotating tail rotor as a result of the rotation round the rotor shaft of the main rotor, should tilt round the swing shaft of the tail rotor at a certain angle.


By measuring the relative angular displacement of the swing and by using the measured signal as an input signal for a microprocessor which controls the drive of the main rotor and the drive of the tail rotor as a function of a stabilizer algorithm, the thrust of the tail rotor can be adjusted so as to counteract the unwanted effect of the disturbance and to thus automatically restore the stable flight conditions for the helicopter, with minimal or any intervention of the pilot.


The main rotor with propeller blades is driven by a rotor shaft on which the blades are mounted. The auxiliary rotor is driven by the rotor shaft of the main rotor and is provided with vanes from the rotor shaft in the sense of rotation of the main rotor.


The auxiliary rotor is mounted in a swinging relationship on an oscillatory shaft and the swinging motion being relatively upwardly and downwardly about the auxiliary shaft. The auxiliary shaft is provided essentially transverse to the rotor shaft of the main rotor. 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.


The angle of incidence of the rotor in the plane of rotation of the rotor and the rotor shaft may vary; and an auxiliary rotor rotatable with the rotor shaft is for relative oscillating movement about the rotor shaft. Different relative positions are such that the auxiliary rotor causes the angle of incidence the main rotor to be different. A linkage between the main and auxiliary rotor causes changes in the position of the auxiliary rotor to translate to changes in the angle of incidence.


The propeller blades of the main rotor and the vanes of 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 vanes of the auxiliary rotor.


There are wings directed transversely of a longitudinal axis of the helicopter body directed transversely and downwardly and a downwardly directed stabilizer at the tail of the helicopter. This facilitates stability on the ground.





DRAWINGS

In order to further explain the characteristics of the disclosure, the following embodiments of an improved helicopter according to the disclosure are given as an example only, without being limitative in any way, with reference to the accompanying drawings, in which:



FIG. 1 schematically represents a helicopter according to the disclosure in perspective;



FIG. 2 represents a top view according to arrow F2 in FIG. 1;



FIGS. 3 and 4 represent respective sections according to lines II-II and III-III in FIG. 2;



FIG. 5 represents a view of the rear rotor part indicated in FIG. 1 by F5 to a larger scale;



FIG. 6 is a rear view according to arrow F6 in FIG. 5;



FIG. 7 represents a variant of FIG. 1;



FIG. 8 represents a variant of FIG. 5;



FIG. 9 represents a different view of the tail rotor of FIG. 8;



FIG. 10 represents a section of the helicopter;



FIG. 11 schematically represents an alternative view of the helicopter according to the disclosure in perspective;



FIG. 12 is a perspective view of the main rotor and auxiliary rotor.



FIG. 13 is a perspective view of the tail rotor and tail stabilizer in a second embodiment of the helicopter;



FIG. 14 represents a side sectional view in the second embodiment of the helicopter;



FIG. 15 represent a perspective view of the second embodiment of the helicopter;



FIG. 16 represents a top view of the second embodiment of the helicopter;



FIG. 17 is a rear view of the second embodiment of the helicopter;



FIG. 18 represents a sectional view of the second embodiment of the helicopter along line !8-!8 of FIG. 16.





DETAILED DESCRIPTION

The helicopter 1 represented in the figures by way of example is a remote-controlled helicopter which essentially consists of a body 2 with a landing gear and a tail 3; a main rotor 4; an auxiliary rotor 5 driven synchronously with the latter and a tail rotor 6.


The main rotor 4 is provided by means of what is called a rotor head 7 on a first upward directed rotor shaft 8 which is bearing-mounted in the body 2 of the helicopter 1 in a rotating manner and which is driven by means of a motor 9 and a transmission 10, whereby the motor 9 is for example an electric motor which is powered by a battery 11.


The main rotor 4 in this case has two propeller blades 12 which are in line or practically in line, but which may just as well be composed of a larger number of propeller blades 12.


