JP5438993B2 - Guided projectile - Google Patents

Description

  The present invention relates to a flying object.

  Conventionally, a flying object has been provided with a radio wave seeker that guides the flying object according to the target to be tracked, and it is known that there are active and semi-active antennas used as a radio wave seeker. ing. In the active antenna, the radar wave transmitted from itself is reflected from the target, and the flying object is guided so as to track the target based on the reflected radar wave. Further, in the semi-active antenna, the radar radio wave transmitted from the high-power ground radar is reflected by the target, and the flying object is guided so as to track the target based on the reflected radar radio wave.

JP 59-81499 A

  By the way, for example, a stealth machine may be tracked as a target. Since this stealth machine includes a radio wave absorber that absorbs high-frequency radar, it is considered difficult to track the above-described radio wave reflected waves. However, if this radio wave absorber is a low frequency radar radio wave, it will be reflected without being absorbed, so when tracking a stealth aircraft as a flying object, it is important to be able to receive the low frequency radar radio waves reflected by the stealth aircraft. Become.

  However, according to Japanese Patent Application Laid-Open No. 59-81499 of the above-mentioned Patent Document 1, the antenna is limited to a size that can be accommodated in the front end portion because the front end portion of the airframe has a radio wave seeker (antenna). . For this reason, the frequency band of the radar radio wave that can be received is limited, the low-frequency radar radio wave cannot be received, and there is a problem that it is difficult to track a stealth machine.

  The present invention has been made to solve the above problems, and an object thereof is to provide a flying object capable of receiving a low-frequency radar radio wave.

  In order to solve the above problems, the present invention employs the following means.

The present invention is a flying body whose position is controlled based on radar radio waves received by the antenna device, the antenna device comprising a plurality of antenna groups, the antenna group having a plurality of antenna elements, The antenna elements provided in the axial direction of the surface of the airframe are provided at predetermined intervals, and the antenna elements included in the antenna groups are arranged adjacent to each other, and in a band shape over the entire circumference of the fuselage of the airframe. The two antenna groups of the antenna devices are arranged in the vicinity of the front end of the fuselage of the fuselage and in the vicinity of the rear end of the fuselage, and then separated from an aircraft etc. Provided is a guided vehicle that is guided toward the vehicle .

According to such a configuration, antenna groups including a plurality of antenna elements are arranged at a plurality of locations on the surface of the body, and an antenna device is configured by the plurality of antenna groups. Thereby, the area which receives a radar electromagnetic wave can be increased, and the opportunity to receive a radar electromagnetic wave can be increased. Further, since reception is performed with an antenna having a large area, not only radar radio waves but also radio waves in a wide frequency range can be received.
In addition, since the antenna group in which the antenna elements are arranged in a band shape over the circumferential direction of the airframe is provided at a predetermined interval in the axial direction of the airframe, the antenna device composed of a plurality of antenna groups can be enlarged. A low-frequency radio wave having a long wavelength can be transmitted and received. Further, the predetermined interval at which each antenna group is provided on the airframe is more preferably equal. Furthermore, the antenna elements are preferably arranged over the entire circumference in the circumferential direction of the trunk.
Furthermore, by arranging two antenna groups in the antenna device in the vicinity of the front end and the rear end of the fuselage, the antenna groups can be arranged over a wide range with respect to the axial direction. The accuracy of synthesis can be improved.

In the guided vehicle which is guided toward a predetermined target after being separated from the aircraft or the like, each antenna group may include the same number of the antenna elements .
Thereby, the precision in the case of synthesizing the radar radio wave received by the antenna can be improved.

In a guided vehicle that is guided toward a predetermined target after being separated from the aircraft or the like, the vehicle includes a control unit that switches between transmission and reception of radar radio waves of the antenna device, and the control unit includes the antenna group. It is also possible to control the control parameter of the radio wave transmitted from the antenna group and transmit it from the antenna group.

  As described above, the control unit that switches between transmission and reception of the antenna device is provided, and the control unit of the radio wave transmitted from the antenna group is controlled by the control unit, and a beam is formed and transmitted. As a result, not only reception of radio waves but also formation and transmission of a desired transmission beam can be used for data communication. The control parameters are, for example, the phase difference of radar radio waves transmitted from the antenna group and the amplitude of radar radio waves.

  According to the present invention, it is possible to receive a low-frequency radar radio wave.

It is the figure which showed the external appearance of the guidance flying body which concerns on embodiment of this invention. It is a block diagram which shows the function of an antenna device.

