JP2014058195A - Position light of rotorcraft - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a position light of a rotorcraft by which whether or not a rotorcraft is coming closer or moving away can be accurately identified.SOLUTION: A position light 10 of a helicopter has: a first induction coil 11A and a second induction coil 11B which are provided integrally rotatable to a rotary shaft 6 of a main rotor 3; a first magnet 12A which is positioned so as to be close to the first induction coil 11A when a blade tip 7 of the main rotor 3 is positioned at a first position and a second magnet 12B which is positioned so as to be close to the second induction coil 11B when the blade tip 7 of the main rotor 3 is positioned at a second position on the opposite side of the first position with the rotary shaft 6 therebetween; and a first light-emitting element 13A which emits red light by induced electromotive force in the first induction coil 11A and a second light-emitting element 13B which emits green light by induced electromotive force in the second induction coil 11B.

Description

  The present invention relates to a wing tip lamp of a rotary wing aircraft.

  A fixed-wing aircraft such as an aircraft is provided with a wing tip lamp for easily identifying the attitude and position of the fuselage. In the case of an aircraft, the tip of the main wing is illuminated with a different color to identify whether the aircraft is approaching or moving away during night flight. For example, in a pair of main wings of an aircraft, it has been conventionally performed to light the left tip in red and the right tip in green (see Patent Document 1 below). In this case, if a third party outside the aircraft confirms that the left side is green and the right side is lit red, it is determined that the aircraft is approaching, and conversely, the left side is red and the right side Can be determined that the aircraft is moving away when it is confirmed that each is lit in green.

Special table 2003-516273 gazette

  However, in the case of a rotary wing aircraft such as a helicopter, the main wing, that is, the tip of an aircraft is not provided with a shape in which the tips are relatively separated from each other. It is difficult to identify whether it is going away. In other words, since the shape of the helicopter when viewed from the front or the rear has no width, even if the left and right are emitted with different colors, the distance between the light emission of each color when viewed from the front or the rear is short. There is a need for a rotary wing tip light that is difficult to identify colors and therefore can accurately identify whether a helicopter is approaching or moving away.

  The present invention has been made in view of the above problems, and an object of the present invention is to provide a blade lamp for a rotorcraft that can accurately identify whether the rotorcraft is approaching or moving away. And

In order to solve the above-described problem, the present invention provides a first induction coil and a second induction coil that are provided so as to be integrally rotatable with respect to a rotation shaft of a rotary blade, and the blade tip of the rotary blade is a first blade. The first magnet disposed so as to be close to the first induction coil when located at the position of the first blade and the blade tip of the rotor blade are on the second side opposite to the first position across the rotating shaft. And a second magnet arranged so as to be close to the second induction coil when positioned at the position of the rotor, and light emitted by the induced electromotive force in the first induction coil provided at the tip of the rotor blade A first light emitting element and a second light emitting element that is provided at a blade tip of the rotor blade and emits light having a color tone different from that of the light of the first light emitting element by an induced electromotive force in the second induction coil; Adopting a wing tip lamp of a rotary wing aircraft.
By adopting such a configuration, in the present invention, when the blade tip of the rotor blade passes through the first position, the induction induction generated by the first induction coil crossing the magnetic flux of the first magnet. When the first light-emitting element provided at the blade tip emits light by electric power and the blade tip of the rotor blade passes through the second position opposite to the first position, the magnetic flux of the second magnet is The second light emitting element provided at the tip of the wing emits light with a different color tone by the induced electromotive force generated when the two induction coils cross. For this reason, the lighting section of the first light-emitting element and the second light-emitting element is limited, and it is possible to switch the color development at the blade tip on the left and right with the rotating shaft of the rotor blade interposed therebetween.

Further, in the present invention, there is provided a configuration in which at least one of the first light emitting element and the second light emitting element has a blinking circuit that blinks at a cycle longer than the rotation cycle of the blade tip of the rotor blade. adopt.
By adopting such a configuration, in the present invention, at least one of the first light emitting element and the second light emitting element emits light with a cycle longer than the rotation cycle of the blade tip of the rotor blade by the blinking circuit. The flashing effect of light emission at the blade tip can be obtained on the left and right sides of the rotating shaft of the rotor blade. In other words, at a general rotating blade rotation speed, it seems to emit light continuously due to the human visual integration effect, so by providing a flashing circuit to flash the light at the tip of the rotating blade, Light emission at the blade tip can be more easily identified.

