US20080299867A1 - Flying object with tandem rotors - Google Patents
Flying object with tandem rotors Download PDFInfo
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- US20080299867A1 US20080299867A1 US12/188,070 US18807008A US2008299867A1 US 20080299867 A1 US20080299867 A1 US 20080299867A1 US 18807008 A US18807008 A US 18807008A US 2008299867 A1 US2008299867 A1 US 2008299867A1
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- Prior art keywords
- rotor
- tandem
- shaft
- main
- auxiliary
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/37—Rotors having articulated joints
- B64C27/41—Rotors having articulated joints with flapping hinge or universal joint, common to the blades
- B64C27/43—Rotors having articulated joints with flapping hinge or universal joint, common to the blades see-saw type, i.e. two-bladed rotor
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- A—HUMAN NECESSITIES
- A63—SPORTS; GAMES; AMUSEMENTS
- A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
- A63H27/00—Toy aircraft; Other flying toys
- A63H27/06—Jet-propelled flying toys, e.g. aeroplanes
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- A—HUMAN NECESSITIES
- A63—SPORTS; GAMES; AMUSEMENTS
- A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
- A63H27/00—Toy aircraft; Other flying toys
- A63H27/12—Helicopters ; Flying tops
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
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- A—HUMAN NECESSITIES
- A63—SPORTS; GAMES; AMUSEMENTS
- A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
- A63H30/00—Remote-control arrangements specially adapted for toys, e.g. for toy vehicles
- A63H30/02—Electrical arrangements
- A63H30/04—Electrical arrangements using wireless transmission
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
A flying object with tandem rotors, in particular a helicopter, has a main rotor and a tandem rotor each with propeller blades which are 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 tandem rotor each have an auxiliary rotor connected respectively to the main rotor and tandem rotor 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 and tandem rotor. There is an acute angle of displacement when viewing the propeller blades relative to the vanes in a direction perpendicular to their respective rotational planes.
Description
- This application is a Continuation of U.S. Utility patent application Ser. No. 11/736,506 filed on Apr. 17, 2007, which in turn is a Continuation-in-Part of both U.S. Utility patent application Ser. No. 11/462,177 filed on Aug. 3, 2006 and U.S. Utility patent application Ser. No. 11/465,781 filed on Aug. 18, 2006, all of which claim priority to Belgian Patent Application No. 2006/0043 filed on Jan. 19, 2006. The contents of these applications are incorporated by reference herein.
- The present disclosure concerns an improved flying object with tandem rotors, in particular a 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.
- A helicopter is a complex machine, which is generally unstable and as a result difficult to control. Significant experience is required to safely operate helicopters without mishaps.
- Typically, a helicopter includes a body, a main rotor and a tail rotor. In other cases a helicopter includes a body, a main rotor and a second tandem rotor. The disclosure is concerned primarily with a helicopter having a main rotor and a tandem rotor.
- Tandem helicopters have two rotors of more or less similar diameter. The rotors are disposed along the helicopter body typically towards each end. The tips of the rotor paths may overlap to a certain extend. In that case one rotor is positioned higher than the other to avoid collision of the rotor blades.
- It has been shown that the counter rotation of rotors on a tandem configuration, where the rotor axes are at a certain distance from each other, have destabilizing and asymmetrical effects. Yaw changes induce fore/aft drift, and the rotors push the tandem to lean over and slip. Different lift forces are required for example to move the helicopter forward or backward, and thereby different torques between the two rotors create undesired yaw effects. The combination of all these effects makes it hard to find a natural trim of the tandem for stable hover without pilot correction on the fore/aft and sideways dimension.
- The main rotor and tandem rotor provide 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 achieved by making the angle of incidence of the propeller blades of the rotors vary cyclically with revolutions of the rotors.
- The rotors have 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 make use of the known phenomenon of gyroscopic precession caused by the Coreolis force and the centrifugal forces to obtain the desired effect.
- In general, the stability of a tandem helicopter includes the result of the interaction between:
- the rotation of the rotor blades; the movements of any possible stabilizing rods;
- the system, such as a gyroscope or the like, to compensate for small undesired variations in the resistance torque of the rotors; and
- control of the helicopter, which controls the rotors.
- 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 or on auto pilot 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 a flying object with tandem rotors, in particular a helicopter. Operating the helicopter becomes simpler and possibly reduces the need for long-standing experience of the pilot.
- The flying object with tandem rotors, in particular a 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 rotors; 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.
- The disclosure concerns a flying object with tandem rotors, in particular a helicopter, including a body with a main rotor with propeller blades which are driven by a rotor shaft and which are mounted to the rotor shaft by a joint. The angle between the surface of rotation of the main rotor and the rotor shaft may vary. There is also a tandem rotor which has propeller blades which are driven by a rotor shaft and which are mounted to the rotor shaft by a joint. The angle between the surface of rotation of the tandem rotor and the rotor shaft may vary.
- The helicopter includes the autostable rotors as described in U.S. patent application Ser. No. 11/462,177, filed on Aug. 3, 2006 and entitled HELICOPTER, and No. 11/465,1781, filed on Aug. 18, 2006 entitled HELICOPTER.
- In one form of the disclosure, the helicopter has both the main rotor and the tandem rotors spinning in the same direction. In another form of the disclosure, the helicopter has the main rotor and the tandem rotors spinning in opposite directions.
- When an external yaw disturbance causes the body to rotate, then both rotors see the same amount of decrease or increase in rotation speed for rotors rotating in the same direction. When the rotors are counter-rotating, the amount is similar but the changes are opposite. This is about equal to the rotation speed of the body.
- The two rotors, namely the main rotor and the tandem rotor, are located at a certain horizontal distance one from another. Those rotors are inclined in the case of same direction turning rotor, such that they essentially compensate for the torque effects induced by the spinning rotors.
- The effects of yaw, pilot induced or uninitiated/unwanted, essentially overcomes drift in the for/after dimension, and undesired inclination of the body. The spiral thrust essentially does not incline or cause sideways drift the body when rotors turn in same direction.
- In one form of the disclosure, the helicopter main and tandem rotors are each provided with an auxiliary rotor which is driven by the shaft of the respective main rotor or tandem rotor. The auxiliary rotor is provided with two vanes extending essentially in line or at an acute angle relative with their longitudinal axes. This acute angle of displacement is determined when viewing the propeller blades relative to the vanes in a direction perpendicular to their respective rotational planes.
- In some other forms of the disclosure, there may be an auxiliary rotor on only one of the main rotor or the tandem rotor.
- The ‘longitudinal’ axis is seen in the plane 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 at a relatively small acute angle with the latter propeller blade axis. As such each vane of the auxiliary rotor is relatively offset from the respective propeller of the main rotor when viewed perpendicular to the plane of rotation of the main rotor and the auxiliary rotor.
- 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 and tandem rotor respectively. 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. The tandem 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 some cases, the yaw control of the tandem helicopter is enhanced by extending the body forwardly and/or rearwardly by using a fin extension and/or extending the body itself in at least one of those directions. Having both the front and the rear extended is an effective yaw control.
- In practice, it appears that such an improved tandem helicopter is more stable and stabilizes itself relatively quickly with or without a restricted intervention of the user.
- 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.
- 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:
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FIG. 1 represents a perspective view of an embodiment of the helicopter with the rotors turning in the same direction; -
FIG. 2 represents a top view of the embodiment of the helicopter with the rotors turning in the same direction; -
FIG. 3 represents a bottom view of the embodiment of the helicopter with the rotors turning in the same direction; -
FIG. 4 represents a front view of the embodiment of the helicopter with the rotors turning in the same direction; -
FIG. 5 is a rear view of the embodiment of the helicopter with the rotors turning in the same direction; -
FIG. 6 is a right view of the embodiment of the helicopter with the rotors turning in the same direction; -
FIG. 7 is a left view of the embodiment of the helicopter with the rotors turning in the same direction; -
FIG. 8 is a sectional side view of the embodiment of the helicopter with the rotors turning in the same direction; -
FIG. 9 is a sectional front view through the front rotor structure of the helicopter with the rotors turning in the same direction. -
FIG. 10 represents another configuration of a tandem helicopter as viewed from the side with the rotors turning opposite to each other; -
FIG. 11 represents another configuration of a tandem helicopter as viewed from the top with the rotors turning opposite to each other; -
FIG. 12 represents a typical diagrammatic configuration of a tandem helicopter as viewed from the top with the rotors turning opposite to each other; -
FIG. 13 represents a typical diagrammatic configuration of a tandem helicopter as viewed from the side with the rotors turning opposite to each other with the stabilizer removed for clarity; -
FIG. 14 represents a typical diagrammatic configuration of a tandem helicopter as viewed from the top with the rotors turning in the opposite direction, with the stabilizer omitted for clarity; -
FIG. 15 represents a typical diagrammatic configuration of a tandem helicopter as viewed from the front with the rotors turning in the opposite direction, with the stabilizer omitted for clarity; -
FIG. 16 represents a typical diagrammatic configuration of a tandem helicopter as viewed from the top with the rotors turning in the same direction; -
FIG. 17 represents a typical diagrammatic configuration of a tandem helicopter as viewed from the front with the rotors turning in the same direction, with the stabilizer omitted for clarity; -
FIG. 18 represents another configuration of a tandem helicopter as viewed from the side; -
FIG. 19 represents another configuration of a tandem helicopter as viewed from the side, with the stabilizer omitted for clarity with the rotors turning in the same direction; -
FIG. 20 represents a configuration of a tandem helicopter ofFIG. 19 as viewed from the top, with the stabilizer omitted for clarity with the rotors turning in the same direction; -
FIG. 21 represents a configuration of a tandem helicopter ofFIG. 19 as viewed from the top, with the stabilizer omitted for clarity with the rotors turning in the same direction; -
FIG. 22 represents another configuration of a tandem helicopter as viewed from the side, with the stabilizer omitted for clarity with the rotors turning in the same direction; -
FIG. 23 represents another configuration of a tandem helicopter as viewed from a perspective side position, with the rotors and stabilizer omitted for clarity with the rotors turning in the same direction; -
FIG. 24A represents the configuration of a tandem helicopter ofFIG. 23 as viewed from the front, with the rotors and stabilizer omitted for clarity with the rotors turning in the same direction; -
FIG. 24B represents the configuration of a tandem helicopter ofFIG. 23 as viewed from the rear, with the rotors and stabilizer omitted for clarity with the rotors turning in the same direction; -
FIG. 25 represents yet another configuration of a tandem helicopter as viewed in perspective with the rotors and stabilizer omitted for clarity with the rotors turning in the same direction; -
FIG. 26 represents the system for controlling yaw in a tandem helicopter with the rotors turning in the same direction; -
FIG. 27 represents a detail of the main rotor and auxiliary rotor; -
FIG. 28 is a further representation of the main rotor and auxiliary rotor; -
FIG. 29 is a further detailed representation of the main rotor and auxiliary rotor and linkages between them; and -
FIG. 30 is a further detailed representation of the main rotor and auxiliary rotor. - A helicopter comprises a body, a main rotor with propeller blades which is driven by a rotor shaft on which the blades are mounted. There is a tandem rotor driven by a second rotor shaft. In some cases the rotor shafts are directed substantially parallel to the rotor shaft of the main rotor. In other cases, the rotor shafts can be inclined relative to each other. One shaft can incline to the left, and the other shaft can incline to the right as viewed from the front or the rear of the helicopter or vice versa.
- An auxiliary rotor is driven by the rotor shaft of the main rotor and is provided with vanes from the rotor shaft for rotation 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 is relatively upwardly and downwardly about the auxiliary shaft.
- The diameter of the auxiliary rotor is smaller than the diameter of the main rotor. The main rotor and the tandem rotor rotate in the same direction.
- The auxiliary shaft for the main rotor 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.
- There is also an auxiliary rotor driven by the rotor shaft of the tandem rotor. There are vanes from the tandem rotor shaft for rotation in the sense of rotation of the tandem 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. There are configurations where only one of the two rotor is equipped with an auxiliary rotor.
- The auxiliary shaft for the tandem rotor is provided essentially transverse to the rotor shaft of the tandem rotor. The tandem 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 tandem rotor
- The main rotor and tandem rotor each includes two propeller blades situated essentially in line with each other in some cases. In other cases, the rotor shafts are inclined relative to each other.
- The propeller blades of the main rotor, and the vanes of the auxiliary rotor are connected to the main rotor with a mechanical linkage that permits the relative movement between the blades of the main propeller and the vanes of the auxiliary rotor. There is a joint of the main rotor to the propeller blades formed of a spindle, which is fixed to the rotor shaft of the main rotor.
- The propeller blades of the tandem rotor, and the vanes of the auxiliary rotor for the tandem rotor are connected to the tandem rotor with a mechanical linkage that permits the relative movement between the blades of the tandem propeller and the vanes of the auxiliary rotor. There is a joint of the tandem rotor to the propeller blades formed of a spindle, which is fixed to the rotor shaft of the tandem rotor.
- The spindle of the main rotor and tandem rotors extend essentially in the longitudinal direction of the propeller blade of the main rotor and tandem rotors respectively. This is parallel to one of the vanes or is located at an acute angle relative to the longitudinal direction.