Hereinafter, an embodiment of a flying object according to the present invention will be described with reference to the drawings.
The flying object according to the present invention will be described by taking a guided flying object guided to a predetermined target after being separated from an aircraft or the like as an example. Moreover, although a target is demonstrated as being a stealth machine, it is not limited to this. In addition, although the case where there are three antenna groups of the antenna device provided in the flying object of the present invention is described as an example, the number of antenna groups is not particularly limited. The number of antenna groups may be two or more, and the accuracy can be improved as the number increases.

FIG. 1 is a diagram showing the appearance of a guided flying object 1 according to an embodiment of the present invention.
The guided flying object 1 includes an antenna device 10. For example, the antenna device 10 is used as a radio wave seeker that measures a distance from a target. The antenna device 10 receives reflected waves of a high-frequency radar (for example, a SAM shooting control radar) and a low-frequency radar (for example, a warning radar) transmitted from the ground toward a stealth machine.

As shown in FIG. 1, the antenna device 10 includes three antenna groups 20a, 20b, and 20c arranged in a distributed manner at a plurality of locations on the surface of the airframe. The antenna groups 20a, 20b, and 20c each have a plurality of antenna elements 30.
Specifically, the antenna groups 20a, 20b, and 20c are provided at predetermined intervals in the axial direction of the airframe (hereinafter referred to as “airframe”) of the guidance flying object 1, and each of the antenna groups 20a, 20b, and 20c. The plurality of antenna elements 30 included in is arranged in a band shape over the circumferential direction of the airframe.

  In addition, the antenna elements 30 are arranged apart from each other so as to be within the area of each antenna group 20a, 20b, 20c (for example, the width of the band when arranged in a band shape). By arranging the antenna elements 30 apart from each other, it becomes easy to compare the phase difference and amplitude of the radar radio waves received by each antenna element 30. Furthermore, by arranging the antenna elements 30 over the entire circumference in the circumferential direction of the fuselage, the area for receiving radar radio waves can be widened and directed to the entire circumference, so that opportunities for receiving radar radio waves can be increased. it can.

  The number of antenna groups 20a, 20b, and 20c is not particularly limited, but the number of antenna elements 30 included in each antenna group 20a may be the same. By aligning the number of antenna elements 30, it is possible to improve the accuracy of the synthesis of radar radio waves received by the antenna elements 30 of the antenna groups 20a, 20b, and 20c.

  Furthermore, it is preferable that two of the three antenna groups are disposed in the vicinity of the front end portion of the airframe and in the vicinity of the rear end portion of the airframe. In the present embodiment, the antenna group 20a is disposed in the vicinity of the front end portion, and the antenna group 20c is disposed in the vicinity of the rear end portion. In this way, by arranging the two antenna groups at the greatest distance, a wider range of radar radio waves can be received.

The antenna groups 20a, 20b, and 20c may be arranged at equal intervals. By setting the equal intervals, accuracy is improved when the radar radio waves are synthesized based on information obtained from the phase difference of the radar radio waves received by each antenna group.
In the present embodiment, since there are three antenna groups 20a, 20b, and 20c, the antenna group 20b that is neither near the front end nor the rear end is disposed at an intermediate position between the antenna group 20a and the antenna group 20c. The antenna groups 20a, 20b, and 20c are arranged at equal intervals.

  The antenna groups 20a, 20b, and 20c are, for example, phased array antennas. By using a phased array antenna, a gimbal can be eliminated.

  FIG. 2 is a block diagram illustrating functions of the antenna device 10 provided in the guided flying object 1. As shown in FIG. 2, the antenna device 10 includes three antenna groups 20a, 20b, and 20c, a transmission / reception switching unit 11, a phase difference detector 12, a radio wave arrival direction calculator 13, and a control unit 14 (control means). ing. The antenna device 10 calculates a target direction based on the received radar radio wave, and outputs the calculation result to an arithmetic device that guides the flying object.

  The controller 14 switches between transmission and reception of the transmission / reception switching unit 11. For example, when the transmission / reception switching unit 11 is switched to the receiver 21 side by the controller 14, radar radio waves are received by the respective antenna elements 30 of the antenna groups 20a, 20b, and 20c, and the received radar radio waves Information is output to the phase difference detector 12. On the other hand, when the transmission / reception switching unit 11 is switched to the transmitter 22 side by the controller 14, the radar radio wave generated in the transmitter 22 is transmitted to each antenna element 30 of each antenna group 20a, 20b, 20c. Sent from

Further, the controller 14 controls the control parameter of the radar radio wave transmitted from the antenna element 30. The control parameter is, for example, the phase difference of radar radio waves transmitted from the antenna group and the amplitude of radar radio waves.
Specifically, when the controller 14 sets the transmission / reception switching unit 11 on the transmitter 22 side, radar radio waves controlled based on the control parameters are transmitted from the individual antenna elements 30. More specifically, the control unit 14 transmits radio waves having a phase difference by controlling the timing of radar radio waves transmitted from each antenna element 30.

