Flying object

Abstract

To provide a flying object that disables a target with a large force when the target can be hit directly, and also can enhances the probability that the target can be disabled even when the target cannot be hit directly.SOLUTION: A flying object 1 comprises: a laser oscillator which irradiates a target 50 with laser light L1; a laser light receiver which receives reflected light from a reflection point where the laser light L1 is reflected; an infrared sensor which measures a temperature of the reflection point by receiving infrared rays; and a controller. The controller determines whether or not a measurement temperature measured by the infrared sensor is within a temperature range corresponding to aerodynamic heating when the laser light receiver receives the reflected light, and then disables the target 50 by executing control over direct destruction for disabling the target 50 by direct hitting when the measurement temperature is within the temperature range, or disables the target 50 by controlling searching for the target 50 and initiation when the laser light receiver does not receive the reflected light or when the measurement temperature is not within the temperature range.SELECTED DRAWING: Figure 4

Description

[Technical field]

[0001] The present disclosure relates to air vehicles that neutralize flying targets. [Background technology]

[0002] In recent years, new types of flying objects have become known that are capable of flying at higher speeds and in irregular trajectories, and are more difficult to encounter than conventional flying objects.

[0003] The projectile that meets the target is fired toward the target and neutralizes the target by hitting it directly. This projectile utilizes the mutual kinetic energy when the projectile collides with the target to directly destroy it and neutralize it.

[0004] To neutralize the new type of projectile, it is necessary to accurately guide the projectile to the target. One of the technologies for accurately guiding the projectile to the target is to use multiple sensors to guide the projectile to the target.

[0005] For example, the flying object described in Patent Document 1 is equipped with a narrowband active radio wave sensor, a wideband passive radio wave sensor, and a light wave sensor, and the flying object is guided to a target by switching between these three sensors. [Prior art documents] [Patent documents]

[0006] [Patent Document 1] Japanese Patent Application Publication No. 4-310888 Summary of the Invention [Problem to be solved by the invention]

[0007] However, the technology of Patent Document 1 has a problem in that if the projectile cannot hit the target directly, the target cannot be neutralized.

[0008] The present disclosure has been made in consideration of the above, and aims to obtain a flying object that can neutralize the target with great force if a direct hit on the target is possible, and can increase the probability of neutralizing the target even if a direct hit on the target is not possible. [Means for solving the problem]

[0009] In order to solve the above-mentioned problems and achieve the object, the flying object of the present disclosure includes a laser oscillator that irradiates a laser beam to a target, a laser beam receiver that receives reflected light at a reflection point that reflects the laser beam, and an infrared sensor that measures the temperature of the reflection point by receiving infrared rays. The flying object of the present disclosure also includes an outer cylinder portion in which the laser oscillator, the laser beam receiver, and the infrared sensor are arranged, and a control device that controls the laser oscillator, the laser beam receiver, and the infrared sensor. When the laser beam receiver receives the reflected light, the control device determines whether the measured temperature measured by the infrared sensor is within a temperature range corresponding to aerodynamic heating, and when the measured temperature is within the temperature range, the control device neutralizes the target by executing control of direct hit destruction that neutralizes the target by a direct hit, and when the laser beam receiver does not receive the reflected light or the measured temperature is not within the temperature range, the control device neutralizes the target by controlling the search and detonation of the target. Effect of the Invention

[0010] The flying object according to the present disclosure has the effect of neutralizing the target with great force if it is able to hit the target directly, and of increasing the probability of neutralizing the target even if it is unable to hit the target directly. [Brief description of the drawings]

[0011] [Figure 1] FIG. 1 is a perspective view showing a schematic configuration of a flying object according to an embodiment; [Diagram 2] FIG. 1 is a front view showing a schematic configuration of a flying object according to an embodiment; [Diagram 3] FIG. 1 is a perspective view showing a schematic configuration of a mounted module included in a flying object according to an embodiment; [Figure 4]FIG. 1 is a diagram for explaining a target nullification process executed by a flying object according to an embodiment; [Diagram 5] 1 is a flowchart showing a procedure of a process executed by a target invalidation system according to an embodiment. [Figure 6] FIG. 1 is a diagram showing a configuration example of a processing circuit provided in a control device for a flying object according to an embodiment, in the case where the processing circuit is realized by a processor and a memory; [Figure 7] FIG. 1 is a diagram showing an example of a processing circuit in a case where the processing circuit in the control device for a flying object according to an embodiment is configured with dedicated hardware; DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0012] Hereinafter, a flying object according to an embodiment of the present disclosure will be described in detail with reference to the drawings.

