WO2018088230A1 - レーダ装置及び航空機 - Google Patents
レーダ装置及び航空機 Download PDFInfo
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- WO2018088230A1 WO2018088230A1 PCT/JP2017/038779 JP2017038779W WO2018088230A1 WO 2018088230 A1 WO2018088230 A1 WO 2018088230A1 JP 2017038779 W JP2017038779 W JP 2017038779W WO 2018088230 A1 WO2018088230 A1 WO 2018088230A1
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- rotation
- antenna
- polarization plane
- rotation mechanism
- control unit
- Prior art date
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- 230000007246 mechanism Effects 0.000 claims abstract description 176
- 230000010287 polarization Effects 0.000 claims abstract description 118
- 238000001514 detection method Methods 0.000 description 14
- 238000010586 diagram Methods 0.000 description 8
- 230000006866 deterioration Effects 0.000 description 7
- 239000000470 constituent Substances 0.000 description 2
- 230000005855 radiation Effects 0.000 description 2
- 230000015556 catabolic process Effects 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 230000005684 electric field Effects 0.000 description 1
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q21/00—Antenna arrays or systems
- H01Q21/24—Combinations of antenna units polarised in different directions for transmitting or receiving circularly and elliptically polarised waves or waves linearly polarised in any direction
- H01Q21/245—Combinations of antenna units polarised in different directions for transmitting or receiving circularly and elliptically polarised waves or waves linearly polarised in any direction provided with means for varying the polarisation
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/88—Radar or analogous systems specially adapted for specific applications
- G01S13/93—Radar or analogous systems specially adapted for specific applications for anti-collision purposes
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/02—Systems using reflection of radio waves, e.g. primary radar systems; Analogous systems
- G01S13/04—Systems determining presence of a target
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/02—Systems using reflection of radio waves, e.g. primary radar systems; Analogous systems
- G01S13/06—Systems determining position data of a target
- G01S13/42—Simultaneous measurement of distance and other co-ordinates
- G01S13/422—Simultaneous measurement of distance and other co-ordinates sequential lobing, e.g. conical scan
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/88—Radar or analogous systems specially adapted for specific applications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/88—Radar or analogous systems specially adapted for specific applications
- G01S13/93—Radar or analogous systems specially adapted for specific applications for anti-collision purposes
- G01S13/933—Radar or analogous systems specially adapted for specific applications for anti-collision purposes of aircraft or spacecraft
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
- G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
- G01S7/024—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00 using polarisation effects
- G01S7/025—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00 using polarisation effects involving the transmission of linearly polarised waves
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
- G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
- G01S7/03—Details of HF subsystems specially adapted therefor, e.g. common to transmitter and receiver
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
- G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
- G01S7/40—Means for monitoring or calibrating
- G01S7/4004—Means for monitoring or calibrating of parts of a radar system
- G01S7/4026—Antenna boresight
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
- H01Q1/281—Nose antennas
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q19/00—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic
- H01Q19/10—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces
- H01Q19/12—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces wherein the surfaces are concave
- H01Q19/17—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces wherein the surfaces are concave the primary radiating source comprising two or more radiating elements
- H01Q19/175—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces wherein the surfaces are concave the primary radiating source comprising two or more radiating elements arrayed along the focal line of a cylindrical focusing surface
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q25/00—Antennas or antenna systems providing at least two radiating patterns
- H01Q25/007—Antennas or antenna systems providing at least two radiating patterns using two or more primary active elements in the focal region of a focusing device
- H01Q25/008—Antennas or antenna systems providing at least two radiating patterns using two or more primary active elements in the focal region of a focusing device lens fed multibeam arrays
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q3/00—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
- H01Q3/02—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole
- H01Q3/04—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole for varying one co-ordinate of the orientation
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q3/00—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
- H01Q3/02—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole
- H01Q3/08—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole for varying two co-ordinates of the orientation
Definitions
- the present invention relates to a radar apparatus and an aircraft.
- the gimbal mechanism changes the direction of the antenna in order to expand the radar coverage.
- a gimbal mechanism for example, there is one in which two axes are orthogonal to each other.
- a gimbal ring for each axis is arranged.
- the antenna is arranged in a state of protruding from the gimbal mechanism so that the gimbal ring does not cover the antenna.
- the radar apparatus using the gimbal mechanism is increased in volume and weight.
- the radar apparatus includes an antenna having an antenna surface that emits radio waves having a predetermined plane of polarization, and a normal direction that is connected to the antenna and orthogonal to the antenna surface is defined as an axial direction of the second rotation axis.
- a second rotation mechanism that rotates the antenna around the second rotation axis, and a direction that is connected to the second rotation mechanism and that is inclined with respect to the second rotation axis is an axial direction of the first rotation axis, and And a first rotation mechanism for rotating the antenna and the second rotation mechanism about a first rotation axis.
