JP5044794B2 - Active defense methods against flying objects - Google Patents

Description

  The present invention detects a flying object equipped with an explosive approaching, and reduces the explosive force of the flying object so that the explosive force of the flying object does not damage the defense-side moving device (for example, an automobile). Active defense against flying objects so that the sensors can avoid losing sight of the target point, or by correcting the flying object's path by indicating the wrong target point Regarding the method.

  As a conventional defense method, there is a method of reducing the explosive force of a flying object by equipping a mobile device (for example, an automobile) to be protected with a box filled with gunpowder and firing the box when the flying object collides. It was. However, when a projectile that has two levels of explosives before and after the projectile collides with the mobile device to be protected, the explosive power of the front gunpowder destroys the box containing the explosives provided in the mobile device, The explosive power of the gunpowder at the rear of the projectile damages the moving device, so the gunpowder box equipped on the moving device has a weak defense.

  In addition, as a method of deceiving a flying object that targets the heat of the vehicle body as a moving device to be protected, there is a method of putting a smoke screen around the vehicle body, but the effect is weak when the vehicle is moving Alternatively, there is a method of changing the surface pattern of infrared rays by providing a plurality of heat source bodies on the vehicle body, but since the flying body has not been confused by the rapid position change of the high temperature heat source, the moving device which is an automobile The probability of colliding with was high.

  Then, when detecting the laser beam irradiated to the mobile device to be protected, the method of remotely projecting the deceptive laser beam and misidentifying the flying body's laser sensor may misdetect surrounding ambient light as a laser beam. The light sensitivity was set incorrectly due to external light.

  In the case of a moving device that is a vehicle equipped with a plurality of gunpowder boxes composed of a metal layer sandwiching a layer of gunpowder, which is installed on the surface of a car body, for example, a bonnet or a door, the approach of a non-guided flying object is particularly important. Since there is no means to detect, the flying object equipped with two levels of explosives before and after the flying object comes into contact with the explosive box on the automobile side, and the explosive force of the explosive on the front side causes the explosive box on the automobile side to The car was severely damaged due to the neutralization and the explosive power of the gunpowder at the rear of the projectile.

  In addition, a moving vehicle traveling at a speed of 40 km / h, for example, does not have means for deceiving the infrared sensor of the flying object, so that the flying path of the flying object is other than the direction of the vehicle. However, the vehicle collided with the moving device, which was an automobile, and the automobile was severely damaged.

  In the defense method for remotely irradiating the laser beam for deception when detecting the pulsed or continuous wave laser beam irradiated to the automobile for guiding the flying object coming in, the wavelength used by the light receiver Since the area is visible light, foreign light is misdetected and fraudulent light is mistakenly projected, or unnecessary light in the visible light range including the laser wavelength range or laser wavelength range illuminated around the automobile, for example, at night False detection of street light, etc., the threshold value becomes high, scattered laser light cannot be received, laser light for deception with accurate pulse code cannot be irradiated (projection), and the flying object is for that deception The flying object collided with the car without being confused by the laser beam, and the car was severely damaged.

  In view of the above points, the present invention detects a flying object approaching and reduces the explosive force of the flying object, reduces the sensor function of the flying object, or determines the course of the flying object. An object of the present invention is to provide an active defense method against a flying object that can be mistaken.

  Other objects and novel features of the present invention will be clarified in embodiments described later.

An active defense method against a flying object according to the present invention is:
A light receiving unit of the light receiving direction of a plurality of different laser beams, and a non-directional antenna and radio receiver may be provided on the defending mobile device,
When receiving radio waves with the radio wave receiver through the omnidirectional antenna, a step of sequentially selecting and operating a plurality of Peltier elements installed on the surface of the defense side moving device;
The amount of visible light at the detection wavelength of the light receiver is calculated from the amount of ultraviolet light around the defense-side moving device, and exceeds the threshold of the amount of visible light at the detection wavelength of the light receiver determined based on the calculated amount of visible light. When the reflected light of the laser is received by any one of the laser light receivers, the received Peltier element in the light receiving direction of the light receiver is selected from the plurality of Peltier elements to operate, and the background temperature of the ground or surface object and a step of Ru is changed to an equivalent temperature,
It is characterized in that the sensor function of a flying object equipped with an infrared sensor and combined with radio wave irradiation is lowered so that the defense side moving device cannot be detected.
The radio wave receiver may be a millimeter wave receiver.

  By using the active defense method for a flying object of the present invention, it is possible to reduce or avoid damage to a defense side moving apparatus such as an automobile due to the explosive force of the flying object approaching at high speed.