[0013] Embodiment Fig. 1 is a perspective view showing a schematic configuration of a flying object according to an embodiment. Fig. 2 is a front view showing a schematic configuration of a flying object according to an embodiment. The flying object 1 destroys and neutralizes a target such as a new type of flying object.

[0014] The flying object 1 judges whether or not it can hit the target directly if it continues flying according to its positional relationship with the target during flight. If a direct hit is possible, the flying object 1 makes a direct hit with the target and neutralizes the target, and if a direct hit is not possible, the flying object 1 neutralizes the target with debris.

[0015] Neutralization by direct hit is a method of destroying and neutralizing a target by directly colliding the projectile 1 with the target. Neutralization by fragmentation is a method of destroying and neutralizing a target by colliding fragmentation caused by detonating a part of the projectile 1 with the target.

[0016] The flying object 1 includes a mounted module 20 disposed on the outer cylinder 10, a control device 5 that controls the mounted module 20, and a proximity sensor (not shown). One or more mounted modules 20 are disposed on the flying object 1. FIG. 2 shows a case where four mounted modules 20 are disposed on the outer cylinder 10 of the flying object 1.

[0017] The mounted module 20 is a module mounted on the flying object 1, and is used to measure the positional relationship with a target. The control device 5 controls the thrust of a propulsion device (not shown) equipped in the flying object 1 according to instructions from a command device (not shown) that commands and controls the flying object 1. A system including the flying object 1 and the command device that commands firing at the target (engagement with the target) is a target neutralization system that neutralizes the target.

[0018] The command device is a device that searches for, detects, captures, tracks, etc. a target, and also commands the flying object 1. The command device transmits instruction information to the flying object 1 based on the acceleration, attitude, position, etc. of the target.

[0019] The command device may transmit instruction information to the flying object 1 using a GPS (Global Positioning System), a celestial navigation device, etc. The command device performs early and mid-term guidance (initial guidance and mid-term guidance) using a ground radar, etc., so that the flying object 1 meets the target.

[0020] During terminal guidance, the flying object 1 switches between neutralizing the target by a direct hit or neutralizing the target by debris, based on the positional relationship between the flying object 1 and the target. During terminal guidance, the flying object 1 searches for (searches for) the target using a radio wave sensor (not shown) or the like, calculates the position of the target relative to the flying object 1 based on the search result, and switches between neutralizing the target by a direct hit or neutralizing the target by debris, based on the positional relationship with the target.

[0021] 3 is a perspective view showing a schematic configuration of a mounting module provided in the flying object according to the embodiment. The mounting module 20 has a laser oscillator 21, a laser beam receiver 22, and an infrared sensor 23. The laser oscillator 21, the laser beam receiver 22, and the infrared sensor 23 are controlled by a control device 5. Mounting modules 20 each including three components, the laser oscillator 21, the laser beam receiver 22, and the infrared sensor 23, are arranged at four locations on the outer cylinder 10 of the flying object 1.

[0022] The laser oscillator 21 irradiates a laser beam in the forward direction of the axis of the flying object 1. The laser beam irradiated by the laser oscillator 21 is reflected and scattered at a reflection point (target surface) of the target. As a result, reflected light (scattered light) is generated at the reflection point of the target. The laser beam receiver 22 measures the reflected light generated at the reflection point of the target.

[0023] Note that the laser beam receiver 22 may detect reflected light generated at a reflection point other than the target. Therefore, when the laser beam receiver 22 detects reflected light, the mounted module 20 measures the temperature in the forward direction of the flying object 1 by the infrared sensor 23. That is, since the laser beam receiver 22 may capture reflected light generated by reflection at a point other than the target, the infrared sensor 23 measures the temperature in the forward direction of the flying object 1.

[0024] When the laser light is reflected from the target reflection point, the infrared sensor 23 measures the temperature at the target reflection point. On the other hand, when the laser light is reflected from a point other than the target reflection point, the infrared sensor 23 measures the temperature at the point other than the target reflection point.

[0025] The temperature at the target's reflection point rises due to aerodynamic heating because the target is flying at high speed. Therefore, when the infrared sensor 23 measures the temperature at the target's reflection point, the measured temperature corresponds to aerodynamic heating. On the other hand, when the infrared sensor 23 measures the temperature at a point other than the target's reflection point, the measured temperature does not correspond to aerodynamic heating.