The tilt or angle of incidence A of the propeller blades 12, in other words the angle A which forms the propeller blades 12 as represented in FIG. 6 with the plane of rotation 14 of the main rotor 4, can be adjusted as, the main rotor 4 is hinge-mounted on this rotor shaft 8 by means of a joint, such that the angle between the plane of rotation of the main rotor and the rotor shaft may freely vary.


In the case of the example of a main rotor 4 with two propeller blades 12, the joint is formed by a spindle 15 of the rotor head 7.


The axis 16 of this spindle 15 is directed transversal to the rotor shaft 8 and essentially extends in the direction of the longitudinal axis 13 of one of the propeller blades 12 and it preferably forms, as represented in FIG. 2, an acute angle B with this longitudinal axis 13.


The tail rotor 6 is driven via a second rotor shaft 17 by means of a second motor 18 and a transmission 19. Motor 16 can be an electric motor. The tail rotor 6 with its rotor shaft 17 and its drive 18-19 is suspended in a swing 20 which can rotate round a swing shaft 21 which is fixed to the tail 3 of the helicopter 1 by two supports 22 and 23.


The swing 20 is provided with an extension piece 24 towards the bottom, which is kept In a central position by means of a spring 25 when in a state of rest, whereby the second rotor shaft 17 in this position is horizontal and directed crosswise to the first rotor shaft 8.


On the lower end of the extension piece 24 of the swing 20 is provided a magnet 26, whereas opposite the position of the magnet 26 in the above-mentioned state of rest of the swing 20 is fixed a magnetic sensor 27 to the tail 3 which makes it possible to measure the relative angular displacement of the swing 20 and thus of the tail rotor 6 round the swing shaft 21.


It is clear that this angular displacement of the swing 20 can also be measured in other ways, for example by means of a potentiometer.


The measured signal can be used as an input signal for a control box, which is not represented in the figures, which controls the drives of the main rotor 4 and of the tail rotor 6 and which is provided with a stabilizer algorithm which will give a counter steering command when a sudden unwanted angular displacement of the tail rotor 6 is measured round the swing shaft 21, resulting from an unwanted rotation of the helicopter 1 round the rotor shaft 8, so as to restore the position of the helicopter 1.


The helicopter 1 is also provided with an auxiliary rotor 5 which is driven substantially synchronously with the main rotor 4 by the same rotor shaft 8 and the rotor head 7.


The main rotor 4 in this case has two vanes 28 which are essentially in line with their longitudinal axis 29, whereby the longitudinal axis 29, seen in the sense of rotation R of the main rotor 4, is essentially parallel to the longitudinal axis 13 of propeller blades 12 of the main rotor 4 or encloses a relatively small acute angle C with the latter, so that both rotors 4 and 5 extend more or less parallel on top of one another with their propeller blades 12 and vanes 28.


The diameter of the auxiliary rotor 5 is preferably smaller than the diameter of the main rotor 4 as the vanes 28 have a smaller span than the propeller blades 12, and the vanes 28 are substantially rigidly connected to each other. This rigid whole forming the auxiliary rotor 5 is provided in a swinging manner on an oscillating shaft 30 which is fixed to the rotor head 7 of the rotor shaft 8. This is directed transversally to the longitudinal axis of the vanes 28 and transversally to the rotor shaft 8.


The main rotor 4 and the auxiliary rotor 5 are connected to each other by a mechanical link which is such of the auxiliary rotor 5 the angle of incidence A of at least one of the propeller blades 12 of the main rotor 4. In the given example this link is formed of a rod 31.


This rod 31 is hinge-mounted to a propeller blade 12 of the main rotor 4 with one fastening point 32 by means of a joint 33 and a lever arm 34 and with another second fastening point 35 situated at a distance from the latter, it is hinge-mounted to a vane 28 of the auxiliary rotor 5 by means of a second joint 36 and a second lever arm 37.


The fastening point 32 on the main rotor 4 is situated at a distance D from the axis 16 of the spindle 15 of the propeller blades 12 of the main rotor 4, whereas the other fastening point 35 on the auxiliary rotor 5 is situated at a distance E from the axis 38 of the oscillatory shaft 30 of the auxiliary rotor 5.