  In FIG. 2, the case where each antenna group 20a, 20b, 20c includes two antenna elements 30 has been described, but the number of antenna elements 30 is not limited to this.

  Further, the switching between transmission and reception of the transmission / reception switching unit 11 performed by the controller 14 is collectively set to the same setting for all the antenna elements 30.

When the transmission / reception switching unit 11 is switched to the receiver 21 side, the radar radio wave received by each antenna element 30 is output to the phase difference detector 12.
On the other hand, when the transmission / reception switching unit 11 is switched to the transmitter 22 side, the controller 14 controls the phase of the radio wave transmitted from each antenna element 30 and sends a signal corresponding to this phase or the like to the transmitter 22. Output to. Thereby, electric power for emitting a radio wave beam in a desired direction from the antenna element 30 is supplied from the transmitter 22 to each antenna element, whereby the radio wave beam is emitted from the antenna element 30 in the desired direction.

  As described above, the transmission / reception switching unit 11 can switch between the receiver 21 and the transmitter 22 by the control unit 14 so that each antenna element 30 can receive the radar radio wave and emit the radar radio wave. .

  In addition, since the transmission / reception switching unit 11 can switch transmission / reception of the antenna element 30 by the control unit 14, the antenna element 30 can also be used as a communication antenna with the ground device.

The phase difference detector 12 measures the phase difference of the radar radio wave received from the antenna element 30 and outputs the phase difference φ of the measurement result to the radio wave arrival direction calculator 13.
The radio wave arrival direction calculator 13 calculates the direction in which the radio wave reflected from the target has arrived based on the phase difference φ measured by the phase difference detector 12, and the calculation result is used as the flying object guidance arithmetic device ( (Not shown).

  Next, the operation of the guided flying object 1 according to the present embodiment will be described. In the following description, the case where the guided flying object 1 is guided by the semi-active method will be described first, and then the case where the guided flying object 1 is guided by the active method will be described.

[In the case of semi-active guidance]
In the case of semi-active guidance, the transmission / reception switching unit 11 is switched to the receiver 21 side by the controller 14, and the guided flying object 1 is in a state where it can receive radar radio waves.
For example, when a low-frequency radar is transmitted from a low-frequency radar on the ground (for example, a warning radar) toward a stealth machine, the low-frequency radar is not absorbed and reflected by the stealth machine. Since the transmission / reception switching unit 11 is switched to the receiver 21 side in the guided flying object 1, the reflected low-frequency radar radio waves are received by the antenna elements 30 arranged in a wide range of the guiding flying object 1. The low frequency radar received by the receiver 21 via the antenna element 30 of the guided flying object 1 is output to the phase difference detector 12. The phase difference detector 12 calculates the phase difference φ of the low-frequency radar input from each antenna element 30 and outputs the phase difference φ to the radio wave arrival direction calculator 13. The radio wave arrival direction calculator 13 calculates the direction in which the low-frequency radar radio waves reflected arrive based on the phase difference φ, and outputs the calculation result to the missile guidance arithmetic unit.

[In case of active guidance]
In the case of active guidance, the transmission / reception switching unit 11 is switched to the transmitter 22 side by the controller 14, and the guided flying object 1 transmits and receives the radar radio wave from the antenna element 30 and then transmits and receives by the controller 14. The switching unit 11 is switched to the receiver 21 side and enters a state of receiving radar radio waves.
For example, the transmission / reception switching unit 11 is switched to the transmitter 22 side by the control unit 14, and the controller 14 controls the phase of the radio wave transmitted from each antenna element 30 and transmits the radio wave in a desired direction. A beam is formed and output from the antenna element 30. The high-frequency radar radio wave transmitted from the antenna element 30 is reflected by the stealth machine. Subsequently, the transmission / reception switching unit 11 is switched to the receiver 21 side by the controller 14, and the reflected radar radio wave of the transmission beam emitted by the antenna element 30 is received. The high-frequency radar received by the receiver 21 via the antenna element 30 of the guided flying object 1 is output to the phase difference detector 12. The phase difference detector 12 calculates the phase difference φ of the high-frequency radar input from each antenna element 30 and outputs the phase difference φ to the radio wave arrival direction calculator 13. The radio wave arrival direction calculator 13 calculates the direction in which the low-frequency radar radio waves reflected arrive based on the phase difference φ, and outputs the calculation result to the missile guidance arithmetic unit.