Further, in the present invention, the third induction coil provided so as to be integrally rotatable with respect to the rotating shaft of the rotor blade, and the third induction coil when the blade tip of the rotor blade is in a third position in front of the nose. A third magnet disposed so as to be close to the induction coil, and a third light emitting element that is provided at a tip of the rotor blade and emits light by an induced electromotive force in the third induction coil, The configuration is adopted.
By adopting such a configuration, in the present invention, when the blade tip of the rotor blade passes through the third position, the induction induction generated by the third induction coil crossing the magnetic flux of the third magnet. The third light emitting element provided at the blade tip emits light by electric power. The third position is in front of the nose, and it becomes easier for the pilot to visually recognize the tip position of the blade tip of the rotor blade when maneuvering the rotorcraft. Therefore, for example, when there is an obstacle in front of the nose, the pilot can easily determine how close the rotorcraft can be to the obstacle.

  According to the present invention, it is possible to obtain a tip lamp of a rotary wing machine that can accurately identify whether the rotary wing machine is approaching or moving away.

It is a front view of the helicopter in a 1st embodiment of the present invention. It is a block diagram of the wing-tip lamp in 1st Embodiment of this invention. It is a top view which shows the lighting area of the wing tip lamp in 1st Embodiment of this invention. It is a block diagram of the wing-tip lamp in 2nd Embodiment of this invention. It is a top view which shows the lighting area of the wing-tip lamp in 3rd Embodiment of this invention.

  Next, embodiments of the present invention will be described with reference to the drawings. In the following description, a single rotor type helicopter is illustrated as a rotary wing aircraft.

(First embodiment)
FIG. 1 is a front view of a helicopter 1 according to the first embodiment of the present invention. FIG. 2 is a configuration diagram of the wing tip lamp 10 in the first embodiment of the present invention. FIG. 3 is a plan view showing a lighting section of the wing tip lamp 10 in the first embodiment of the present invention. In FIG. 3, a dot pattern is attached to the lighting section of the wing tip lamp 10.
In FIG. 1, reference numeral 2 indicates an airframe, and reference numeral 3 indicates a main rotor (rotary blade). Moreover, the code | symbol 4 shown in FIG. 3 has shown the tail rotor.

  As shown in FIG. 1, the main rotor 3 is provided with a wing tip lamp (a wing tip lamp of a rotary wing machine) 10. The blade tip lamp 10 of the present embodiment is provided on each of the plurality of blades 5 of the main rotor 3. In the present embodiment, the main rotor 3 has two blades 5 and two wing tip lamps 10 are provided correspondingly. However, the wing tip lamp 10 includes at least one of the plurality of blades 5. It suffices if one is provided.

  As shown in FIG. 2, the wing tip lamp 10 includes a first induction coil 11A and a second induction coil 11B. The first induction coil 11 </ b> A and the second induction coil 11 </ b> B are provided so as to be integrally rotatable with respect to the rotary shaft 6 provided at the center of the main rotor 3. The first induction coil 11 </ b> A is integrally fixed to the upper portion of the rotating shaft 6, and the second induction coil 11 </ b> B is integrally fixed to the lower portion of the rotating shaft 6. As described above, in the present embodiment, the first induction coil 11 </ b> A and the second induction coil 11 </ b> B are provided so as to be shifted by two stages in the axial direction of the rotating shaft 6.

  The wing tip lamp 10 includes a first magnet 12A and a second magnet 12B. The first magnet 12A and the second magnet 12B of the present embodiment are composed of permanent magnets, electromagnets, or the like. The first magnet 12A is arranged so as to be close to the first induction coil 11A when the blade tip 7 of the main rotor 3 is located at the first position. Here, the first position refers to a position where the wing tip 7 is located on the left side of the fuselage 2 in the plan view shown in FIG.

  On the other hand, the second magnet 12B comes close to the second induction coil 11B when the blade tip 7 of the main rotor 3 is located at the second position opposite to the first position across the rotation shaft 6. Is arranged. That is, the second position refers to a position where the wing tip 7 is located on the right side of the fuselage 2 in the plan view shown in FIG. The first magnet 12 </ b> A and the second magnet 12 </ b> B have a positional relationship facing each other across the rotation shaft 6 in the left-right direction orthogonal to the traveling direction of the machine body 2.