It is Embodiment 1 of the active defense method with respect to the flying body which concerns on this invention, Comprising: It is a block diagram which shows a circuit structure when a radar and an explosive unit are combined. In Embodiment 1, it is the external view which installed the gunpowder unit and the antenna group of the radar in the motor vehicle. It is a top view which shows the relationship between the antenna group and flying body in the said radar. FIG. 3 is an explanatory diagram of a time series of pulses input to a propagation time detector in the circuit configuration of the first embodiment. Embodiment 2 of an active defense method for a flying object according to the present invention, which has a circuit configuration in which the function is improved by adding means for detecting the operation of an automobile as a defense side moving device to Embodiment 1. FIG. It is Embodiment 3 of the active defense method with respect to the flying body which concerns on this invention, Comprising: It is a block diagram which shows a circuit structure when a radar and a Peltier device unit are combined. In Embodiment 3, it is the external view which installed the Peltier device unit and the antenna group of the radar in the motor vehicle. It is Embodiment 4 of the active defense method with respect to the flying body which concerns on this invention, Comprising: It is a top view which shows the relationship between the antenna group in a radar, and a flying body. FIG. 10 is a three-dimensional view showing a relationship between an antenna group and a flying object in a radar according to a fifth embodiment of an active defense method against a flying object according to the present invention. It is Embodiment 6 of the active defense method with respect to the flying body which concerns on this invention, Comprising: It is a three-dimensional view which shows the relationship between the antenna group in a radar, and a flying body. Embodiments 7 and 8 of the active defense method for a flying object according to the present invention, showing a circuit configuration when receiving a laser beam for guiding the flying object and projecting a direct modulation type deception laser beam. It is a block diagram. It is explanatory drawing which showed the outline of the light reception area | region of the laser irradiated with respect to the motor vehicle, the spread of the diffuse reflection light, and the light reception light projection unit installed in the motor vehicle. It is explanatory drawing which showed the principle which a flying body flies based on the diffused reflected light by projecting a laser beam with respect to a motor vehicle. It is explanatory drawing which showed the predicted flight path | route of the flying body when the deception laser is projected from the light reception light projection unit. It is the graph which showed the relationship between the wavelength of sunlight, and utilization energy. FIG. 10 is a block diagram showing a circuit configuration when an active defense method for a flying object according to a ninth embodiment of the present invention is received, and a laser beam for guiding a flying object and a deceptive laser beam of an external modulation system are projected. It is. It is Embodiment 10 of the active defense method with respect to the flying body which concerns on this invention, Comprising: It is a block diagram which shows a circuit structure when combining a millimeter wave receiver, a laser beam receiver, and a Peltier device unit.

In the following, an embodiment of an active defense method for a flying object will be described with reference to the drawings as the best mode for carrying out the present invention.
A first embodiment of an active defense method for a flying object according to the present invention will be described with reference to FIGS. FIG. 1 is a block diagram of the circuit configuration of the first embodiment, and FIG. 2 shows that three antennas are installed on the upper part (roof) of the automobile as a defense side moving device, and a plurality of gunpowder boxes are installed on the left side of the automobile. FIG. 3 is a plan view showing simultaneous equations for deriving the relationship between the flying object to be detected and the three antennas and the position of the flying object.

  FIG. 1 is a block diagram of an overall configuration including a radar for detecting a flying object and a means for igniting a gunpowder box corresponding to an estimated position when the flying object collides with the automobile, which is provided in an automobile which is a defense side moving apparatus. is there. An omnidirectional radar that detects a flying object uses a single transmission / reception antenna 6 and two reception antennas 16 to transmit a continuous wave transmission wave 7 that is code-modulated from the single transmission / reception antenna 6. A transmission means is provided corresponding to the transmission / reception antenna 6 and the two reception antennas 16 and receives a reflected radio wave (reception wave 9) in which the transmission radio wave transmitted by the transmission means is reflected by the flying object 8. Receiving means. The transmission / reception antenna 6 corresponds to the reception unit A10, and the two reception antennas 16 correspond to the reception unit B17 and the reception unit C18, respectively.

  FIG. 2 is a schematic diagram when the antenna group is installed in the automobile 35. One transmitting / receiving antenna 6 and two receiving antennas 16 are, for example, omnidirectional whip antennas, is set up. Each antenna may be a batch antenna as long as it exhibits characteristics close to omnidirectionality.

  In addition, the automobile 35 shown in FIG. 2 is equipped with a gunpowder unit 21 having a gunpowder box at a plurality of locations such as the left and right side surfaces (doors) and the front surface (bonnet) of the automobile body. A gunpowder box is a box filled with gunpowder, specifically a box with a metal layer sandwiching a layer of gunpowder, set to release thermal power from the automobile surface to the side facing the space, and the metal layer is formed by ignition. It has a function of reducing the explosive force of the flying object by flying and damaging the flying object.

FIG. 3 shows the positional relationship between a flying object as a moving object and an antenna group as viewed from above, with a transmitting antenna and a receiving antenna arranged on a plane. Each antenna of the antenna group in this figure is arranged at each vertex of an equilateral triangle, and one antenna is used for both transmission and reception. That is, the transmitting / receiving antenna 6 is located at the vertex A (d, 0) of the equilateral triangle indicated by the XY orthogonal coordinates on the XY plane (specifically, the horizontal plane) formed by the X axis in FIG. 3 and the Y axis orthogonal thereto. Receiving antennas 16 are disposed at B (0, 3 ^1/2 · d) and C (−d, 0), respectively. The antenna arrangement point in FIG. 3 represents a feeding point. For example, when the antenna is a whip antenna, the length is not considered. The position of the flying object 8 is indicated by coordinates (x, y). A reflected radio wave obtained by reflecting a transmission wave 7 (a continuous wave code-modulated as described later) transmitted from the transmission / reception antenna 6 is received by the antennas 6 and 16 at three points as a reception wave 9.

  The coordinates (x, y) of the flying object 8 moving on the XY plane are calculated by solving the binary simultaneous equations (1) described in FIG. The equation (1) is an equation when the antenna is arranged as shown in FIG. 3, and the equation changes when the arrangement is different as shown in FIG. 8 (FIG. 8 will be described later).

