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WO1993005363A1 - Systeme d'antenne stabilisee - Google Patents

Systeme d'antenne stabilisee Download PDF

Info

Publication number
WO1993005363A1
WO1993005363A1 PCT/US1992/007599 US9207599W WO9305363A1 WO 1993005363 A1 WO1993005363 A1 WO 1993005363A1 US 9207599 W US9207599 W US 9207599W WO 9305363 A1 WO9305363 A1 WO 9305363A1
Authority
WO
WIPO (PCT)
Prior art keywords
antenna
bearing assembly
azimuth
further defined
arm
Prior art date
Application number
PCT/US1992/007599
Other languages
English (en)
Inventor
Lawrence F. Anderson
Dieter Moenig
Original Assignee
Anderson Lawrence F
Dieter Moenig
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Anderson Lawrence F, Dieter Moenig filed Critical Anderson Lawrence F
Publication of WO1993005363A1 publication Critical patent/WO1993005363A1/fr

Links

Classifications

    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/12—Supports; Mounting means
    • H01Q1/18—Means for stabilising antennas on an unstable platform

Definitions

  • Stabilized platforms for shipboard mounting of microwave antennas and the like normally employ some type of pendulum system or gyro stabilization, and these systems are widely employed for satellite tracking and navigation of vessels.
  • the present invention provides a marked improvement by stabilizing the antenna itself with a resultant reduction of weight of mast-mounted radomes, limitation of vibrations, reduction of noise of operation, and limitless azimuth anhle variation.
  • One of the requirements of shipboard antenna tracking systems is minimum weight because of the necessity of mounting same atop a mast of a ship so that the moment thereof during substantial pitch, roll or yaw with not unduly affect the vessel or the structural integrity of the mast and antenna mounting. It is also important that the system not be subject to undue vibrations that may originate from the carrier thereof or within the system itself. Another factor of importance for antennas employed for navigation or the like, is the noise of operation of the stabilization system.
  • the present invention addresses all of the foregoing problems to provide a major advancement in this field.
  • a stabilized antenna tracking system wherein the antenna itself is continuously directed toward an object such as a satellite, rather than stabilizing a platform upon which the antenna is mounted.
  • an object such as a satellite
  • the present invention proceeds alternatively to gyro-stabilize the antenna itself, while at the same time providing an unlimited azimuth angle variation and an extremely rapid reorientation of the antenna to lock into another satellite, for example, when navigational positioning requires such a change to continue uninterrupted position "fixes".
  • the present invention provides a three axis gyro stabilized antenna employing silent torque motors to control the gyroscope or gyroscopes together with means for "softening" gyroscope action for rapid reorientation of the antenna, or the like during intentional shifting of the antenna direction.
  • a universal joint or igimbals of particular construction is herein mated wi th an unlimited azimuth angle bearing mount to provide a degree of angular corrections in antenna direction unknown in conventional stabilization systems.
  • a "mounting arm" of unique configuration which accommodates degrees of motion beyond that available with conventional systems.
  • Figure 1 is a side elevational view of a stabilization system in accordance with the present invention
  • Figure 2 is a rear elevational view of the system of Figure 1;
  • Figure 3 is a central vertical sectional view of through a pedestal bearing assembly of the present system;
  • Figure 4 is a side elevational view of the hub and drive mechanism for the pedestal bearing assembly of Figure 3;
  • Figure 5 is a rear elevational view partially in section of a universal joint and parabola drive assembly as employed in the present invention
  • Figure 6 is a side elevational view of the elements of Figure 5;
  • Figure 7 is a schemic illustration of control means of the present invention.
  • the present invention includes a microwave antenna 11 having a parabolic dish 12 and a feed antenna 13 all mounted upon a base 14 that is adapted to be attached to some structure such as the mast of a ship, for example.
  • the antenna 11 is movable about three axes intersecting adjacent the center of the dish 12 at the back thereof for aiming the antenna at a satellite, for example, and maintaining such aim during movements of the antenna.
  • the present invention provides for accomplishing the aiming by stabilizing the antenna itself rather than stabilizing a platform upon which an antenna may be mounted and one or more gyroscopes are herein employed for this purpose, as described below.
  • the antenna mount includes an azimuth rotating arm 16 having a first horizontal section 17 and an upwardly inclined second section 18 that is shown to extend upwardly at an of angle about 40° to the first section,
  • the arm 16 is mounted by the first section 17 thereof upon a pedestal bearing assembly 21 in the base 14.
  • This tube 22 serves as a vibration absorption element and mounts the antenna 11 by means of gimbals or a universal joint 26.
  • the foregoing antenna mounting system will be see to provide for movement about three axes indicated in Figure 1 as ⁇ , ⁇ and ⁇ which intersect at the point A which is in fact the inter-section of the axes of the universal joint 26 mounting the antenna 11 on the center line thereof.
  • the antenna may thus be pivoted over a very wide range of angles, and the dashed lines 31 and 32, in Figure 1, indicate extreme positions of rotation of the antenna in the plane of that figure.
  • the degree of pitch and roll is limited, but the degree of angular variation in azimuth is not.
  • the present invention further provides for unlimited angular movement in azimuth, as further described below.
  • the antenna itself is herein stabilized and the present invention employes one or more gyroscopes or gyros mounted on the antenna itself, and energized to rotate at high speed for maintaining the antenna stabilized in space.
  • the illustrated embodiment hereof employs two gyros 33 and 34 mounted on the back of the dish 12.
  • the axes of rotation of the gyros is the line of sight of the antenna to a satellite, for example, and inasmuch as the gyros are spinning in a plane perpendicular to the line of sight, the gyros cause the antenna to continue to point to a satellite even though a ship upon which the antenna is mounted may roll or pitch.
  • a parabola drive assembly 36 is herein provided to apply corrective torques to the gyros 33 and 34, as further described below.
  • FIGS 3 and 4 generally illustrating the pedestal bearing assembly and drive 21.
  • This assembly comprises a hub rotary mounted on the fixed base 14.
  • the assembly 21 includes a vertical pedestal tube 41 adapted for connection to the bottom of base 14 interiorly thereof by mounting generally indicated at 42.
  • a hub 43 is mounted for rotation upon the tube 41 by means of upper and lower bearings 46 and 47 respectively and carries the antenna 11.
  • the hub 43 is connected to or forms a part of the azimuth arm 16 and is rotated about the pedestal tube 41 by an electric motor 48.
  • a cogged pulley wheel 49 is mounted atop the pedestal tube 41 and is connected by a cogged belt or timing belt 51- to a cogged motor pulley wheel 52 affixed to the shaft 53 of the motor 48.
  • the motor 48 is mounted on a lateral extension 56 of the hub 43 as generally indicated in Figure 4.
  • the pedestal bearing assembly 21 includes a number of elements for mounting the hub on the pedestal tube and including bearing sleeves 61 interiorly of the bearings 46 and 47 with a cylindrical bearing separator 62 therebetween about the tube 41.
  • Upper and lower bearing adaptors 63 and 64 fit about the bearings 46 and 47 respectively, and a top plate 66 is disposed above the upper bearing adaptor with bolts 67 extending therethrough into the lower bearing adaptor for securing the bearing to the hub 43.
  • the bearing sleeves 61 are notched to accept the upper and lower bearings 46 and 47 agai nst the pedestal tube 41 and these sleeves are f ormed of an insulating material.
  • the upper and lower bearings 46 and 47 of the pedestal bearing assembly 21 are employed to form an electrically conducting path from the stationery portion of the assembly to the rotary or hub portion in order to provide electrical power to the rotary mounted elements of the present invention.
  • Electrical connections are schematically illustrated in Figure 3, wherein a pair of electrical conductors 71 and 72 are shown to be separately connected to inner portions, or radially inner parts of the bearings 46 and 47 through appropriate openings provided in elements of the bearing assembly.
  • the pedestal bearing assembly 21 not only provides for controlled azimuth positioning of the azimuth arm 16 and consequently the antenna mounted thereon, but also provides for electrical connections to the interior or rotary portion of the invention. While the connection of RF energy may be conventional, the present invention also provides for the connection of AC power without the use of cables that necessarily wrap about the vertical axis or azimuth axis of the antenna. It is known from conventional stabilization systems that powering of same to the rotary portion of the system necessarily incorporates provisions for cable wrap and unwrap as the azimuth angle changes radically. The conventional use.
  • the parabolic drive assembly 36 hereof is herein provided to controllably precess the gyros 33 and 34, and referring to
  • FIG. 5 and 6 of the drawings it will be seen that such assembly is connected to the universal joint 26, Referring more particularly to these figures, there is shown an L-shaped bracket 81 secured to the inner or upper end of the tube 22, and mounting a first shaft 82 of the joint 26.
  • a housing 83 is mounted by bearings for rotation about the shaft 82, and carries a pulley wheel 84 at one end thereof.
  • a timing belt 86 extends about the pulley wheel 84 and about a pulley wheel
  • the pulley wheels are preferably to mesh with the cogs on the timing belt.
  • the drive assembly 36 also includes a second motor 91 mounted on an arm 92 mounted on a shaft 93 extending from the housing 83.
  • the shaft 93 is mounted within a cylinder 94 secured to the housing 83 and is carried by bearings 96.
  • the arm 92 is secured as by bolts or the like to the back of the parabola or dish 12.
  • a timing belt 101 extends about a pulley wheel 102 on the shaft of the motor 91, and also about a pulley wheel 103 secured to the housing 83. It will be appreciated that energization of the motor 91 will cause the. arm 92 to rotate about the shaft 93, and thus to swing the parabola 12 about the axis of the shaft 93.
  • the motors 88 and 91 are provided as torque motors, i.e., conventional motors that upon energization may operate at zero RPM, and in either direction.
  • Energization of the motor 91 will cause the shaft thereof to attempt to turn and inasmuch as the shaft is connect to the housing 83 by the timing belt 101, the result is that a torque will be applied to the arm 92 in an effort to rotate the parabola about the axis of the shaft 93.
  • energization of the motor 88 will cause the belt 86 to attempt to turn the pulley wheel 84 on the housing 83, so as to transmit to the parabola a torque about the axis of the shaft
  • the antenna 11 of the present invention is mounted to move about the vertical axis ⁇ , the horizontal axis ⁇ , and the cross axis ft. Azimuth movement about the vertical axis ⁇ is accomplished by the motor 48 through the pedestal bearing assembly 21, and is controlled by the heading of a ship or the like mounting the antenna with respect to a target such as a satellite.
  • Movement of the antenna about the the two mutually perpendicularly horizontal axes ⁇ and ⁇ is accomplished by the torque motors 88 and 91 which apply appropriate precessing forces to the gyro scopes 33 and 34 .
  • Control of the torque motors 88 and 91 is derived from motion sensor 106 and 108 associated with the universal joint 26.
  • Control of the antenna is schematically illustrated in Figure 7 wherein the above described elements of the present invention are schematically illustrated as being connected to a computer 111.
  • Outputs from the motion sensors 106 and 108 are applied to the computer as are signals from a turn indicator 112 associated with the pedestal bearing assembly and signals from a ship's gyro indicating ship heading at a terminal 116.
  • the computer 111 applies control signals to the azimuth bearing motor 48 and torque motors 88 and 91.
  • the antenna 11 hereof is directed toward a target such as a satellite and is then stabilized in such direction despite motions of the means, such as a the ship, mounting the antenna.
  • the system corrects for imbalances, vibrations, and the like which tend to cause the antenna to stray from the line of sight thereof.
  • the torgue motors 88 and 91 precess the gyros 33 and 34 by the application of appropriate forces to the antenna parabola 12.
  • the gyroscopes 33 and 34 are driven by conventional single phase capacitor motor and the present invention operates the computer 111 to reverse the drive of these motors in order rapidly slow down the gyroscopes in order "soften” the gyroscopes so that rapid processing of the gyros may be accomplished.
  • the gyroscope on the left is shown to include a rotating disk 116 driven by a capacitor motor 117 energized from a terminal 118 through a switch 119.
  • Control means 121 is provided to switch the drive of motor 17 from one direction to the nother and such means 121 are controlled by the computer 111.
  • the switch 119 and control means 121 may comprise a Triad, and same is operated to rapidly slow down rotation of the gyro disk 116 so that the antenna dish may be rapidly moved from one direction to another either for switching the aim thereof from one target to another or for stopping the gyros so that maintenance may be carried out on the system.
  • the present invention may incorporate a substantial amount of sophisticated control equipment, however, the basic elements of the present invention are described about with respect to the stabilized mounting of an antenna aboard means such as a ship that may be subject to wide variations in position and direction. It will be appreciated that mounting of the present invention atop a tall mast on a ship moving through rough sea results in the antenna itself making many varied and sometimes radical motions.
  • the gyroscopes, as corrected by the torque motors, hereof will maintain their line of sight to a target such as a satellite, and by means of the azimuth control hereof variations in ship's heading is compensated.
  • the stabilization system of the present invention is of relatively low weight and in fact a system built in accordance with this invention weighs only about 80% of the lightest ship board antenna stabilization presently known. This saving of weight at the top of the mast upon a ship is extremely important inasmuch as the lever arm of the mast materially increases the effect of the weight, not only with regard to the strain on the mast, itself, but also with regard to the stability of the ship carrying the present invention.
  • vibrations which are extremely detrimental to antenna stabilization it is noted that mounting the antenna by means of the tube 22 decreases vibrations transmitted to the parabola 12 and from same. Additionally, the exclusion of step motors in the present invention materially reduces the mount of vibration introduced into the system internally thereof.
  • vibrations of the parabola or disk 12 produce sound waves with are amplified and broadcast therefrom as from a horn and thus on pleasure craft, for example, the amount of noise generated and broadcast by a conventional antenna stabilization system may be very objectional, whereas the present invention produces an almost silent operation.
  • the stabilized antenna of the present invention is preferably enclosed in an envelope, and there is indicated in Figure 1 of the drawings, a radome 126 which may be formed of fiberglass or the like which is pervious to microwave radiation for enclosing the antenna.
  • a radome 126 which may be formed of fiberglass or the like which is pervious to microwave radiation for enclosing the antenna.
  • the overall system may have a height of slightly more than four feet and a diameter of less than four feet.
  • the present invention as described above, will be seen to provide numerous and significant advantages over prior art antenna stabilization systems.
  • the present system provides a substantially silent operation with unlimited azimuth variations to preclude the problem of cable wrap with a materially reduced weight of overall system and capability of rapidly realigning the line of sight of the antenna despite the use of gyroscopes thereon.

Landscapes

  • Details Of Aerials (AREA)
  • Variable-Direction Aerials And Aerial Arrays (AREA)

Abstract

Un système de poursuite à antenne stabilisée produit une stabilisation gyroscopique à trois axes de l'antenne (11) et du réflecteur (12) uniquement, et utilise des moteurs couples silencieux (88 et 91) produisant une variation d'angle azimutal illimitée et un bras de montage unique (16) permettant de maximiser le degré de déplacement de l'antenne.
PCT/US1992/007599 1991-09-09 1992-09-08 Systeme d'antenne stabilisee WO1993005363A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US75587991A 1991-09-09 1991-09-09
US755,879 1991-09-09

Publications (1)

Publication Number Publication Date
WO1993005363A1 true WO1993005363A1 (fr) 1993-03-18

Family

ID=25041053

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US1992/007599 WO1993005363A1 (fr) 1991-09-09 1992-09-08 Systeme d'antenne stabilisee

Country Status (1)

Country Link
WO (1) WO1993005363A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2368467A (en) * 2000-10-25 2002-05-01 Stanford Components Ltd Satellite signal receiving unit
RU2375792C1 (ru) * 2008-07-07 2009-12-10 Федеральное государственное образовательное учреждение высшего профессионального образования "ЮЖНЫЙ ФЕДЕРАЛЬНЫЙ УНИВЕРСИТЕТ" (ЮФУ) Самостабилизирующееся устройство для антенн и приборов судовой радиоэлектронной аппаратуры
US9300039B2 (en) 2010-10-25 2016-03-29 Thales Triaxial positioner for an antenna
US9577313B2 (en) 2011-12-08 2017-02-21 Spacecom Holding Aps Pedestal for tracking antenna
CN112928444A (zh) * 2021-01-23 2021-06-08 新万基卫星技术有限公司 一种船载动中通用天线

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4442435A (en) * 1980-06-03 1984-04-10 Tokyo Shibaura Denki Kabushiki Kaisha Gyro stabilization platform for scanning antenna
US4582291A (en) * 1981-04-28 1986-04-15 Matthews Robert J Mechanically stabilized platform system
US4833932A (en) * 1986-07-12 1989-05-30 The General Electric Company, P.L.C. Stabilised mount
US4913308A (en) * 1989-04-28 1990-04-03 Culbertson Russell D Liner retainer apparatus and method

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4442435A (en) * 1980-06-03 1984-04-10 Tokyo Shibaura Denki Kabushiki Kaisha Gyro stabilization platform for scanning antenna
US4582291A (en) * 1981-04-28 1986-04-15 Matthews Robert J Mechanically stabilized platform system
US4833932A (en) * 1986-07-12 1989-05-30 The General Electric Company, P.L.C. Stabilised mount
US4913308A (en) * 1989-04-28 1990-04-03 Culbertson Russell D Liner retainer apparatus and method

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2368467A (en) * 2000-10-25 2002-05-01 Stanford Components Ltd Satellite signal receiving unit
GB2368467B (en) * 2000-10-25 2002-09-11 Stanford Components Ltd Satellite signal receiving unit
RU2375792C1 (ru) * 2008-07-07 2009-12-10 Федеральное государственное образовательное учреждение высшего профессионального образования "ЮЖНЫЙ ФЕДЕРАЛЬНЫЙ УНИВЕРСИТЕТ" (ЮФУ) Самостабилизирующееся устройство для антенн и приборов судовой радиоэлектронной аппаратуры
US9300039B2 (en) 2010-10-25 2016-03-29 Thales Triaxial positioner for an antenna
US9577313B2 (en) 2011-12-08 2017-02-21 Spacecom Holding Aps Pedestal for tracking antenna
CN112928444A (zh) * 2021-01-23 2021-06-08 新万基卫星技术有限公司 一种船载动中通用天线

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