- 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 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. The rod is fixed to lever arms with its fastening point respectively part of the main rotor and of the auxiliary rotor A similar construction applies between the propeller blade of the tandem rotor and the vanes of the auxiliary rotor of the tandem rotor
- 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. A similar construction and configuration applies for the propeller blade of the tandem rotor and the vanes of the auxiliary rotor of the tandem rotor
- The longitudinal axis of the vanes of the auxiliary rotor in the plane of rotation is located at an acute angle relative to each other. This angle can be about 10° to about 17° with the longitudinal axis of one of the propeller blades of the main rotor. In another form, the longitudinal axis of one of the propeller blades of the main rotor in the plane of rotation, is located at an acute angle with the axis of a spindle mounting these propeller blades to the rotor shaft.
- The ‘longitudinal’ axis is seen in the plane 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 at a relatively small acute angle with the latter propeller blade axis. Each vane of the auxiliary rotor is relatively offset from the respective propeller of the main rotor that is closest to it.
- When viewed perpendicular to the plane of rotation of the main rotor and the auxiliary rotor this offset is a small acute angle. In some case each vane and its respective closest or related propeller are aligned and not offset. The vanes can be of any size and shape. The vanes can have a shape as a blade. In some situations there can be a rod which is at a relatively small angle, for instance about 17 degrees relative to the propeller. The blades of the vanes can have any suitable profile as viewed from an end, a cross-section laterally through the vane or longitudinally through the vane or longitudinally from a side. In some cases the rods are cylindrical elements and may have weights disposed at different points on the rods.
- In a different manner, there is provided a helicopter having a body; and a main rotor with propeller blades which is driven by a rotor shaft and which is mounted on this rotor shaft. The system permits the angle of incidence of the main rotor in the plane of rotation of the rotor and the rotor shaft to vary. An auxiliary rotor is rotatable with the rotor shaft and is for relative oscillating movement about the rotor shaft. Different relative positions are established so that the auxiliary rotor causes the angle of incidence the main rotor to be different.
- In yet a different manner, a helicopter has a body; and a main rotor with propeller blades which is driven by a rotor shaft and which is mounted on this rotor shaft. The angle between the plane of rotation of the main rotor and the rotor shaft may vary. An auxiliary rotor is driven by the rotor shaft of the main rotor and is provided with two vanes. The main rotor and the auxiliary rotor are 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. There is a tandem rotor which is driven by a second rotor shaft which is directed substantially parallel to the rotor shaft of the main rotor.
- The helicopter can be such the main rotor and the tandem rotor rotate in the same direction. Alternatively the main rotor and the tandem rotor rotate in the opposite.
- The
helicopter 1 represented in the figures generally by way of example is a remote-controlled helicopter which essentially includes abody 2 which can include some form of a landing gear. There is afirst system 4 being amain rotor 4 a; anauxiliary rotor 5 a driven synchronously, and also asecond system 5 being atandem rotor 4 b; anauxiliary rotor 5 b driven synchronously. Theauxiliary rotors - The
main rotor 4 a is provided by arotor head 7 a on a first upward directedrotor shaft 8 a which is bearing-mounted in thebody 2 of thehelicopter 1 in a rotating manner. This is driven by amotor 9 a and atransmission 10 a, including gearing. Themotor 9 a is for example an electric motor which is powered by an electric microprocessor andbattery 11. The tandem rotor system is similarly constructed, namely there is amotor 9 b and atransmission 10 b, whereby themotor 9 b is for example an electric motor which is powered by abattery 11. - The
main rotor 4 a in this case has twopropeller blades 12 a which are in line or practically in line, but which may just as well be composed of a larger number ofpropeller blades 12 a. Thetandem rotor 4 b in this case has twopropeller blades 12 b which are in line or practically in line, but which may just as well be composed of a larger number ofpropeller blades 12 b. - The tilt or angle of incidence A, as shown in detail in
FIG. 27 , of thepropeller blades 12 a, in other words the angle A which forms thepropeller blades 12 a as represented with the plane ofrotation 14 of themain rotor 4 a, can be adjusted as, themain rotor 4 a is hinge-mounted on thisrotor shaft 8 a 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. A similar, but not necessarily identical, configuration and operation is provided for the tandem rotor system. For instance, the tandem rotor may be more or less more or less weight in the auxiliary rotor, or a different size or shape relative to the main rotor system. - In the case of the example of a
main rotor 4 a with twopropeller blades 12 a, the joint is formed by aspindle 15 a of therotor head 7 a. A similar configuration and operation is provided for the tandem rotor system with regard torotors blades 12 b. - The
axis 14 a of theauxiliary rotor 5 a preferably forms an acute angle B with thelongitudinal axis 13 a of therotor 4 a. A similar configuration and operation is provided for the tandem rotor system with regard torotors blades 12 b. There is a similar relationship withaxis - The
helicopter 1 is also provided with anauxiliary rotor 5 a which is driven substantially synchronously with themain rotor 4 a by thesame rotor shaft 8 a and therotor head 7 a. A similar configuration and operation is provided for the tandem rotor system with regard torotors - The
auxiliary rotor 5 a in this case has two vanes which are essentially in line with theirlongitudinal axis 14 a. Thelongitudinal axis 14 a, seen in the sense of rotation R of themain rotor 4 a, is essentially parallel to thelongitudinal axis 13 a of propeller blades 12 of themain rotor 4 a or encloses a relatively small acute angle B with the latter. Bothrotors vanes 5 a. A similar configuration and operation is provided for the tandem rotor system with regard torotors FIG. 2 the angle is betweenaxis 14 a and the hinging line of rotor 13 going through the spindle 15. The hinging line, not represented, is parallel to the longitudinal axis, but may be varied to alter or tune the stability system. In the case represented the angles B and F are about the same so that the angle G is about Zero degrees. - The diameter of the
auxiliary rotor 5 a is preferably smaller than the diameter of themain rotor 4 a as thevanes 5 a have a smaller span than the propeller blades 12, and thevanes 5 a are substantially rigidly connected to each other. This rigid whole forming theauxiliary rotor 5 a is provided in a swinging manner on anoscillating shaft 30 which is fixed to therotor head 7 a of therotor shaft 8 a. This is directed transversally to the longitudinal axis of the vanes 12 and transversally to therotor shaft 8 a. A similar configuration and operation is provided for the tandem rotor system with regard torotors - The
main rotor 4 a and theauxiliary rotor 5 a are connected to each other by a mechanical link such that the angle of incidence A of at least one of the propeller blades 12 of themain rotor 4 a is set. In the given example this link is formed of arod 31. A similar configuration and operation is provided for the tandem rotor system with regard torotors - This
rod 31 is hinge-mounted to a propeller blade 12 of themain rotor 4 a with onefastening point 32 by means of a joint 33 and alever arm 34 and with anothersecond fastening point 35 situated at a distance from the latter, it is hinge-mounted to a vane of theauxiliary rotor 5 a by means of a second joint 36 and asecond lever arm 37. A similar configuration and operation is provided for the tandem rotor system with regard torotors - The
fastening point 32 on themain rotor 4 a is situated at a distance D from the axis 16 of the spindle 15 of thepropeller blades 12 a of themain rotor 4 a, whereas theother fastening point 35 on theauxiliary rotor 5 a is situated at a distance E from the axis 38 of theoscillatory shaft 30 of theauxiliary rotor 5 a. A similar configuration and operation is provided for the tandem rotor system with regard torotors - The distance D is preferably larger than the distance E. Distance E is represented in
FIGS. 2 , 29 and 30 and the distance between the axis ofoscillatory shaft 30 and the axis oflever arm 37. Distance D is about double the distance of E. Both fastening points 32 and 35 of therod 31 are situated. This is in the sense of rotation R on the same side of thepropeller blades 12 a of themain rotor 4 a or of thevanes 28 of theauxiliary rotor 5 a. In other words they are both situated in front of or at the back of thepropeller blades 12 a andvanes 5 a, as seen in the sense of rotation. A similar configuration and operation is provided for the tandem rotor system with regard torotors - Also preferably, the
longitudinal axis 14 a of thevanes 5 a of theauxiliary rotor 5 a, seen in the sense of rotation R, encloses an angle B with thelongitudinal axis 13 a of thepropeller blades 12 a of themain rotor 4 a, which enclosed angle B is in the order, of magnitude of about 10° to about 17°, whereby thelongitudinal axis 14 a of thevanes 5 a leads thelongitudinal axis 13 a of thepropeller blades 12 a, seen in the sense of rotation R. Different angles in a range of, for example, 5° to 25° could also be in order. A similar configuration and operation is provided for the tandem rotor system with regard torotors - The
auxiliary rotor 5 a is provided with two stabilizingweights 39 which are each fixed to avane 5 a at a distance from the rotor shaft 8. A similar configuration and operation is provided for the tandem rotor system with regard torotors - 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. A similar configuration and operation is provided for the tandem rotor system with regard torotors - As a function of the type of helicopter, it is possible to search for the most appropriate values and relations of the angles B by experiment; the relation between the distances D and E and G and F which are described below; the size of the
weights 39 and the relation of the diameters between themain rotor 4 a and theauxiliary rotor 5 a so as to guarantee a maximum auto stability. A similar configuration and operation is provided for the tandem rotor system with regard torotors - The operation of the
improved helicopter 1 according to the disclosure is as follows: - In flight, the
rotors main rotors helicopter 1 rise or descend or maintain it at a certain height, and the rotors develop a laterally directed force which is used to steer thehelicopter 1. A similar configuration and operation is provided for the tandem rotor system with regard torotors - It is impossible for the
main rotor 4 a to adjust itself, and it will turn in theplane 114 a in which it has been started, usually the plane perpendicular to therotor shaft 8 a. Under the influence of gyroscopic precession, turbulence and other factors, it will take up an arbitrary undesired position if it is not controlled. A similar configuration and operation is provided for the tandem rotor system with regard torotors - The surface of rotation of the
auxiliary rotor 5 a may take up another inclination in relation to the surface ofrotation 114 a of themain rotor 4 a, whereby bothrotors rotor shaft 8 a. - 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, theauxiliary rotor 5 a keeps turning in a plane which is essentially perpendicular to therotor shaft 8 a. - 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, theauxiliary rotor 5 a does not immediately follow this movement, since theauxiliary rotor 5 a can freely move round theoscillatory shaft 30. - The
main rotor 4 a and theauxiliary rotor 5 a are placed in relation to each other in such a manner that a swinging motion of theauxiliary rotor 5 a is translated almost immediately in the pitch or angle of incidence A of the propeller blades 12 being adjusted. A similar configuration and operation is provided for the tandem rotor system with regard torotors - For a two-bladed
main rotor 4 a, this means that the propeller blades 12 and thevanes 28 of bothrotors main rotor 4 a and a smallerauxiliary rotor 5 a. A similar configuration and operation is provided for the tandem rotor system with regard torotors - This angle can be calculated or determined by experiment for any
helicopter 1 or per type of helicopter, and this angle can be different for the rotor and the tandem rotor. - If the axis of
rotation 8 a takes up another inclination than the one which corresponds to the above-mentioned position of equilibrium in a situation whereby thehelicopter 1 is hovering, the following happens: A similar configuration and operation is provided for the tandem rotor system with regard torotors - A first effect is that the
auxiliary rotor 5 a will first try to preserve its absolute inclination, as a result of which the relative inclination of the surface of rotation of theauxiliary rotor 5 a in relation to therotor shaft 8 a changes. A similar configuration and operation is provided for the tandem rotor system with regard torotors - 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 themain rotor 4 a and will decrease on the diametrically opposed side of this main rotor. A similar configuration and operation is provided for the tandem rotor system with regard torotors - Since the relative position of the
main rotor 4 a and theauxiliary rotor 5 a are selected such that a relatively immediate effect is obtained. This change in the upward force makes sure that therotor shaft 8 a and thebody 2 are forced back into their original position of equilibrium. - A second effect is that, since the distance between the far ends of the vanes and the plane of
rotation 14 of themain rotor 4 a is no longer equal and since also thevanes 28 cause an upward force, a larger pressure is created between themain rotor 4 a and theauxiliary rotor 5 a on one side of themain rotor 4 a than on the diametrically opposed side. A similar configuration and operation is provided for the tandem rotor system with regard torotors - 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. - If necessary, this aspect of the disclosure may be applied separately, just as the aspect of the
auxiliary rotor 5 a can be applied separately to a helicopter having amain rotor 4 a combined with anauxiliary rotor 5 a. A similar configuration and operation is provided for the tandem rotor system with regard torotors - 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 a and theauxiliary rotor 5 a are not necessarily be made as a rigid whole. Thepropeller blades 12 a and thevanes 5 a can also be provided on therotor head 7 a such that they are mounted and can rotate relatively separately. In that case, for example, tworods 31 may be applied to connect each time onepropeller blade 12 a to onevane 5 a. A similar configuration and operation is provided for the tandem rotor system with regard torotors - 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 a having more than two propeller blades 12, one should preferably be sure that at least onepropeller blade 12 a is essentially parallel to one of thevanes 5 a of the auxiliary rotor. The exact angle is determined by testing and can be different from zero. The joint of themain rotor 4 a is preferably made as a ball joint or as a spindle 15 which is directed essentially transversely to the axis of theoscillatory shaft 30 of theauxiliary rotor 5 a and which essentially extends in the longitudinal direction of the onepropeller blade 12 a concerned which is essentially parallel to thevanes 5 a. A similar configuration and operation is provided for the tandem rotor system with regard torotors - In another format, the helicopter comprises a body, and a main rotor with propeller blades which is driven by a rotor shaft on which the blades are mounted. 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 that 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.