The distance D is preferably larger than the distance E, and about the double of this distance E, and both fastening points 32 and 35 of the rod 31 are situated, seen in the sense of rotation R on the same side of the propeller blades 12 of the main rotor 4 or of the vanes 28 of the auxiliary rotor 5, in other words they are both situated in front of or at the back of the propeller blades 12 and vanes 28, seen in the sense of rotation.


Also preferably, the longitudinal axis 29 of the vanes 28 of the auxiliary rotor 5, seen in the sense of rotation R, encloses an angle F with the longitudinal axis 13 of the propeller blades 12 of the main rotor 4, which enclosed angle F is in the order, of magnitude of about 10°, whereby the longitudinal axis 29 of the vanes 28 leads the longitudinal axis 13 of the propeller blades 12, seen in the sense of rotation R. Different angles in a range of, for example, 5° to 25° could also be in order.


The auxiliary rotor 5 is provided with two stabilizing weights 39 which are each fixed to a vane 28 at a distance from the rotor shaft 8.


Further, the helicopter 1 is provided with a receiver, so that it can be controlled from a distance by means of a remote control which is not represented.


As a function of the type of helicopter, it is possible to search for the most appropriate values and relations of the angles B, F and G by experiment; the relation between the distances D and E; the size of the weights 39 and the relation of the diameters between the main rotor 4 and the auxiliary rotor 5 so as to guarantee a maximum auto stability.


The operation of the improved helicopter 1 according to the disclosure is as follows:


In flight, the rotors 4, 5 and 6 are driven at a certain speed, as a result of which a relative air stream is created in relation to the rotors, as a result of which the main rotor 4 generates an upward force so as to make the helicopter 1 rise or descend or maintain it at a certain height, and the tail rotor 6 develops a laterally directed force which is used to steer the helicopter 1.


It is impossible for the main rotor 4 to adjust itself, and it will turn in the plane 14 in which it has been started, usually the horizontal plane. Under the influence of gyroscopic precession, turbulence and other factors, it will take up an arbitrary undesired position if it is not controlled.


The surface of rotation of the auxiliary rotor 5 may take:


up another inclination in relation to the surface of rotation 14 of the main rotor 8, whereby both rotors 5 and 4 may take up another inclination in relation to the rotor, shaft 8.


This difference in inclination may originate in any internal or external force or disturbance whatsoever.


In a situation whereby the helicopter 1 is hovering stable, on a spot in the air without any disturbing internal or external forces, the auxiliary rotor 5 keeps turning in a plane which is essentially perpendicular to the rotor shaft 8.


If, however, the body 2 is pushed out of balance due to any disturbance whatsoever, and the rotor shaft 8 turns away from its position of equilibrium, the auxiliary rotor 5 does not immediately follow this movement, since the auxiliary rotor 5 can freely move round the oscillatory shaft 30.


The main rotor 4 and the auxiliary rotor 5 are placed in relation to each other in such a manner that a swinging motion of the auxiliary rotor 5 is translated almost immediately in the pitch or angle of incidence A of the propeller blades 12 being adjusted.


For a two-bladed main rotor 4, this means that the propeller blades 12 and the vanes 28 of both rotors 4 and 5 must be essentially parallel or, seen in the sense of rotation R, enclose an acute angle with one another of for example 10° in the case of a large main rotor 4 and a smaller auxiliary rotor 5.


This angle can be calculated or determined by experiment for any helicopter 1 or per type of helicopter.


If the axis of rotation 8 takes up another inclination than the one which corresponds to the above-mentioned position of equilibrium in a situation whereby the helicopter 1 is hovering, the following happens:


A first effect is that the auxiliary rotor 5 will first try to preserve its absolute inclination, as a result of which the relative inclination of the surface of rotation of the auxiliary rotor 5 in relation to the rotor shaft 8 changes.


