JP6122930B1 - Illumination bullet simulator and method - Google Patents

Abstract

Since an illuminating bullet is a pyrotechnic product, it cannot be reused, and is a consumable product, so that it costs money for each use. Also, since the performance of a single light bullet is affected by weather conditions, for example, the ignition intensity is weak on rainy days, it does not always show a constant performance, and it has an adverse effect on the results of training and actual battles. There is a fear. An illumination bomb simulation apparatus according to an embodiment includes a light source that emits light with an intensity according to supplied power, a power source for supplying light to the light source, and power supplied from the light source to the light source. A light source power source control unit for controlling the light source, a light source, a power source for the light source, and a flying body equipped with the power source control unit for the light source, and a flight control unit mounted on the flying body and controlling the flight of the flying body ing. Then, while the flying object is falling, the light source power source control unit controls the power supplied from the light source power source to the light source according to the light emission intensity changing behavior when the actual lighting bullet is dropped. [Selection] Figure 1

Description

  Embodiments of the present invention relate to an apparatus and method for simulating lighting bullets without using pyrotechnics.

  The illuminating bullet is used to illuminate the surroundings and secure a visual field or signal by emitting light when emitted from the airplane, ship, vehicle or the like in the air during nighttime training or actual battles.

JP 2007-46841 A

  However, such conventional illumination bullets have the following problems.

  That is, since this type of lighting bullet is a pyrotechnic (see, for example, Patent Document 1), not only handling is required, but in use, training is performed within a certain range for safety management. Will not be able to enter.

  For this reason, depending on the type of training, it is difficult to carry out the training itself as well as to carry out it safely.

  Moreover, since it is a pyrotechnic product, it cannot be reused naturally, and since it is a consumable product, it will cost each time it is used.

  In addition, because it is a pyrotechnic, the performance of the lighting bullet alone depends on the weather conditions, for example, the ignition intensity is weak on rainy days. And may adversely affect the results of actual battles.

  The present invention has been made in view of such circumstances, and by using a light source that is not a pyrotechnic for illumination, the restrictions required from the viewpoint of safety management are eliminated, and weather conditions It is an object of the present invention to provide an apparatus and method for simulating an illuminating bullet that can always exhibit a certain illumination capability without being influenced by the cost and that is excellent in cost performance by being reusable.

  The illumination bullet simulation device of the embodiment is a device that simulates an illumination bullet, and includes a light source that emits light with an intensity according to the supplied power, a light source power source for supplying power to the light source, and a light source power source. A power source control unit for controlling the power supplied to the light source, a flying body equipped with the light source, the power source for the light source, and the power source control unit for the light source, and mounted on the flying body to control the flight of the flying body The light source power supply control unit supplies power supplied from the light source power source to the light source according to the light emission intensity change behavior when the actual lighting bullet is dropped. Control.

It is a functional block diagram which shows the structural example of the illumination bullet simulation apparatus to which the illumination bullet simulation method of embodiment of this invention is applied. It is an external view which shows an example of a drone main body. It is a schematic diagram which shows an example of a remote controller. It is a figure for demonstrating the principle by which the light from a light source is diffused by a diffuser lens. It is a figure for demonstrating the principle by which the light from a light source is spread | diffused by a diffusion plate. It is a figure which shows the light emission intensity change behavior at the time of the fall of an actual illumination bullet. It is a figure for demonstrating the power control by pulse width modulation. It is a flowchart which shows the operation example of the illumination bullet simulation apparatus to which the illumination bullet simulation method of embodiment of this invention is applied.

  Hereinafter, an illumination bullet simulation device to which the illumination bullet simulation method of each embodiment of the present invention is applied will be described with reference to the drawings.

  FIG. 1 is a functional block diagram showing a configuration example of an illumination bullet simulating apparatus to which the illumination bullet simulation method of the embodiment of the present invention is applied.

  That is, the illuminating bullet simulation device 10 of the present embodiment is a device that simulates an illuminating bullet, and includes a drone main body 10 that is a flying object and a remote flight control unit 60 that remotely controls the drone main body 10. It becomes.