[0026] The control device 5 judges whether or not the measured temperature is within a temperature range corresponding to aerodynamic heating (within a temperature region corresponding to aerodynamic heating). If the measured temperature is within the temperature region corresponding to aerodynamic heating, the control device 5 judges that the target is geometrically on the direct hit course of the flying object 1. On the other hand, if the measured temperature is not within the temperature region corresponding to aerodynamic heating, the control device 5 judges that the target is geometrically not on the direct hit course of the flying object 1.

[0027] In this way, the control device 5 determines whether the missile 1 is in a position relative to the target that allows a direct hit before the target and the missile 1 meet, in order to decide whether to neutralize a target, such as a new type of missile that follows an irregular trajectory, by either a direct hit or by debris.

[0028] The flying object 1 is guided in the initial and mid-term by a command device, and then is terminally guided using a radio wave sensor and an IR (Infrared) sensor (not shown) equipped on the flying object 1. The radio wave sensor and the IR sensor are devices for searching for a target.

[0029] The control device 5 guides the flying object 1 using the radio wave sensor and the IR sensor, and then determines whether the flying object 1 will hit the target directly based on the reflected light detected by the laser light receiver 22 and the temperature measured by the infrared sensor 23, and determines whether to neutralize the flying object 1 by a direct hit or by fragments of the detonation site. In this way, the control device 5 executes control to neutralize the target using the determined neutralization method.

[0030] 4 is a diagram for explaining the target nullification process executed by the flying object according to the embodiment. When the flying object 1 is launched, it heads toward the target 50. The command device guides the flying object 1 in the initial and middle stages so that the flying object 1 and the target 50 face each other head-on.

[0031] Thereafter, during terminal guidance in which the flying object 1 searches for the target 50 using a radio wave sensor or the like, the control device 5 activates the three components of the onboard module 20. That is, during terminal guidance, the control device 5 activates the laser oscillator 21, the laser light receiver 22, and the infrared sensor 23. The laser oscillator 21 of the flying object 1 irradiates laser light L1 in the forward direction of the aircraft axis (s1).

[0032] The flying object 1 is guided to be head-on using a radio wave sensor, an IR sensor, etc., and then when the laser light L1 irradiated ahead of the flying object 1 is reflected by the target 50, the laser light receiver 22 measures the reflected light of the laser light L1. The laser light receiver 22 sends the measurement result of this reflected light to the control device 5.

[0033] Based on the measurement result of the reflected light, the control device 5 makes an initial judgment as to whether or not there is a possibility that the flying object 1 is located on a direct hit course with the target 50. In this case, since there is a possibility that the flying object 1 will capture reflected light generated at a reflection point other than the target 50, the infrared sensor 23 is used to measure the temperature of the measurement point (reflection point). The infrared sensor 23 sends this temperature measurement result to the control device 5. The control device 5 judges whether or not the measured temperature is within a temperature range corresponding to aerodynamic heating. In other words, the control device 5 judges whether or not the temperature of the measurement point of the target 50 is within the range of temperatures that have risen due to the target 50 flying at high speed.

[0034] If the temperature at the measurement point is within a temperature range corresponding to aerodynamic heating, the control device 5 secondarily determines that the target 50 is geometrically on the direct hit course of the flying object 1 (s2). In this case, the control device 5 does not output an instruction to search for the enemy using the proximity sensor, nor executes control of detonation. The control device 5 then executes control of direct hit destruction to neutralize the target 50 by having the flying object 1 directly hit the target 50. As a result, the flying object 1 heads toward the target 50. The flying object 1 then neutralizes the target 50 by having the flying object 1 directly hit the target 50 as an object that meets the target (s3).

[0035] On the other hand, when the temperature at the measurement point is outside the temperature range corresponding to aerodynamic heating, the control device 5 secondarily judges that the target 50 is not geometrically on the direct hit course of the flying object 1. Also, when the laser light receiver 22 does not measure reflected light of a specific value or more, the control device 5 secondarily judges that the target 50 is not geometrically on the direct hit course of the flying object 1. Then, the control device 5 controls the search for the target 50 using a proximity sensor and detonation. As a result, the flying object 1 detects the target 50 using the proximity sensor and executes detonation, thereby neutralizing the target 50 with the fragments at the detonation site (s4).

[0036] In this way, the flying object 1 grasps the positional relationship between the target 50 and the flying object 1 intercepting the target 50 during terminal guidance, and selects a method of neutralizing the target 50 according to the positional relationship. This allows the launched flying object 1 to effectively neutralize the target 50.