As a result, the rod 31 will adjust the angle of incidence A of the propeller blades 12, so that the upward force of the propeller blades 12 will increase on one side of the main rotor 4 and will decrease on the diametrically opposed side of this main rotor.


Since the relative position of the main rotor 4 and the auxiliary rotor 5 are selected such that a relatively immediate effect is obtained. This change in the upward force makes sure that the rotor shaft 8 and the body 21 are forced back into their original position of equilibrium.


A second effect is that, since the distance between the far ends of the vanes 28 and the plane of rotation 14 of the main rotor 4 is no longer equal and since also the vanes 28 cause an upward force, a larger pressure is created between the main rotor 4 and the auxiliary rotor 5 on one side of the main rotor 4 than on the diametrically opposed side.


A third effect plays a role when the helicopter begins to tilt over to the front, to the back or laterally due to a disturbance. Just as in the case of a pendulum, the helicopter will be inclined to go back to its original situation. This pendulum effect does not generate any destabilizing gyroscopic forces as with the known helicopters that are equipped with a stabilizer bar directed transversally to the propeller blades of the main rotor. It acts to reinforce the first and the second effect.


The effects have different origins but have analogous natures. They reinforce each other so as to automatically correct the position of equilibrium of the helicopter 1 without any intervention of a pilot.


The tail rotor 6 is located in a swinging manner and provides for an additional stabilization and makes it possible for the tail rotor 6 to assume the function of the gyroscope which is often used in existing helicopters, such as model helicopters.


In case of a disturbance, the body 2 may start to turn round the rotor shaft 8. As a result, the tail rotor 6 turns at an angle in one or other sense round the swinging shaft 21. This is due to the gyroscopic precession which acts on the rotating tail rotor 6 as a result of the rotation of the tail rotor 6 round the rotor shaft 8. The angular displacement is a function of the amplitude of the disturbance and thus of the rotation of the body 2 round the rotor shaft 8. This is measured by the sensor 27.


The signal of the sensor 27 is used by a control box of a computer to counteract the failure and to adjust the thrust of the tail rotor 6 so as to annul the angular displacement of the tail rotor 6 which is due to the disturbance.


This can be done by adjusting the speed of the tail rotor 6 and/or by adjusting the angles of incidence of the propeller blades of the tail rotor 6, depending on the type of helicopter 1.


If necessary, this aspect of the disclosure may be applied separately, just as the aspect of the auxiliary rotor 5 can be applied separately, as is illustrated for example by means of FIG. 7, which represents a helicopter 1 according to the, disclosure having a main rotor 4 combined with an auxiliary rotor 5, but whose tail rotor 6 is of the conventional type, i.e. whose shaft cannot turn in a swing but is bearing-mounted in relation to the tail 3.


In practice, the combination of both aspects makes it possible to produce a helicopter which is very stable in any direction and any flight situation and which is easy to control, even by persons having little or no experience.


It is clear that the main rotor 4 and the auxiliary rotor 5 must not necessarily be made as a rigid whole. The propeller blades 12 and the vanes 28 can also be provided on the rotor head 7 such that they are mounted and can rotate relatively separately. In that case, for example, two rods 31 may be applied to connect each time one propeller blade 12 to one vane 28.


It is also clear that, if necessary, the joints and hinge joints may also be realized in other ways than the ones represented, for example by means of torsion-flexible elements.


In the case of a main rotor 4 having more than two propeller blades 12, one should preferably be sure that at least one propeller blade 12 is essentially parallel to one of the vanes 28 of the auxiliary rotor. The joint of the main rotor 4 is preferably made as a ball joint or as a spindle 15 which is directed essentially transversely to the axis of the oscillatory shaft 30 of the auxiliary rotor 5 and which essentially extends in the longitudinal direction of the one propeller blade 12 concerned which is essentially parallel to the vanes 28.


In another format, the helicopter comprises a body with a tail; a main rotor with propeller blades which is driven by a rotor shaft on which the blades are mounted. A tail rotor is driven by a second rotor shaft directed transversally to the rotor shaft of the main rotor. An auxiliary rotor is driven by the rotor shaft of the main rotor and is provided with vanes from the rotor shaft in the sense of rotation of the main rotor.