  The first magnet 12A and the second magnet 12B are fixed to the body 2 side so that the first induction coil 11A and the second induction coil 11B fixed to the rotating shaft 6 side rotate relatively. It has become. As shown in FIG. 2, the first magnet 12A is provided at a height corresponding to the rotation trajectory of the first induction coil 11A. On the other hand, the second magnet 12B is provided at a height corresponding to the rotation orbit of the second induction coil 11B. The first magnet 12A and the second magnet 12B are induction coils other than the corresponding induction coil. Specifically, the first magnet 12A is the second induction coil 11B, and the second magnet 12B is the first. The induction coil 11A is arranged so as not to affect the magnetic flux.

  The wing tip lamp 10 includes a first light emitting element 13A and a second light emitting element 13B. The first light emitting element 13A is provided at the blade tip 7 of the main rotor 3, and a circuit is formed so that light is emitted by the induced electromotive force in the first induction coil 11A. The first light emitting element 13A emits red light, and in the present embodiment, is formed of a red LED (Light Emitting Diode). On the other hand, the second light emitting element 13B is provided at the blade tip 7 of the main rotor 3, and a circuit is formed so as to emit light by the induced electromotive force in the second induction coil 11B. The second light emitting element 13B emits green light having a color tone different from that of the first light emitting element 13A. In the present embodiment, the second light emitting element 13B includes a green LED.

  The configuration of another wing tip lamp 10 provided in the main rotor 3 is substantially the same as the configuration of the wing tip lamp 10 described above, and the first magnet 12A and the second magnet 12B are different from each other. The explanation is omitted because it is only used in common.

  Next, functions and effects of the wing tip lamp 10 of the helicopter 1 having the above-described configuration will be described.

  In the present embodiment, when the blade tip 7 passes the first position (left side position) shown in FIG. 3 due to the rotation of the main rotor 3, the first induction coil 11A that rotates integrally with the rotating shaft 6 is One magnet 12A is approached and traverses its magnetic flux. Then, an induced electromotive force is generated in the first induction coil 11A, and the first light emitting element 13A provided on the blade tip 7 emits red light by the induced electromotive force. As a result, the wing tip lamp 10 lights red on the left side with the nose in front. At this time, the second induction coil 11B (see FIG. 2) disposed directly below the first induction coil 11A is located on the opposite side of the rotary shaft 6 with respect to the second magnet 12B. The second light emitting element 13B is turned off without being affected by the magnetic flux of the second magnet 12B.

  Further, when the blade tip 7 passes the second position (right side position) shown in FIG. 3 due to the rotation of the main rotor 3, the second induction coil 11B that rotates integrally with the rotary shaft 6 is the second magnet. Close to 12B and cross its magnetic flux. Then, an induced electromotive force is generated in the second induction coil 11B, and the second light emitting element 13B provided at the blade tip 7 emits green light by the induced electromotive force. As a result, the wing tip lamp 10 lights in green on the right side with the nose in front. At this time, the first induction coil 11A (see FIG. 2) arranged immediately above the second induction coil 11B is located on the opposite side of the rotary shaft 6 with respect to the first magnet 12A. The first light emitting element 13A is turned off without being affected by the magnetic flux of the first magnet 12A.

  Then, at the timing when the wing tip 7 of the main rotor 3 passes through the left side position and the right side position of the fuselage 2, the wing tip lamp 10 emits light with a different color tone. As described above, according to the wing tip lamp 10 of the present embodiment, it is possible to switch the color at the wing tip 7 on the left and right sides of the rotating shaft 6 of the main rotor 3 without using a mechanical switching device. In addition, since the lighting sections of the first light emitting element 13A and the second light emitting element 13B are limited to the left and right, the light emitted at two points is seen when the body 2 is viewed from the front and from the side. The appearance (interval) is different, and a third party who observes the helicopter 1 from the outside can easily determine whether the direction of the airframe 2 is the front direction or the side direction.