  The drone body 10 includes a flight drive unit such as one or more propellers 12, a radio device 14, a ROM 16, a flight control circuit 18, a GPS 20, a timer 22, and a light source power supply control circuit 24. And a light source 26 such as a battery, a light source driving circuit 28, a light source 30, and a diffusing unit 32.

  The remote flight control unit 60 includes a terminal device 62 and a radio device 64.

  FIG. 2 is an external view showing an example of the drone body 10.

  In the example shown in FIG. 2, a propeller 12 is provided on the upper portion of the drone body 10 as an example of a flight drive unit. The propeller 12 generates energy for flying the drone body 10 by being driven to rotate.

  The driving of the propeller 12 is controlled by a flight control circuit 18 that controls the flight of the drone body 10. Specifically, the flight control circuit 18 controls the driving of the propeller 12 so as to fly the drone body 10 in accordance with a flight plan programmed in advance and written in the ROM 16. Alternatively, the GPS 20 measures the position of the drone body 10 in flight, and the flight control circuit 18 determines the position of the drone body 10 based on the position of the drone body 10 measured by the GPS 20 and the flight plan described above. Flight may be controlled. Furthermore, the timer 22 measures the flight time of the drone main body 10, and the flight control circuit 18 controls the flight of the drone main body 10 based on the flight time measured by the timer 22 and the flight plan described above. May be. Furthermore, the flight control circuit 18 controls the flight of the drone body 10 based on the position of the drone body 10 measured by the GPS 20, the flight time measured by the timer 22, and the flight plan described above. May be.

  Although the above describes the autonomous flight method of the drone body 10, in the present embodiment, it is also possible to remotely control the flight of the drone body from the remote flight control unit 60. In FIG. 1, the remote flight control unit 60 is shown to include a terminal device 62 and a wireless device 64, but, like the terminal device 62, a function for receiving an operation input from an operator, A function of transmitting an operation input to the drone body 10 and receiving various information (for example, position information measured by the GPS 20) transmitted from the drone body 10 and passing it to the terminal device 62 as in the machine 64. 3 may be realized as a remote controller 66 in which a terminal device 62 and a radio device 64 as shown in FIG.

  On the display 68 of the remote controller 66, position information measured by the GPS 20 and information such as speed and acceleration calculated by the terminal device 62 based on the position information are also displayed.

  The operator can manually control the flight of the drone main body 10 by operating the operation lever 70 of the remote controller 66 in consideration of the displayed information.

  A light source 30 such as a xenon lamp, an LED, or a halogen lamp is fixed to the lower portion of the drone body 10.

  As an example, the maximum light amount of an actual illumination bullet is about 60 candela. On the other hand, a xenon lamp having a light quantity of 350,000 candela is commercially available. Therefore, if two xenon lamps are mounted on the drone body 10 as the light source 30, the maximum light quantity of the illumination bullet can be realized. Incidentally, since this commercially available xenon lamp has a weight of about 2 kg and is lightweight, it is possible to mount two on the drone body 10. Although the actual illumination bullet is a point light source, the light quantity of 350,000 candela is so bright that even if a plurality of xenon lamps are used as the light source, the plurality of xenon lamps are brought close to each other. If it is arranged, it will be seen from the human eye as a single point light source like an actual lighting bullet.

  Moreover, as an example, the actual illumination range of the illumination bullet is about 1200 m in diameter. In the present embodiment, in order to realize such a wide illumination range, the diffusing unit 32 that is a diffusing plate or a diffusing lens for diffusing the light emitted by the light source 30 in the ground direction is used. It is fixed on the light exit side.

  FIG. 4 is a conceptual diagram showing an example of this state, and shows an example in which light emitted from the light source 30 is diffused by a diffusion lens 32a, which is an example of the diffusion unit 32, and illuminates the ground side.