The auxiliary rotor is mounted in a swinging relationship on an oscillatory shaft and the swinging motion being relatively upwardly and downwardly about the auxiliary shaft. The auxiliary shaft is provided essentially transverse to the rotor shaft of the main rotor. 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.


The angle of incidence of the rotor in the plane of rotation of the rotor and the rotor shaft may vary. An auxiliary rotor rotatable with the rotor shaft is for relative oscillating movement about the rotor shaft. Different relative positions are such that the auxiliary rotor causes the angle of incidence the main rotor to be different. A linkage between the main and auxiliary rotor causes changes in the position of the auxiliary rotor to translate to changes in the angle of incidence.


The propeller blades of the main rotor and the vanes of 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 vanes of the auxiliary rotor. A joint of the main rotor to the propeller blades is formed of a spindle which is fixed to the rotor shaft of the main rotor.


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.


The body includes wings directed transversely of a longitudinal axis of the helicopter body. The wings are 100 and 102 directed transversely and downwardly whereby the tips 104 and 106 of the wings permit for stabilizing the helicopter body when on the ground.


There is a downwardly directed stabilizer 108 at the tail of the helicopter. FIG. 15 also shows a radio control unit for operation with the helicopter. This unit can have appropriate computerized controls for signaling the operation of the motors operating the rotors and their relative positions.


The present disclosure is not limited to the embodiments described as an example and represented in the accompanying figures. Many different variations in size and scope and features are possible. For instance, instead of electrical motors being provided others forms of motorized power are possible. A different number of blades may be provided to the rotors.


A helicopter according to the disclosure can be made in all sorts of shapes and dimensions while still remaining within the scope of the disclosure. In this sense although the helicopter in some senses has been described as toy or model helicopter, the features described and illustrated can have use in part or whole in a full-scale helicopter.

Claims
  • 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 between a propeller blade of the main rotor 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.
  • 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 a second rotor; a tail rotor which is driven by a second rotor shaft, 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, the convex curve extending over a portion of the length 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 between a propeller blade of the main rotor 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; and wherein the main rotor includes two propeller blades situated essentially in line with each other, and the elongated members are respectively two rotor elements situated essentially in line with each other, preferably there being only the two blades and only the two rotors respectively, 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 generally longitudinal length of the blade, and wherein each rotor blade portion of the includes a transverse concave curve in a profile on its bottom face from a position towards a leading edge towards a position towards a trailing edge, the transverse concave curve preferably being present over a substantial portion of the generally longitudinal length of the blade.
  • 3. 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 determined 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 essentially parallel to the generally longitudinal axis of at least one of the propeller blades of the main rotor or at a relatively small acute angle relative to the generally longitudinal axis of the propeller blade, the angle preferably being 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 between a propeller blade of the main rotor 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.
  • 4. 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.
  • 5. A helicopter according to claim 2 wherein there is a center line being selectively a line from a radial end area of the auxiliary rotor passing to the rotor shaft.
  • 6. A helicopter according to claim 3 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.
  • 7. A helicopter according to claim 1 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 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 transverse convex curve preferably being present over a substantial generally longitudinal length of the blade.
  • 8. 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.
  • 9. 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 canes, 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 the rotor shaft.
  • 10. A helicopter according to claim 3 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 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.
  • 11. 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.
  • 12. 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.
  • 13. 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.
  • 14. 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.
  • 15. 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.
  • 16. 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.
  • 17. 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.
  • 18. A helicopter according to claim 3 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.
  • 19. A helicopter according to claim 5 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.
Priority Claims (1)
Number Date Country Kind
2006/0043 Jan 2006 BE national
RELATED APPLICATION

This application is a divisional of U.S. patent application Ser. No. 11/465,781 filed on Aug. 18, 2006, which is a Continuation-in-Part of U.S. patent application Ser. No. 11/462,177, filed on Aug. 3, 2006 and entitled HELICOPTER, which claims priority to Belgian Patent Application No. 2006/0043 entitled AUTOSTABIELE HELICOPTER by Alexander VAN DE ROSTYNE, which was filed on Jan. 19, 2006. The contents of these applications are incorporated by reference herein.