Here, when the flying object flies over a space that is not on the XY plane, an error occurs in the radio wave time t _A in the equation (1), and thus an error occurs in the coordinates (x, y) of the flying object 8. Come. In this case, it is wise to apply the antenna arrangement of FIG. 9 (FIG. 9 will be described later). If the XY plane cannot be physically maintained, such as when there are restrictions on the unevenness of the automobile body or the location where it can be installed as shown in FIG. 2, the antenna is on a multi-plane that is vertically displaced from the XY plane near the XY plane ( That is, it may be arranged in a region close to the XY plane. In this case also the error occurs in t _A, the coordinates of the projectile (x, y) error arises in.

  In the radar shown in FIG. 1, the transmission means for transmitting the transmission wave 7 of the continuous wave code-modulated from one transmitting / receiving antenna 6 is a high-frequency oscillator 1, a modulator 2, a code generator 3, and a power amplifier. 4. Also, the receiving means corresponding to the point A transmitting / receiving antenna 6 is the receiving unit A10, the receiving means corresponding to the point B receiving antenna 16 is the receiving unit B17, and the receiving means corresponding to the point C receiving antenna 16 is the receiving unit. C18 respectively. Each receiving unit includes a mixer 11, an amplifier 12, a band pass filter (BPF) 13, a waveform shaper 14 and a correlator 15. The code generator 3 and the circulator 5 are shared by the transmission means and the reception means, and the propagation time detector 19 and the computer 20 are shared by each reception unit.

  As shown in FIG. 1, the gunpowder unit 21 provided in the car 35 of FIG. 2 is composed of a shorting switch 22, a detonator 23, and a gunpowder box 24 for releasing thermal power from the car surface toward the space. 20 is selectively fired.

  The computer 20 has functions of a flying object position calculation, a flying object future position calculation, a flying object speed calculation, a firing box selection (selection of a gunpowder box to be fired), and a firing command.

  The short-circuit switch 21 is in a short-circuit state so that electricity is not supplied to the detonator 23 when no command is received from the computer 20, so that the gunpowder box 24 is not accidentally ignited.

  The overall operation according to the configuration of the first embodiment will be described.

The carrier wave output from the high-frequency oscillator 1 of the radar transmission means included in FIG. 1 is modulated by the modulator 2 with a code such as an M-sequence code or a GOLD sequence code created by the code generator 3, and is output by the power amplifier 4. The power is amplified and transmitted as a transmission radio wave from the transmission / reception antenna 6 via the circulator 5. Assuming that the frequency of the transmission wave 7 is f, the frequency of the reception wave 9 that is a reflected radio wave reflected from the approaching flying object 8 is f + f _d , and the Doppler frequency f _d is added.

Video In the receiving means of the radar, the received wave 9 whose main mixer at 11, is mixed with the carrier wave of the output of the high frequency oscillator 1 frequency f _d of the street receiving unit A10 a transceiver antenna 6, the circulator 5 at point A The signal is extracted, amplified by the amplifier 12, and input to the waveform shaper 14 through the BPF 13 that passes only the desired frequency band. The waveform shaper 14 converts the signal into a high signal and a low signal, and inputs the digital signal to the correlator 15.

  The output code of the waveform shaper 14 and the reverse sign of the code of the code generator 3 are input to the correlator 15 (for example, SAW convolver), and a correlation pulse signal is output when the correlation is obtained. Here, the reverse code means that one cycle of a code used for modulation at the time of transmission is [1011. . . 1010], the reverse sign is an array of 0, 1 numbers from the end of one cycle to the top [0101. . . 1101].

In the propagation time detector 19, the time between the code generation trigger notifying the start of one cycle of the code from the code generator 3 and the correlation peak output of the correlator 15 in the receiving unit A10, that is, the radio wave transmitted at point A is The propagation time t _A when reflected by the flying object 8 and received at point _A is output.

On the other hand, the received radio wave 9 received through the receiving antenna 16 at the points B and C is input to the receiving unit B17 and the receiving unit C18, and operates in the same manner as the receiving unit A10. The radio wave input to the device 19 and transmitted at point A is reflected by the flying object, and the propagation time t _B is received when received at point B. At the same time, the radio wave transmitted at point A is reflected by the flying object and at point C. The propagation time t _C when received is obtained. Since the antenna arrangement is known, the computer 20 as the position calculating means calculates the solution of the simultaneous equations (1) shown in FIG. 3 based on the propagation times t _A , t _B , and t _C , and the flight. The position coordinates (x, y) of the body 8 are calculated every moment, and the speed and the future position are also calculated from the change of the position coordinates (x, y). The prediction of the future position is calculated by performing linear regression on the position of the flying object at high speed in the computer 20.

However the speed of the although not written in the block diagram projectile 8 can be calculated from the frequency f and the Doppler frequency f _d of the carrier of the high frequency oscillator 1 output, even to obtain a radial velocity for the projectile good. However, the line-of-sight speed in this case shows the correct speed when the flying object approaches so as to make a rear-end collision with the transmission / reception antenna 6, but when it approaches so as to graze the transmission / reception antenna 6, an error occurs in the speed.

  FIG. 4 shows the relationship between the code generation trigger of the code generator 3 input to the propagation time detector 19 and each correlation peak. The antenna group and the flying object are in the arrangement shown in FIG.

  In FIG. 4, a pair of a code generation trigger and each correlation peak is repeatedly drawn as time passes. The interval between the code generation triggers is determined by the number of bits in one period of the code and the clock frequency of the code.