  FIG. 5 is a conceptual diagram showing another example, in which light emitted from the light source 30 is diffused by a curved diffusion plate 32b which is an example of the diffusion unit 32, and illuminates the ground side. ing.

  In the present embodiment, the drone body 10 on which such a light source 30 and the diffusing unit 32 are mounted is dropped while changing the light emission intensity of the light source 30 according to the light emission intensity change behavior when the actual illumination bullet is dropped. This simulates a lighting bullet.

  As an example, the actual falling speed of the lighting bullet is about 10 m / sec. Therefore, the flight control circuit 18 or the remote flight control unit 60 controls the drone body 10 to drop at a dropping speed of about 10 / second.

  Further, the light emission intensity changing behavior when the actual lighting bullet is dropped is grasped in advance, for example, as shown by a curve A in FIG. Since an actual illuminating bullet is a pyrotechnic, as shown by curve A in FIG. 6, light emission starts gradually at a light emission altitude a (for example, a sky number of 100 m), and (b) the light quantity gradually decreases. (C) After shining with the maximum light amount for a while while falling, (d) The light amount gradually decreases, and when it approaches the altitude e from the ground, it eventually disappears. The time from the start of light emission at the altitude a to the extinction at the altitude e, that is, the combustion time, is, for example, about 70 seconds.

  On the other hand, the light source 30 such as a xenon lamp, an LED, or a halogen lamp is not a pyrotechnic, so if the supplied power is constant, the amount of light regardless of the altitude, as shown by the straight line B in FIG. Is constant.

  Therefore, in the present embodiment, the electric power supplied to the light source 30 is controlled so that the light amount of the light source 30 becomes the light emission intensity change behavior when the actual lighting bullet falls as shown by the curve A.

  In order to realize this, the light source power supply control circuit 24 controls the power supplied from the light source power supply 26 to the light source drive circuit 28 by performing, for example, pulse width modulation.

  Power control by pulse width modulation will be described with reference to FIG. The light source power supply control circuit 24 sends, for example, a pulse having a voltage pattern as shown in FIG. In response to this, the light source power supply 26 supplies power to the light source drive circuit 28 when the voltage is high (H). In response to this, the light source drive circuit 28 turns on the light source 30 and the voltage low ( In the case of L), power is not supplied to the light source driving circuit 28, and the light source 30 is not turned on accordingly.

  When the light source power supply control circuit 24 controls from the state shown in FIG. 7A to reduce the pulse width (that is, to reduce the duty ratio) as shown in FIG. Since the time during which the light source 30 is turned on is shortened, the amount of light from the light source 30 is reduced. When the light source power supply control circuit 24 controls the pulse width to be further shortened (that is, the duty ratio is further reduced) as shown in FIG. 7C, the light source 30 is turned on per unit time. Since the time is further shortened, the amount of light from the light source 30 is further reduced.

  If such a principle is utilized, the light source power supply control circuit 24 can control the light quantity by the light source 30 by controlling the duty ratio to be changed. Therefore, the light source power supply control circuit 24 sends pulses to the light source power supply 26 so that the duty ratio gradually increases during the period (b) in the curve A in FIG. The pulse is sent to the light source power source 26 without changing the ratio, and in the period (d), the pulse is sent to the light source power source 26 so that the duty ratio gradually decreases, whereby the emission intensity change behavior as shown by the curve A Is realized. The light source power supply control circuit 24 does not send a pulse to the light source power supply 26 before the start of the period (b) and after the end of the period (d).

  According to such pulse width modulation, lighting and extinction of the light source are repeated. However, if the pulse frequency is 30 Hz or higher, the switching between lighting and extinction can no longer be recognized with the naked eye. Accordingly, the frequency of the pulse is assumed to be 30 Hz or more.

  Next, the operation of the illumination bullet simulation device to which the illumination bullet simulation method of the present embodiment configured as described above is applied will be described with reference to the flowchart of FIG.

  As described above, when the drone main body 10 is caused to fly, there are a case where the drone body 10 is performed according to a pre-programmed flight plan and a case where the drone body 10 is performed using remote control by the remote flight control unit 60.