- Tandem helicopters have two rotors of more or less similar diameter the rotors are disposed along the helicopter body typically one at each end. The tip rotor paths may be overlapping to a certain extend. In that case one rotor is positioned higher than the other to avoid that the rotor blades collide.
-
FIG. 7 represents a typical configuration. Both rotors exercise a lift force to compensate for the weight of the body. If the combined lift force exceeds the weight of the tandem, there will be lift off. - Stability and equilibrium of the tandem helicopter can be analyzed in 4 dimensions that need control to keep the tandem on a spot in space, or along a desired trajectory. These controls can be active (by the pilot, or assisted by electronics), or passive (by aerodynamic and mechanical design).
- These dimensions are represented in
FIGS. 10 and 11 . -
- forward/backward (100)
- sideward left/right (200)
- up/down vertical (300)
- yaw (400)
- These 4 dimensions have no absolute reference in space. Therefore, constant corrections have to be performed in flight to keep the tandem flying as desired. Both in real size and hobby/toy tandems, it is generally known that this implies very specific and complicated set of stabilizing devices like gyro's and feedback systems, on top of permanent pilot controls.
- To accomplish stability in
dimension certain extent dimension 400, the tandem helicopter is equipped with autostable rotors as described inFIGS. 10 and 17 . This rotor system wants the helicopter to resist by rotor design any deviation indimensions certain extent dimension 400. -
Dimension 300 usually does not require anything more than the input of the pilot to choose and keep the desired altitude, or climbing and descending speed. -
Dimension 400, the yaw around the vertical axis needs to deal with the torque effects of the main rotors, and any external disturbances that induce yaw changes. - A rotor produces torque as a side effect of the thrust generated. This torque will go against the direction of rotation of the rotor. In a classical helicopter with main and tail rotor, this torque is compensated by the tail rotor. If no such compensation existed, the body would rotate around the vertical axis in a direction against the rotation of the rotor. The main rotor turning in a clockwise direction induces a torque on the body in counter clockwise direction. To keep the body from turning permanently around its vertical axis, the tail rotor is added to compensate for torque with a sideward force.
- In tandem helicopters as shown in
FIGS. 12 and 13 , the two rotors are turning so that the rotation of onerotor 1000 in direction 1100 (clockwise) creates a torque on thebody 2 in direction 113 (counterclockwise) around thecenter axis 500. The rotation of theother rotor 2000 in direction 1200 (counterclockwise) creates a torque on the body in direction 114 (clockwise) around the center axis of that rotor. This is illustrated inFIG. 13 . - Torque 113 and
torque 114 are in a perfect case of equal size, however of opposite direction. Therefore, they annulate and the body of the tandem does not rotate by itself. - Yaw Behavior
- That perfect case assumes that both rotors turn at identical speed, have identical drag, have identical lift, and that no external disturbances like air gusts and turbulences have influence.
- In reality, none of this is absolutely true. So although the body more or less keeps its yaw position, it will constantly and randomly change direction because of all the above factors. It is up to the pilot, assisted by eventual gyro stabilizer, or other devices, to correct for that.
- The smaller the model is, the more these factors have effect due to the lower inertia of the tandem, requiring speedier correction input from the pilot.
- Yaw Instability
- The counter rotation configuration annulates torque on the body. However, it causes a problem related to yaw stability.
- Consider art tandem helicopter in a hovering position, and suppose it is in perfect still position in hover flight. This is shown in
FIG. 13 . Therotor 1000 androtor 2000 turn in opposite direction. Therotor 1000 androtor 2000 createidentical lift forces - Consider the same tandem helicopter in hovering position, and suppose that as the result of any of the effects described (air gusts, turbulence, slight change in relative rotor rpm, etc) the body starts turning in one direction (clockwise in this example), around the
vertical centerline 500 of the tandem helicopter ofFIG. 13 . Therotor 1000 androtor 2000 turn in opposite directions. Because of the body rotation and direction of rotation,rotor 1000 increases its rotation speed whilerotor 2000 decreases rotation speed relative to the air. Because lift force at constant pitch varies with rotation speed, therotor 1000 androtor 2000 create now different lift forces, 3000 is higher and 4000 is lower. Because of the difference in the lift forces, the body is no longer in equilibrium and tend to raise the front end whererotor 1000 is and lower the back end adjacent torotor 2000. Because of the difference in lift forces, the torque onrotor 1000 increases, and the torque onrotor 2000 decreases. - The changes in torque are of the same amount but in a different direction, so they balance out each other and do not influence the yaw disturbance.
- When the
body 2 starts turning in one direction (clockwise in this example), around thevertical centerline 500 of the tandem helicopter (FIG. 13 ), then the lift force along the span of one rotor varies along the position relative to the body and the body rotation axis. The increase/decrease in lift will be higher the further from the body rotation axis. This further amplifies the destabilizing of the helicopter and raises the front end whererotor 1000 is and lowers the back end adjacent torotor 2000 even more. - The
body 2 no longer stays horizontal and raises the high lift rotor and lower the low lift rotor. The increase in lift ofrotor 1000 is accompanied by a move of the center of lift further from the centerline of the helicopter (longer lever). The associated decrease in lift ofrotor 2000 is accompanied by a move of the center of lift closer to the center line of the helicopter (shorter lever). Both effects combined reinforce the tendency to incline backwards caused by the differences in thrust as such. This inclination results in unwanted and parasite backward speed. That further destabilizes the tandem on top of the initial yaw disturbance. - Left-Right Asymmetry in Counter-Rotating Configuration
- The counter-rotating rotors create a tandem that is symmetrical in aerodynamic, gyroscopic effects. This is supposed to facilitate lay-out of the components, the body and the overall design of the body.
- However, counter-rotating rotors have an asymmetric effect on the sideward thrust on the tandem body.
Rotor 1000 androtor 2000 are counter-rotating. The rotors create a down-flow of air to create lift, but that down flow has a spiraling component in the direction of rotation of the rotor. When the tips of both rotors reach the center of thebody 2, this spiraling air is hitting the side of thebody 2 with an airflow component. - A 3 stage effect is created on the tandem:
-
- a. The
body 2 sees a one sided thrust force, this side force tends to push the helicopter in the direction offorce 4000. - b. This
force 4000 makes the tandem incline to one side and both rotors incline in an equal amount. - c. The lift force is no longer vertical but has a horizontal vector component. This vector pushes the tandem to the opposite direction. This increases the sideward force that hits the
body 2.
- a. The
- So, in spite of the apparent symmetry of the counter rotating configuration, the tandem will have a strong tendency to lean over and slip to one side. This tendency varies with the surface of the body, the weight of the tandem, the rotation speed of the rotors, the relative distance from the rotor(s) to the body, the position of the center of gravity. Overall, this tendency increases with a decrease in weight of the tandem. A possible solution is to move the center of gravity sideward to align the body back to vertical.
- The unidirectional tandem rotors are illustrated with reference to the figures.
- The counter rotation rotors on a tandem configuration, where the rotor axes are at a certain distance from each other, have destabilizing and asymmetrical effects. Yaw changes induce fore/aft drift, and the rotor pushes the tandem to lean over and slip. The combination of these effects makes it very hard to find a natural trim of the tandem for stable hover without pilot correction, or gyro, etc., on the fore/aft and sideways dimension.
- The solution is to have the rotors spinning in the same direction. When an external yaw disturbance causes the body to rotate, then both rotors will see the same amount of decrease or increase in rotation speed equal to the rotation speed of the body.
- Lift forces on both rotors change equally, so the body stays horizontal. This change in lift force does make the tandem ascent or descent. However, because there is no body inclination, this is not a destabilizing effect.
- The sideward spiraling forces of the rotor thrust still hit the
body 2, but now in opposite direction such that they cancel out. The body does not incline, nor slips sideways. - The torque of
rotor 1000 androtor 2000, in this case of clockwise rotation of both rotors, now adding up into a new torque. The rotors are inclined in such a way, namely amount and direction that a horizontal thrust force on both rotor axis creates a counter torque that cancels out the sum of the rotor torque. - The thrust on
rotor 1000 has a horizontal component centered on therotor 1000 axis. The thrust onrotor 2000 has a horizontal component centered on therotor 1000 axis. Those two forces exercise a torque on thebody 2 in the opposite direction of the first torque. The size of thrusts depends on the inclination of therotors - The required degree of inclination of the rotors depends mainly on:
-
- the type of rotor shape and airfoil;
- the horizontal distance between both rotors; and
- the shape of the
body 2 which also has an influence on the angle.
- This inclination is relatively small and is independent of rpm. When the rpm changes higher, for example, so does the torque induced by the rotor. The higher rpm means a higher lift and a higher horizontal thrust component and thus a higher corrective thrusts. It is possible to increase rpm at one rotor, the rear rotor for example, and decrease the rpm on the other rotor, the front rotor, without any asymmetrical torque effects that cause the body to turn around or yaw. This makes it possible to move the helicopter forward or backward using this method without the need for yaw correction.
- Counter rotating rotors on tandem helicopters create tendency to drift in the for/after and sideway direction, and induces inclination of the body. This leads to instability in flight unless a pilot, mechanical or electronic system creates the necessary corrective input.
- The current disclosure uses two rotors at a certain horizontal distance one from another, rotating in the same direction. Those rotors are inclined such that they compensate for the torque effects induced by the spinning rotors. The effects of yaw (pilot induced or uninitiated/unwanted) no longer create drift in the for/after dimension, nor does it cause undesired inclination of the body. The spiral thrust no longer inclines and drifts the body sideways.
- The body design is another element enhancing the stability against undesired yaw affects.
- The body shape of a typical tandem helicopter is determined to an extent by functional matters. As shown in
FIG. 18 , there is a need to interconnect both rotors and their drive systems, and that leads to a long and mainly rectangular central part A. Then there is a typical nose end B added to house the pilot(s) and a tail end with increased surface C to act as a directional stabilizer for forward flight. This is similar to the fins on an arrow. - The size of B and C, mainly the part that sticks out under the E and D ends of the rotors has an impact on yaw stability.
- A shape shown in
FIG. 19 with extension fins F and G has a relatively higher yaw stability, and resists and even stops any unwanted yaw effects due to asymmetry in torque between the rotors and external disturbances. Furthermore, when the pilot gives a wanted yaw input, this shape dampens the effect, avoid overshooting of the effect versus the desired effect, and acts as a ‘damper’. The result is more comfort for the pilot, and a much more stable tandem helicopter. - The reasons why this works are at least 3 fold. First, the surfaces F and G are at the outermost distance from the centerline H compared with the rest of the body. This is further illustrated in
FIG. 20 . In case of yaw around the centerline H clockwise, for example, the lateral surfaces F and G operate like aerodynamic brakes, because they have to overcome the pressure of theair - This braking effect slows down the yaw rotation, and eventually stops it. The shape of F and G can be any desired profile.
- Secondly, the surfaces F and G are in the downwards airflow as generated by the two rotors, and tend to align to that downward force. This is a function similar to a vane effect.
- Thirdly, If the body rotates, then the surfaces of fins F and G will see the downflow from the rotor thrust combined with the movement as result of the yaw, as a combined flow that no longer is in line with the surface of fins F or G but with a certain angle of attack. This angle of attack creates a lift force perpendicular to the surfaces of fins F and G opposite to the direction of movement. These lift forces 500 and 600 counter the yaw movement and further dampen it. See
FIG. 21 . - The shape of the fin parts F and G can be any desirable profile. As is shown in
FIG. 22 , the front extension is integrated in the body design. The back fin G end can be a transparent foil of plastic. - Alternatively, both extension fins F and G are made of transparent plastic so as to respect a desired shape of a body and yet to have the effect of yaw stabilization. This is shown in
FIG. 23 . - The surfaces of fins F and G can be inclined to be more or less in line with the airflow of the incline rotor shafts the embodiment of the rotors rotating in the same direction. This intensifies the effect and reduces airflow friction over those surfaces, as shown in
FIGS. 24A and 24B . - The effect of increased yaw stability is also accomplished in the case of having one of the surface of fins F or G. Alternatively, the ratio between the surface of fins F and G can be significantly different from 1 to 1. In that case, the effect is still there. It may be somewhat reduced because the effects of both rotors are not used to a full extent.
- In some cases where the ratio between F and G is largely different from 1 to 1, and due to the arrow effect briefly described above, the helicopter only feels comfortable moving (due to an eventual forward command given by the pilot) in the
direction 80 opposite the main lateral surface of the body. This is shown inFIG. 25 . - One of the surfaces of fins F and G can be added or removed depending on the main direction of movement. In usual flight, helicopters will hover or fly forward, so only surface G may be needed. This is shown in
FIG. 25 . - The fin extensions F and/or G can reach essentially the outer circumferential point reached by the rotating rotor. Even if they do not reach to the other circumferential point, there will be a stabilizing effect.