  In addition, a third party observing the helicopter 1 from the outside can determine that the helicopter 1 is approaching when confirming that the left side of the wing tip 7 is green and the right side of the wing tip 7 is lit red, On the contrary, if it is confirmed that the left side of the wing tip 7 is lit red and the right side of the wing tip 7 is lit green, it can be determined that the helicopter 1 is moving away. The airframe 2 itself of the helicopter 1 has a shape with no horizontal width when viewed from the front or the rear, but the main rotor 3 has a sufficient lateral width, and each color at the wing tip 7 when viewed from the front or the rear. Therefore, it is easy to identify each emission color. For this reason, it is possible to accurately identify whether the helicopter 1 approaches or moves away during night operation.

  Therefore, according to the above-described embodiment, the first induction coil 11 </ b> A and the second induction coil 11 </ b> B provided so as to be integrally rotatable with respect to the rotation shaft 6 of the main rotor 3, and the blade tip 7 of the main rotor 3. Is located close to the first induction coil 11A and the blade tip 7 of the main rotor 3 is opposite to the first position with the rotating shaft 6 in between. In the first induction coil 11A provided at the wing tip 7 of the main rotor 3 and the second magnet 12B arranged so as to be close to the second induction coil 11B when located at the second position on the side The first light emitting element 13A that emits light by the induced electromotive force and the light emitting element having a color tone different from the light of the first light emitting element 13A are emitted by the induced electromotive force in the second induction coil 11B provided at the blade tip 7 of the main rotor 3. By adopting the wing tip lamp 10 of the helicopter 1 having the second light emitting element 13B, the wing tip lamp 10 that can accurately identify whether the helicopter 1 is approaching or moving away is provided. can get.

(Second Embodiment)
Next, a second embodiment of the present invention will be described. In the following description, the same or equivalent components as those of the above-described embodiment are denoted by the same reference numerals, and the description thereof is simplified or omitted.

FIG. 4 is a configuration diagram of the wing tip lamp 10 according to the second embodiment of the present invention.
As shown in FIG. 4, in the second embodiment, the first light emitting element 13 </ b> A and the second light emitting element 13 </ b> B have a blinking circuit 20 that blinks at a cycle longer than the rotation cycle of the blade tip 7 of the main rotor 3. This is different from the above embodiment.

  The blinking circuit 20 is provided between the first induction coil 11A and the first light emitting element 13A, and between the second induction coil 11B and the second light emitting element 13B. The blinking circuit 20 provided between the first induction coil 11A and the first light emitting element 13A causes, for example, the charge induced in the first induction coil 11A to be charged by a charging means such as a capacitor, and the charging voltage is When a predetermined threshold value is exceeded, the switch means such as a transistor is turned “ON” to discharge the first light emitting element 13A. If the reference voltage at which the switch means is “ON” is set to an integral multiple of the voltage accumulated by a single induction, it can be blinked at a cycle that is an integral multiple of the rotation cycle of the blade tip 7 of the main rotor 3. . The flashing circuit 20 between the second induction coil 11B and the second light emitting element 13B has the same configuration.

  As described above, in the second embodiment, the first light emitting element 13A and the second light emitting element 13B flash and emit light at a cycle longer than the rotation cycle of the blade tip 7 of the main rotor 3 by the flashing circuit 20. The flashing effect of light emission at the blade tip 7 is obtained on the left and right sides of the rotating shaft 6. That is, when the first light-emitting element 13A and the second light-emitting element 13B emit light at the same period as the rotation period of the blade tip 7 of the main rotor 3 at a general rotational speed of the main rotor 3, the human visual integration effect Therefore, the flashing circuit 20 is provided to flash the light at the wing tip 7 of the main rotor 3 so as to alert the surroundings, and at the wing tip 7 of the main rotor 3. Light emission can be more easily identified. Note that the blinking effect is not necessarily obtained by both the first light emitting element 13A and the second light emitting element 13B, and may be obtained by either one.

(Third embodiment)
Next, a third embodiment of the present invention will be described. In the following description, the same or equivalent components as those of the above-described embodiment are denoted by the same reference numerals, and the description thereof is simplified or omitted.

FIG. 5 is a plan view showing a lighting section of the wing tip lamp 10 in the third embodiment of the present invention. In FIG. 5, a dot pattern is attached to the lighting section of the wing tip lamp 10 as in FIG.
As shown in FIG. 5, in the third embodiment, the third induction coil 11 </ b> C provided so as to be integrally rotatable with respect to the rotating shaft 6 of the main rotor 3, and the wing tip 7 of the main rotor 3 are located in front of the nose. The third magnet 12C disposed so as to be close to the third induction coil 11C when in the third position, and the induced electromotive force in the third induction coil 11C provided at the blade tip 7 of the main rotor 3 It differs from the said embodiment by the point which has 13 C of 3rd light emitting elements which light-emit.