  In order to fly the drone main body 10 in accordance with a pre-programmed flight plan, it is necessary to program the flight plan and store it in the ROM 16 (S1).

  This flight plan includes, as position information, a drop start position, a drop speed, a drop end position, and a retreat position from the drop end position of the drone body 10. Furthermore, a duty ratio control pattern corresponding to the light emission intensity change behavior when the actual lighting bullet is dropped, which is made by the light source power supply control circuit 24, is included.

  When the drone body 10 is activated, the flight control circuit 18 controls the propeller 12 according to the position information included in the flight plan stored in the ROM 16, and thereby the flight toward the fall start position is performed. Start (S2).

  The current position of the drone body 10 in flight is constantly measured by the GPS 20 and sent to the flight control circuit 18 and the light source power supply control circuit 24. The flight control circuit 18 controls the propeller 12 in consideration of the current position sent from the GPS 20 in addition to the fall start position included in the flight plan. Thereby, the drone body 10 accurately moves to the drop position start position (S3).

  In addition, instead of automatically moving the drone body 10 to the fall start position according to a pre-programmed flight plan as in steps S1 to S3, the user operates the remote flight control unit 60 such as the remote controller 66. Thus, the drone body 10 may be moved to the drop start position. As described above, the position information measured by the GPS 20 and information such as the speed and acceleration calculated by the terminal device 62 based on the position information are also displayed on the display 68 of the remote controller 66. Therefore, the user can move the drone main body 10 to the drop start position by operating the remote controller 66 while referring to these pieces of information.

  When the drone body 10 moves to the drop start position, the drone body 10 starts dropping (S4). In order to start the fall, the fall start timing is included in the flight plan as the fall start time information, and when the fall disclosure time is reached, the flight control circuit 18 starts the drop of the drone body 10. You may do it.

  In addition, the user transmits a drop start instruction to the drone main body 10 by operating the remote flight control unit 60 such as the remote controller 66, and the radio device 14 receives the drop start instruction and the flight control circuit. In response to this, the flight control circuit 18 may start the drone body 10 to drop.

  Alternatively, the timing for starting the fall is included in the flight plan as the elapsed time after moving to the fall start position, while the elapsed time after the drone body 10 moves to the fall start position is 22 is timed and sent to the flight control circuit 18. The flight control circuit 18 starts dropping the drone body 10 when the elapsed time sent from the timer 22 matches the elapsed time included in the flight plan. You may make it let it.

  When the drone body 10 falls, the flight control circuit 18 controls the rotation of the propeller 12 so that the drop speed (for example, 10 m / sec) included in the flight plan is reached, and the fall speed is controlled. As a result, the drone body 10 falls in the same manner as an actual lighting bullet. Thus, even while the drone body 10 is falling, the position information is measured by the GPS 20 and sent to the flight control circuit 18 and the light source power supply control circuit 24.

  At the same time as the drone body 10 starts dropping, a light emission start signal is sent from the flight control circuit 18 to the light source power supply control circuit 24 (S5). As a result, the light source power supply control circuit 24 sends a pulse to the light source power supply 26 while changing the duty ratio so as to correspond to the light emission intensity changing behavior when the actual illumination bullet is dropped (S6).

  For example, as shown in curve (b) of FIG. 6, a pulse is sent to the light source power supply 26 while gradually increasing the duty ratio so that the emission intensity gradually increases for a while after the start of dropping. . This is realized, for example, by changing the duty ratio as shown in FIG. 7C → FIG. 7B → FIG. 7A.

  Next, as shown in curve (c) of FIG. 6, the pulse having the maximum duty ratio is continuously sent to the light source power supply 26 so as to maintain the maximum light emission intensity for a while. This is realized, for example, by sending the pulse of FIG. 7A to the light source power source 26 for a while.

  Thereafter, as indicated by curve A in FIG. 6, a pulse is sent to the light source power supply 26 while gradually decreasing the duty ratio so that the emission intensity gradually decreases. This is realized, for example, by changing the duty ratio as shown in FIG. 7A → FIG. 7B → FIG. 7C.