- the direction of the antenna that is, the radiation direction of the radio wave can be changed. For this reason, the coverage of the radar apparatus can be wide.
- the direction of the antenna is changed by the first rotation mechanism, the direction of the polarization plane of the antenna is also changed. Therefore, the antenna is rotated in the antenna plane around the second rotation axis by the second rotation mechanism.
- the direction of the polarization plane can be set to a predetermined direction. For this reason, the polarization plane of the antenna can be set to a predetermined direction suitable for the operation of the radar apparatus.
- the antenna when the antenna is provided in the radome, it is possible to suppress deterioration in detection performance due to a change in radome characteristics by setting the direction of the polarization plane to a fixed direction. Then, the first rotating mechanism is connected to the second rotating mechanism, the second rotating mechanism is connected to the antenna, and these rotating mechanisms perform a rotating operation without providing a mechanism having a large volume such as a gimbal mechanism. Since the direction of the antenna can be easily changed with a simple configuration, a compact configuration can be achieved.
- the first rotation axis is a roll axis of a body on which the antenna is mounted.
- a control unit that controls the first rotation mechanism and the second rotation mechanism is further provided, a reference polarization plane serving as a reference is preset, and the control unit is configured so that the polarization plane of the antenna is It is preferable to control the first rotation mechanism and the second rotation mechanism so as to be a reference polarization plane.
- the polarization plane of the antenna can be maintained at the reference polarization plane, so that deterioration in detection performance can be suppressed.
- control unit controls the rotation direction of the second rotation mechanism to the reverse rotation direction when the rotation direction of the first rotation mechanism is controlled to the normal rotation direction.
- the direction of the polarization plane of the antenna that changes in the forward rotation direction by the rotation of the first rotation mechanism can be canceled (cancelled) by the rotation in the reverse rotation direction of the second rotation mechanism.
- the polarization plane of the antenna can be easily maintained at the reference polarization plane.
- the reference polarization plane is a polarization plane fixed with reference to an airframe coordinate system of an airframe on which the antenna is mounted.
- the direction of the polarization plane can be made constant. Degradation of performance can be suppressed.
- the reference polarization plane is preferably a polarization plane fixed with respect to the ground coordinate system.
- the polarization plane fixed with respect to the ground coordinate system is, for example, a polarization plane of vertical polarization.
- control unit obtains posture information that is information related to a posture angle of a body on which the antenna is mounted, and based on the posture information, the polarization plane of the antenna is based on a ground coordinate system. It is preferable to control the first rotation mechanism and the second rotation mechanism so that the reference polarization plane is fixed.
- the antenna polarization plane can be maintained at the reference polarization plane fixed with respect to the ground, so that deterioration in detection performance is suppressed. Can do.
- a polarization plane fuselage fixing mode for fixing the reference polarization plane with reference to the fuselage coordinate system of the aircraft on which the antenna is mounted and a polarization plane ground fixed mode for fixing the reference polarization plane with reference to the ground coordinate system are prepared in advance, and it is preferable that the control unit includes a switching circuit that switches between the polarization plane body fixing mode and the polarization plane ground fixed mode.
- the polarization plane body fixing mode and the polarization plane ground fixed mode can be switched as appropriate, so that versatility can be enhanced.
- control unit individually controls the first rotation mechanism and the second rotation mechanism, and inputs a first angle command signal to the first rotation mechanism, and inputs the first angle command signal to the second rotation mechanism. It is preferable that the second angle command signal is input to control the first rotation mechanism and the second rotation mechanism simultaneously.
- the first rotating mechanism and the second rotating mechanism can be quickly controlled by individually controlling the first rotating mechanism and the second rotating mechanism at the same time, the time lag can be suppressed. Can be detected quickly with high accuracy.
- a direction that is provided on the second rotation shaft and is orthogonal to the second rotation shaft is defined as an axial direction of the third rotation shaft, and the first rotation shaft is centered on the third rotation shaft. It is preferable to further include a third rotation mechanism that inclines the two rotation axes.
- the inclination angle of the second rotation shaft with respect to the first rotation shaft can be set to an appropriate angle by the third rotation mechanism, for example, the antenna surface is raised toward the detected target, that is, the target and In the direction facing the antenna surface, the second rotation axis can be inclined with respect to the first rotation axis so that the area of the antenna surface is maximized. For this reason, since the loss of the radio wave radiated from the antenna surface can be suppressed, the detection distance can be increased, and a farther target can be detected. Further, for example, by covering the antenna surface, that is, by increasing the inclination angle of the second rotation axis with respect to the first rotation axis, the coverage area can be made wider. From the above, it is possible to further increase the versatility by inclining the second rotation axis with respect to the first rotation axis by the third rotation mechanism.