  The third induction coil 11 </ b> C is provided, for example, directly above the first induction coil 11 </ b> A shown in FIG. 2, and the induction coil is provided with a three-stage shift in the axial direction of the rotating shaft 6. The third magnet 12C is provided at a height corresponding to the rotational trajectory of the third induction coil 11C, and is an induction coil other than the corresponding induction coil, specifically, the first induction coil 11A and the second induction coil. The arrangement is such that the magnetic flux is not affected by the induction coil 11B. The third light emitting element 13C is provided at the blade tip 7 of the main rotor 3, and a circuit is formed so that light is emitted by the induced electromotive force in the third induction coil 11C. The third light emitting element 13C preferably emits light in a color tone different from that of the first light emitting element 13A and the second light emitting element 13B, and includes, for example, a white or blue LED.

  In such a third embodiment, when the blade tip 7 of the main rotor 3 passes through the third position, the induced electromotive force generated by the third induction coil 11C crossing the magnetic flux of the third magnet 12C. As a result, the third light emitting element 13C provided at the blade tip 7 emits light. The third position is in front of the nose, and it becomes easier for the pilot to visually recognize the tip position of the wing tip 7 of the main rotor 3 when manipulating the helicopter 1. For this reason, for example, when a rescue operation is performed and there is an obstacle in front of the nose, the pilot can easily determine how close the helicopter 1 can be to the obstacle.

  As mentioned above, although preferred embodiment of this invention was described referring drawings, this invention is not limited to the said embodiment. Various shapes, combinations, and the like of the constituent members shown in the above-described embodiments are examples, and various modifications can be made based on design requirements and the like without departing from the gist of the present invention.

  For example, in the present embodiment, the form in which the light emitting element is provided in the main rotor has been described, but the present invention is not limited to this form, and for example, the form in which the light emitting element is provided in the tail rotor may be used. Further, the light emitting element is not limited to the LED, and may be an incandescent bulb, for example.

  Further, for example, in the third embodiment, the form in which the third induction coil and the third light emitting element are separately provided has been described. However, the present invention is not limited to this form. For example, only the third magnet is disposed. For the third induction coil and the third light emitting element, at least one of the first induction coil and the second induction coil, at least one of the first light emitting element and the second light emitting element is used. It may be a form commonly used.

  DESCRIPTION OF SYMBOLS 1 ... Helicopter (rotary wing machine), 3 ... Main rotor (rotary wing), 6 ... Rotating shaft, 7 ... Blade tip, 10 ... Blade tip light, 11A ... 1st induction coil, 11B ... 2nd induction coil, 11C ... 3rd induction coil, 12A ... 1st magnet, 12B ... 2nd magnet, 12C ... 3rd magnet, 13A ... 1st light emitting element, 13B ... 2nd light emitting element, 13C ... 3rd Light emitting element

Claims (3)

A first induction coil and a second induction coil provided so as to be integrally rotatable with respect to the rotating shaft of the rotor blade;
When the blade tip of the rotor blade is located at the first position, the first magnet disposed so as to be close to the first induction coil and the blade tip of the rotor blade sandwich the rotation shaft. A second magnet disposed close to the second induction coil when located at a second position opposite to the first position;
A first light emitting element that is provided at the tip of the rotor blade and emits light by an induced electromotive force in the first induction coil, and an induced electromotive force that is provided in the tip of the rotor blade and is provided in the second induction coil. And a second light-emitting element that emits light having a color tone different from that of the light from the first light-emitting element.   2. The flash circuit according to claim 1, further comprising: a blinking circuit that blinks at least one of the first light emitting element and the second light emitting element at a cycle longer than a rotation cycle of a blade tip of the rotary blade. Wing tip lamp of the described rotary wing aircraft. A third induction coil provided so as to be integrally rotatable with respect to the rotating shaft of the rotor blade;
A third magnet disposed so as to be close to the third induction coil when a tip of the rotor blade is in a third position in front of the nose;
And a third light-emitting element that is provided at a blade tip of the rotor blade and emits light by an induced electromotive force in the third induction coil. Wing tip light.

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