-
FIG. 26 represents a system for controlling yaw. The yaw of a tandem helicopter as illustrated inFIG. 26 with rotors turning in the same direction can be controlled by changing the incidence of one rotor shaft ofrotor 1000 versus the other rotor shaft of thetandem rotor 2000. This change in inclination changes the size of the horizontal components of the lift forces. This varies the size of the torque, which in turn varies the turning direction of the body. One method of varying this incidence is represented inFIG. 26 . The two rotor shafts of the tworotors central boom 12000. Thiscentral boom 12000 is split in twoparts system 3000, or use other actuators like piezo actuators, polymer actuators, magnet/coil assemblies and comparable technologies. - 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.
- While the apparatus and method have been described in terms of what are presently considered to be the most practical and preferred embodiments, it is to be understood that the disclosure need not be limited to the disclosed embodiments. In some cases there may be more than two propellers and/or vanes on one or more of the respective main rotors or tandem rotors and their respective auxiliary rotors. Also the acute angle between the propeller and vane can vary in extent and can be less than 10° and more than 17°.
- Although the invention has been described in detail with regard to a tandem helicopter, it is clear that the rotors can cause other objects to fly in a similar stabilized manner. The body of those objects can take different forms, for instance different toy vehicles or toy figurines. These could be robots, insects, motorcars, flying saucers, airplanes, or any other body type that one may want to fly above the ground, floor or base.
- It is intended to cover various modifications and similar arrangements included within the spirit and scope of the claims, the scope of which should be accorded the broadest interpretation so as to encompass all such modifications and similar structures. The present disclosure includes any and all embodiments of the following claims.
Claims (18)
1. A remote control toy helicopter comprising:
a body;
a main rotor with propeller blades driven by a first rotor shaft on which the blades are mounted, and a main motor for rotating the main rotor;
a tandem rotor with propeller blades driven by a second rotor shaft mounted at a distance relative to the first rotor shaft, and a tandem motor for rotating the tandem rotor;
an auxiliary rotor driven by the first rotor shaft of the main rotor in the same sense of rotation of the main rotor;
the auxiliary rotor being 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;
the main rotor and the auxiliary rotor being 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 first rotor shaft and the tandem rotor shaft being essentially upwardly directed and the plane of rotation of the main rotor propeller blades and the tandem rotor propeller blades being essentially to create upward lift; and the diameter of the propeller blades of the main rotor and the propeller blades of the tandem rotor being about equal;
wherein the main rotor and the tandem rotor rotate in the same direction; and
a battery for the main rotor and tandem rotor, and the main rotor and the tandem rotor being controllable by a remote controller remote from the body.
2. A helicopter as claimed in claim 1 , wherein the body includes a front end and the extent of the body at the front end is substantially at the same position as the outer circumferential position of the main rotor, and wherein the body includes a rear end and the extent of the body at the rear end is substantially the same position as the outer circumferential position of the tandem rotor.
3. A helicopter as claimed in claim 1 , wherein the body includes a rear end and the extent of the body at the rear end is substantially the same position as the outer circumferential position of the tandem rotor.
4. A helicopter as claimed in claim 1 , wherein at least one of the first rotor shaft for the main rotor or the second rotor shaft for the tandem rotor is relatively inclined in relation to a vertical axis through the body, the inclination being opposite to each other relative to the vertical axis, and including a linkage between the first rotor shaft and the tandem rotor shaft and including a motor for moving the linkage whereby the relative angle of the first rotor shaft and the second rotor shaft is selectively variable relative to the vertical axis.
5. A helicopter according to claim 1 , wherein the auxiliary rotor includes elongated members, the elongated members being for driven for rotation with the first rotor, and wherein the elongated members have a generally longitudinal axis located at an acute angle relative to a generally longitudinal axis of one of the respective propeller blades of the main rotor, and wherein each propeller blade has a profile wherein along the direction of its generally longitudinal axis of each propeller blade there is a first longitudinal convex curve from a position towards the first rotor shaft to a position towards an end area of the blade.
6. A helicopter according to claim 1 , including an auxiliary rotor driven by the second rotor shaft of the tandem rotor in the sense of rotation of the tandem rotor, the auxiliary rotor of the tandem rotor being 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 tandem rotor, the tandem rotor and the auxiliary rotor being 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 tandem rotor.
7. A helicopter according to claim 1 , wherein the main rotor and tandem rotor each include two propeller blades, the blades of each rotor being situated essentially in line with each other, and the two blades for each rotor being elongated, and wherein each propeller 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, and a transverse convex curve preferably being present over a substantial generally longitudinal length of the blade.
8. A helicopter according to claim 7 , wherein each propeller blade 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, and the transverse convex curve preferably being present over a substantial generally longitudinal length of the blade.
9. A helicopter as claimed in claim 1 , wherein at least one of the rotor shaft for the main rotor or the rotor shaft for the tandem rotor is relatively inclined in relation to a vertical axis through the body, and including a motor for changing the axis of the first rotor shaft or the second rotor shaft, whereby the relative angle of the first rotor shaft or the second rotor shaft is selectively variable relative to the vertical axis.
10. A helicopter as claimed in claim 1 , wherein the first shaft and the second shaft are relatively inclined to the vertical axis through the body, and wherein the inclination of the first rotor shaft and the second rotor shaft are oppositely inclined relative to the vertical axis and including a motor for changing the axis of the first rotor shaft or the second rotor shaft, whereby the relative angle of the first rotor shaft or the second rotor shaft is selectively variable relative to the vertical axis.
11. A remote control toy helicopter comprising:
a body;
a main rotor with propeller blades which is driven by a first rotor shaft and which is mounted on the first rotor shaft, and a main motor for rotating the main rotor;
a first auxiliary rotor operable with the main rotor, the auxiliary rotor being provided with two elongated members, the motion of the first auxiliary rotor controlling the angle of incidence of at least one of the propeller blades of the main rotor;
a tandem rotor with propeller blades driven by a second rotor shaft mounted at a distance relative to the rotor shaft of the main rotor, and a tandem motor for rotating the tandem rotor;
a second auxiliary rotor with the tandem rotor, and the second auxiliary rotor being provided with two elongated members, the motion of the second auxiliary rotor controlling the angle of incidence of at least one of the propeller blades of the tandem rotor;
wherein the body or an extension of the body extends substantially to the circumferential end of the main rotor and the circumferential end of tandem rotor; and
a battery for the main rotor and tandem rotor, and the main rotor and the tandem rotor being controllable by a remote controller remote from the body
12. A helicopter according to claim 11 , wherein the main rotor and the tandem rotor rotate in the same direction.
13. A helicopter according to claim 11 , wherein the first and second auxiliary rotors are mounted such that the longitudinal axis of one of the propeller blades of the main rotor and tandem rotor is located relative to the longitudinal axis of the respective elongated members of the first and second auxiliary rotors, such that the acute angle between the plane of rotation of the main rotor and the first rotor shaft and the tandem rotor and the second rotor shaft is variable; and wherein the longitudinal axis of one of the propeller blades of the main rotor and tandem rotor is located at an acute angle relative to the longitudinal axis of a respective elongated member of the first and second auxiliary rotor, and wherein the main rotor and the tandem rotor rotate in the same direction.
14. A helicopter according to claim 11 , wherein the auxiliary rotors respectively include elongated members, the elongated members being for driven for rotation with the first rotor, and wherein the elongated members have a generally longitudinal axis located at an acute angle relative to a generally longitudinal axis of one of the respective propeller blades of the main rotor and tandem rotor, and wherein each propeller blade has a profile wherein along the direction of its generally longitudinal axis of each propeller blade there is a first longitudinal convex curve from a position towards the first rotor shaft to a position towards an end area of the blade and wherein the main rotor and the tandem rotor rotate in the same direction.
15. A helicopter according to claim 11 , wherein the main rotor and tandem rotor each include two propeller blades, the blades of each rotor being situated essentially in line with each other, and the two blades for each rotor being elongated, and wherein each propeller 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, and the transverse convex curve preferably being present over a substantial generally longitudinal length of the blade and wherein the main rotor and the tandem rotor rotate in the same direction.
16. A helicopter as claimed in claim 11 , wherein at least one of the first rotor shaft for the main rotor or the second rotor shaft for the tandem rotor is relatively inclined in relation to a vertical axis through the body.
17. A helicopter as claimed in claim 11 , wherein the first shaft and the second shaft are relatively inclined to the vertical axis through the body, and wherein the inclination of the first rotor shaft and the second rotor shaft are oppositely inclined relative to the vertical axis, and including a motor for changing the axis of the first rotor shaft or the second rotor shaft, whereby the relative angle of the first rotor shaft or the second rotor shaft is selectively variable relative to the vertical axis.