  As described above, the position of the flying object 8 is detected by the radar and the future position of the flying object 8 is predicted by the computer 20. As a result, the flying object 8 collides with an automobile to be protected and explodes and damages the automobile. If it is assumed that the explosive unit is selected, the explosive unit 21 corresponding to the estimated collision position is selected, the explosive box 24 is ignited before the flying object 8 collides with the automobile, and the flying object 8 or explosive equipped with the explosive is supplied. The explosive force of the flying object 8 provided in two stages before and after the flying object is reduced to reduce the damage to the automobile.

  According to the first embodiment, the following effects can be obtained.

(1) The automobile 35 shown in FIG. 2 as the defense side moving device can detect and track the approaching flying object 8 at high speed by the radar installed therein. Specifically, one omnidirectional transmitting / receiving antenna and two omnidirectional receiving antennas are arranged at arbitrary points on the same plane (or including multiple planes in the vicinity of the same plane) and transmitted from the transmitting / receiving antenna 6. A code-modulated continuous wave reflected from the flying object 8 is received at a receiving point (a point where one transmitting / receiving antenna 6 and two receiving antennas 16 are arranged), and a plane is generated based on the propagation time of each reflected wave. The flying object 8 approaching above can be detected and tracked at high speed, and it can be estimated which part of the automobile 35 will collide.

(2) The gunpowder box 24 selected by the computer 20 as corresponding to the estimated collision position from among a plurality of gunpowder boxes 24 before the flying object 8 contacts the gunpowder box 24 mounted on the body of the automobile 35. Is fired and the metal layer of the gunpowder box 24 is blown to damage the flying object 8 and reduce the explosive force of the flying object 8.

(3) The radar uses a combination of three omnidirectional antennas, not a rotary antenna that drives an antenna with a motor, and the position information and speed of the flying object 8 that moves (approaches) at high speed. Information can be obtained instantaneously. Therefore, it is possible to secure time for taking measures against the approach of the flying object 8, and as a result, before the flying object 8 contacts the explosive box 24 on the side of the automobile 35. The explosive force of the flying object 8 can be reduced by firing the gunpowder box 24.

(4) Since the transmission wave 7 is a code modulation wave, the mutual interference of the radar and the radio wave interference from other transmission stations are reduced, and the radio wave interference given to the receiving unit by the transmission wave transmitted by itself is suppressed. be able to.

   FIG. 5 shows a block diagram of the second embodiment of the present invention. In this case, the vehicle as the defense side moving device includes any or all of the GPS receiver 25, the vehicle speed pulse (speed pulse) generator 26 for detecting the traveling speed of the vehicle, and the triaxial acceleration sensor 27. Then, new functions are added to the first embodiment shown in FIG. 1 so as to obtain the detailed operation status of the automobile by adding these outputs to the computer 20. Other configurations are the same as those of the first embodiment described above, and the same or corresponding parts are denoted by the same reference numerals and description thereof is omitted.

  The GPS receiver 25 provides an outline of the vehicle speed and the traveling direction of the vehicle, and the details of the vehicle speed can be obtained by a vehicle speed pulse in which the speed and the pulse number output from the vehicle speed pulse generator 26 are proportional to each other. The stop can be obtained from the acceleration of the triaxial acceleration sensor 27. As a result, in addition to the flying object position calculation, the flying object future position calculation, the flying object speed calculation, the ignition box selection (selection of the gunpowder box to be ignited), and the ignition command, the computer 20 calculates the vehicle speed relating to the vehicle operation and the course direction of the vehicle. A calculation function is provided, and the prediction accuracy of the collision position of the flying object 8 can be improved.

  FIG. 6 shows a block diagram of the third embodiment of the present invention, and FIG. 7 shows a configuration in which a Peltier element 33 is mounted on a car 35 as a defense side moving device instead of the explosive unit 21 of FIG. In the example of FIG. 6, at least a Peltier element unit 29 having a plurality of Peltier elements 33 arranged on the left side of the car and a Peltier element unit 29 having a plurality of Peltier elements 33 arranged on the right side of the car are provided. Each Peltier element unit 29 includes a switch 30, a polarity direction switch 31, a current controller 32, and a temperature sensor 34 in addition to the Peltier element 33. When the Peltier element unit 29 is selected from the computer 20, the switch 30 supplies power to the Peltier element 33 via the polarity direction switch 31 and the current controller 32. The polarity direction switch 31 switches whether the front side of the Peltier element 33 (the side facing the space from the automobile surface) is heated or cooled. The temperature sensor 34 monitors the surface temperature of the Peltier element 33 and controls the current by the current controller 32 so that the temperature becomes a background simulation temperature.

  Further, an infrared sensor 28 for detecting the temperature of the ground or a surface object (for example, trees) is mounted on the automobile, and the temperature detection output is applied to the computer 20. As a result, in addition to the flying object position calculation, the flying object future position calculation, the flying object speed calculation, the vehicle speed calculation, and the vehicle course direction calculation function, the computer 20 has a background temperature calculation, a Peltier element unit selection, and a Peltier element temperature setting function. Have. Other configurations are the same as those of the second embodiment described above, and the same or corresponding parts are denoted by the same reference numerals and description thereof is omitted.