  As described below, there are two methods for determining the timing for changing the duty ratio: a method based on the positioning result by the GPS 20 and a method based on the time measurement result by the timer 22.

  When performing based on the positioning result by the GPS 20, the light source power supply control circuit 24 gradually increases the duty ratio from the altitude a to the altitude f shown in FIG. 6 based on the positioning result sent from the GPS 20, Further, after the altitude f, the pulse is sent to the light source power source 26 while keeping the duty ratio constant from the altitude g to the altitude g and further gradually decreasing the duty ratio from the altitude g to the altitude e.

  On the other hand, since the drop speed of the drone main body 10 is controlled as described above, the position of the drone main body 10 can be grasped from the elapsed time from the start of the fall timed by the timer 22.

  Therefore, when performing based on the time measurement result by the timer 22, the light source power supply control circuit 24 starts the fall from the altitude a shown in FIG. 6 to the altitude f based on the time measurement result sent from the timer 22. During the elapsed time, the duty ratio is gradually increased, and thereafter the duty ratio is kept constant during the elapsed time from falling from the altitude f to the altitude g, and then from the altitude g to the altitude e. During the elapsed time until falling, the pulse is sent to the light source power supply 26 while gradually decreasing the duty ratio.

  In this way, when the pulse is sent to the light source power source 26, the light source power source 26 supplies power to the light source drive circuit 28 when the voltage is high (H), and in response to this, the light source drive circuit 28 is supplied. The light source 30 is turned on. On the other hand, when the voltage is low (L), power is not supplied to the light source driving circuit 28, and the light source 30 is not turned on accordingly (S7).

  Accordingly, when the light source power supply control circuit 24 sends a pulse to the light source power supply 26 while gradually increasing the duty ratio, the light emitted from the light source 30 gradually increases accordingly. When the light source power supply control circuit 24 sends a pulse to the light source power supply 26 with the maximum duty ratio, the light from the light source 30 is maintained at the maximum accordingly. When the light source power supply control circuit 24 sends a pulse to the light source power supply 26 while gradually decreasing the duty ratio, the light from the light source 30 gradually darkens accordingly.

  The light emitted from the light source 30 is diffused in the ground direction by the diffusing unit 32 which is a diffusion plate or a diffusing lens fixed on the light emitting side of the light source 30, and the illumination range of an actual illumination bullet having a diameter of about 1200 m is used. A wide illumination range corresponding to is realized.

  When the drone body 10 descends to the altitude e in FIG. 6, the drone body 10 stops emitting light from the light source 30. Thereafter, the aircraft automatically flies to the retreat position determined in the flight plan, or flies to the retreat position according to a user operation by the remote flight control unit 60 such as the remote controller 66, and is collected there (S8). ).

  As described above, according to the illumination bullet simulating apparatus to which the illumination bullet simulation method of the present embodiment is applied, it is possible to faithfully simulate an actual illumination bullet without using pyrotechnics by the above-described operation. Can do. Therefore, not only can the safety at the time of use be remarkably improved, but also reuse is possible, so that the cost performance is greatly improved.

  Also, with conventional pyrotechnic lighting bullets, the performance of the lighting bullet alone depends on the weather conditions, for example, the ignition intensity is weak on rainy days, so it can always exhibit a certain level of performance. Instead, there was a risk of adverse effects on the results of training and actual battles. However, according to the illumination bullet simulation device to which the illumination bullet simulation method of the present embodiment is applied, all such problems are eliminated, and stable illumination can be realized without being affected by weather conditions. Therefore, it is possible to always provide the ability as expected.

  In addition to being freed from the need for special safety management required for handling pyrotechnics, there are no restrictions on inaccessible areas during use. , Operational behavior becomes possible.