  As described above, according to the flying object according to the present embodiment, the three antenna groups 20a, 20b, and 20c including the plurality of antenna elements 30 are arranged in the circumferential direction in a band shape, and each antenna group 20a, 20b, 20c are arranged at equal intervals, and two antenna groups of the antenna groups are spaced from each other in the axial direction of the guide flying object 1 and are arranged in the vicinity of the front end portion and the rear end portion. Thus, since the antenna elements are distributed over a wide range from the vicinity of the front end portion to the vicinity of the rear end portion of the airframe, radar waves having a long wavelength are received using the entire airframe as an antenna. Thereby, even a low-frequency radar radio wave having a long wavelength can be received. Also, by disposing the antenna elements 30 in a distributed manner, the sensitivity of radar radio waves in the antenna device can be improved.

  In addition, the transmission / reception switching unit 11 can perform both reception and transmission by switching the antenna element 30 to the receiver 21 side and the transmitter 22 side under the control of the controller 14. Thereby, semi-active guidance and active guidance can be performed.

  In this way, by switching transmission / reception of the transmission / reception switching unit 11 connected to the antenna element 30, it is used as a communication antenna with a semi-active guidance, an active guidance, and a ground device. Therefore, it is not necessary to provide individual components, and the size and cost of the device can be reduced.

  In addition, the antenna element 30 included in the guide flying body 1 according to the present embodiment is an antenna element that can emit a high-frequency radar radio wave because it emits a high-frequency radar radio wave when performing the active guidance.

  In addition, in the guidance flying object 1 which concerns on this embodiment, although demonstrated as what uses a semi-active system guidance and an active system guidance separately, it is not limited to this. For example, a combination of semi-active guidance and active guidance may be used. Specifically, when the guided vehicle 1 is far from the target (for example, a stealth aircraft), the semi-active guidance is performed, and after the guided flying vehicle 1 has sufficiently approached the stealth aircraft, the active flying guidance is performed. It is switched and used by a combination such as switching. Thereby, the precision of guidance can be improved. More specifically, the guide flying object 1 switches to the active type guidance when the radio wave intensity of the reflected radar radio wave received by the semi-active type becomes a predetermined radio wave intensity.

  Further, although the semi-active method and the active method are switched according to the radio wave intensity of the radar radio wave received by the antenna element 30, the present invention is not limited to this. For example, the guided vehicle 1 receives the reflected radar radio wave from the target in synchronization with the radar radio wave transmitted to the target from the ground, and receives the reflected radar radio wave timing and the reflected radar radio wave reception timing transmitted from the ground. It is also possible to calculate the distance between the guided flying object 1 and the target based on the time difference between and to switch between the semi-active method and the active method based on this distance.

  Further, in the guided flying body according to the present embodiment, the active method and the semi-active method are switched by the controller 14 in one aircraft, but the present invention is not limited to this. For example, one of a plurality (for example, two aircrafts) of the guided flying bodies may be operated by active type guidance, and the other may be operated by semi-active type guidance. This eliminates the need for the controller 14 in each guided projectile.

  As mentioned above, although embodiment of this invention was explained in full detail with reference to drawings, the specific structure is not restricted to this embodiment, The design change etc. of the range which does not deviate from the summary of this invention are included.

DESCRIPTION OF SYMBOLS 1 Guide flying object 10 Antenna apparatus 11 Transmission / reception switching part 12 Phase difference detector 13 Radio wave arrival direction calculator
20a, 20b, 20c Antenna group 30 Antenna element

Claims (3)

A flying object whose position is controlled based on radar radio waves received by the antenna device,
The antenna device includes a plurality of antenna groups,
The antenna group is
A plurality of antenna elements are provided at predetermined intervals in the axial direction of the surface of the airframe, and the antenna elements included in each antenna group are arranged adjacent to each other, and the circumferential direction of the fuselage of the airframe It is arranged in a band shape over the entire circumference of the two antenna groups of the antenna device, and the like aircraft being disposed near the rear end of the body near the tip and the body of the machine body A guided flying object that is guided toward a predetermined target after being separated . Each of the antenna groups includes the same number of the antenna elements, and the guided flying object is guided toward a predetermined target after being separated from the aircraft or the like according to claim 1. Control means for switching between transmission and reception of radar radio waves of the antenna device, wherein the control means controls a control parameter of radio waves transmitted from the antenna group and causes the antenna group to transmit the control parameter. A guided vehicle that is guided toward a predetermined target after being separated from the aircraft or the like according to claim 1 or claim 2.

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