18. A remote control toy helicopter comprising:
a body;
a main rotor with propeller blades which is driven by a first rotor shaft and which is mounted on the first rotor shaft, and a main motor for rotating the main rotor;
a first auxiliary rotor operable with the main rotor, the auxiliary rotor being provided with two elongated members, the motion of the first auxiliary rotor controlling the angle of incidence of at least one of the propeller blades of the main rotor;
a tandem rotor with propeller blades driven by a second rotor shaft mounted at a distance relative to the rotor shaft of the main rotor, and a tandem motor for rotating the tandem rotor;
a second auxiliary rotor with the tandem rotor, and the second auxiliary rotor being provided with two elongated members, the motion of the second auxiliary rotor controlling the angle of incidence of at least one of the propeller blades of the tandem rotor;
wherein the body or an extension of the body extends substantially to the circumferential end of the main rotor and the circumferential end of tandem rotor,
a battery for the main rotor and tandem rotor, and the main rotor and the tandem rotor being controllable by a remote controller remote from the body; and
wherein the first shaft and the second shaft are relatively inclined to the vertical axis through the body, and wherein the inclination of the first rotor shaft and the second rotor shaft are oppositely inclined relative to the vertical axis, and including a third motor for changing the axis of the first rotor shaft or the second rotor shaft, whereby the relative angle of the first rotor shaft or the second rotor shaft is selectively variable relative to the vertical axis, and wherein the third motor is located relatively closer to either the first rotor shaft or the second rotor shaft.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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US12/188,070 US20080299867A1 (en) | 2006-01-19 | 2008-08-07 | Flying object with tandem rotors |
Applications Claiming Priority (6)
Application Number | Priority Date | Filing Date | Title |
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BE2006/0043A BE1016960A3 (en) | 2006-01-19 | 2006-01-19 | IMPROVED HELICOPTER. |
BE2006/0043 | 2006-01-19 | ||
US11/462,177 US20070164148A1 (en) | 2006-01-19 | 2006-08-03 | Helicopter |
US11/465,781 US7815482B2 (en) | 2006-01-19 | 2006-08-18 | Helicopter |
US11/736,506 US20070181742A1 (en) | 2006-01-19 | 2007-04-17 | Flying object with tandem rotors |
US12/188,070 US20080299867A1 (en) | 2006-01-19 | 2008-08-07 | Flying object with tandem rotors |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US11/736,506 Continuation US20070181742A1 (en) | 2006-01-19 | 2007-04-17 | Flying object with tandem rotors |
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US20080299867A1 true US20080299867A1 (en) | 2008-12-04 |
Family
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Family Applications (4)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/462,177 Abandoned US20070164148A1 (en) | 2006-01-19 | 2006-08-03 | Helicopter |
US12/188,070 Abandoned US20080299867A1 (en) | 2006-01-19 | 2008-08-07 | Flying object with tandem rotors |
US12/264,890 Abandoned US20090047862A1 (en) | 2006-01-19 | 2008-11-04 | Flying object with tandem rotors |
US12/696,183 Active 2031-02-25 US8308522B2 (en) | 2006-01-19 | 2010-01-29 | Flying toy |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/462,177 Abandoned US20070164148A1 (en) | 2006-01-19 | 2006-08-03 | Helicopter |
Family Applications After (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/264,890 Abandoned US20090047862A1 (en) | 2006-01-19 | 2008-11-04 | Flying object with tandem rotors |
US12/696,183 Active 2031-02-25 US8308522B2 (en) | 2006-01-19 | 2010-01-29 | Flying toy |
Country Status (4)
Country | Link |
---|---|
US (4) | US20070164148A1 (en) |
EP (1) | EP2351607B1 (en) |
CN (2) | CN201012292Y (en) |
BE (1) | BE1016960A3 (en) |
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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US20090163110A1 (en) * | 2006-01-19 | 2009-06-25 | Silverlit Toys Manufactory Ltd. | Remote controlled toy helicopter |
US20100003886A1 (en) * | 2008-07-02 | 2010-01-07 | Bob Cheng | Model helicopter |
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US8002604B2 (en) | 2006-01-19 | 2011-08-23 | Silverlit Limited | Remote controlled toy helicopter |
US8123176B2 (en) | 2009-12-24 | 2012-02-28 | Spin Master Ltd. | Velocity feedback control system for a rotor of a toy helicopter |
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Families Citing this family (27)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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Citations (80)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US934771A (en) * | 1906-04-02 | 1909-09-21 | Wallace Rupert Turnbull | Aeroplane and hydroplane. |
US1446718A (en) * | 1921-08-25 | 1923-02-27 | Charles C Tankel | Vertical-rising aeroplane and aerofoil |
US1470017A (en) * | 1919-02-04 | 1923-10-09 | Alfred J Cleary | Wing for flying machines |
US1828783A (en) * | 1926-06-18 | 1931-10-27 | Oehmichen Etienne | Lifting device |
US1925156A (en) * | 1930-08-26 | 1933-09-05 | Sidney P Vaughn | Method of driving propellers and rotative wing systems |
US2110563A (en) * | 1934-06-25 | 1938-03-08 | Thaon Andre | Aircraft of the autogyro type |
US2272643A (en) * | 1941-01-11 | 1942-02-10 | Peters Harry | Toy convertible automobile-plane |
US2466821A (en) * | 1944-10-23 | 1949-04-12 | John M Owen | Helicopter |
US2487020A (en) * | 1945-02-12 | 1949-11-01 | Gilerease Leonard | Helicopter |
US2514822A (en) * | 1949-08-19 | 1950-07-11 | Jr Frank H Wolfe | Helicopter automobile |
US2554938A (en) * | 1946-07-01 | 1951-05-29 | Joseph D Catalano | Amphibian helicopter |
US2563731A (en) * | 1945-04-17 | 1951-08-07 | Wilbur L Masterson | Land, sea, and air plane |
US2614637A (en) * | 1948-03-26 | 1952-10-21 | Landgraf Fred | Air screw with automatic pitch mechanism |
US2639874A (en) * | 1948-09-10 | 1953-05-26 | Edward A Stalker | Helicopter wings and other aircraft structures with boundary layer control |
US2801494A (en) * | 1954-12-31 | 1957-08-06 | Ernst Max | Remotely controlled toy aircraft |
US2818123A (en) * | 1955-06-23 | 1957-12-31 | Hiller Helicopters | Rotary wing aircraft |
US2923494A (en) * | 1958-03-26 | 1960-02-02 | Richard A Strong | Ground-air vehicle |
US2980187A (en) * | 1957-02-28 | 1961-04-18 | Rodrigo M Smyth-Davila | Helicopter |
US2987848A (en) * | 1958-07-10 | 1961-06-13 | Neuhaus Gottfried | Toy aeroplane |
US3068611A (en) * | 1959-09-01 | 1962-12-18 | Harold R Shoemake | Toy aircraft |
US3116896A (en) * | 1961-04-05 | 1964-01-07 | Eltra Corp | Combination helicopter-automobile |
US3135334A (en) * | 1960-12-05 | 1964-06-02 | Lockheed Aircraft Corp | Rotor |
US3321022A (en) * | 1963-10-25 | 1967-05-23 | Oguri Yoshiyuki | Rotary wing assembly |
US3370809A (en) * | 1965-06-29 | 1968-02-27 | United Aircraft Corp | Convertiplane |
US3371886A (en) * | 1966-01-14 | 1968-03-05 | Robert O. Schertz | Aircraft adapted for highway usage |
US3391746A (en) * | 1967-05-15 | 1968-07-09 | Samuel Chayes | Helicopter control system |
US3450374A (en) * | 1966-03-03 | 1969-06-17 | Moore Alvin E | Resiliently flexible vehicle |
US3460628A (en) * | 1961-11-06 | 1969-08-12 | Bendix Corp | Laminated tension-torsion tie-bar |
US3481559A (en) * | 1968-11-20 | 1969-12-02 | Steven Postelson Apostolescu | Helicopter-automobile-boat and air suspension car combination |
US3554467A (en) * | 1968-02-19 | 1971-01-12 | Universal Helicar Co | Counterrotating rotor transmission for helicoptors |
US3558081A (en) * | 1969-02-20 | 1971-01-26 | Airmarine Corp | Airborne vehicles |
US3662487A (en) * | 1968-10-12 | 1972-05-16 | Uwe C Seefluth | Balloon-type aircraft toy |
US3759629A (en) * | 1969-05-12 | 1973-09-18 | J Abramopaulos | Combined land and air vehicle |
US3905565A (en) * | 1973-09-27 | 1975-09-16 | Herman Gopp Kolwey | Tilt axis dual rotor helicopter and control system |
US4084345A (en) * | 1977-06-24 | 1978-04-18 | Toytown Corporation | Toy helicopter |
US4173321A (en) * | 1971-03-08 | 1979-11-06 | Karl Eickmann | Vehicle for traveling in the air and on the ground equipped with hydraulically driven propellers |
USD287738S (en) * | 1985-02-06 | 1987-01-13 | Kenner Parker Toys Inc. | Toy helicopter |
US4759514A (en) * | 1986-09-30 | 1988-07-26 | The Boeing Company | Tail rotor yaw position control for a helicopter |
US4880355A (en) * | 1987-06-29 | 1989-11-14 | Aerospatiale Societe Nationale Industrielle | Blade with curved end for a rotary airfoil of an aircraft |
US4941803A (en) * | 1989-02-01 | 1990-07-17 | United Technologies Corporation | Airfoiled blade |
US4981456A (en) * | 1988-06-20 | 1991-01-01 | Yamaha Hatsudoki Kabushiki Kaisha | Remote controlled helicopter |
US5190242A (en) * | 1989-12-18 | 1993-03-02 | Nichols Edward H | Model jet helicopter with solid-circular rotor blade |
US5203520A (en) * | 1991-10-28 | 1993-04-20 | Jozef Przygodzki | Helicar |
US5252100A (en) * | 1989-06-06 | 1993-10-12 | Wildgear Inc. | Variable rotor-blade-attack angle helicopter toy |
US5304090A (en) * | 1993-01-19 | 1994-04-19 | Vanni Robert R | Toy helicopter having forwardly inclined rotor shaft |
US5505407A (en) * | 1993-09-09 | 1996-04-09 | Fran Rich Chi Associates | Air-land vehicle |
US5915649A (en) * | 1996-08-23 | 1999-06-29 | Mcdonnell Douglas Helicopter Company | Roadable helicopter |
US5971320A (en) * | 1997-08-26 | 1999-10-26 | Jermyn; Phillip Matthew | Helicopter with a gyroscopic rotor and rotor propellers to provide vectored thrust |
US6086016A (en) * | 1997-01-21 | 2000-07-11 | Meek; Stanley Ronald | Gyro stabilized triple mode aircraft |
US20020049518A1 (en) * | 2000-10-23 | 2002-04-25 | Futaba Corporation | Sterring control device for radio-controlled model helicopter |
US6745977B1 (en) * | 2003-08-21 | 2004-06-08 | Larry D. Long | Flying car |
US6899586B2 (en) * | 2001-03-28 | 2005-05-31 | Steven Davis | Self-stabilizing rotating toy |
US20050121552A1 (en) * | 2001-11-07 | 2005-06-09 | Jeffrey Rehkemper | Propellers and propeller related vehicles |
US6938853B2 (en) * | 2002-03-15 | 2005-09-06 | University Of Maryland, College Park | Biomimetic mechanism for micro aircraft |
US6978969B1 (en) * | 2003-03-05 | 2005-12-27 | Neal Larry R | Fly-drive vehicle |
US7108803B1 (en) * | 1998-08-17 | 2006-09-19 | Symrise Gmbh & Co. Kg | Gas odorization method |
US20070012818A1 (en) * | 2004-08-12 | 2007-01-18 | Seiko Epson Corporation | Miniature aircraft |
US20070017724A1 (en) * | 1998-09-17 | 2007-01-25 | Rajasingham Arjuna I | Easy ejector seat with skeletal crash safety beam |
US7178757B1 (en) * | 2004-02-10 | 2007-02-20 | Charlene Breese | Motorcycle rider autogyro |
US7188803B2 (en) * | 2003-10-24 | 2007-03-13 | Toyota Jidosha Kabushiki Kaisha | Vertical take-off and landing aircraft |
US20070158494A1 (en) * | 2004-01-08 | 2007-07-12 | Burrage Robert G | Tilt-rotor aircraft |
US7246769B2 (en) * | 2001-06-04 | 2007-07-24 | Urban Aeronautics, Ltd. | Vehicles particularly useful as VTOL vehicles |
US7273195B1 (en) * | 2005-09-15 | 2007-09-25 | Golliher Clayton R | Vertical lift craft |