  Although several embodiments of the present invention have been described, these embodiments are presented by way of example and are not intended to limit the scope of the invention. These embodiments can be implemented in various other forms, and various omissions, replacements, and changes can be made without departing from the spirit of the invention. These embodiments and their modifications are included in the scope and gist of the invention, and are also included in the invention described in the claims and the equivalents thereof.

10 drone body, 12 propeller, 14 radio, 16 ROM, 18 flight control circuit, 20 GPS, 22 timer, 24 light source power supply control circuit, 26 light source power supply, 28 light source drive circuit, 30 light source, 32 diffusion unit, 32a Diffuser lens, 32b Diffuser plate, 60 Remote flight control unit, 62 Terminal device, 64 Radio device, 66 Remote controller, 68 Display, 70 Operation lever

Claims (23)

A device that simulates a light bullet,
A light source that emits light with an intensity according to the supplied power;
A light source for supplying power to the light source;
A light source power control unit for controlling power supplied from the light source power source to the light source;
A flying object equipped with the light source, the power source for the light source, and the power source control unit for the light source;
A flight control unit mounted on the aircraft and controlling the flight of the aircraft,
While the flying object is falling, the light source power source control unit controls the power supplied from the light source power source to the light source according to the light emission intensity changing behavior when the actual lighting bullet is dropped. A lighting bullet simulator.   The illumination bullet simulator according to claim 1, wherein the light source power supply control unit controls electric power supplied to the light source by pulse width modulation.   The illumination bullet simulation apparatus according to claim 1, wherein the light emission intensity change behavior is grasped in advance.   The illumination bullet simulator according to any one of claims 1 to 3, further comprising a diffusing unit that diffuses light emitted from the light source in the flying body.   The illumination bullet simulating apparatus according to claim 4, wherein the diffusion unit is a diffusion plate or a diffusion lens.   6. The illumination bullet simulating apparatus according to claim 1, wherein the flight control unit controls the flight of the flying object in accordance with a pre-programmed flight plan. The aircraft further includes a GPS for measuring the position of the aircraft,
The illuminating bullet simulator according to claim 6, wherein the flight control unit controls the flight of the flying object based on the position of the flying object measured by the GPS and the pre-programmed flight plan. A timer for measuring the flight time of the aircraft,
The illuminating bullet simulation apparatus according to claim 6, wherein the flight control unit controls flight of the flying object based on a flight time measured by the timer and the pre-programmed flight plan.   The illumination bullet simulator according to any one of claims 1 to 5, further comprising a remote flight control unit that is provided separately from the flying object and controls the flight control unit from a remote location.   The illumination bullet simulator according to any one of claims 1 to 9, wherein the light source is a xenon lamp.   The illumination bullet simulator according to any one of claims 1 to 10, wherein the light source includes a plurality of lamps.   The illuminating bullet simulator according to claim 1, wherein the flying object is a drone. A method of simulating a light bullet,
A method in which a flying object equipped with a light source is dropped while changing the light emission intensity of the light source according to the light emission intensity change behavior when the actual lighting bullet is dropped.   The method according to claim 13, wherein the light emission intensity of the light source is changed by controlling the power supplied to the light source by pulse width modulation.   The method according to claim 13 or 14, wherein the light emission intensity change behavior is known in advance.   The method according to claim 13, wherein the light emitted by the light source is diffused.   17. A method according to any one of claims 13 to 16, wherein the flight of the vehicle is controlled according to a pre-programmed flight plan.   The method according to claim 17, wherein the flight of the air vehicle is controlled based on the pre-programmed flight plan and the position of the air vehicle measured by a GPS mounted on the air vehicle.   18. The method of claim 17, wherein the flight of the air vehicle is controlled based on the pre-programmed flight plan and the flight time of the air vehicle timed by a timer mounted on the air vehicle. The method according to any one of claims 13 to 16 , wherein the flight of the air vehicle is controlled by a remote controller.   21. A method according to any one of claims 13 to 20, wherein the light source is a xenon lamp.   The method according to any one of claims 13 to 21, wherein the light source comprises a plurality of lamps.   The method according to any one of claims 13 to 22, wherein the flying object is a drone.