- An aircraft according to the present invention includes the above-described radar device and an airframe on which the radar device is mounted on the nose.
- the target can be suitably detected by a compact radar device having a wide coverage area.
- FIG. 1 is a perspective view schematically showing an aircraft provided with a radar apparatus according to the first embodiment.
- FIG. 2 is a perspective view schematically showing the radar apparatus according to the first embodiment.
- FIG. 3 is an explanatory diagram relating to a coverage area of the radar apparatus according to the first embodiment.
- FIG. 4 is an explanatory diagram regarding a control unit of the radar apparatus according to the first embodiment.
- FIG. 5 is a perspective view schematically showing a radar apparatus according to the second embodiment.
- FIG. 6 is an explanatory diagram relating to the coverage area of the radar apparatus according to the second embodiment.
- FIG. 7 is an explanatory diagram relating to a control unit of the radar apparatus according to the second embodiment.
- FIG. 1 is a perspective view schematically showing an aircraft provided with the radar apparatus according to the first embodiment.
- FIG. 2 is a perspective view schematically showing the radar apparatus according to the first embodiment.
- FIG. 3 is an explanatory diagram relating to a coverage area of the radar apparatus according to the first embodiment.
- FIG. 4 is an explanatory diagram regarding a control unit of the radar apparatus according to the first embodiment.
- the direction connecting the nose and the tail is the axial direction of the roll axis
- the direction connecting the left wing and the right wing orthogonal to the roll axis is the axial direction of the pitch axis.
- the direction perpendicular to the roll axis and the pitch axis is the axial direction of the yaw axis.
- the aircraft 1 is provided with an attitude detection sensor 7 for detecting the attitude of the airframe 5 (see FIG. 2), and is electrically connected to a control unit 24 of the radar apparatus 10 described later.
- a gyro sensor is applied to the posture detection sensor 7, and posture information that is information related to the posture angle ⁇ ⁇ b> 2 of the body 5 is output to the control unit 24.
- the attitude angle ⁇ 2 of the machine body 5 is an inclination angle when the machine body 5 is tilted from the horizontal state with the roll axis as the center.
- the radar apparatus 10 will be described with reference to FIGS. 1 and 2.
- the radar device 10 is provided inside a radome provided at the nose of the airframe 5.
- the radar apparatus 10 includes a first rotation mechanism 21, a second rotation mechanism 22, an antenna 23, and a control unit 24.
- the first rotation mechanism 21 changes the coverage of the antenna 23 by changing the direction of the antenna 23.
- the first rotating mechanism 21 is fixed to a frame (not shown) of the body 5.
- the first rotation mechanism 21 has a first rotation axis I 1, and the axial direction of the first rotation axis I 1 is the same as the roll axis of the aircraft 1.
- the fixed side of the first rotating shaft I1 is the base end side (machine tail side), and the distal end side (nose side) of the first rotating shaft I1 is the rotating side.
- the control unit 24 is electrically connected to the first rotation mechanism 21, and the rotation operation is controlled by the control unit 24.
- the first rotation mechanism 21 has a second rotation mechanism 22 connected to the rotation side. Then, the first rotation mechanism 21 rotates the connected second rotation mechanism 22 so as to have a predetermined rotation angle around the first rotation axis I1.
- the second rotating mechanism 22 changes the direction of the polarization plane of the antenna 23.
- the second rotation mechanism 22 is connected to the first rotation mechanism 21 at the base end side (machine tail side).
- the second rotation mechanism 22 has a second rotation axis I2, and the axial direction of the second rotation axis I2 is an axis inclined with respect to the first rotation axis I1.
- the inclination angle of the second rotation axis I2 with respect to the first rotation axis I1 is defined as the antenna inclination angle ⁇ (see FIG. 3).
- the base end side (machine tail side) of the second rotating shaft I2 is the connection side with the first rotating mechanism 21, and the tip end side (nose side) of the second rotating shaft I2. ) Is the rotation side.
- the second rotation mechanism 22 is electrically connected to the control unit 24, and the rotation operation is controlled by the control unit 24.
- the second rotation mechanism 22 has an antenna 23 connected to the rotation side. Then, the second rotation mechanism 22 rotates the connected antenna 23 around the second rotation axis I2 so that a predetermined rotation angle is obtained.
- the antenna 23 is an antenna capable of radiating directional radio waves.
- a phased array antenna in which a plurality of antenna elements are arranged in an array is applied.
- the antenna 23 has an antenna surface 28 that emits radio waves having a predetermined plane of polarization, and the antenna surface 28 is a flat surface.
- the antenna surface 28 is formed in a circular shape.
