JP2008236769A - Lens antenna apparatus - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a lens antenna apparatus suitable for mounting on a mobile in which multibeam is realized with a simple and stable structure. <P>SOLUTION: A guide rail 130 is laid in parallel along the circumferential surface of the hemispherical lens 120 in a hemispherical lens antenna 100 and a plurality of radiators 140-160 are located and secured onto the guide rail 130. Since the radio beams of the plurality of radiators are subjected to directivity control during operation by regulating an AZ axis rotary mechanism 220, an EL axis rotary mechanism 230, and an xEL axis rotary mechanism 240, a small, lightweight and high precision satellite tracking performance is attained inexpensively. Since no driving section exists on the guide rail 130, even a multibeam to an adjoining satellite does not interfere with the driving section and a plurality of radiators can be arranged. Consequently, multibeam is attained with a simple and stable structure and an arrangement suitable for mounting on a mobile is attained. <P>COPYRIGHT: (C)2009,JPO&INPIT

Description

  The present invention relates to a lens antenna device that is used in a ground station of a satellite communication system and uses a spherical lens that focuses a radio wave beam, and particularly relates to a lens antenna device that has a structure suitable for mounting on a mobile object.

  Conventionally, by using a spherical lens that can focus a radio wave beam, a radiator is arranged at a predetermined position on the lower hemisphere of the spherical lens, and the directivity of the radiator is aligned with the center direction of the spherical lens, thereby obtaining a predetermined value. Development of a lens antenna device that forms a radio beam in the direction is in progress. This type of antenna device can direct a radio beam anywhere on the celestial sphere by simply moving the radiator position on the lower hemisphere of the spherical lens. There is no need to rotationally drive the drive system, and the drive system can be easily downsized.

  However, in the lens antenna device, since the spherical lens itself is a restriction on miniaturization, it is no longer possible to reduce the overall size. In addition, due to the spherical shape, there is a problem that handling during assembly is not easy. Therefore, as shown in Patent Documents 1 and 2, the upper hemisphere lens obtained by dividing the spherical lens is placed on the radio wave reflector, and the radio wave from the celestial sphere is focused by the hemisphere lens and reflected by the radio wave reflector. Thus, a hemispherical lens antenna device has been proposed that can capture radio waves on the peripheral surface side of the hemispherical lens.

This hemispherical lens antenna device has been attracting attention as being mounted on a moving body because it can be easily downsized. On the other hand, there is a demand for communication with a plurality of geostationary satellites in geostationary orbit. Therefore, it is desired to realize a multi-beam lens antenna device with a simple and stable structure.
JP 2001-025732 A JP 2003-110352 A

  As described above, it has been desired to realize a multi-beam lens antenna device with a simple and stable structure.

  The present invention has been made in view of the above situation, and an object of the present invention is to provide a lens antenna device that is suitable for mounting on a moving body by realizing a multi-beam structure with a simple and stable structure.

  In order to achieve the above object, a lens antenna device according to the present invention includes a fixed base disposed horizontally at an installation position, a rotation base mounted on the fixed base so as to be rotatable around an azimuth axis, and the rotation base. A hemispherical lens antenna mounted on a hemispherical lens that bisects a spherical lens that focuses a radio wave beam, and an elevator that passes through the center point of the hemispherical lens and that is orthogonal to the azimuth axis. A guide rail installed in parallel along the peripheral surface of the hemispherical lens, a wire moving mechanism for moving the wire along the guide rail , Radio waves that are disposed opposite to the hemispherical lens at arbitrary positions on the wire, are adjusted in polarization axis, and are focused by the hemispherical lens. A plurality of radiators each including an antenna element that forms a beam; an AZ axis rotation mechanism that rotates the rotation base around the azimuth axis; and an EL axis rotation mechanism that rotates the guide rail around the elevation axis. The plurality of radiators are a plurality of communication satellites each having a communication partner arranged on a geostationary orbit, and are positioned and fixed to the wire in accordance with the direction of the communication satellite corresponding to the initial setting, The radio wave beam of each of the plurality of radiators is controlled in direction by adjustment of the AZ axis rotation mechanism, the EL axis rotation mechanism, and the wire movement mechanism.

  Alternatively, a fixed base that is horizontally disposed at the installation position, a rotary base that is rotatably mounted on the fixed base around the azimuth axis, and an elevation shaft that passes through the center and is orthogonal to the azimuth axis on the rotary base. Is suspended in parallel with a spherical lens that focuses a radio wave beam, and an elevation axis that passes through the center of the spherical lens and that is perpendicular to the azimuth axis, and is parallel to the lower peripheral surface of the spherical lens. A guide rail, a wire moving mechanism for moving the wire along the guide rail, and moving the wire along the guide rail, respectively, and arranged to face the spherical lens at an arbitrary position on the wire. A plurality of radiators including antenna elements that are adjusted in polarization axis and form a radio wave beam focused by the spherical lens; The AZ axis rotation mechanism that rotates the rotation base around the azimuth axis, and the EL axis rotation mechanism that rotates the guide rail around the elevation axis. A plurality of communication satellites arranged in orbit, which are positioned and fixed directly on the wire in accordance with the direction of the communication satellite corresponding to the initial setting, and the radio wave beams of the plurality of radiators are the AZ Direction control is performed by adjusting the shaft rotation mechanism, the EL shaft rotation mechanism, and the wire moving mechanism.

  According to the present invention, the guide rail is installed in parallel along the hemispherical lens peripheral surface of the hemispherical lens antenna, and a plurality of radiators are positioned and fixed on the wires laid along the guide rail. Since the structure is such that the radio wave beam of each of the plurality of radiators is controlled by adjusting the AZ axis rotation mechanism, EL axis rotation mechanism, and wire movement mechanism, the satellite tracking performance is small, lightweight, low cost, and highly accurate. Since there is no drive unit on the guide rail, it is possible to arrange multiple radiators without interference of the drive unit even with multi-beams to adjacent satellites. A lens antenna device that is realized by the structure and is suitable for mounting on a moving body can be provided.

  Hereinafter, embodiments of the present invention will be described in detail with reference to the drawings.

  1A and 1B are schematic structural views showing a basic structure of a lens antenna device according to an embodiment of the present invention, where FIG. 1A is a perspective view seen obliquely from above, FIG. 1B is a side sectional view, and FIG. The perspective view seen from the lower part is shown. FIG. 2 is a conceptual diagram showing the coupling relationship of each component in the structure shown in FIG. Here, it is assumed that communication is performed with three communication satellites (not shown; hereinafter referred to as geostationary satellites) mounted on a mobile object and in geostationary orbit.

  The antenna unit 100 of the lens antenna apparatus shown in FIG. 1 has a hemispherical lens 120 that is a half of a spherical lens called a Luneberg placed on a flat radio wave reflecting plate 110, and extends along the circumferential surface of the hemispherical lens 120. Thus, the three radiators 140 to 160 are fixedly arranged on the guide rail 130 formed and arranged in a semicircular arc shape.

  Here, it is desirable that the radio wave reflector 110 is ideally a plane that extends infinitely, but actually the size is determined from the allowable range of antenna characteristics (gain, side lobe, etc.).

  The spherical lens is also referred to as a spherical dielectric lens, and is configured by stacking dielectrics on concentric spherical surfaces, and can focus substantially parallel radio waves passing therethrough at one point. In general, each dielectric constant of a laminated dielectric material becomes lower toward the outside. The hemispherical lens 120 used in the present embodiment is obtained by dividing the spherical lens by a plane passing through the center of the sphere. Since the radio wave reflector 110 is disposed under the cross section, the hemispherical lens 120 can be handled substantially as a spherical lens. .

  That is, in the antenna unit 100 configured as described above, radio waves from a geostationary satellite are incident from the side circumferential surface of the hemispherical lens 120. At this time, if the lens is a spherical lens, the radio wave is focused in the lens. However, in this embodiment, the hemispherical lens 120 that bisects the spherical lens is used and placed on the radio wave reflecting plate 110. The radio wave focused at is reflected by the radio wave reflector 110 at the cross section of the hemispherical lens 120. Therefore, the incident radio wave of the hemispherical lens 120 takes a path symmetric with respect to the case of the spherical lens. Therefore, the radiators 140 to 160 are arranged at the focal position, that is, the focal point of the radio wave beam formed on the side circumferential surface of the hemispherical lens 120. Thereby, the radiators 140 to 160 can receive radio waves from three geostationary satellites, and conversely, radio waves can be transmitted to each geostationary satellite.

  The antenna unit 100 having the above configuration is mounted on a rotating base 210 that is arranged on the fixed base 200 so as to be rotatable around the AZ axis. On the back surface of the rotation base 210, an AZ drive mechanism 220 for rotating the rotation base 210 around the AZ axis on the fixed base 200 is provided.

  Here, usually, radiators 140 to 160 are arranged in accordance with the azimuth and elevation angle of a geostationary satellite as a communication partner, with antenna unit 100 being substantially horizontal. However, for example, when it is used near an equator or in a mountainous slope, the radio wave incident angle and the outgoing angle of the hemispherical lens 120 become acute angles, and the radiators 140 to 160 become blocking targets. Therefore, as shown in the figure, the antenna unit 100 on the rotation base 210 is appropriately inclined with respect to the fixed base 200 from the horizontal plane. Thereby, radiator 140-160 can be removed from the range of blocking.

  In addition, the guide rail 130 is rotatable about the rotation base 210 with an EL (elevation) axis passing through the center point of the hemispherical lens 120 and orthogonal to the AZ (azimuth) axis as a fulcrum. It is formed so that it may become parallel along. An EL drive mechanism 230 for rotating the guide rail 130 around the EL axis is provided on the rotation base 210 side with respect to one end portion of the guide rail 130.

  On the guide rail 130, three radiators 140 to 160 each having an antenna element that forms a radio wave beam focused by the hemispherical lens 120 are disposed to face the hemispherical lens 120 at arbitrary positions. The position and polarization axis of each of the radiators 140 to 160 are determined according to the direction of the geostationary satellite corresponding to each at the time of initial setting. In either case, since the communication partner is a geostationary satellite, they can be arranged on the same guide rail 130.

  The guide rail 130 is provided with a mechanism 240 for controlling movement of the mounted radiators 140 to 160 along the guide rail 130 while maintaining the positional relationship with each other during tracking of the satellite. This mechanism is hereinafter referred to as an xEL (cross elevation) drive mechanism.

  As described above, in the lens antenna device of the present invention, as shown in FIG. 3, the positions of the radiators 140 to 160 are separated from each other by the three driving mechanisms around the AZ axis, the EL axis, and the xEL axis. It is possible to adjust freely along the peripheral surface of the hemispherical lens 120 while maintaining the above, and thus the directions of the three geostationary satellites can always be tracked.

  Since the guide rail 130 is overloaded above the rotation axis by the radiators 140 to 160, the xEL drive mechanism 240, etc., fine adjustment becomes difficult during rotation around the EL axis. Therefore, it is desirable to provide a balance weight 250 near the rotation axis of the guide rail 130 to reduce the upper load.

  Hereinafter, a specific configuration of each mechanism unit will be described.

  4A and 4B show a wire-type structure for realizing the xEL drive mechanism 240. FIG. 4A is a schematic perspective view, FIG. 4B is a detailed perspective view partially shown in section, and FIG. 4C is a cross-sectional view. In this method, the guide rail 130 is made hollow, the annular wire 241 is passed through the hollow interior, the pulleys 242 and 243 inside the guide rail both ends, and one pulley 242 is rotated in the forward and reverse directions by the motor 244 with a speed reducer. The wire 241 is moved back and forth, and the radiators 140 to 160 are respectively fixed to one side of the wire 241.

  Here, as shown in FIG. 4B, the guide rail 130 is partially opened on the peripheral surface side of the hemispherical lens 120, and guide frames 131 and 132 are formed on both side surface portions. On the other hand, the base 141 of the radiator (represented by 140 here) is provided with pulleys 142 and 143 that engage with the guide frames 131 and 132 of the guide rail 130, and an opening portion of the guide rail 130 at the center. A convex piece 144 is formed so as to be connected to the internal wire 241. By setting it as such a structure, with the movement of the wire 241, the radiators 140-160 can be simultaneously and smoothly moved along a guide rail.

  FIG. 5 shows a case of a V roller gear system as another system of the xEL drive mechanism 240 described above. In this method, the length of the guide rail 130 is extended longer than a semicircle, the inner and outer surfaces of one end are concave, the inner surface of the other end is concave, and the gear groove is formed on the outer surface. Is formed. On the rotation base 210, below the EL axis, the inner and outer sides of one end of the guide rail 130 are supported by three V rollers 245A, 245B, and 245C so as to be slidable, and the inner side of the other end. Is held by the V rollers 246A and 246B, the gear 247 is engaged with the outer gear groove, and the drive motor 248 to which the gear 247 is coupled is rotated in the forward and reverse directions. In the case of this configuration, since the entire guide rail can be rotated along the peripheral surface of the hemispherical lens 120, the radiators 140 to 160 may be directly fixed to the guide rail 130. Although this method is structurally complicated, a relatively stable EL drive can be expected because the center of gravity of the entire guide rail is lowered.

  By the way, in the case where the antenna aperture becomes large, the beam becomes sharp, and the driving accuracy on the AZ, EL, and xEL3 axes is insufficient with respect to the tracking accuracy, in addition to these axes, it is shown in FIG. As described above, X // which performs high-precision driving on the support part of the radiators 140 to 160 on a partial spherical surface in which the radial direction from the lens center is constant or on a plane perpendicular to the beam forming the pseudo-spherical surface. Y tables 140A, 150A, and 160A may be provided. According to this configuration, coarse adjustment (low frequency, large amplitude) is performed with three axes of AZ axis, EL axis, and xEL axis, and fine adjustment (high frequency, small amplitude) is performed with the X / Y table, and the sharing of the adjustment is performed. By separating, satellite tracking can be performed reliably. Originally, three axes are required for coarse adjustment, and three axes are required for the fine adjustment, plus two more axes in the direction of the X / Y table plus the polarization axis. By taking the axis configuration shown in FIG. Only the driving unit around the polarization axis, which is not very sensitive in tracking accuracy, can be separated independently without being combined with the remaining two axes, so that driving is omitted.

  FIG. 7 shows a structure in which the balance weight mechanism 250 for the EL drive of the guide rail 130 is realized by a spur gear system. In this system, the large first gear 251 is mounted on the EL shaft, the small second gear 252 is engaged with the first gear 251 above the EL shaft, and the shaft of the second gear 252 is the rotation base. Fix to 210. A balance weight (weight) 253 extends in the predetermined direction on the rotation shaft of the second gear 252.

  This structure has an unbalance that occurs around the EL axis with respect to the guide rail 130 and an object mounted on the guide rail 130, for example, in the vicinity of a position of 45 ° out of 30 ° to 60 ° in which the guide rail 130 is roughly operated. The balance weight 253 can be roughly canceled out. That is, the angle on the weight side is 45 ° when the guide rail 130 is approximately 45 °, and the counter-balance is generally achieved. In this case, the motor torque in the disturbance (translational vibration) has a weight approximately reduced by a reduction ratio on the EL axis, reduces the overall mass, and is balanced on the EL axis. The purpose is to minimize the impact on the environment. Further, in the reduction gear, it is desirable that the anti-backlash and the structure have sufficient rigidity with respect to the control frequency.

  FIG. 8 shows a structure realized by a bevel gear system as another configuration of the balance weight mechanism 250. In this system, the first bevel gear 254A is mounted on the EL shaft, the second bevel gear 254B is meshed with the first bevel gear 254A, and the third bevel gear 254C is coaxial with the second bevel gear 254B and has a large diameter. The fourth bevel gear 254D is meshed with the balance weight 255 extending in a direction orthogonal to the rotation axis of the fourth bevel gear 254D. Even with this structure, the balance weight 255 can roughly cancel out the unbalance generated around the EL axis with respect to the guide rail 130 and the object mounted on the guide rail 130.

  In the above embodiment, the geostationary satellite tracking algorithm drives the AZ and EL axes so that the guide rail 130 on the xEL axis coincides with the celestial equator (hereinafter referred to as the equator). Along the way, the satellite positions on the equator are matched. Since the distance between satellites on the equator and the polarization angle of the satellite with respect to the equator are constant, a multi-beam is established for all the satellites simultaneously by only the above control.

  When not in operation, it is assumed that large disturbances will occur, so each shaft must have a evacuation mode that prevents external disturbances from being applied to the drive unit or the structure unit using a storlock or unexcited operation brake. Is desirable.

  When used as a multi-beam, in some of the receive-only beams, if the antenna aperture is used as it is, there is a margin in gain and the beam tracking accuracy can be relaxed. The drive unit for fine adjustment may be omitted by widening the beam by shifting or the like.

  In addition, the present invention is not limited to the configuration of the above embodiment, and various modifications can be made.

1 is a schematic configuration diagram illustrating a basic structure of a lens antenna device according to an embodiment of the present invention. The conceptual diagram which shows the coupling | bonding relationship of each component in the structure shown in FIG. FIG. 2 is a perspective view schematically showing three drive mechanisms around an AZ axis, an EL axis, and an xEL axis shown in FIG. 1. The figure which shows the structure of the wire system which implement | achieves an xEL drive mechanism in the structure shown in FIG. The figure which shows the structure of the V roller gear system which implement | achieves an xEL drive mechanism in the structure shown in FIG. The perspective view which shows a mode that the X / Y table was provided in each radiator for the tracking fine adjustment in the structure shown in FIG. The side view which shows the structure which implement | achieved the balance weight mechanism with respect to EL drive of a guide rail by the spur gear system in the structure shown in FIG. The side view which shows the structure which implement | achieved the balance weight mechanism with respect to EL drive of a guide rail by the bevel gear system in the structure shown in FIG.

Explanation of symbols

  DESCRIPTION OF SYMBOLS 100 ... Antenna part, 110 ... Radio wave reflector, 120 ... Hemispherical lens, 130 ... Guide rail, 140-160 ... Radiator, 200 ... Fixed base, 210 ... Rotation base, 220 ... AZ drive mechanism, 230 ... EL drive mechanism, 240 ... xEL drive mechanism, 250 ... balance weight.

Claims (6)

A fixed base arranged horizontally at the installation position;
A rotating base mounted on the fixed base so as to be rotatable around the azimuth axis;
A hemispherical lens antenna that is mounted on the rotating base and is formed by placing a hemispherical lens that bisects a spherical lens that focuses a radio wave beam on a radio wave reflector;
A guide rail that passes through the center point of the hemispherical lens, and has an elevation axis perpendicular to the azimuth axis as a fulcrum, and is laid in parallel along the peripheral surface of the hemispherical lens;
A wire moving mechanism for moving the wire along the guide rail and moving the wire along the guide rail;
A plurality of radiators each including an antenna element that is arranged to be opposed to the hemispherical lens at an arbitrary position on the wire and whose polarization axis is adjusted and forms a radio wave beam focused by the hemispherical lens;
An AZ axis rotation mechanism that rotates the rotation base around the azimuth axis;
An EL axis rotation mechanism for rotating the guide rail around the elevation axis,
The plurality of radiators are a plurality of communication satellites each having a communication partner arranged in a geostationary orbit, and are positioned and fixed to the wire in accordance with the direction of the communication satellite corresponding to the initial setting,
The lens antenna device according to claim 1, wherein the radio wave beams of the plurality of radiators are controlled in direction by adjustment of the AZ axis rotation mechanism, the EL axis rotation mechanism, and the wire movement mechanism. A fixed base arranged horizontally at the installation position;
A rotating base mounted on the fixed base so as to be rotatable around the azimuth axis;
A spherical lens that is suspended on the rotation base with an elevation axis passing through the center and orthogonal to the azimuth axis as a fulcrum, and focuses the radio wave beam,
A guide rail that passes through the center of the spherical lens and has an elevation axis perpendicular to the azimuth axis as a fulcrum, and is laid in parallel along the lower peripheral surface of the spherical lens;
A wire moving mechanism for moving the wire along the guide rail and moving the wire along the guide rail;
A plurality of radiators each including an antenna element which is disposed opposite to the spherical lens at an arbitrary position on the wire and whose polarization axis is adjusted and forms a radio wave beam focused by the spherical lens;
An AZ axis rotation mechanism that rotates the rotation base around the azimuth axis;
An EL axis rotation mechanism for rotating the guide rail around the elevation axis,
The plurality of radiators are a plurality of communication satellites each having a communication partner arranged in a geostationary orbit, and are positioned and fixed directly on the wire in accordance with the direction of the communication satellite corresponding to the initial setting,
The lens antenna device according to claim 1, wherein the radio wave beams of the plurality of radiators are controlled in direction by adjustment of the AZ axis rotation mechanism, the EL axis rotation mechanism, and the wire movement mechanism.   The lens antenna device according to claim 1, wherein the radiator includes an X-Y axis adjustment mechanism for adjusting a radio wave focusing point of the antenna element on a fixed support portion.   3. The lens according to claim 1, further comprising a balance weight provided at at least one end of the guide rail for canceling an unbalance generated when the guide rail is rotated by the EL shaft rotation mechanism. Antenna device.   2. A control device for automatically controlling directivity control of a radio wave beam by adjusting the AZ axis rotation mechanism, the EL axis rotation mechanism, and the wire movement mechanism so as to track a satellite of a communication partner. 3. The lens antenna device according to 2.   The AZ-axis rotation mechanism, the EL-axis rotation mechanism, and the wire movement mechanism each include a evacuation mode that is set so that a disturbance that occurs during non-operation is not a load on the drive unit and the structure unit. Or the lens antenna apparatus of 2.

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