  In this case, the approach of the flying object 8 is detected by the radar, the Peltier element unit 29 near the position where the flying object 8 is predicted to collide is selected by the computer 20, and a plurality of Peltier elements installed on the left side surface of the automobile, for example, are selected. The element 33 is quickly changed to a specific temperature. The specific temperature is a background simulation temperature calculated by the computer 20 based on the background temperature of the ground or surface object obtained from the infrared sensor 28 or the background temperature and the density of the Peltier elements 33 installed in the automobile. It is said. For example, if there is a vehicle body part where the Peltier element 33 is not installed, the background simulation temperature is set so that the average temperature of the Peltier element 33 and the area of the vehicle body part without the Peltier element approaches the background temperature. can do.

  In this way, the Peltier element 33 near the position where the flying object 8 is predicted to collide is selected and operated, and the temperature is changed to a temperature equivalent to the background temperature of the ground or surface object. As the surface temperature of the Peltier element 33 approaches the background temperature, the infrared sensor (temperature sensor) of the flying object 8 captured and flying as a target based on the temperature difference between the background temperature and the body of the automobile 35 is used in the background. It can be deceived as being present, and it is possible to remove the capture and not to update the new flight path of the flying object 8, that is, to keep the current traveling direction and not to follow the movement of the vehicle position with the speed of the vehicle 35. it can.

  In addition, for the infrared sensor of the remote flying object 8, it appears that the target has disappeared and deceives it, whether the car 35 is moving or stationary, and the new flying object 8 has searched. It can be prevented from colliding with the automobile by heading to the heat source.

  FIG. 8 is a fourth embodiment of the present invention, and shows another example of the antenna arrangement of the radar provided in the automobile as the defense side moving apparatus. FIG. 8 shows the simultaneous equations for deriving the positional relationship between the flying object and the antenna group and the position of the flying object when the transmitting antenna and the receiving antenna are arranged on a plane and viewed from above. The transmitting / receiving antenna 6 is connected to the apex A (2d, 0) of the right triangle on the XY plane (specifically, the horizontal plane) of FIG. 8 and the apex B (0, d), C (0 , 0) is provided with a receiving antenna 16, respectively. The antenna arrangement point in FIG. 8 represents a feeding point.

The radar transmitting means and receiving means are as shown in the block diagram of FIG. 1, and in the computer 20 based on the known antenna arrangement and propagation times t _A , t _B and t _C as in the first, second and third embodiments. The solution of the simultaneous equations (2) shown in FIG. 8 can be calculated, and the position coordinates (x, y) of the flying object 8 can be calculated. Then, the future position of the flying object is calculated from the position coordinates of the flying object, and the explosive force of the flying object 8 is obtained by selecting and firing one of the gunpowder boxes provided in the automobile as in the first and second embodiments. Can be attenuated. Alternatively, when the automobile includes the Peltier element unit 29 having the Peltier element 33 as in the third embodiment, any one of the plurality of Peltier element units 29 is selected and operated, and the selected Peltier element 33 is It is possible to make the vehicle undetectable by changing the temperature of the flying object 8 equipped with the infrared sensor to a temperature equivalent to the background temperature of the ground or the surface object, and lowering the sensor function.

FIG. 9 is a fifth embodiment of the present invention and shows another example of the antenna arrangement of the radar provided in the automobile as the defense side moving apparatus. FIG. 9 shows the positional relationship between the antenna group in which the receiving antenna 16 is added to the XZ plane perpendicular to the XY plane or the YZ plane and the flying object 8 in the space, and simultaneous equations for deriving the position of the flying object. is there. Each antenna of the antenna group in this figure is arranged at each vertex of a triangular pyramid having ABCD as a vertex, and one antenna is used for both transmission and reception. That is, transmission and reception antenna 6 at the apexes of an equilateral triangle A (d, 0,0) indicated by the XYZ orthogonal coordinates on the XY plane (horizontal plane specifically) of FIG. 9, the vertex B ^{(0, 3 1/2} · d, 0), C (−d, 0, 0), the receiving antenna 16 is arranged in the same manner as in FIG. 3, and a vertex D (0, 0, 3 ^1/2. A receiving antenna 16 is arranged in d). As in FIG. 3, in FIG. 9, the antenna arrangement point represents a feeding point.

  The coordinates (x, y, z) of the flying object 8 moving in the XYZ space are calculated by solving the ternary simultaneous equations (3) shown in FIG. The equation (3) is an equation when the antennas are arranged as shown in FIG. 9, and the equation changes depending on the arrangement.

The propagation times t _A , t _B , t _C , and t _d in the equation (3) are the same as those in FIG. 1 (however, a receiving unit D (not shown) corresponding to the receiving antenna 16 at point D is added). ).

 According to the fifth embodiment, even when the flying object 8 moves in a space away from the XY plane, the position of the flying object 8 can be calculated with higher accuracy by taking the height in the Z-axis direction into consideration. Is possible. Then, the future position of the flying object is calculated from the position coordinates of the flying object, and the explosive force of the flying object 8 is obtained by selecting and firing one of the gunpowder boxes provided in the automobile as in the first and second embodiments. Can be attenuated. Alternatively, when the automobile includes the Peltier element unit 29 having the Peltier element 33 as in the third embodiment, any one of the plurality of Peltier element units 29 is selected and operated, and the selected Peltier element 33 is It is possible to make the vehicle undetectable by changing the temperature of the flying object 8 equipped with the infrared sensor to a temperature equivalent to the background temperature of the ground or the surface object, and lowering the sensor function.

FIG. 10 is a sixth embodiment of the present invention, and shows another example of the antenna arrangement of the radar provided in the automobile as the defense side moving apparatus. In FIG. 10, the transmitting / receiving antenna 6 is arranged on the Z axis, and two receiving antennas 16 are arranged not only on the X axis but also on the Y axis, and the position of the flying object 8 in space with these antenna groups. The simultaneous equations for deriving the relationship and the position of the flying object are shown. Vertices of an equilateral triangle indicated by XYZ orthogonal coordinates on the XY plane in FIG. 10 A (d, 0,0), the vertex ^{B (0,3 1/2 · d, 0} ), the vertex C (-d, 0,0) Is arranged at a point D (0, −3 ^1/2 · d, 0) symmetrical to the vertex B with respect to the X axis, and further from the XY plane in the Z axis direction. The transmitting / receiving antenna 6 is arranged at the shifted vertex E (0, 0, 3 ^1/2 · d). As in FIG. 3, in FIG. 10, the antenna arrangement point represents a feeding point.

  In the case of the sixth embodiment, the transmission unit and the reception unit may have the same configuration as in FIG. 1 (however, a reception unit corresponding to the number of reception antennas is added).

  In the case of the antenna group of FIG. 10, since two receiving antennas are arranged on the Y axis, spatial diversity is formed, and when the radio wave 9 of one receiving antenna on the Y axis is weak, the other receiving antenna is strong. The correlation peak is preferentially used based on the output of the waveform shaper 14 of FIG. Therefore, fading due to multipath can be prevented (changes in the received wave can be prevented), and thus position data can be prevented from missing, and the accurate position coordinates (x, y, z) of the flying object 8 can be obtained. Then, the future position of the flying object is calculated from the position coordinates of the flying object, and the explosive force of the flying object 8 is obtained by selecting and firing one of the gunpowder boxes provided in the automobile as in the first and second embodiments. Can be attenuated. Alternatively, when the automobile includes a Peltier element unit having a Peltier element as in the third embodiment, any one of the plurality of Peltier element units is selected and operated, and the selected Peltier element is used as the ground or surface object. It is possible to make the vehicle undetectable by lowering the sensor function of the flying object 8 equipped with an infrared sensor by changing the temperature to the same temperature as the background temperature of the vehicle.

  Instead of providing two receiving antennas on the Y-axis, spatial diversity may be configured by arranging two receiving antennas on the Z-axis.

  Thus, by arranging more receiving antennas than the minimum necessary number, it is possible to configure space diversity and improve the radar tracking performance.

  In the first to sixth embodiments, the three antennas are arranged on the XY plane. However, the position of each antenna on the XY plane is arbitrary, and any three of the regions close to the XY plane are used. An antenna placed at each point can also be used.

  In Embodiments 5 and 6, when four or more antennas are used, the antennas arranged at three or more points on the XY plane or in a region close to the XY plane, and the XY plane or the XY plane It is possible to use an antenna disposed on an XZ or YZ plane perpendicular to a region close to or an arbitrary point in a region close to the plane.

  In general, the XY plane is set to the horizontal plane and the Z-axis is set to the vertical direction. However, the present invention can be applied even if the XY plane is a plane having a predetermined angle with respect to the horizontal plane and the Z-axis is perpendicular thereto. .

  Embodiments 7 and 8 of the present invention will be described with reference to FIGS. Here, the seventh embodiment whose block diagram is shown in FIG. 11 is a protection method when pulsed laser light has been irradiated in the case of protecting a flying object that is aimed at the position irradiated with laser light. The eighth embodiment shown in the same block diagram is a defense method corresponding to a continuous wave (monopulse) laser (when a continuous wave laser beam has been irradiated).

  First, in FIG. 12 to FIG. 14, the state of diffuse reflected light when the vehicle that is the target of the flying object is irradiated with the laser beam, the flying principle of the flying object flying with the position irradiated with the laser beam as the target, etc. Will be described.

  FIG. 12 is a side view of a flying object flying with the position irradiated with the laser beam as a target. When the laser beam 38 is irradiated or projected on the left side surface of the automobile 35 which is a defense side moving device, it diffuses. The reflected light spreads, resulting in an angular range 39 that includes weak diffusely reflected light. FIG. 12 shows a light receiving area 37 of the laser in the light receiving and projecting unit 36 (equipped in the automobile 35) having the light receiver and the projector at this time.

  FIG. 13 is a plan view showing the flying principle of a flying object. When a third person projects laser light 38 from the projector 41 onto the automobile 35, it includes strong diffuse reflected light together with an angle range 39 including weak diffuse reflected light. An angle range 40 is generated, and the flying object 8 moves toward the automobile 35 while drawing a flight path 42 based on the angle range 40 including strong diffuse reflected light.

  FIG. 14 is a plan view showing a flight path when the flight path of the flying object 8 flying aiming at the position irradiated with the laser beam is forced by deception. When the weakly diffuse reflected light of the laser beam 38 is received, the deceptive laser beam 43 is projected from the light receiving / projecting unit 36 to a position away from the automobile 35. At this time, an angle range 44 including strong diffuse reflected light due to deceptive light is generated at the position where the deceiving laser beam 43 is projected, and the flying object 8 flies on a new flight path 45.

  In Embodiment 7 using the configuration of the block diagram of FIG. 11 (protection method when pulsed laser light is irradiated), first, laser light 38 of a pulse (signal such as digital 01001011) (see FIGS. 12 and 13). ) Is received by the light receiver 46 and applied to the gate 49 and the gate 51 as an electrical signal. In the gate 49, when the threshold output of the threshold setter 48 is exceeded, the output voltage of the light receiver 46 is applied to the counter or integrator 50. In the counter, the number of pulses per unit time is counted and when the preset number is reached, the gate 51 is opened for a certain period of time, or the pulse of the voltage output from the light receiver 46 is integrated by an integrator using an operational amplifier to obtain a preset voltage. When it reaches, the gate 51 is opened for a certain time.

  FIG. 15 shows the relationship between the wavelength of sunlight and the energy used, and the intensity relationship between the energy used for ultraviolet rays used by the threshold value setting ultraviolet sensor 47 of the threshold setting device 48 and the energy used for visible light can be seen. Based on this relationship, the intensity of visible light can be calculated by the threshold setting device 48 from the intensity of ultraviolet rays around the automobile due to the weather of an arbitrary date and time. That is, the threshold value setter 48 can calculate the visible light amount at that time from the amount of ultraviolet light detected by the ultraviolet sensor 47, and can set the threshold value corresponding to the calculated visible light amount.

  The threshold value output by the threshold setting unit 48 is determined as follows. The UV sensor 47 that detects the UVA (long wavelength UV) band in the sunlight spectrum of FIG. 15 determines the amount of UV light around the automobile 35, and the average amount of energy used at this time is 50% (FIG. 15). The amount of visible light based on sunlight when the detection wavelength of the light receiver 46 is set to 500 nm is determined from FIG. The threshold is a voltage corresponding to the amount of energy used exceeding 90%.

  The relationship between the wavelength and the energy used in FIG. 15 is recorded in the threshold setting device 48, and the threshold is sequentially set according to the amount of ultraviolet rays, that is, according to arbitrary weather, and the light in the visible light region or the laser wavelength region is set. Light such as an unnecessary electric lamp that is emitted does not affect the threshold value, and the threshold value is increased by general electric lamp light, so that weak laser scattered light cannot be received.

  Since the gate 51 is not opened unless the number of pulses set by the counter or integrator 50 is reached, the false detection probability is further reduced. In particular, in the case of a counter, continuous laser light and continuous visible light can be cut, which is effective for detecting pulsed laser light.

  When the gate 51 is opened, the waveform shaper 52 mainly regenerates a distorted pulse train, but the threshold value output of the threshold value setter 48 is also added to the waveform shaper 52, and only the signal having a voltage equal to or higher than the threshold value is used. A pulse train corresponding to the irradiated pulsed laser beam is generated. The reason for this is to prevent a code error due to noise when generating a pulse train when light having the same wavelength as the laser wavelength is included as noise. By applying the pulse train generated by the waveform shaper 52 to the laser diode 53, the laser diode 53 directly modulates the fraudulent laser beam 43, amplifies it by the optical amplifier 54, and as shown in FIG. The deception laser beam 43 is projected to a position away from the automobile 35 from the projector of the light receiving and projecting unit 36 mounted on the vehicle. As a result, an incorrect course can be shown for the flying object 8, and the course of the flying object 8 is corrected so as not to collide with the automobile. In this case, since the laser diode 53 is directly turned on and off for modulation, the wavelength of the laser light generated in the laser diode 53 fluctuates when the laser diode 53 is turned on.

  In the waveform shaper 52, when the output signal from the light receiver 46 stops for a certain period of time, the waveform before being interrupted that is sequentially recorded in the memory in the waveform shaper 52 is output for a certain period of time. This prevents a break.

  In the eighth embodiment using the configuration of the block diagram of FIG. 11 (protection method when continuous wave laser light has been irradiated), first, the continuous wave laser light 38 (see FIGS. 12 and 13) is received by the light receiver 46. And is applied to the gate 49 and the gate 51 as an electrical signal. In the gate 49, when the threshold output of the threshold setter 48 is exceeded, the output voltage of the light receiver 46 is applied to the integrator 50. When the integration value by the integrator 50 reaches a preset voltage, the gate 51 is opened for a predetermined time. Subsequent operations are the same as in the seventh embodiment (protection method when pulsed laser light has been irradiated).

  In the case of Embodiments 7 and 8 in FIG. 11, a sensor that detects a pulsed or continuous wave laser beam emitted by a third party toward a vehicle for the purpose of guiding a flying object is used. At this time, in order not to detect the combined light of the laser light and the ambient light, the visible light is cut using the ultraviolet sensor 47 without using the same visible light sensor as the laser light, and the threshold setting unit 48 The amount of visible light in the laser wavelength band around the automobile is calculated from the amount of ultraviolet rays, and the threshold value is set corresponding to the calculated value. Then, by detecting the laser beam with the intensity exceeding the threshold, the false detection probability is lowered, and a pulse or continuous wave deception laser beam equivalent to the irradiated laser beam is projected to a position away from the automobile. By doing so, it is possible to indicate an incorrect course with respect to the flying object, and it is possible to correct the course of the flying object so as not to collide with the automobile.

  FIG. 16 shows a ninth embodiment of the present invention. In the process of producing the deceptive laser beam 43 of FIG. 14, the modulator 55 modulates the output of the laser diode 53 with the output of the waveform shaper 52. Other configurations are the same as those of the seventh and eighth embodiments described above, and the same or corresponding parts are denoted by the same reference numerals and description thereof is omitted.

  As shown in FIG. 16, when the external modulation by the modulator 55 is used, the spectrum of the fraudulent laser beam 43 does not spread and is strongly projected as a single wavelength light.

  FIG. 17 shows a block diagram of the tenth embodiment of the present invention. In this case, the automobile as the defense-side moving device has a plurality of light receivers 46 having different light receiving directions in order to detect laser light, and a direction switching device that is selectively connected to the light receiver 46 for switching the light receiving directions. In addition to a switch 56, an ultraviolet sensor 47, a threshold setting device 48, and a gate 49, an omnidirectional antenna 57 and a millimeter wave receiver 58 are provided to receive millimeter wave radio waves. The computer 20 receives the output of the gate 49 and the output of the millimeter wave receiver 58, the infrared sensor 28, and the Peltier element unit 29 having a plurality of Peltier elements 33.

  The functions of the ultraviolet sensor 47, the threshold setting device 48, and the gate 49 are the same as those of the seventh embodiment shown in FIG. 11, and light such as an unnecessary lamp that emits light in the visible light region or laser wavelength region affects the threshold. In order to prevent light from being scattered, it is possible to prevent a weak laser scattered light from being received due to an increase in threshold value caused by general electric light.

  The configuration including the computer 20, the infrared sensor 28, and the plurality of Peltier element units 29 performs the same function as that of the third embodiment shown in FIG. The computer 20 has laser irradiation surface calculation, background temperature calculation, Peltier element unit selection, and Peltier element temperature setting functions. The computer 20 controls the temperature of the Peltier element 33 to bring the surface temperature of the Peltier element 33 close to the background temperature, and captures and jumps as a target infrared sensor (based on the temperature difference between the background temperature and the vehicle body). Deceiving the background as a temperature sensor).

  In this case, first, a millimeter wave radar wave transmitted from a third party (for example, a flying object) is received by the millimeter wave receiver 58 through the omnidirectional antenna 57 and the information is added to the computer 20. Further, the outputs of a plurality of light receivers 46 having different light receiving directions are applied to the computer 20 through the switch 56. When the computer 20 receives the millimeter wave, it determines that the flying object is approaching. However, since the receiving direction of the millimeter wave is unknown, the Peltier element unit 29 is selected in order to suppress the concentration of power consumption. If the light receiving direction is determined by the specific light receiver 46, only the Peltier element unit 29 in that direction is selected. The set temperature calculation and the Peltier element unit operating method are the same as in FIG.

  The tenth embodiment is effective for defense against a flying object that uses radio wave irradiation together with target tracking.

  In the third embodiment of FIG. 6 and the tenth embodiment of FIG. 17, the Peltier element units having a plurality of Peltier elements are shown as examples provided on the left side and the right side of the car. It may be placed on the roof.

  Although the embodiments of the present invention have been described above, it will be obvious to those skilled in the art that the present invention is not limited to these embodiments, and various modifications and changes can be made within the scope of the claims.

DESCRIPTION OF SYMBOLS 1 High frequency oscillator 2 Modulator 3 Code generator 4 Power amplifier 5 Circulator 6 Transmission / reception antenna 7 Radio wave (transmission wave)
8 Flying object 9 Radio wave (received wave, transmitted wave reflected from flying object)
10, 17, 18 Receiving unit 11 mixer 12 amplifier 13 BPF (band pass filter)
DESCRIPTION OF SYMBOLS 14 Waveform shaper 15 Correlator 16 Reception antenna 19 Propagation time detector 20 Computer 21 Gunpowder unit 22 Short-circuit switch 23 Detonator 24 Gunpowder box 25 GPS receiver 26 Vehicle speed pulse generator 27 3-axis acceleration sensor 28 Infrared sensor 29 Peltier device unit 30 Switch 31 Polarity direction switch 32 Current controller 33 Peltier element 34 Temperature sensor 35 Automobile 36 Light receiving and projecting unit 37 Light receiving area of the light receiving and projecting unit 38 Laser light 39 Angle range including weak diffuse reflected light 40 Angle including strong diffuse reflected light Range 41 Projector 42 Flight path 43 Deceptive laser light 44 Angular range including strong diffuse reflected light due to deception light 45 New flight path 46 Light receiver 47 Ultraviolet sensor 48 Threshold setting device 49, 51 Gate 50 Counter or integrator 52 Wave Shaper 53 laser diode 54 an optical amplifier 55 modulator 56 switches 57 antenna 58 millimeter wave receiver

Claims (2)

A light receiving unit of the light receiving direction of a plurality of different laser beams, and a non-directional antenna and radio receiver may be provided on the defending mobile device,
When receiving radio waves with the radio wave receiver through the omnidirectional antenna, a step of sequentially selecting and operating a plurality of Peltier elements installed on the surface of the defense side moving device;
The amount of visible light at the detection wavelength of the light receiver is calculated from the amount of ultraviolet light around the defense-side moving device, and exceeds the threshold of the amount of visible light at the detection wavelength of the light receiver determined based on the calculated amount of visible light. When the reflected light of the laser is received by any one of the laser light receivers, the received Peltier element in the light receiving direction of the light receiver is selected from the plurality of Peltier elements to operate, and the background temperature of the ground or surface object and a step of Ru is changed to an equivalent temperature,
An active defense method for a flying object, characterized in that an infrared sensor is mounted and a sensor function of the flying object that uses radio wave irradiation is lowered so that the defense side moving device cannot be detected. The active defense method for a flying object according to claim 1, wherein the radio wave receiver is a millimeter wave receiver.

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