- Such a coverage area of the antenna 23 is a predetermined antenna coverage area E that is a region radially extending outward from the antenna surface 28 around the second rotation axis I2 (see FIG. 3).
- the plane of polarization of the radio wave radiated from the antenna 23 is a plane including the vibration of the electric field in the radio wave and the propagation direction of the radio wave, and is a plane orthogonal to the antenna plane 28.
- the polarization plane of the radio wave radiated from the antenna surface 28 is maintained to be a preset reference polarization plane.
- the control unit 24 can individually control the first rotation mechanism 21 and the second rotation mechanism 22.
- the control unit 24 inputs the first angle command signal to the first rotation mechanism 21, whereby the first rotation mechanism 21 has the first rotation axis I1 so that the predetermined rotation angle is based on the first angle command signal. Rotate around.
- the control unit 24 inputs the second angle command signal to the second rotation mechanism 22, so that the second rotation mechanism 22 performs the second rotation so as to have a predetermined rotation angle based on the second angle command signal. Rotate about axis I2.
- the control unit 24 controls the first rotation mechanism 21 and the second rotation mechanism 22 so that the polarization plane of the antenna 23 becomes the reference polarization plane.
- two reference polarization planes are prepared, and there are a polarization plane fixed with respect to the ground coordinate system on the ground and a polarization plane fixed with reference to the body coordinate system of the body 5.
- the polarization plane fixed with respect to the ground coordinate system on the ground is a polarization plane of vertical polarization perpendicular to the ground.
- the polarization plane of vertical polarization is used.
- the polarization plane of horizontal polarization may be used according to the operation of the radar apparatus 10.
- the plane of polarization fixed with respect to the body coordinate system of the body 5 is, for example, a plane of polarization that is a plane including the roll axis and the yaw axis of the body 5.
- the plane of polarization including the roll axis and the yaw axis of the airframe 5 is used, but the plane of polarization according to the characteristics of the radome may be used, and is not particularly limited.
- the control unit 24 includes a switching circuit 31 that switches between a polarization plane body fixing mode that is fixed based on the body coordinate system and a polarization plane ground fixed mode that is fixed based on the ground coordinate system.
- the switching circuit 31 is in an OFF state in which attitude information is not input when the polarization plane body fixing mode is executed, and is in an ON state in which attitude information is input when the polarization plane ground fixed mode is executed. That is, the control unit 24 enters the polarization plane ground fixed mode by setting the switching circuit 31 to the ON state, and enters the polarization plane body fixing mode by setting the switching circuit 31 to the OFF state.
- the control unit 24 controls the first rotation mechanism 21 and the second rotation mechanism 22 so that the polarization plane of the antenna 23 becomes a predetermined reference polarization plane fixed in the body coordinate system in the polarization plane body fixing mode. . Since the switching circuit 31 is in the OFF state, the control unit 24 does not receive posture information, and the requested antenna direction, that is, the direction in which the antenna coverage area E is desired to be expanded (coverage area expansion direction). Based on such a rotation angle ⁇ 1, the first rotation mechanism 21 and the second rotation mechanism 22 are rotated.
- the control unit 24 inputs the rotation angle ⁇ 1 as the first angle command signal to the first rotation mechanism 21.
- the control unit 24 rotates the first rotation mechanism 21 in the forward rotation direction to the rotation angle ⁇ 1
- the direction of the polarization plane is changed to the forward rotation direction together with the direction of the antenna 23. Is done. Therefore, the control unit 24 rotates the rotation direction of the second rotation mechanism 22 in the reverse rotation direction by the same angle as the rotation angle ⁇ 1. That is, the control unit 24 inputs the rotation angle ⁇ 1 as the second angle command signal to the second rotation mechanism 22.
- control unit 24 can cancel the rotation of the polarization plane in the forward rotation direction by the first rotation mechanism 21 by the rotation of the polarization plane in the reverse rotation direction by the second rotation mechanism 22, so that the polarization plane is the reference polarization.
- the wavefront can be maintained.
- the first rotation mechanism 21 may be set in the reverse rotation direction
- the second rotation mechanism 22 may be set in the normal rotation direction.
- the control unit 24 controls the first rotation mechanism 21 and the second rotation mechanism 22 so that the polarization plane of the antenna 23 becomes a predetermined reference polarization plane fixed to the ground coordinate system. . Since the switching circuit 31 is in the ON state, the control unit 24 receives posture information (information on the posture angle ⁇ 2), so that the input posture information and the required antenna coverage E are obtained. The first rotation mechanism 21 and the second rotation mechanism 22 are rotated based on the correct rotation angle ⁇ 1.
- the control unit 24 inputs the rotation angle ⁇ 1 as the first angle command signal to the first rotation mechanism 21.
- the direction of the polarization plane is set in the positive rotation direction together with the direction of the antenna 23.
- the direction of the polarization plane is also changed by the attitude angle ⁇ 2 of the body 5.
- the control unit 24 rotates the rotation direction of the second rotation mechanism 22 in the reverse rotation direction by the same angle as the rotation angle ⁇ 1 and is the same as the attitude angle ⁇ 2 of the airframe 5 detected by the attitude detection sensor 7.
- the rotation direction of the second rotation mechanism 22 is rotated in the reverse rotation direction by the angle. That is, the control unit 24 inputs a value obtained by adding the rotation angle ⁇ 1 and the posture angle ⁇ 2 to the second rotation mechanism 22 as the second angle command signal. For this reason, the control unit 24 can cancel the rotation of the polarization plane in the forward rotation direction by the first rotation mechanism 21 by the rotation of the polarization plane in the reverse rotation direction by the second rotation mechanism 22, and the attitude of the airframe 5. Since the rotation of the polarization plane due to the change in phase can be offset by the rotation by the second rotation mechanism 22, the polarization plane can be maintained at the reference polarization plane. Note that the forward rotation direction of the first rotation mechanism 21 may be either clockwise or counterclockwise. Similarly, the reverse rotation direction of the second rotation mechanism 22 is the forward rotation direction of the first rotation mechanism 21. Any reverse rotation direction may be used.
- control unit 24 individually controls the first rotation mechanism 21 and the second rotation mechanism 22, and inputs the first angle command signal toward the first rotation mechanism 21, and the second rotation mechanism. In order to input the second angle command signal toward the motor 22, the first rotating mechanism 21 and the second rotating mechanism 22 are simultaneously controlled.
- the antenna 23 is centered on the first rotation axis I1 by the first rotation mechanism 21.
- the direction of the antenna 23 that is, the radiation direction of the radio wave can be changed. For this reason, the coverage area of the radar apparatus 10 can be wide.
- the second rotation mechanism 22 causes the antenna surface 28 to be centered around the second rotation axis I 2.
- the direction of the polarization plane can be set to a predetermined direction.
- the polarization plane of the antenna 23 can be set to a predetermined direction suitable for the operation of the radar apparatus 10. Then, the first rotating mechanism 21 is connected to the second rotating mechanism 22, the second rotating mechanism 22 is connected to the antenna 23, and these rotating mechanisms 21 and 22 perform a rotating operation, so that the volume of the gimbal mechanism or the like can be obtained. Since the direction of the antenna 23 can be easily changed with a simple configuration without providing a large mechanism, a compact configuration can be achieved.
- the coverage area around the roll axis of the body 5 can be expanded.
- the polarization plane of the antenna 23 can be maintained at the reference polarization plane, so that deterioration in detection performance can be suppressed.
- the direction of the polarization plane of the antenna 23 that changes in the forward rotation direction by the rotation of the first rotation mechanism 21 is canceled (offset) by the rotation of the second rotation mechanism 22 in the reverse rotation direction. Therefore, the polarization plane of the antenna 23 can be easily maintained at the reference polarization plane.
- the direction of the polarization plane is constant. Therefore, it is possible to suppress deterioration in detection performance due to a change in radome characteristics.
- the attitude of the airframe 5 on which the antenna 23 is mounted is changed by fixing the reference polarization plane with respect to the ground in the polarization plane fixed mode, Since the direction of the polarization plane in the space can be made constant, deterioration in detection performance due to a change in the attitude of the body 5 can be suppressed.
- the polarization plane airframe fixed mode and the polarization plane ground fixed mode can be appropriately switched by the switching circuit 31, so that the versatility of the radar apparatus 10 can be enhanced.
- the first rotating mechanism 21 and the second rotating mechanism 22 can be quickly controlled by individually controlling the first rotating mechanism 21 and the second rotating mechanism 22 at the same time.
- the time lag can be suppressed, and accurate and quick detection can be performed.
- the target can be suitably detected by the compact radar device 10 having a wide coverage area.
- FIG. 5 is a perspective view schematically showing a radar apparatus according to the second embodiment.
- FIG. 6 is an explanatory diagram relating to the coverage area of the radar apparatus according to the second embodiment.
- FIG. 7 is an explanatory diagram relating to a control unit of the radar apparatus according to the second embodiment.
- the radar apparatus 50 according to the second embodiment further includes a third rotation mechanism 53 in addition to the radar apparatus 10 according to the first embodiment.
- the third rotation mechanism 53 changes the direction of the antenna 23 to change the coverage area of the antenna 23.
- the third rotation mechanism 53 is provided between the first rotation mechanism 21 and the second rotation mechanism 22.
- the third rotating mechanism 53 has a third rotating shaft I3 provided on the second rotating shaft I2, and the axial direction of the third rotating shaft I3 is a direction orthogonal to the second rotating shaft I2. .
- the third rotating mechanism 53 has the first rotating mechanism 21 connected to the nose side and the second rotating mechanism 22 connected to the nose side.
- the third rotation mechanism 53 is electrically connected to the control unit 24, and the rotation operation is controlled by the control unit 24.
- the third rotation mechanism 53 performs the second rotation of the second rotation mechanism 22 with respect to the first rotation axis I1 of the first rotation mechanism 21 so as to have a predetermined antenna inclination angle ⁇ around the third rotation axis I3.
- the axis I2 is tilted.
- the control unit 24 can individually control the third rotation mechanism 53 in addition to the first rotation mechanism 21 and the second rotation mechanism 22.
- the control unit 24 inputs a signal having a predetermined antenna inclination angle ⁇ to the third rotation mechanism 53, so that the third rotation mechanism 53 has a third antenna inclination angle ⁇ based on the signal. It rotates around the rotation axis I3.
- the control unit 24 based on the antenna inclination angle (necessary coverage angle) ⁇ 1 necessary for obtaining the required coverage, and the angle (antenna coverage angle) ⁇ 2 of the antenna coverage E,
- the antenna coverage angle ⁇ 2 is the maximum beam swing angle of the radio wave that the antenna 23 can radiate.
- the minimum antenna inclination angle ⁇ is the minimum antenna inclination angle ⁇ allowed when the target is not in front (in the roll axis direction).
- the control unit 24 calculates the minimum antenna inclination angle ⁇ based on the necessary coverage angle ⁇ 1 and the antenna coverage angle ⁇ 2.
- the control unit 24 calculates the minimum antenna inclination angle ⁇ , and if the minimum antenna inclination angle ⁇ is smaller than zero ( ⁇ ⁇ 0), the rotation by the third rotation mechanism 53 is executed assuming that the minimum antenna inclination angle ⁇ is zero. do not do.
- the control unit 24 calculates the minimum antenna inclination angle ⁇ , and performs rotation by the third rotation mechanism 53 so that the minimum antenna inclination angle ⁇ is equal to or greater than zero when the minimum antenna inclination angle ⁇ is equal to or greater than zero.
- the third rotation mechanism 53 can set the inclination angle of the second rotation axis I2 with respect to the first rotation axis I1 to an appropriate angle. For example, toward the detected target object.
- the second rotation axis I2 may be inclined with respect to the first rotation axis I1 so that the antenna surface 28 stands up, that is, the area of the antenna surface 28 is maximized in the direction in which the target and the antenna surface 28 face each other. it can. For this reason, since the loss of the electric wave radiated
- the coverage area can be made wider.
- the third rotating mechanism 53 can be made more versatile by inclining the second rotating shaft I2 with respect to the first rotating shaft I1.
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Abstract
Description
実施形態1に係るレーダ装置10は、例えば、図1に示すように、航空機1の機体5の機首に搭載されるものであり、目標物を探知するものとなっている。ここで、図1は、実施形態1に係るレーダ装置が設けられる航空機を模式的に示す斜視図である。図2は、実施形態1に係るレーダ装置を模式的に示す斜視図である。図3は、実施形態1に係るレーダ装置の覆域に関する説明図である。図4は、実施形態1に係るレーダ装置の制御部に関する説明図である。
次に、図5から図7を参照して、実施形態2に係るレーダ装置50について説明する。なお、実施形態2では、重複した記載を避けるべく、実施形態1と異なる部分について説明し、実施形態1と同様の構成である部分については、同じ符号を付して説明する。図5は、実施形態2に係るレーダ装置を模式的に示す斜視図である。図6は、実施形態2に係るレーダ装置の覆域に関する説明図である。図7は、実施形態2に係るレーダ装置の制御部に関する説明図である。
5 機体
7 姿勢検出センサ
10 レーダ装置
21 第1回転機構
22 第2回転機構
23 アンテナ
24 制御部
28 アンテナ面
31 切替回路
50 レーダ装置(実施形態2)
53 第3回転機構
I1 第1回転軸
I2 第2回転軸
I3 第3回転軸
φ アンテナ傾斜角
φ1 必要覆域角度
φ2 アンテナ覆域角度
E アンテナ覆域
Claims (11)
- 所定の偏波面となる電波を放射するアンテナ面を有するアンテナと、
前記アンテナに接続され、前記アンテナ面に直交する法線方向を第2回転軸の軸方向とし、前記第2回転軸を中心に、前記アンテナを回転させる第2回転機構と、
前記第2回転機構に接続され、前記第2回転軸に対して傾斜する方向を第1回転軸の軸方向とし、前記第1回転軸を中心に、前記アンテナ及び前記第2回転機構を回転させる第1回転機構と、を備えることを特徴とするレーダ装置。 - 前記第1回転軸は、前記アンテナが搭載される機体のロール軸であることを特徴とする請求項1に記載のレーダ装置。
- 前記第1回転機構及び前記第2回転機構を制御する制御部を、さらに備え、
基準となる基準偏波面が予め設定されており、
前記制御部は、前記アンテナの前記偏波面が、前記基準偏波面となるように、前記第1回転機構及び前記第2回転機構を制御することを特徴とする請求項1または2に記載のレーダ装置。 - 前記制御部は、前記第1回転機構の回転方向を正回転方向に制御する場合、前記第2回転機構の回転方向を逆回転方向に制御することを特徴とする請求項3に記載のレーダ装置。
- 前記基準偏波面は、前記アンテナが搭載される機体の機体座標系を基準として固定される偏波面であることを特徴とする請求項3または4に記載のレーダ装置。
- 前記基準偏波面は、地上座標系を基準として固定される偏波面であることを特徴とする請求項3から5のいずれか1項に記載のレーダ装置。
- 前記制御部は、前記アンテナが搭載される機体の姿勢角に関する情報である姿勢情報を取得しており、前記姿勢情報に基づいて、前記アンテナの前記偏波面が、地上座標系を基準として固定される前記基準偏波面となるように、前記第1回転機構及び前記第2回転機構を制御することを特徴とする請求項6に記載のレーダ装置。
- 前記基準偏波面を、前記アンテナが搭載される機体の機体座標系を基準として固定する偏波面機体固定モードと、
前記基準偏波面を、地上座標系を基準として固定する偏波面地上固定モードと、が予め用意されており、
前記制御部は、前記偏波面機体固定モードと、前記偏波面地上固定モードとを切り替える切替回路を有することを特徴とする請求項3から7のいずれか1項に記載のレーダ装置。 - 前記制御部は、前記第1回転機構と前記第2回転機構とを個別に制御しており、前記第1回転機構に向けて第1角度指令信号を入力し、前記第2回転機構に向けて第2角度指令信号を入力して、前記第1回転機構と前記第2回転機構とを同時に制御することを特徴とする請求項3から8のいずれか1項に記載のレーダ装置。
- 前記第2回転軸上に設けられると共に前記第2回転軸に直交する方向を第3回転軸の軸方向とし、前記第3回転軸を中心に、前記第1回転軸に対して前記第2回転軸を傾斜させる第3回転機構を、さらに備えることを特徴とする請求項1から9のいずれか1項に記載のレーダ装置。
- 請求項1から10のいずれか1項に記載のレーダ装置と、
前記レーダ装置を機首に搭載する機体と、を備えることを特徴とする航空機。
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GB1903819.9A GB2576803B (en) | 2016-11-11 | 2017-10-26 | Radar device and aircraft |
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Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS4946849A (ja) * | 1972-07-31 | 1974-05-07 | ||
JPS57125503A (en) * | 1981-01-28 | 1982-08-04 | Tokyo Keiki Co Ltd | Antenna automatic directivity device |
JP2016005168A (ja) * | 2014-06-18 | 2016-01-12 | 三菱電機株式会社 | アンテナ装置 |
Family Cites Families (36)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3903523A (en) * | 1949-08-19 | 1975-09-02 | Philco Ford Corp | Microwave antennas and arrays thereof |
US3984837A (en) * | 1975-03-31 | 1976-10-05 | The United States Of America As Represented By The Secretary Of The Navy | Rotatable and tiltable radome with independent scan and tilt antenna |
US4148029A (en) * | 1976-10-13 | 1979-04-03 | Westinghouse Electric Corp. | System for estimating acceleration of maneuvering targets |
FR2378318A1 (fr) * | 1977-01-21 | 1978-08-18 | Thomson Csf | Systeme de poursuite d'une cible mobile |
US4179696A (en) * | 1977-05-24 | 1979-12-18 | Westinghouse Electric Corp. | Kalman estimator tracking system |
FR2406831A1 (fr) * | 1977-10-21 | 1979-05-18 | Thomson Csf | Systeme de poursuite d'une cible mobile |
US4219814A (en) * | 1978-12-26 | 1980-08-26 | Rca Corporation | Scanning radar |
US5225839A (en) * | 1980-12-29 | 1993-07-06 | Okurowski Frank A | All weather tactical strike system (AWTSS) and method of operation |
US4786912A (en) * | 1986-07-07 | 1988-11-22 | Unisys Corporation | Antenna stabilization and enhancement by rotation of antenna feed |
JPS63123456A (ja) * | 1986-11-12 | 1988-05-27 | Kenzo Hoshino | 塗装法及び装置 |
US7741991B1 (en) * | 1987-06-26 | 2010-06-22 | Mbda Uk Limited | Radar tracking system |
US5202695A (en) * | 1990-09-27 | 1993-04-13 | Sperry Marine Inc. | Orientation stabilization by software simulated stabilized platform |
US5149011A (en) * | 1991-06-20 | 1992-09-22 | The United States Of America As Represented By The Secretary Of The Air Force | Radar boresight error compensator |
EP0631342A1 (en) * | 1993-06-23 | 1994-12-28 | Ail Systems, Inc. | Antenna mirror scanner with constant polarization characteristics |
JPH0791896A (ja) | 1993-09-27 | 1995-04-07 | Mitsubishi Heavy Ind Ltd | 飛しょう体のレーダ方式誘導装置 |
US5922039A (en) * | 1996-09-19 | 1999-07-13 | Astral, Inc. | Actively stabilized platform system |
JP4191858B2 (ja) * | 1999-08-27 | 2008-12-03 | 有限会社泰成電機工業 | 断熱パネル及びそれを用いた断熱二重床の施工方法 |
GB0103782D0 (en) * | 2001-02-09 | 2001-11-21 | Alenia Marconi Systems Ltd | Improvements in or relating to scanning antenna systems |
JP2002280801A (ja) * | 2001-03-16 | 2002-09-27 | Mitsubishi Electric Corp | アンテナ装置及び導波管回転結合器 |
US6483458B1 (en) * | 2001-05-30 | 2002-11-19 | The Boeing Company | Method for accurately tracking and communicating with a satellite from a mobile platform |
US6774860B2 (en) * | 2002-05-15 | 2004-08-10 | Northrop Grumman Corporation | UAV (unmanned air vehicle) servoing dipole |
US7109937B2 (en) * | 2004-11-29 | 2006-09-19 | Elta Systems Ltd. | Phased array planar antenna and a method thereof |
US7528613B1 (en) * | 2006-06-30 | 2009-05-05 | Rockwell Collins, Inc. | Apparatus and method for steering RF scans provided by an aircraft radar antenna |
JP5365764B2 (ja) * | 2006-11-17 | 2013-12-11 | 株式会社トリガー | 刈払い用チップソー |
IL192601A (en) * | 2008-07-03 | 2014-07-31 | Elta Systems Ltd | Discovery / Transmission Device, System and Method |
US20100245196A1 (en) * | 2009-03-25 | 2010-09-30 | Eyal Miron | Antenna positioning system |
US20100271274A1 (en) * | 2009-04-27 | 2010-10-28 | Honeywell International Inc. | Self-stabilizing antenna base |
US8988274B2 (en) * | 2009-11-16 | 2015-03-24 | The Board Of Regents Of The University Of Oklahoma | Cylindrical polarimetric phased array radar |
US9812776B2 (en) * | 2012-04-02 | 2017-11-07 | Furuno Electric Co., Ltd. | Antenna device |
US9696416B2 (en) * | 2013-03-15 | 2017-07-04 | Blase Guy E | Mobile radar system |
FR3004586B1 (fr) * | 2013-04-16 | 2015-04-10 | Airbus Operations Sas | Radar meteorologique embarque a antenne rotative |
US10069200B2 (en) * | 2014-03-19 | 2018-09-04 | Insitu, Inc. | Mechanically steered and horizontally polarized antenna for aerial vehicles, and associated systems and methods |
CN104133432B (zh) * | 2014-05-27 | 2016-08-24 | 北京航天万达高科技有限公司 | 一种非正交六杆动中通伺服系统及控制方法 |
DE102015101721A1 (de) * | 2015-02-06 | 2016-08-11 | Lisa Dräxlmaier GmbH | Positionierungssystem für Antennen |
EP3264523A4 (en) * | 2015-02-24 | 2018-10-24 | Nec Corporation | Space stabilizing apparatus and space stabilizing method |
US10756428B2 (en) * | 2017-02-13 | 2020-08-25 | General Dynamics Mission Systems, Inc. | Systems and methods for inertial navigation system to RF line-of sight alignment calibration |
-
2016
- 2016-11-11 JP JP2016220597A patent/JP6760825B2/ja active Active
-
2017
- 2017-10-26 WO PCT/JP2017/038779 patent/WO2018088230A1/ja active Application Filing
- 2017-10-26 US US16/335,061 patent/US11223143B2/en active Active
- 2017-10-26 GB GB1903819.9A patent/GB2576803B/en active Active
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS4946849A (ja) * | 1972-07-31 | 1974-05-07 | ||
JPS57125503A (en) * | 1981-01-28 | 1982-08-04 | Tokyo Keiki Co Ltd | Antenna automatic directivity device |
JP2016005168A (ja) * | 2014-06-18 | 2016-01-12 | 三菱電機株式会社 | アンテナ装置 |
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