USD561085S1 (en) * | 2006-08-03 | 2008-02-05 | Silverlit Toys Manufactory, Ltd. | Helicopter propeller |
USD561676S1 (en) * | 2006-01-19 | 2008-02-12 | Silverlit Toys Manufactory, Ltd. | Helicopter |
US20080067284A1 (en) * | 2004-10-12 | 2008-03-20 | Bakker Jan W D | Personal Land And Air Vehicle |
USD568947S1 (en) * | 2007-10-31 | 2008-05-13 | Silverlit Toys Manufactory, Ltd. | Helicopter |
US20080207079A1 (en) * | 2007-02-07 | 2008-08-28 | Spin Master Ltd. | Transformable toy vehicle |
USD576215S1 (en) * | 2007-10-31 | 2008-09-02 | Silverlit Toys Manufactory, Ltd. | Helicopter body |
USD579403S1 (en) * | 2006-01-19 | 2008-10-28 | Silverlit Toys Manufactory, Ltd. | Helicopter propeller rotor |
USD580344S1 (en) * | 2006-08-03 | 2008-11-11 | Silverlit Toys Manufactory, Ltd. | Helicopter rotors, blades and shafts |
USD580845S1 (en) * | 2006-01-19 | 2008-11-18 | Silverlit Toys Manufactory, Ltd. | Helicopter |
USD581856S1 (en) * | 2006-08-03 | 2008-12-02 | Silverlit Toys Manufactory Ltd. | Helicopter blade, shafts and fins |
USD582833S1 (en) * | 2007-10-31 | 2008-12-16 | Silverlit Toys Manufactory Ltd. | Rotors for helicopter |
USD583297S1 (en) * | 2007-10-31 | 2008-12-23 | Silverlit Toys Manufactory Ltd. | Helicopter rotors |
US20090008479A1 (en) * | 2007-04-10 | 2009-01-08 | Oxford Technologies | Aerosol can extension |
US20090047861A1 (en) * | 2006-01-19 | 2009-02-19 | Silverlit Toys Manufactory Ltd. | Remote controlled toy helicopter |
US20090047862A1 (en) * | 2006-01-19 | 2009-02-19 | Silverlit Toys Manufactory, Ltd. | Flying object with tandem rotors |
US20090104836A1 (en) * | 2006-01-19 | 2009-04-23 | Silverlit Toys Manufactory, Ltd. | Remote controlled toy helicopter |
US20090117812A1 (en) * | 2006-01-19 | 2009-05-07 | Silverlit Toys Manufactory, Ltd. | Flying object with tandem rotors |
Family Cites Families (186)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2384516A (en) | 1945-09-11 | Aircraft | ||
US1403909A (en) * | 1920-06-26 | 1922-01-17 | Moir George Evenly | Flying machine |
US1446522A (en) * | 1921-03-05 | 1923-02-27 | Ansley Aerial Company | Aeroplane |
US1557789A (en) * | 1923-04-30 | 1925-10-20 | Thurman H Bane | Helicopter airplane |
GB255936A (en) | 1925-04-28 | 1926-07-28 | Harold Frederick Pitcairn | Improvements relating to aircraft |
US1800470A (en) * | 1926-06-18 | 1931-04-14 | Oehmichen Etienne | Sustaining device with regulators |
GB272871A (en) | 1926-06-18 | 1928-07-19 | Etienne Oehmichen | Sustaining device with regulator |
GB281721A (en) | 1926-12-03 | 1928-08-02 | Nicolas Florine | An improved helicopter |
US1793368A (en) * | 1929-04-26 | 1931-02-17 | Johnson Helicopter Toy Aeropla | Toy helicopter aeroplane |
US1773281A (en) | 1929-05-06 | 1930-08-19 | Rossiter S Scott | Aircraft |
US2030578A (en) * | 1933-07-24 | 1936-02-11 | Flettner Anton | Aircraft |
US2275094A (en) * | 1940-04-30 | 1942-03-03 | Paul K Guillow | Toy biplane |
US2307381A (en) * | 1940-07-12 | 1943-01-05 | Gustavus A Bess | Helicopter propeller |
US2368698A (en) * | 1943-03-10 | 1945-02-06 | Bell Aircraft Corp | Helicopter aircraft |
US2429502A (en) | 1943-08-21 | 1947-10-21 | Arthur M Young | Captive helicopter-kite means |
US2532683A (en) | 1943-11-15 | 1950-12-05 | Harry G Traver | Helicopter having adjustable rotors and stabilizing fins |
US2439143A (en) * | 1944-03-07 | 1948-04-06 | Nemeth Stephan Paul | Toy helicopter |
US2413831A (en) * | 1945-03-15 | 1947-01-07 | Arthur M Jordan | Amusement device |
US2411596A (en) | 1945-06-11 | 1946-11-26 | Plastie Parts Dev Corp | Toy |
US2629570A (en) * | 1945-08-09 | 1953-02-24 | Orson A Carnahan | Helicopter-airplane |
US2486059A (en) | 1945-10-09 | 1949-10-25 | Horace T Pentecost | Control mechanism for helicopters with coaxial rotors |
US2629568A (en) * | 1946-08-10 | 1953-02-24 | Douglas Aircraft Co Inc | Tandem rotor helicopter |
US2469144A (en) * | 1946-11-13 | 1949-05-03 | Ideal Novelty & Toy Co | Toy airplane |
US2646848A (en) | 1947-02-18 | 1953-07-28 | Bell Aircraft Corp | Automatic helicopter rotor stabilizer |
US2481750A (en) | 1947-06-03 | 1949-09-13 | United Helicopters Inc | Helicopter |
US2599957A (en) * | 1947-10-24 | 1952-06-10 | Neville E Walker | Miniature airplane with balancing weight |
US2633924A (en) * | 1948-02-26 | 1953-04-07 | Bell Aircraft Corp | Helicopter aircraft control |
US2720928A (en) | 1950-06-30 | 1955-10-18 | Warto Aristides | Aircraft propeller |
US2708081A (en) * | 1950-09-11 | 1955-05-10 | Black John Oliver | Convertible aircraft structure |
FR1040719A (en) | 1951-04-19 | 1953-10-19 | Constructions Aeronautiques Sudest | Flight control for rotary wing aircrafts |
US2750131A (en) | 1951-06-11 | 1956-06-12 | Alan C Thomson | Steering control for helicopter |
US2822994A (en) * | 1953-08-27 | 1958-02-11 | Warto Aristides | Aircraft with pivotally mounted fuselage |
US2725494A (en) | 1954-09-30 | 1955-11-29 | Gen Electric | Oscillation-suppressed tachometer indicator |
US2950074A (en) | 1956-10-15 | 1960-08-23 | Apostolescu Stefan | Helicopter |
DE1270408B (en) | 1958-09-30 | 1968-06-12 | Bell Helicopter Corp | Damping device for the rotor of a helicopter with a semi-rigid blade connection |
US3029048A (en) * | 1959-09-28 | 1962-04-10 | Brooks Earnest | Helicopter |
US3031017A (en) | 1959-09-30 | 1962-04-24 | United Aircraft Corp | Cyclic pitch control |
US3080001A (en) * | 1959-10-07 | 1963-03-05 | Lockheed Aircraft Corp | Helicopter |
US3035643A (en) | 1959-10-13 | 1962-05-22 | Bell Aerospace Corp | Device to alter dynamic characteristics of rotor systems |
FR1265789A (en) | 1960-08-24 | 1961-06-30 | Hiller Aircraft Corp | Device for controlling the boundary layer of an aerodynamic surface, in particular of a helicopter blade |
US3093929A (en) | 1961-01-16 | 1963-06-18 | Robbins Saul | Toy helicopters |
GB958536A (en) | 1961-10-12 | 1964-05-21 | Kenneth Horatio Wallis | Improvements in or relating to rotary winged aircraft |
US3106964A (en) | 1962-01-22 | 1963-10-15 | Lockheed Aircraft Corp | Helicopter rotor |
GB956536A (en) * | 1962-10-01 | 1964-04-29 | Lockheed Aircraft Corp | Helicopter |
US3213944A (en) | 1962-11-05 | 1965-10-26 | Nichols Charles Ross | Stabilizing means for helicopters |
US3180424A (en) * | 1963-03-25 | 1965-04-27 | Constantine A Serrindes | Propeller structure |
US3228478A (en) * | 1964-04-29 | 1966-01-11 | Bell Aerospace Corp | Control lag compensator for rotary wing aircraft |
US3231222A (en) * | 1964-05-20 | 1966-01-25 | Scheutzow Helicopter Corp | Rotary wing aircraft |
DE1267096B (en) | 1964-05-22 | 1968-04-25 | Boelkow Gmbh | Device for the longitudinal stabilization of rotary wing aircraft in high-speed flight |
GB1116164A (en) | 1965-05-17 | 1968-06-06 | Joseph Wagner | Control system for helicopters |
US3409249A (en) | 1966-06-29 | 1968-11-05 | United Aircraft Corp | Coaxial rigid rotor helicopter and method of flying same |
CA1017729A (en) * | 1968-09-12 | 1977-09-20 | Evan A. Fradenburgh | Mechanism for synchronously varying diameter of a plurality of rotors and for limiting the diameters thereof |
US3592559A (en) | 1969-08-28 | 1971-07-13 | Nasa | Variable geometry rotor system |
US3572616A (en) * | 1969-09-18 | 1971-03-30 | United Aircraft Corp | Pitch control mechanism for bladed rotor |
US3625631A (en) | 1969-11-03 | 1971-12-07 | Bell Aerospace Corp | Rotor hub and blade folding system |
DE1963931A1 (en) | 1969-12-20 | 1971-07-15 | Dornier Ag | Combination aircraft |
DE2409227A1 (en) | 1974-02-27 | 1975-09-04 | Schlueter Dieter | Driving rotor for remote control helicopter - has coupled adjustable auxiliary and main rotor blades under swash plate control |
US3933324A (en) * | 1974-08-02 | 1976-01-20 | Stanislaw Ostrowski | Helicopter with opposite rotating torque cancelling horizontal propeller |
GB1533251A (en) | 1976-04-14 | 1978-11-22 | Payne J | Electrically powered toys |
US4053123A (en) | 1976-04-16 | 1977-10-11 | Chadwick-Helmuth Company, Inc. | Method and apparatus to determine need for rotor blade pitch adjustment and/or blade substitution |
US4025230A (en) | 1976-05-13 | 1977-05-24 | Lockheed Aircraft Corporation | Advanced control system for a rotor and/or a compound or rotary wing vehicle |
US4073086A (en) * | 1976-06-09 | 1978-02-14 | Takara Co., Ltd. | Vehicle toy |
US4099687A (en) * | 1976-07-22 | 1978-07-11 | Roberts Lawrence T | All-axis control of aircraft in deep stall |
US4118143A (en) | 1977-03-29 | 1978-10-03 | Franz Kavan | Stabilizing and control device for two-bladed helicopter rotors |
USD253003S (en) | 1977-06-09 | 1979-09-25 | Toytown Corporation | Toy helicopter |
US4195439A (en) * | 1978-04-13 | 1980-04-01 | Kramer Dale C | Toy flying object |
US4227856A (en) | 1978-07-12 | 1980-10-14 | The United States Of Ameria As Represented By The Secretary Of The Navy | Reverse velocity rotor system for rotorcraft |
US4307533A (en) | 1979-02-09 | 1981-12-29 | California R & D Center | Insect simulating mobile toy having flappable wings |
ES8102955A1 (en) | 1980-04-18 | 1981-02-16 | Campos Herruzo Juan | Rotor blade pitch control for helicopter with coaxial rotors. |
US4519746A (en) | 1981-07-24 | 1985-05-28 | United Technologies Corporation | Airfoil blade |
US4522563A (en) | 1982-07-06 | 1985-06-11 | Bell Helicopter Textron, Inc. | Elastomeric system for mounting a helicopter rotor |
GB2160612B (en) * | 1984-06-21 | 1987-12-02 | Jaguar Cars | A mechanism for transmitting rotational motion from one shaft to another |
US4629440A (en) | 1985-07-08 | 1986-12-16 | Mattel, Inc. | Animated toy |
USD294605S (en) * | 1985-10-24 | 1988-03-08 | Takara Co., Ltd. | Reconfigurable toy helicopter |
US4660802A (en) * | 1985-11-08 | 1987-04-28 | Rao Medical Devices, Inc. | Liquid flow control device |
GB8615109D0 (en) | 1986-06-20 | 1986-07-23 | Westland Plc | Helicopter rotor |
US5151014A (en) | 1989-06-30 | 1992-09-29 | Airflow Research And Manufacturing Corporation | Lightweight airfoil |
DE3929886A1 (en) * | 1989-09-08 | 1991-03-28 | Dornier Conrado | AIRPLANE WITH ENGINE GONDOLAS TILTABLE ABOVE A CROSS AXLE |
US5015187A (en) | 1990-02-28 | 1991-05-14 | Byron Hatfield | Helicopter remote control system |
DE4017402A1 (en) * | 1990-05-30 | 1991-12-05 | Dieter Schlueter | Blades of helicopter rotor - are stabilised by stabilising rods connected to swash plate |
US5255871A (en) | 1990-11-29 | 1993-10-26 | Minoru Ikeda | Helicopter having rotors equipped with flaps |
US5108043A (en) * | 1991-03-29 | 1992-04-28 | Bell Helicopter Textron, Inc. | Twin engine helicopter accesssory drive |
US5209429A (en) | 1991-05-16 | 1993-05-11 | United Technologies Corporation | Helicopter with retractable rotor for transport |
JP2998943B2 (en) | 1991-05-31 | 2000-01-17 | 株式会社キーエンス | Propeller rotating surface tilting device for toys using propeller |
US5141176A (en) * | 1991-06-12 | 1992-08-25 | Grumman Aerospace Corporation | Tilt wing VTOL aircraft |
US5240204A (en) | 1991-07-19 | 1993-08-31 | Kunz Bernard P | Lift generating method and apparatus for aircraft |
US5609312A (en) | 1991-09-30 | 1997-03-11 | Arlton; Paul E. | Model helicopter |
US5628620A (en) | 1991-09-30 | 1997-05-13 | Arlton; Paul E. | Main rotor system for helicopters |
FR2689854B1 (en) * | 1992-04-14 | 1994-07-01 | Eurocopter France | MONOROTOR HELICOPTER WITH MIXED ANTI-TORQUE SYSTEM AND METHOD FOR COUNTING THE TORQUE INDUCED BY THIS MONOROTOR. |
ES2074010B1 (en) | 1993-07-14 | 1998-05-16 | Univ Pais Vasco | AERODYNAMIC PROFILES OF SIMPLE GEOMETRY |
US5395275A (en) * | 1993-08-09 | 1995-03-07 | Johnson; Lonnie | Toy airplane and launcher |
USD357894S (en) | 1993-09-20 | 1995-05-02 | Bell Helicopter Textron Inc. | Helicopter |
US5370341A (en) | 1994-04-05 | 1994-12-06 | Leon; Ross | Ultralight helicopter and control system |
US5879131A (en) * | 1994-04-25 | 1999-03-09 | Arlton; Paul E. | Main rotor system for model helicopters |
DE9414652U1 (en) * | 1994-09-09 | 1994-11-03 | Schlueter Dieter | Rotor head for a helicopter, in particular a remote-controlled model helicopter |
ES2141982T3 (en) | 1995-02-15 | 2000-04-01 | Bruno Ziegler | GIRAVION WITH GYROSCOPIC STABILIZATION OF THE ROTOR. |
US5511947A (en) * | 1995-02-17 | 1996-04-30 | The Boeing Company | Cyclic pitch control having torsion spring system |
USD378606S (en) * | 1995-09-08 | 1997-03-25 | Zamperla, Inc. | Helicopter ride |
USD372741S (en) | 1995-09-26 | 1996-08-13 | Tsai Wen H | Toy helicopter |
USD388048S (en) | 1996-05-13 | 1997-12-23 | Bell Helicopter Textron Inc. | Helicopter |
US5749540A (en) | 1996-07-26 | 1998-05-12 | Arlton; Paul E. | System for controlling and automatically stabilizing the rotational motion of a rotary wing aircraft |
FR2755941B1 (en) | 1996-11-19 | 1999-01-15 | Eurocopter France | ARROW BLADE AT ARROW FOR AIRCRAFT TURNING WING |
FR2765550B1 (en) * | 1997-07-07 | 1999-10-01 | Eurocopter France | DEVICE FOR PITCHING THE BLADES OF A MAIN ROTOR OF A GIRAVION |
USD390942S (en) * | 1997-07-16 | 1998-02-17 | American Auto Accessories, Inc. | Helicopter air freshener container |
US6659721B1 (en) | 1998-04-07 | 2003-12-09 | University Of Central Florida | High efficiency ceiling fan blades |
US6039541A (en) * | 1998-04-07 | 2000-03-21 | University Of Central Florida | High efficiency ceiling fan |
US6884034B1 (en) * | 1998-04-07 | 2005-04-26 | University Of Central Florida | Enhancements to high efficiency ceiling fan |
USD425853S (en) | 1998-04-17 | 2000-05-30 | Finmeccanica S.P.A. | Helicopter |
ES2172362B1 (en) | 1999-04-06 | 2003-12-01 | Saiz Manuel Munoz | PERFECTED AERODYNAMIC PROFILE. |
US7400348B2 (en) * | 1998-05-15 | 2008-07-15 | Hoyos Carlos A | Remote controlled imaging system |
US6030177A (en) * | 1998-12-18 | 2000-02-29 | Sikorsky Aircraft Corporation | Drive system for a variable diameter tilt rotor |
US6302652B1 (en) | 1998-12-24 | 2001-10-16 | General Dynamics Government Systems Corporation | Elliptical propeller and windmill blade assembly |
JP3053620B1 (en) | 1999-02-25 | 2000-06-19 | 株式会社コミュータヘリコプタ先進技術研究所 | Rotary blade flap drive |
JP4180726B2 (en) | 1999-03-29 | 2008-11-12 | 勝彦 荒木 | helicopter |
USD421279S (en) * | 1999-04-12 | 2000-02-29 | Wen-Ho Tsai | Toy helicopter |
US6543726B2 (en) * | 1999-05-21 | 2003-04-08 | Vortex Holding Company | Fluid flow straightening techniques |
IT1308096B1 (en) * | 1999-06-02 | 2001-11-29 | Finmeccanica Spa | TILTROTOR |
US6467726B1 (en) | 1999-06-29 | 2002-10-22 | Rokuro Hosoda | Aircraft and torque transmission |
CA2316418A1 (en) | 1999-08-20 | 2001-02-20 | Cartercopters, L.L.C. | High speed rotor aircraft |
JP2003515041A (en) * | 1999-11-25 | 2003-04-22 | ジェイデン デービッド ハーマン | Single-wing or multi-wing rotor |
US6632119B2 (en) | 2000-03-01 | 2003-10-14 | Marvel Enterprises, Inc. | Winding device and ornithopter utilizing same |
US6460802B1 (en) | 2000-09-13 | 2002-10-08 | Airscooter Corporation | Helicopter propulsion and control system |
WO2002064426A1 (en) | 2001-02-14 | 2002-08-22 | Airscooter Corporation | Ultralight coaxial rotor aircraft |
US6886777B2 (en) | 2001-02-14 | 2005-05-03 | Airscooter Corporation | Coaxial helicopter |
US6616095B2 (en) | 2001-02-16 | 2003-09-09 | Bell Helicopter Textron Inc. | Coupled aircraft rotor system |
US6688936B2 (en) * | 2001-03-28 | 2004-02-10 | Steven Davis | Rotating toy with directional vector control |
US7497759B1 (en) * | 2001-03-28 | 2009-03-03 | Steven Davis | Directionally controllable, self-stabilizing, rotating flying vehicle |
US7255623B2 (en) | 2001-03-28 | 2007-08-14 | Steven Davis | Self-stabilizing rotating toy |
AU2002329966A1 (en) | 2001-09-04 | 2003-03-18 | Paul E. Arlton | Rotor system for helicopters |
JP2003103066A (en) | 2001-09-28 | 2003-04-08 | Kyosho Corp | Rotor pitch control mechanism of model helicopter |
USD467861S1 (en) | 2001-11-06 | 2002-12-31 | General Helicopter, Inc. | Helicopter |
US6758436B2 (en) | 2001-11-07 | 2004-07-06 | Rehco, Llc | Pneumatic driven propeller related vehicles |
US6659395B2 (en) | 2001-11-07 | 2003-12-09 | Rehco, Llc | Propellers and propeller related vehicles |
GB2383273B (en) | 2001-12-17 | 2004-06-02 | Wen-Long Wu | Toy |
JP3973433B2 (en) | 2002-01-31 | 2007-09-12 | 富士重工業株式会社 | Composite rotorcraft |
BE1014724A6 (en) | 2002-03-25 | 2004-03-02 | Rostyne Alexander Van De | Device for the operation of a helicopter. |
AUPS330502A0 (en) | 2002-06-28 | 2002-07-25 | Kusic, Tom | Tandem powered power tilting aircraft - june 2002 |
US6749401B2 (en) | 2002-07-22 | 2004-06-15 | Arthur Vanmoor | Hydrodynamically and aerodynamically optimized leading edge structure for propellers, wings, and airfoils |
US7097427B2 (en) | 2002-08-02 | 2006-08-29 | Bell Helicopter Textron Inc. | Helicopter main rotor blade balance weight retention assembly |
US6789764B2 (en) | 2002-09-24 | 2004-09-14 | The Boeing Company | Dual-flight mode tandem rotor wing |
JP3673253B2 (en) | 2002-10-06 | 2005-07-20 | ヒロボー株式会社 | Coaxial reversing radio control helicopter and blade tilt mechanism of radio control helicopter |
CN1254297C (en) | 2002-10-06 | 2006-05-03 | 飞龙宝株式会社 | Coaxile reverse rotating type radio controlled vertiplane |
US6755716B2 (en) | 2002-11-01 | 2004-06-29 | Mattel, Inc. | Projectile shooting toy |
DE10256916B4 (en) | 2002-11-28 | 2006-12-28 | Siegfried Pauli | helicopter |
US6719244B1 (en) * | 2003-02-03 | 2004-04-13 | Gary Robert Gress | VTOL aircraft control using opposed tilting of its dual propellers or fans |
USD496695S1 (en) | 2003-03-14 | 2004-09-28 | Steven Davis | Flying toy |
US20040184915A1 (en) | 2003-03-21 | 2004-09-23 | Makoto Kunii | Model helicopter rotor pitch control mechanism |
US6896221B1 (en) * | 2003-04-16 | 2005-05-24 | Einar Einarsson | Vertical takeoff and landing aircraft |
NO20032282A (en) * | 2003-05-20 | 2004-11-22 | Proxflyer As | Rotor that generates lifting and use of rotor |
US6960112B2 (en) | 2003-08-12 | 2005-11-01 | Mattel, Inc. | Airfoil blade with cushioned edge for powered toy aircraft |
US20050061909A1 (en) * | 2003-08-19 | 2005-03-24 | Winston Peter R. | Radio controlled helicopter |
DE20314041U1 (en) | 2003-09-10 | 2004-03-04 | Grüntjens, Norbert | Rotor head for model helicopter, has central piece formed by two mirror symmetrical parts |
JP2005152005A (en) | 2003-11-20 | 2005-06-16 | Taiyo Kogyo Kk | Radio control helicopter toy |
US7147182B1 (en) * | 2004-02-23 | 2006-12-12 | Kenneth Warren Flanigan | Gas-powered tip-jet-driven tilt-rotor compound VTOL aircraft |
JP2006051217A (en) | 2004-08-12 | 2006-02-23 | Seiko Epson Corp | Flying body |
US7946526B2 (en) | 2004-11-05 | 2011-05-24 | Nachman Zimet | Rotary-wing vehicle system |
JP2006158612A (en) | 2004-12-07 | 2006-06-22 | Taiyo Kogyo Kk | Flying toy |
FR2880866B1 (en) | 2005-01-14 | 2008-08-22 | De Salaberry Bernard Lucien Ch | ROTOR HEAD ORIENTATION DEVICE FOR HELICOPTER |
US7100866B2 (en) | 2005-01-14 | 2006-09-05 | Rehco, Llc | Control system for a flying vehicle |
US7789340B2 (en) * | 2005-02-04 | 2010-09-07 | Silverlit Limited | Propulsion system for model airplane |
JP3723820B2 (en) | 2005-03-22 | 2005-12-07 | ヒロボー株式会社 | Coaxial inversion radio control helicopter |
USD524229S1 (en) | 2005-05-30 | 2006-07-04 | Sirorsky Aircraft Corporation | Rigid coaxial rotor helicopter with auxiliary propulsion (small) |
USD524718S1 (en) | 2005-05-31 | 2006-07-11 | Sikorsky Aircraft Corporation | Rigid coaxial rotor helicopter with dual auxiliary propulsion |
USD524230S1 (en) | 2005-05-31 | 2006-07-04 | Sikorsky Aircraft Corporation | Rigid coaxial rotor helicopter with auxiliary propulsion (large) |
USD524227S1 (en) | 2005-05-31 | 2006-07-04 | Sikorsky Aircraft Corporation | Rigid coaxial rotor unmanned helicopter with auxiliary propulsion |
USD524228S1 (en) | 2005-05-31 | 2006-07-04 | Sikorsky Aircraft Corporation | Rigid coaxial rotor heavy lift helicopter |
US7861967B2 (en) * | 2008-04-25 | 2011-01-04 | Abe Karem | Aircraft with integrated lift and propulsion system |
US7802754B2 (en) * | 2005-08-15 | 2010-09-28 | Abe Karem | Tilt outboard wing for tilt rotor aircraft |
US20100120321A1 (en) * | 2005-09-30 | 2010-05-13 | Rehco Llc | Vertical take off plane |
US7264199B2 (en) | 2005-10-18 | 2007-09-04 | The Boeing Company | Unloaded lift offset rotor system for a helicopter |
JP4343167B2 (en) | 2005-11-10 | 2009-10-14 | 株式会社タイヨー | Radio controlled helicopter toy |
US20070215750A1 (en) | 2005-11-18 | 2007-09-20 | Michael Shantz | Radio controlled helicopter |
US7815482B2 (en) | 2006-01-19 | 2010-10-19 | Silverlit Toys Manufactory, Ltd. | Helicopter |
US7662013B2 (en) | 2006-01-19 | 2010-02-16 | Silverlit Toys Manufactory Ltd. | Helicopter with horizontal control |
USD544825S1 (en) | 2006-01-19 | 2007-06-19 | Silverlit Toys Manufactory, Ltd. | Helicopter propeller rotor |
USD554040S1 (en) | 2006-01-19 | 2007-10-30 | Silverlit Toys Manufactory, Ltd. | Helicopter propeller |
USD559764S1 (en) * | 2006-01-19 | 2008-01-15 | Silverlit Toys Manufactory, Ltd. | Helicopter |
USD552531S1 (en) | 2006-01-19 | 2007-10-09 | Silverlit Toys Manufactory, Ltd. | Helicopter propeller |
US20070178798A1 (en) | 2006-01-27 | 2007-08-02 | Aling Lai | Model helicopter |
US7854593B2 (en) | 2006-02-16 | 2010-12-21 | Sikorsky Aircraft Corporation | Airfoil for a helicopter rotor blade |
USD548803S1 (en) | 2006-04-27 | 2007-08-14 | Nachman Zimet | Helicopter |
US7674091B2 (en) | 2006-11-14 | 2010-03-09 | The Boeing Company | Rotor blade pitch control |
US7841829B2 (en) | 2006-11-15 | 2010-11-30 | Sikorsky Aircraft Corporation | Rotor system with pitch flap coupling |
DE202007000987U1 (en) | 2007-01-23 | 2007-04-12 | Dauschek Klaus | Rotary body arrangement for remote controlled model helicopter, has rotary shaft revolving around rotary shaft axis at which main rotor blades are engaged around main rotor blades axis |
US7997526B2 (en) * | 2007-03-12 | 2011-08-16 | Peter Greenley | Moveable wings on a flying/hovering vehicle |
US20090008497A1 (en) | 2007-07-05 | 2009-01-08 | Spin Master Ltd. | Rotary-wing miniature gyro helicopter |
-
2006
- 2006-01-19 BE BE2006/0043A patent/BE1016960A3/en not_active IP Right Cessation
- 2006-08-03 US US11/462,177 patent/US20070164148A1/en not_active Abandoned
-
2007
- 2007-01-15 CN CNU2007200018477U patent/CN201012292Y/en not_active Expired - Fee Related
- 2007-01-15 CN CNU2007200018481U patent/CN201012293Y/en not_active Expired - Fee Related
-
2008
- 2008-08-07 US US12/188,070 patent/US20080299867A1/en not_active Abandoned
- 2008-11-04 US US12/264,890 patent/US20090047862A1/en not_active Abandoned
-
2010
- 2010-01-29 US US12/696,183 patent/US8308522B2/en active Active
- 2010-12-06 EP EP10193761.3A patent/EP2351607B1/en not_active Not-in-force