[0037] If the target 50 is a new type of ballistic missile, the target 50 flies on an irregular trajectory, and it may be difficult to have the flying object 1 directly hit the target 50. Even if the flying object 1 is unable to neutralize the target 50 by a direct hit, it can damage the target 50 using fragments from the detonation site within the flying object 1, rendering the target 50 unable to fly and seizing its ability to carry out its mission.

[0038] In this way, the flying object 1 selects a direct hit or detonation based on the positional relationship with the target 50, and can appropriately neutralize the target 50 according to the positional relationship with the target 50. That is, when the flying object 1 can directly hit the target 50, it can neutralize the target 50 with great force by directly hitting the target 50, and even when it cannot directly hit the target 50, it can increase the probability of neutralizing the target 50 by detonation.

[0039] 5 is a flowchart showing the procedure of the process executed by the target neutralization system according to the embodiment. When the flying object 1 is launched (step S10), the command device guides the flying object 1 in the initial and middle stages (step S20) using a ground radar or the like. After this, the flying object 1 starts terminal guidance by itself (step S30).

[0040] The flying object 1 activates three components, the laser oscillator 21, the laser beam receiver 22, and the infrared sensor 23 (step S40). The laser oscillator 21 irradiates the laser beam L1 in the forward direction of the axis of the flying object 1 (step S50). The laser beam receiver 22 measures the reflected light corresponding to the laser beam L1. The laser beam receiver 22 sends the measurement result of the reflected light to the control device 5.

[0041] The control device 5 determines whether the laser beam receiver 22 has measured the reflected light based on the measurement result of the reflected light (step S60). When the measurement result of the reflected light is equal to or greater than a specific value, the control device 5 determines that the laser beam receiver 22 has measured the reflected light. When the measurement result of the reflected light is equal to or greater than a specific value, the control device 5 determines that there is a possibility that the flying object 1 is on a direct hit course with the target 50.

[0042] When the laser beam receiver 22 measures the reflected light (step S60, Yes), the infrared sensor 23 measures the temperature of the reflection point (step S70). The infrared sensor 23 sends the temperature measurement result to the control device 5.

[0043] The control device 5 judges whether or not the temperature measured by the infrared sensor 23 is within a temperature range corresponding to aerodynamic heating (step S80). If the temperature at the measurement point is within a temperature range corresponding to aerodynamic heating (step S80, Yes), the control device 5 judges that the laser light L1 measured by the laser light receiver 22 is reflected light from the target 50, and that the flying object 1 will directly hit the target 50 (step S90). In this case, the control device 5 does not output an instruction to search for an enemy using the proximity sensor, and does not execute control of detonation (step S100).

[0044] The control device 5 executes a direct hit destruction control to neutralize the target 50 by making the flying object 1 directly hit the target 50. As a result, the flying object 1 directly hits the target 50, and the target 50 is neutralized (step S110).

[0045] On the other hand, if the temperature at the measurement point is outside the temperature range corresponding to aerodynamic heating (step S80, No), the control device 5 determines that the laser light L1 measured by the laser light receiver 22 is not reflected light from the target 50, but that the laser light receiver 22 has measured reflected light reflected from a place other than the target 50 (step S120). In this case, the control device 5 determines that the flying object 1 will not directly hit the target 50 (step S130). Then, the control device 5 controls the search and detonation using the proximity sensor. As a result, the flying object 1 detects the target 50 by the proximity sensor and executes detonation (step S140). As a result, the fragments of the detonation site collide with the target 50, and the target 50 is neutralized (step S150).

[0046] Furthermore, in step S60, if the laser beam receiver 22 does not measure the reflected light (step S60, No), the control device 5 determines that the laser beam L1 did not hit the target 50 (step S160). In this case, the processes of steps S130 to S150 are executed.

[0047] Here, we will explain the hardware configuration of the control device 5 equipped in the flying object 1. The control device 5 is realized by a processing circuit. The processing circuit may be a processor and memory that executes a program stored in a memory, or may be dedicated hardware.

[0048] 6 is a diagram showing an example of the configuration of a processing circuit in the flying object control device according to the embodiment, which is realized by a processor and a memory. A processing circuit 90 shown in FIG.

[0049] When the processing circuit 90 is composed of a processor 91 and a memory 92, each function of the processing circuit 90 is realized by software, firmware, or a combination of software and firmware. The software or firmware is written as a data processing program and stored in the memory 92. In the processing circuit 90, the processor 91 reads out and executes the data processing program stored in the memory 92 to realize each function. That is, the processing circuit 90 includes a memory 92 for storing a data processing program that results in the processing of the control device 5 being executed. This data processing program can also be said to be a program for causing the control device 5 to execute each function realized by the processing circuit 90. This data processing program may be provided by a storage medium in which the data processing program is stored, or may be provided by other means such as a communication medium.

[0050] Here, the processor 91 is, for example, a CPU (Central Processing Unit), a processing device, an arithmetic device, a microprocessor, a microcomputer, or a DSP (Digital Signal Processor), etc. Also, the memory 92 is, for example, a non-volatile or volatile semiconductor memory such as a RAM (Random Access Memory), a ROM (Read Only Memory), a flash memory, an EPROM (Erasable Programmable ROM), an EEPROM (Electrically EPROM), a magnetic disk, a flexible disk, an optical disk, a compact disk, a mini disk, or a DVD (Digital Versatile Disc), etc.

[0051] 7 is a diagram showing an example of a processing circuit provided in the control device of the flying object according to the embodiment, which is configured with dedicated hardware. The processing circuit 93 shown in FIG. 7 corresponds to, for example, a single circuit, a composite circuit, a programmed processor, a parallel programmed processor, an ASIC (Application Specific Integrated Circuit), an FPGA (Field Programmable Gate Array), or a combination of these. The processing circuit 93 may be partially realized with dedicated hardware and partially realized with software or firmware. In this way, the processing circuit 93 can realize each of the above-mentioned functions by dedicated hardware, software, firmware, or a combination of these.

[0052] In this way, the flying object 1 according to the embodiment uses the mounted module 20 to determine whether the flying object 1 will hit the target 50 directly during terminal guidance, and selects either neutralization by direct hit or neutralization by debris based on the result of the determination. In this case, the flying object 1 determines whether the target 50 is on the direct hit course of the flying object 1 based on the temperature of the reflection point of the laser light L1 on the target 50 measured using the infrared sensor 23. This allows the flying object 1 to grasp the positional relationship between the target 50 and the flying object 1 during terminal guidance without being affected by radio wave interference or the like, and to select a method of neutralizing the target 50 according to the positional relationship.

[0053] Thus, according to the embodiment, the flying object 1 judges whether or not the measured temperature measured by the infrared sensor 23 when the laser light receiver 22 receives the reflected light is within the temperature range corresponding to aerodynamic heating. Then, when the measured temperature is within the temperature range, the flying object 1 neutralizes the target 50 by executing control of direct hit destruction to neutralize the target 50 by a direct hit. Also, when the laser light receiver 22 does not receive the reflected light and when the measured temperature is not within the temperature range, the flying object 1 neutralizes the target 50 by controlling the search and detonation of the target 50. Therefore, when the flying object 1 can directly hit the target 50, it can neutralize the target 50 with a large force, and even when it cannot directly hit the target 50, it can increase the probability of neutralizing the target 50.

[0054] The configurations shown in the above embodiments are merely examples, and may be combined with other known technologies. Parts of the configurations may be omitted or modified without departing from the spirit of the invention. [Explanation of symbols]

[0055] 1 flying object, 5 control device, 10 outer tube, 20 mounted module, 21 laser oscillator, 22 laser light receiver, 23 infrared sensor, 50 target, 90, 93 processing circuit, 91 processor, 92 memory, L1 laser light.

Claims

1. A laser oscillator for irradiating a target with a laser beam; a laser beam receiver that receives a reflected beam at a reflection point of the laser beam; an infrared sensor that receives infrared rays to measure the temperature of the reflection point; an outer cylinder portion in which the laser oscillator, the laser beam receiver, and the infrared sensor are disposed; a control device for controlling the laser oscillator, the laser beam receiver, and the infrared sensor; Equipped with The control device determines whether or not the measured temperature measured by the infrared sensor when the laser light receiver receives the reflected light is within a temperature range corresponding to aerodynamic heating, and if the measured temperature is within the temperature range, neutralizes the target by executing control of direct hit destruction that neutralizes the target by a direct hit, and if the laser light receiver does not receive the reflected light or the measured temperature is not within the temperature range, neutralizes the target by controlling search and detonation of the target. A flying object characterized by:

2. The control device controls terminal guidance after initial and middle stage guidance based on an instruction from a command device that commands engagement with the target, and controls the laser oscillator, the laser light receiver, and the infrared sensor during the terminal guidance.

2. The flying object according to claim 1 .

3. a plurality of mounting modules each having the laser oscillator, the laser light receiver, and the infrared sensor are disposed on the outer cylinder portion; 3. The flying object according to claim 1 or 2.

Images