US Referenced Citations (201)
Number Name Date Kind
1403909 Moir Jan 1922 A
1446522 Smith Feb 1923 A
1773281 Scott Aug 1930 A
1800470 Oehmichen Apr 1931 A
1925156 Vaughn Sep 1933 A
2030578 Flettner Feb 1936 A
2110563 Thaon Mar 1938 A
2307381 Bess Jan 1943 A
2368698 Young Feb 1945 A
2384516 Young Sep 1945 A
2411596 Shapiro Nov 1946 A
2413831 Jordan Jan 1947 A
2429502 Young Oct 1947 A
D149130 Katenberter et al. Mar 1948 S
2439143 Nemeth Apr 1948 A
D153314 Piasecki Apr 1949 S
D153315 Piasecki Apr 1949 S
D153316 Piasecki Apr 1949 S
D153317 Piasecki Apr 1949 S
2469144 Baggott May 1949 A
2481750 Hiller, Jr. et al. Sep 1949 A
2486059 Pentecost Oct 1949 A
2487020 Gilerease Nov 1949 A
2514822 Wolfe, Jr. Jul 1950 A
2532683 Traver Dec 1950 A
2554938 Catalano May 1951 A
D163938 Douglas Jul 1951 S
2563731 Masterson Aug 1951 A
2629568 Croshere, Jr. et al. Feb 1953 A
2633924 Young Apr 1953 A
2639874 Stalker May 1953 A
2646848 Young Jul 1953 A
2629570 Carnahan Dec 1953 A
D171569 Apostolescu Mar 1954 S
2725494 Anderson Nov 1955 A
D178081 Papadakos Jun 1956 S
2750131 Thomson Jun 1956 A
D181643 Graham Dec 1957 S
D184501 Wlashin et al. Feb 1959 S
2923494 Strong Feb 1960 A
D187625 Apostolescu Apr 1960 S
D187895 Douglas May 1960 S
2950074 Apostolescu Aug 1960 A
2980187 Smyth-Davila Apr 1961 A
3029048 Brooks et al. Apr 1962 A
3035643 Kelley et al. May 1962 A
3068611 Lauderdale Dec 1962 A
3080001 Culver et al. Mar 1963 A
3093929 Robbins et al. Jun 1963 A
3106964 Culver et al. Oct 1963 A
3116896 Sigler et al. Jan 1964 A
3135334 Culver Jun 1964 A
3180424 Serriades Apr 1965 A
3213944 Nichols et al. Oct 1965 A
3228478 Edenborough Jan 1966 A
3231222 Scheutzow Jan 1966 A
D205326 Postelson-Apostolescu Jul 1966 S
3370809 Leoni Feb 1968 A
3371886 Schertz Mar 1968 A
3391746 Cardoso Jul 1968 A
3409249 Bergquist et al. Nov 1968 A
3448810 Vogt Jun 1969 A
3450374 Moore Jun 1969 A
3481559 Apostolescu Dec 1969 A
3572616 Ulisnik Mar 1971 A
3592559 Ward Jul 1971 A
D221453 Swanberg Aug 1971 S
3625631 Covington, Jr. et al. Dec 1971 A
3662487 Seefluth May 1972 A
3759629 Abramopaulos Sep 1973 A
3771924 Buchstaller Nov 1973 A
D232168 Leoni Jul 1974 S
D232170 Diamond et al. Jul 1974 S
D234350 Beckert et al. Feb 1975 S
3933324 Ostrowski Jan 1976 A
D239930 Ulisnik May 1976 S
4024230 Kastan May 1977 A
4025230 Kastan May 1977 A
4053123 Chadwick Oct 1977 A
4073086 Ogawa Feb 1978 A
4084345 Tanaka Apr 1978 A
4118143 Kavan Oct 1978 A
4142697 Fradenburgh Mar 1979 A
D253003 Tanaka Sep 1979 S
4173321 Eickmann Nov 1979 A
4227856 Verrill et al. Oct 1980 A
4307533 Sims et al. Dec 1981 A
4519746 Wainauski et al. May 1985 A
4522563 Reyes et al. Jun 1985 A
4629440 McKittrick et al. Dec 1986 A
D294605 Matsumoto Mar 1988 S
4880355 Vuillet et al. Nov 1989 A
4981456 Sato et al. Jan 1991 A
5015187 Lord May 1991 A
5108043 Canavespe Apr 1992 A
5151014 Greenwald et al. Sep 1992 A
5190242 Nichols Mar 1993 A
5209429 Doolin et al. May 1993 A
5240204 Kunz Aug 1993 A
5252100 Osawa et al. Oct 1993 A
5255871 Ikeda Oct 1993 A
5259729 Fujihira et al. Nov 1993 A
5304090 Vanni Apr 1994 A
5370341 Leon Dec 1994 A
D357894 Arnold et al. May 1995 S
5505407 Chiappetta Apr 1996 A
5511947 Schmuck Apr 1996 A
D372741 Tsai Aug 1996 S
D378606 Tamagnini Mar 1997 S
5609312 Arlton et al. Mar 1997 A
5628620 Arlton May 1997 A
D388048 Taylor et al. Dec 1997 S
D390942 Mei Feb 1998 S
5749540 Arlton May 1998 A
5836545 Arlton et al. Nov 1998 A
5879131 Arlton et al. Mar 1999 A
5906476 Arlton May 1999 A
5915649 Head Jun 1999 A
6000911 Toulmay et al. Dec 1999 A
D421279 Tsai Feb 2000 S
6032899 Mondet et al. Mar 2000 A
6039541 Parker et al. Mar 2000 A
D425853 Caporaletti May 2000 S
6086016 Meek Jul 2000 A
6302652 Roberts Oct 2001 B1
6398618 Wu Jun 2002 B1
6435453 Carter, Jr. Aug 2002 B1
6460802 Norris Oct 2002 B1
6467726 Hosoda Oct 2002 B1
D467861 Lee Dec 2002 S
6499690 Katayama et al. Dec 2002 B1
6543726 Illingworth Apr 2003 B2
6632119 Chernek et al. Oct 2003 B2
6659395 Rehkemper et al. Dec 2003 B2
6659721 Parker et al. Dec 2003 B1
6702552 Harman Mar 2004 B1
6719244 Gress Apr 2004 B1
6732973 Rehkemper May 2004 B1
6745977 Long et al. Jun 2004 B1
6749401 Vanmoor Jun 2004 B2
6758436 Rehkemper et al. Jul 2004 B2
6789764 Bass et al. Sep 2004 B2
6884034 Parker et al. Apr 2005 B1
6886777 Rock May 2005 B2
6899586 Davis May 2005 B2
6929215 Arlton Aug 2005 B2
6960112 Helmlinger et al. Nov 2005 B2
6978969 Neal Dec 2005 B1
D524227 Stille et al. Jul 2006 S
D524228 Scott et al. Jul 2006 S
D524229 Stille et al. Jul 2006 S
D524230 Stille et al. Jul 2006 S
D524718 Scott et al. Jul 2006 S
7100866 Rehkemper et al. Sep 2006 B2
7178758 Rehkemper Feb 2007 B2
7188803 Ishiba Mar 2007 B2
7198223 Phelps, III et al. Apr 2007 B2
7204453 Muren Apr 2007 B2
D544825 Van De Rostyne et al. Jun 2007 S
D545755 Van De Rostyne et al. Jul 2007 S
D546269 Van De Rostyne et al. Jul 2007 S
7246769 Yoeli Jul 2007 B2
D548803 Zimet Aug 2007 S
7264199 Zientek Sep 2007 B2
7273195 Golliher Sep 2007 B1
D552531 Van De Rostyne et al. Oct 2007 S
D554040 Van De Rostyne et al. Oct 2007 S
7306186 Kusic Dec 2007 B2
D559764 Wai Jan 2008 S
D561084 Wai Feb 2008 S
D561679 Wai Feb 2008 S
20020008759 Hoyos Jan 2002 A1
20020109044 Rock Aug 2002 A1
20020134883 Stamps et al. Sep 2002 A1
20040087241 Agostini et al. May 2004 A1
20040184915 Kunii et al. Sep 2004 A1
20040222329 Kuhns et al. Nov 2004 A1
20040245376 Muren Dec 2004 A1
20050121552 Rehkemper Jun 2005 A1
20050121553 Isawa et al. Jun 2005 A1
20060102777 Rock May 2006 A1
20060121819 Isawa Jun 2006 A1
20060231677 Zimet et al. Oct 2006 A1
20070012818 Miyazawa et al. Jan 2007 A1
20070017724 Rajasingham Jan 2007 A1
20070105475 Gotou et al. May 2007 A1
20070164148 Van De Rostyne Jul 2007 A1
20070164149 Van De Rostyne Jul 2007 A1
20070164150 Van de Rostyne Jul 2007 A1
20070178798 Lai Aug 2007 A1
20070181742 Van de Rostyne et al. Aug 2007 A1
20070187549 Owen Aug 2007 A1
20070215750 Shantz et al. Sep 2007 A1
20070262197 Phelps et al. Nov 2007 A1
20070272794 Van de Rostyne Nov 2007 A1
20080076319 Van de Rostyne Mar 2008 A1
20080076320 Van de Rostyne Mar 2008 A1
20080085653 Van de Rostyne Apr 2008 A1
20080111399 Zierten May 2008 A1
20080112808 Schmaling et al. May 2008 A1
20080207079 Corsiglia et al. Aug 2008 A1
Foreign Referenced Citations (46)
Number Date Country
338599 Dec 1926 BE
1016960 Nov 2007 BE
1 270 408 Jun 1968 DE
40 17 402 Dec 1991 DE
94 14 652 Nov 1994 DE
203 14 041 Apr 2004 DE
0 250 135 Dec 1987 EP
0 727 350 Aug 1996 EP
1462362 Sep 2004 EP
P0233821 Aug 1957 ES
P0234258 Sep 1957 ES
P0245313 Apr 1959 ES
P0283794 Jan 1963 ES
490715 Apr 1980 ES
275141 Jul 1982 ES
0298826 Jan 1989 ES
0464158 Jan 1992 ES
2 074 010 Aug 1995 ES
0727350 Aug 1996 ES
2 172 362 Sep 2002 ES
1238185 Sep 2002 ES
1462362 Sep 2004 ES
255936 Jul 1926 GB
272871 May 1927 GB
281721 Aug 1928 GB
916894 Jan 1963 GB
956536 Apr 1964 GB
958536 May 1964 GB
1081341 Aug 1967 GB
2 436 258 Sep 2007 GB
S30-7668 Oct 1930 JP
S32-003535 Jun 1932 JP
1269699 Oct 1989 JP
5192452 Aug 1993 JP
8150818 Jun 1996 JP
9048398 Feb 1997 JP
9512515 Dec 1997 JP
10076996 Mar 1998 JP
2000-272594 Oct 2000 JP
2003-103066 Apr 2003 JP
2003-220999 Aug 2003 JP
2004-121798 Apr 2004 JP
2005-193905 Jul 2005 JP
2006-051217 Feb 2006 JP
WO 03080433 Oct 2003 WO
WO2006075096 Jul 2006 WO
Related Publications (1)
Number Date Country
20070221781 A1 Sep 2007 US
Divisions (1)
Number Date Country
Parent 11465781 Aug 2006 US
Child 11754752 US
Continuation in Parts (1)
Number Date Country
Parent 11462177 Aug 2006 US
Child 11465781 US