Patent Citations (87)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US934771A (en) * | 1906-04-02 | 1909-09-21 | Wallace Rupert Turnbull | Aeroplane and hydroplane. |
US1470017A (en) * | 1919-02-04 | 1923-10-09 | Alfred J Cleary | Wing for flying machines |
US1446718A (en) * | 1921-08-25 | 1923-02-27 | Charles C Tankel | Vertical-rising aeroplane and aerofoil |
US1828783A (en) * | 1926-06-18 | 1931-10-27 | Oehmichen Etienne | Lifting device |
US1925156A (en) * | 1930-08-26 | 1933-09-05 | Sidney P Vaughn | Method of driving propellers and rotative wing systems |
US2110563A (en) * | 1934-06-25 | 1938-03-08 | Thaon Andre | Aircraft of the autogyro type |
US2272643A (en) * | 1941-01-11 | 1942-02-10 | Peters Harry | Toy convertible automobile-plane |
US2466821A (en) * | 1944-10-23 | 1949-04-12 | John M Owen | Helicopter |
US2487020A (en) * | 1945-02-12 | 1949-11-01 | Gilerease Leonard | Helicopter |
US2563731A (en) * | 1945-04-17 | 1951-08-07 | Wilbur L Masterson | Land, sea, and air plane |
US2554938A (en) * | 1946-07-01 | 1951-05-29 | Joseph D Catalano | Amphibian helicopter |
US2614637A (en) * | 1948-03-26 | 1952-10-21 | Landgraf Fred | Air screw with automatic pitch mechanism |
US2639874A (en) * | 1948-09-10 | 1953-05-26 | Edward A Stalker | Helicopter wings and other aircraft structures with boundary layer control |
US2514822A (en) * | 1949-08-19 | 1950-07-11 | Jr Frank H Wolfe | Helicopter automobile |
US2801494A (en) * | 1954-12-31 | 1957-08-06 | Ernst Max | Remotely controlled toy aircraft |
US2818123A (en) * | 1955-06-23 | 1957-12-31 | Hiller Helicopters | Rotary wing aircraft |
US2980187A (en) * | 1957-02-28 | 1961-04-18 | Rodrigo M Smyth-Davila | Helicopter |
US2923494A (en) * | 1958-03-26 | 1960-02-02 | Richard A Strong | Ground-air vehicle |
US2987848A (en) * | 1958-07-10 | 1961-06-13 | Neuhaus Gottfried | Toy aeroplane |
US3068611A (en) * | 1959-09-01 | 1962-12-18 | Harold R Shoemake | Toy aircraft |
US3135334A (en) * | 1960-12-05 | 1964-06-02 | Lockheed Aircraft Corp | Rotor |
US3116896A (en) * | 1961-04-05 | 1964-01-07 | Eltra Corp | Combination helicopter-automobile |
US3460628A (en) * | 1961-11-06 | 1969-08-12 | Bendix Corp | Laminated tension-torsion tie-bar |
US3321022A (en) * | 1963-10-25 | 1967-05-23 | Oguri Yoshiyuki | Rotary wing assembly |
US3370809A (en) * | 1965-06-29 | 1968-02-27 | United Aircraft Corp | Convertiplane |
US3371886A (en) * | 1966-01-14 | 1968-03-05 | Robert O. Schertz | Aircraft adapted for highway usage |
US3450374A (en) * | 1966-03-03 | 1969-06-17 | Moore Alvin E | Resiliently flexible vehicle |
US3391746A (en) * | 1967-05-15 | 1968-07-09 | Samuel Chayes | Helicopter control system |
US3554467A (en) * | 1968-02-19 | 1971-01-12 | Universal Helicar Co | Counterrotating rotor transmission for helicoptors |
US3662487A (en) * | 1968-10-12 | 1972-05-16 | Uwe C Seefluth | Balloon-type aircraft toy |
US3481559A (en) * | 1968-11-20 | 1969-12-02 | Steven Postelson Apostolescu | Helicopter-automobile-boat and air suspension car combination |
US3558081A (en) * | 1969-02-20 | 1971-01-26 | Airmarine Corp | Airborne vehicles |
US3759629A (en) * | 1969-05-12 | 1973-09-18 | J Abramopaulos | Combined land and air vehicle |
US4173321A (en) * | 1971-03-08 | 1979-11-06 | Karl Eickmann | Vehicle for traveling in the air and on the ground equipped with hydraulically driven propellers |
US3905565A (en) * | 1973-09-27 | 1975-09-16 | Herman Gopp Kolwey | Tilt axis dual rotor helicopter and control system |
US4084345A (en) * | 1977-06-24 | 1978-04-18 | Toytown Corporation | Toy helicopter |
USD287738S (en) * | 1985-02-06 | 1987-01-13 | Kenner Parker Toys Inc. | Toy helicopter |
US4759514A (en) * | 1986-09-30 | 1988-07-26 | The Boeing Company | Tail rotor yaw position control for a helicopter |
US4880355A (en) * | 1987-06-29 | 1989-11-14 | Aerospatiale Societe Nationale Industrielle | Blade with curved end for a rotary airfoil of an aircraft |
US4981456A (en) * | 1988-06-20 | 1991-01-01 | Yamaha Hatsudoki Kabushiki Kaisha | Remote controlled helicopter |
US4941803A (en) * | 1989-02-01 | 1990-07-17 | United Technologies Corporation | Airfoiled blade |
US5252100A (en) * | 1989-06-06 | 1993-10-12 | Wildgear Inc. | Variable rotor-blade-attack angle helicopter toy |
US5190242A (en) * | 1989-12-18 | 1993-03-02 | Nichols Edward H | Model jet helicopter with solid-circular rotor blade |
US5203520A (en) * | 1991-10-28 | 1993-04-20 | Jozef Przygodzki | Helicar |
US5304090A (en) * | 1993-01-19 | 1994-04-19 | Vanni Robert R | Toy helicopter having forwardly inclined rotor shaft |
US5505407A (en) * | 1993-09-09 | 1996-04-09 | Fran Rich Chi Associates | Air-land vehicle |
US5915649A (en) * | 1996-08-23 | 1999-06-29 | Mcdonnell Douglas Helicopter Company | Roadable helicopter |
US6086016A (en) * | 1997-01-21 | 2000-07-11 | Meek; Stanley Ronald | Gyro stabilized triple mode aircraft |
US5971320A (en) * | 1997-08-26 | 1999-10-26 | Jermyn; Phillip Matthew | Helicopter with a gyroscopic rotor and rotor propellers to provide vectored thrust |
US7108803B1 (en) * | 1998-08-17 | 2006-09-19 | Symrise Gmbh & Co. Kg | Gas odorization method |
US20070017724A1 (en) * | 1998-09-17 | 2007-01-25 | Rajasingham Arjuna I | Easy ejector seat with skeletal crash safety beam |
US20020049518A1 (en) * | 2000-10-23 | 2002-04-25 | Futaba Corporation | Sterring control device for radio-controlled model helicopter |
US6899586B2 (en) * | 2001-03-28 | 2005-05-31 | Steven Davis | Self-stabilizing rotating toy |
US7246769B2 (en) * | 2001-06-04 | 2007-07-24 | Urban Aeronautics, Ltd. | Vehicles particularly useful as VTOL vehicles |
US20050121552A1 (en) * | 2001-11-07 | 2005-06-09 | Jeffrey Rehkemper | Propellers and propeller related vehicles |
US6938853B2 (en) * | 2002-03-15 | 2005-09-06 | University Of Maryland, College Park | Biomimetic mechanism for micro aircraft |
US6978969B1 (en) * | 2003-03-05 | 2005-12-27 | Neal Larry R | Fly-drive vehicle |
US6745977B1 (en) * | 2003-08-21 | 2004-06-08 | Larry D. Long | Flying car |
US7188803B2 (en) * | 2003-10-24 | 2007-03-13 | Toyota Jidosha Kabushiki Kaisha | Vertical take-off and landing aircraft |
US20070158494A1 (en) * | 2004-01-08 | 2007-07-12 | Burrage Robert G | Tilt-rotor aircraft |
US7178757B1 (en) * | 2004-02-10 | 2007-02-20 | Charlene Breese | Motorcycle rider autogyro |
US20070012818A1 (en) * | 2004-08-12 | 2007-01-18 | Seiko Epson Corporation | Miniature aircraft |
US20080067284A1 (en) * | 2004-10-12 | 2008-03-20 | Bakker Jan W D | Personal Land And Air Vehicle |
US7273195B1 (en) * | 2005-09-15 | 2007-09-25 | Golliher Clayton R | Vertical lift craft |
USD561677S1 (en) * | 2006-01-19 | 2008-02-12 | Silverlit Toys Manufactory, Ltd. | Helicopter |
US20090047861A1 (en) * | 2006-01-19 | 2009-02-19 | Silverlit Toys Manufactory Ltd. | Remote controlled toy helicopter |
USD561678S1 (en) * | 2006-01-19 | 2008-02-12 | Silverlit Toys Manufactory, Ltd. | Helicopter |
USD585810S1 (en) * | 2006-01-19 | 2009-02-03 | Silverlit Toys Manufactory Ltd. | Helicopter propeller |
US20090163110A1 (en) * | 2006-01-19 | 2009-06-25 | Silverlit Toys Manufactory Ltd. | Remote controlled toy helicopter |
USD561676S1 (en) * | 2006-01-19 | 2008-02-12 | Silverlit Toys Manufactory, Ltd. | Helicopter |
US20090117812A1 (en) * | 2006-01-19 | 2009-05-07 | Silverlit Toys Manufactory, Ltd. | Flying object with tandem rotors |
USD579403S1 (en) * | 2006-01-19 | 2008-10-28 | Silverlit Toys Manufactory, Ltd. | Helicopter propeller rotor |
USD580343S1 (en) * | 2006-01-19 | 2008-11-11 | Silverlit Toys Manufactory, Ltd. | Helicopter blades, tail and fins |
US20090047862A1 (en) * | 2006-01-19 | 2009-02-19 | Silverlit Toys Manufactory, Ltd. | Flying object with tandem rotors |
USD580845S1 (en) * | 2006-01-19 | 2008-11-18 | Silverlit Toys Manufactory, Ltd. | Helicopter |
USD581341S1 (en) * | 2006-01-19 | 2008-11-25 | Silverlit Toys Manufactory, Ltd. | Helicopter rotor, frame and fins |
US20090104836A1 (en) * | 2006-01-19 | 2009-04-23 | Silverlit Toys Manufactory, Ltd. | Remote controlled toy helicopter |
USD582336S1 (en) * | 2006-08-03 | 2008-12-09 | Silverlit Toys Manufactory Ltd. | Helicopter blade, shafts and fins |
USD581856S1 (en) * | 2006-08-03 | 2008-12-02 | Silverlit Toys Manufactory Ltd. | Helicopter blade, shafts and fins |
USD580344S1 (en) * | 2006-08-03 | 2008-11-11 | Silverlit Toys Manufactory, Ltd. | Helicopter rotors, blades and shafts |
USD561085S1 (en) * | 2006-08-03 | 2008-02-05 | Silverlit Toys Manufactory, Ltd. | Helicopter propeller |
US20080207079A1 (en) * | 2007-02-07 | 2008-08-28 | Spin Master Ltd. | Transformable toy vehicle |
US20090008479A1 (en) * | 2007-04-10 | 2009-01-08 | Oxford Technologies | Aerosol can extension |
USD583297S1 (en) * | 2007-10-31 | 2008-12-23 | Silverlit Toys Manufactory Ltd. | Helicopter rotors |
USD582833S1 (en) * | 2007-10-31 | 2008-12-16 | Silverlit Toys Manufactory Ltd. | Rotors for helicopter |
USD576215S1 (en) * | 2007-10-31 | 2008-09-02 | Silverlit Toys Manufactory, Ltd. | Helicopter body |
USD568947S1 (en) * | 2007-10-31 | 2008-05-13 | Silverlit Toys Manufactory, Ltd. | Helicopter |
Cited By (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8002604B2 (en) | 2006-01-19 | 2011-08-23 | Silverlit Limited | Remote controlled toy helicopter |
US20090047862A1 (en) * | 2006-01-19 | 2009-02-19 | Silverlit Toys Manufactory, Ltd. | Flying object with tandem rotors |
US8308522B2 (en) | 2006-01-19 | 2012-11-13 | Silverlit Limited | Flying toy |
US7662013B2 (en) | 2006-01-19 | 2010-02-16 | Silverlit Toys Manufactory Ltd. | Helicopter with horizontal control |
US7815482B2 (en) | 2006-01-19 | 2010-10-19 | Silverlit Toys Manufactory, Ltd. | Helicopter |
US8357023B2 (en) | 2006-01-19 | 2013-01-22 | Silverlit Limited | Helicopter |
US20090163110A1 (en) * | 2006-01-19 | 2009-06-25 | Silverlit Toys Manufactory Ltd. | Remote controlled toy helicopter |
US20100003886A1 (en) * | 2008-07-02 | 2010-01-07 | Bob Cheng | Model helicopter |
US8702466B2 (en) | 2008-07-02 | 2014-04-22 | Asian Express Holdings Limited | Model helicopter |
US7883392B2 (en) | 2008-08-04 | 2011-02-08 | Silverlit Toys Manufactory Ltd. | Toy helicopter |
US8123176B2 (en) | 2009-12-24 | 2012-02-28 | Spin Master Ltd. | Velocity feedback control system for a rotor of a toy helicopter |
US8123175B2 (en) | 2009-12-24 | 2012-02-28 | Spin Master Ltd. | Velocity feedback control system for a rotor of a toy helicopter |
US10377478B2 (en) * | 2015-01-21 | 2019-08-13 | FLIR Unmanned Aerial Systems AS | Thrust-generating rotor assembly |
USD985678S1 (en) * | 2020-09-08 | 2023-05-09 | Silverlit Limited | Propulsion unit for a toy plane |
Also Published As
Publication number | Publication date |
---|---|
EP2351607B1 (en) | 2015-01-28 |
BE1016960A3 (en) | 2007-11-06 |
US20100124865A1 (en) | 2010-05-20 |
CN201012293Y (en) | 2008-01-30 |
EP2351607A2 (en) | 2011-08-03 |
US8308522B2 (en) | 2012-11-13 |
US20070164148A1 (en) | 2007-07-19 |
US20090047862A1 (en) | 2009-02-19 |
EP2351607A3 (en) | 2014-01-15 |
CN201012292Y (en) | 2008-01-30 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: SILVERLIT TOYS MANUFACTORY, LTD., HONG KONG Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:VAN DE ROSTYNE, ALEXANDER JOZEF MAGDALENA;CHOI, KEI FUNG;REEL/FRAME:021359/0215;SIGNING DATES FROM 20070414 TO 20070416 |
|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |