CN2405318Y - Anti-angle-turbulent type all direction follow antenna - Google Patents
Anti-angle-turbulent type all direction follow antenna Download PDFInfo
- Publication number
- CN2405318Y CN2405318Y CN99241672U CN99241672U CN2405318Y CN 2405318 Y CN2405318 Y CN 2405318Y CN 99241672 U CN99241672 U CN 99241672U CN 99241672 U CN99241672 U CN 99241672U CN 2405318 Y CN2405318 Y CN 2405318Y
- Authority
- CN
- China
- Prior art keywords
- moment
- gyrorotor
- axle
- antenna
- reaction
- Prior art date
- Legal status (The legal status 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 status listed.)
- Expired - Fee Related
Links
Images
Classifications
-
- 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
- H01Q19/13—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 being a single radiating element, e.g. a dipole, a slot, a waveguide termination
-
- 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
Landscapes
- Variable-Direction Aerials And Aerial Arrays (AREA)
Abstract
The utility model relates to an anti-angle-turbulent type all direction follow antenna, which is composed of an aerial, a reaction torque blast fan, a reaction torque fan electromotor, a gyroscope rotor, etc. Compared with the prior art, the utility model has the advantages of high constancy, reliability, high anti-interference capability, simple structure and low cost, and is suitable for popularization and disseminating. The utility model solves the problems of poly system monitoring items, complicated system, frequent actuator action, narrow frequency response, expensive cost, low reliability, bad anti-interference capability and inconvenient use and maintenance, etc. that exists in the prior product.
Description
The utility model relates to a kind of radio tracking system, particularly relates to a kind of motion carrier radio tracking antenna system.
With in the Tracking Antenna System, all motions of pedestal or carrier all directly or by the servomechanism indirect transfer are given antenna at fixed pedestal formula motion carrier.Usually, the angular speed that the motion involving vibrations of antenna pedestal (carrier) is produced is bigger than the angular speed that relative motion produced between target and the antenna, and it is changeable, it is the main cause that causes the aerial angle tracking error, in order to guarantee the accurate tracking target of antenna, the top priority of system is a stabilized antenna itself, the usual practice of this type of system stability antenna is at present: the angular movement state of ceaselessly measuring carrier (or pedestal), when carrier rotates, the control servomechanism makes antenna rotate with the angular speed of opposite sign but equal magnitude, and this system monitoring project is many, system complex, actuator acts frequently, frequency response is narrow, thereby involves great expense, and reliability is low, poor anti jamming capability, working service inconvenience.
The purpose of this utility model is: a kind of servo-actuated gyroscope type antenna mechanism that self can resist the angle disturbance of all directions (or three rotational freedom on) is provided, be applied to motion carrier with in the automatic tracking antenna system, to improve stability, reliability and antijamming capability, and simplified system, reduce cost, and then civilian general product is provided.
The utility model is to constitute like this: antenna (5) is connected on the interior ring (3), moment of reaction blast fan (9) and moment of reaction blast fan (14) are connected on the axle of moment of reaction fan electromotor (10) and moment of reaction fan electromotor (16), moment of reaction fan electromotor (10) is connected fan electromotor trailing arm (7) and fan electromotor trailing arm (15) again respectively with moment of reaction fan electromotor (16), fan electromotor trailing arm (7) and fan electromotor trailing arm (15) are connected on the interior ring (3), gyrorotor (6) connects gyrorotor axle (19), gyro drive motors (12) connects gyrorotor bearing pedestal (8), gyrorotor axle (19) is connected on the axle of gyro drive motors (12) by gyrorotor bearing pedestal (8), gyrorotor bearing pedestal (8) is installed on the outer shroud (11), outer shroud (11) is installed on the support (13), support (13) is installed on the column (2), column (2) is fixed on the antenna pedestal (1), with inner axle (17) and inner axle (20) gyrorotor bearing pedestal (8) is installed on the outer shroud (11), with outer annulate shaft (18) and outer annulate shaft (21) outer shroud (11) is installed on the support (13), support (13) is fixed on the axle (22), axle (22) utilizes Bearing Installation on column (2), and moment of reaction blast fan (9) is vertical mutually with the rotating shaft of moment of reaction blast fan (14) and jointly perpendicular to the axis of gyrorotor axle (19).
Accompanying drawing the 1, the 2nd, structural representation of the present utility model.
Compared with prior art, the utility model stability is high, and reliability and antijamming capability are strong, and structure relatively Simply, cheap, be suitable for popularizing, solved the problem that existing product exists.
Embodiment of the present utility model: antenna (5) is connected on the interior ring (3), moment of reaction blast fan (9) and moment of reaction blast fan (14) are connected on the axle of moment of reaction fan electromotor (10) and moment of reaction fan electromotor (16), moment of reaction fan electromotor (10) is connected fan electromotor trailing arm (7) and fan electromotor trailing arm (15) again respectively with moment of reaction fan electromotor (16), fan electromotor trailing arm (7) and fan electromotor trailing arm (15) are connected on the interior ring (3), gyrorotor (6) connects gyrorotor axle (19), gyro drive motors (12) connects gyrorotor bearing pedestal (8), gyrorotor axle (19) is connected on the axle of gyro drive motors (12) by gyrorotor bearing pedestal (8), gyrorotor bearing pedestal (8) is installed on the outer shroud (11), outer shroud (11) is installed on the support (13), support (13) is installed on the column (2), column (2) is fixed on the antenna pedestal (1), with inner axle (17) and inner axle (20) gyrorotor bearing pedestal (8) is installed on the outer shroud (11), with outer annulate shaft (18) and outer annulate shaft (21) outer shroud (11) is installed on the support (13), support (13) is fixed on the axle (22), axle (22) utilizes Bearing Installation on column (2), moment of reaction blast fan (9) is vertical mutually with the rotating shaft of moment of reaction blast fan (14) and jointly perpendicular to the axis of gyrorotor axle (19), spherical antenna seat (4) is fixed on the antenna pedestal (1); In the present embodiment, system parameters and requirement: antenna diameter: 1.6m; Antenna and annex quality: 6.2kg; Center of gravity 0.31m (to the summit); Carrier max line acceleration: 1g; Maximum rocking tendency: 15 °; 30 °/S of maximum angular frequency; The adjusting time: less than 1.4S/1 °; Anti-angle-turbulent type omnidirectional tracking antenna mechanism major parameter is selected: spin rotor momentum: 140kg.m2.S-1; Interior ring assemblies maximum rotation inertia (to the gimbals center): 2.9kg.m2; The maximum moment of supporting and the internal ring assemblies of other harmful moments: less than 0.1N.M; Fan blade number: size: length * wide * groove depth=0.21m * 0.1m * 0.03mm; Fan electromotor power: 180W; Fan motor rotational speed: 750r/min, the angle of pitch :-18 °～108 °; But interior ring deflection angle in outer shroud: ± 18 °; Hurricane globe size: diameter * wall thickness=2m * 0.002m (material glass steel); The main performance of mechanism: supporting and the caused antenna deflection of other harmful moments maximum angular rate: less than 0.04 °/S; Blast fan maximum effect moment: 2.1N.M; Antenna yaw rate during the input of step control signal: 0.82 °/S, maximum nutating amplitude: less than 0.018 °; The angle of pitch allows pedestal beat ± 18 ° in 0 °～90 °; During use: outer annulate shaft (18) and outer annulate shaft (21) constitute the outer shroud rack shaft of three free gyroes, outer shroud (11) can rotate around it, its corner forms the angle of pitch, inner axle (17) and inner axle (20) constitute free gyroscope by the ring support rotating shaft, gyrorotor bearing pedestal (8) can rotate around it, angle range exceeds with the inclination angle maximum of waving that surpasses carrier, the corner of the axis of this corner and support (13) column (2) is united the formation azimuth, gyrorotor (6) can be made high speed rotating under the driving of gyro drive motors (12), moment of reaction blast fan (9) and moment of reaction blast fan (14) are driven by moment of reaction fan electromotor (10) and moment of reaction fan electromotor (16) respectively can make forward or reverse, interior ring assemblies (promptly being fixed on all members and annex on the gyrorotor bearing pedestal (8)) is when the spatial direction of the axis of gyrorotor axle (19) or antenna (5) is in the normal range (NR), has only the constraint of this point of gimbals center, do not get in touch and have machinery with antenna pedestal, and no matter the axis of gyrorotor axle (19) or antenna (5) is horizontal still vertical position, all has 2 deflection degrees of freedom.Except the faint influence of bearing frictional torque and other harmful moments (causing) by rigging error and feeder cable collection, any motion of antenna pedestal (1) and column (2) can not cause the axis tilt of gyrorotor axle (19) or antenna (5), and the moment of momentum of gyrorotor (6) is big more, the influence of bearing frictional torque and other harmful moments is more little, the stability that is antenna is high more, can make the moment of momentum of gyrorotor (6) enough big, so that the influence of bearing frictional torque and other harmful moments is in the allowed band, thereby make antenna (5) be in " isolation " state to the angular displacement (disturbance) of antenna pedestal (1) or column (2), when needs make the axis tilt of antenna (5), make moment of reaction blast fan (9), moment of reaction blast fan (14) rotates, because the reaction force of air, interior ring assemblies obtains the moment of couple, make gyrorotor (6) thereby the axis tilt of generation precession drive antenna (5), the blade of moment of reaction blast fan (9) and support (13) is made symmetrical bathtub construction, purpose is to obtain the resistance symmetry of big coefficient of air resistance and rotating, the influence of ring assemblies balance in when the effect of spherical antenna seat (4) is to avoid external wind, the while can increase the wind loading rating of system.
Claims (3)
1, omnidirectional's follow antenna of anti-angle-turbulent type, it is characterized in that: antenna (5) is connected on the interior ring (3), moment of reaction blast fan (9) and moment of reaction blast fan (14) are connected on the axle of moment of reaction fan electromotor (10) and moment of reaction fan electromotor (6), moment of reaction fan electromotor (10) is connected fan electromotor trailing arm (7) and fan electromotor trailing arm (15) again respectively with moment of reaction fan electromotor (16), fan electromotor trailing arm (7) and fan electromotor trailing arm (15) are connected on the interior ring (3), gyrorotor (6) connects gyrorotor axle (19), gyro drive motors (12) connects gyrorotor bearing pedestal (8), gyrorotor axle (19) is connected on the axle of gyro drive motors (12) by gyrorotor bearing pedestal (8), gyrorotor bearing pedestal (8) is installed on the outer shroud (11), outer shroud (11) is installed on the support (13), support (13) is installed on the column (2), and column (2) is fixed on the antenna pedestal (1).
2, according to omnidirectional's follow antenna of the described this anti-angle-turbulent type of claim 1, it is characterized in that: gyrorotor bearing pedestal (8) is installed on the outer shroud (11) with inner axle (17) and inner axle (20), with outer annulate shaft (18) and outer annulate shaft (21) outer shroud (11) is installed on the support (13), support (13) is fixed on the axle (22), and axle (22) utilizes Bearing Installation on column (2).
3, according to omnidirectional's follow antenna of claim 1,2 described this anti-angle-turbulent types, it is characterized in that: moment of reaction blast fan (9) is vertical mutually with the rotating shaft of moment of reaction blast fan (14) and jointly perpendicular to the axis of gyrorotor axle (19).
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN99241672U CN2405318Y (en) | 1999-11-25 | 1999-11-25 | Anti-angle-turbulent type all direction follow antenna |
| PCT/CN2000/000520 WO2001056109A1 (en) | 1999-11-25 | 2000-11-27 | An omnidirectional follower antenna apparatus |
| AU16901/01A AU1690101A (en) | 1999-11-25 | 2000-11-27 | An omnidirectional follower antenna apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN99241672U CN2405318Y (en) | 1999-11-25 | 1999-11-25 | Anti-angle-turbulent type all direction follow antenna |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2405318Y true CN2405318Y (en) | 2000-11-08 |
Family
ID=5317513
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN99241672U Expired - Fee Related CN2405318Y (en) | 1999-11-25 | 1999-11-25 | Anti-angle-turbulent type all direction follow antenna |
Country Status (3)
| Country | Link |
|---|---|
| CN (1) | CN2405318Y (en) |
| AU (1) | AU1690101A (en) |
| WO (1) | WO2001056109A1 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103149482A (en) * | 2013-02-26 | 2013-06-12 | 浙江中星光电子科技有限公司 | Inspection device and method for ship-borne satellite signal receiving antenna |
| CN103737575A (en) * | 2013-12-31 | 2014-04-23 | 北京机械设备研究所 | Spatial orientation pointing device |
| CN106030118A (en) * | 2014-06-13 | 2016-10-12 | 依必安-派特圣乔根有限责任两合公司 | Antenna arrangement having a fan unit |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2075758B (en) * | 1980-05-03 | 1983-11-30 | Marconi Co Ltd | A stabilised antenna arrangement |
| DE8905673U1 (en) * | 1989-05-05 | 1989-06-22 | Richard Hirschmann GmbH & Co, 7300 Esslingen | Antenna that can be swivelled using a motor spindle |
-
1999
- 1999-11-25 CN CN99241672U patent/CN2405318Y/en not_active Expired - Fee Related
-
2000
- 2000-11-27 WO PCT/CN2000/000520 patent/WO2001056109A1/en active Search and Examination
- 2000-11-27 AU AU16901/01A patent/AU1690101A/en not_active Abandoned
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103149482A (en) * | 2013-02-26 | 2013-06-12 | 浙江中星光电子科技有限公司 | Inspection device and method for ship-borne satellite signal receiving antenna |
| CN103149482B (en) * | 2013-02-26 | 2015-06-10 | 浙江中星光电子科技有限公司 | Inspection device and method for ship-borne satellite signal receiving antenna |
| CN103737575A (en) * | 2013-12-31 | 2014-04-23 | 北京机械设备研究所 | Spatial orientation pointing device |
| CN106030118A (en) * | 2014-06-13 | 2016-10-12 | 依必安-派特圣乔根有限责任两合公司 | Antenna arrangement having a fan unit |
| CN106030118B (en) * | 2014-06-13 | 2019-04-26 | 依必安-派特圣乔根有限责任两合公司 | Antenna system with fan unit |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2001056109A1 (en) | 2001-08-02 |
| AU1690101A (en) | 2001-08-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA1058523A (en) | Wind-driven power plant | |
| US7677862B2 (en) | Vertical axis wind turbine with articulating rotor | |
| US20080012346A1 (en) | Wind-turbine with load-carrying skin | |
| CN105281034A (en) | Miniature antenna servo apparatus | |
| CN103115233B (en) | A kind of spacescan support with Self-balancing | |
| CN101924266B (en) | Spherical three-degree-of-freedom parallel mechanism antenna structure system | |
| CN2405318Y (en) | Anti-angle-turbulent type all direction follow antenna | |
| CN109667358A (en) | Self-adaptive mechanical drive rotational inertia adjusting type control system | |
| CN108933332A (en) | A kind of symmetrical four-freedom hybrid formula antenna structure system | |
| US20060032985A1 (en) | Clutch driven reaction wheel steering unit | |
| CN106927066B (en) | A kind of five axis position markers | |
| CN201887143U (en) | Small-sized antenna pedestal with compact structure | |
| US6191749B1 (en) | Arrangement comprising an antenna reflector and a transceiver horn combined to form a compact antenna unit | |
| CN109743895B (en) | Three Degree Of Freedom high-precision driving device | |
| CN213816395U (en) | Large-scale radio telescope of unidirectional cable drive every single move motion formula | |
| CN2508470Y (en) | Moveable satellite signal receiving device | |
| CN212587715U (en) | A horizontal motion structure of a parabolic antenna turntable | |
| KR20130142515A (en) | A aerial wind power generating system | |
| CN216624555U (en) | Antenna pedestal and radar | |
| CN205718939U (en) | A kind of space shuttle attitude gyro | |
| CN107357324B (en) | Control-moment gyro, control moment gyroscope and mobile devices | |
| TWM596277U (en) | Wind power generating device | |
| WO2011034028A1 (en) | Solar power generator | |
| CN219096988U (en) | Miniature control moment gyro structure | |
| JP7193394B2 (en) | Combined wind and wave power generator |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |