CN101262086B - Parallel antenna structure system - Google Patents
Parallel antenna structure system Download PDFInfo
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- CN101262086B CN101262086B CN2008100363989A CN200810036398A CN101262086B CN 101262086 B CN101262086 B CN 101262086B CN 2008100363989 A CN2008100363989 A CN 2008100363989A CN 200810036398 A CN200810036398 A CN 200810036398A CN 101262086 B CN101262086 B CN 101262086B
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Abstract
本发明涉及一种并联机构天线结构系统。它由一个天线反射体联结一个天线座架构成，天线座架是六个伺服电机分别驱动六个直线伸缩驱动装置，该六个直线伸缩驱动装置的上端与一块上平台铰连，而下端与一块下平台铰连，构成六自由度并联机构。本发明能圆满解决获取卫星、运载火箭等飞行器的遥感遥测信号和数据，实现天线“过顶”空域连续跟踪，达到半球工作空域。
The invention relates to a parallel mechanism antenna structure system. It consists of an antenna reflector connected with an antenna pedestal. The antenna pedestal is six servo motors respectively driving six linear telescopic drive devices. The lower platform is hinged to form a six-degree-of-freedom parallel mechanism. The invention can satisfactorily acquire remote sensing and telemetry signals and data of aircraft such as satellites and carrier rockets, realize the continuous tracking of the antenna "over the top" airspace, and reach the hemispherical working airspace.
Description
Technical field
The present invention relates to a kind of antenna structure system based on parallel institution.The antenna structure system that is used for space remote sensing, satellite " three is distant " technology (remote sensing, remote measurement, telecontrol engineering) and satellite communication.Antenna structure system and servo-control system, feed feeder system (be called for short: day, watch, present) are formed antenna system, realize remote sensing, telemetry and telecommand information is obtained and instruct, and realize that satellite communication information transmits and handle.Especially can obtain the telemetered signal and the data in the effective spatial domains of aircraft such as satellite, carrier rocket, realize not having the Continuous Tracking antenna system on top " blind area ", satisfactorily resolve any attitude Continuous Tracking in antenna hemisphere work spatial domain.Technical scheme of the present invention belongs to electromechanical integration technology area.
Background technology
The antenna-reflected body portion generally has main reflector panel, back frame structure, centerbody, balance weight structure, and subreflector and focus control and supporting construction thereof or feedforward supporting construction are formed; The antenna mount part generally is made up of antenna pedestal supporting construction, driving shaft system and transmission device, feeder line and cable wind, Data Detection transfer device and safety guard.
At present; Known in the world space remote sensing, satellite " three is distant " technology (remote sensing, remote measurement, telecontrol engineering) adopt classical pitching-orientation type (EL-AZ type) antenna; Pitching-orientation type antenna exists " blind awl " zone that can't " cross and push up " Continuous Tracking in the antenna zenith position, and the size (being the cone-apex angle of blind awl) in blind awl zone depends on the distance and the aircraft horizontal flight speed of antenna and aircraft.Low rail remote sensing antenna is not satisfactorily resolved so far as yet the problem of " crossing the top " Continuous Tracking.Introduce the notion of a sky line following " blind awl district " earlier, classical pitching-orientation type antenna pedestal is when tracking target, and (in the formula: V is the horizontal velocity of target flight to antenna bearingt angular speed: β=V/ (R*cos ε); R is the air line distance that antenna arrives target; ε is an antenna elevation angle; β is an antenna bearingt angular speed), when target near the antenna zenith through the time, elevation angle ε → 90 °, cos ε → 0, β → ∞.But motor-driven power is limited, and the antenna rotational angular also is limited, and under certain driving power, antenna can only be followed the tracks of the target below a certain elevation angle, near pitching-orientation type antenna zenith, exist can't Continuous Tracking " blind awl district ".
At present; Pitching in the engineering reality-orientation type (EL-AZ type) antenna exists " blind awl " zone that can't " cross and push up " Continuous Tracking in the antenna zenith position, can't adopt classical pitching-orientation type antenna to be implemented in the antenna zenith position and " cross and push up " Continuous Tracking.Can only select to avoid the satellite transit track and build the satellite ground station antenna through the place of antenna zenith.
The remote sensing remote measurement low orbit satellite Antenna Design of traditional classical generally adopts pitching-orientation type (EL-AZ type) antenna pedestal; There was top " blind awl district " in it; Pitching-orientation type antenna can't be crossed top " blind awl district " spatial domain Continuous Tracking satellite at satellite, realizes the demand of the uninterrupted continuous operation of signal.
Summary of the invention
The problem that the objective of the invention is to the prior art existence provides a kind of parallel antenna structure system; Realize not having the Continuous Tracking antenna system on top " blind area "; Satisfactorily resolve any attitude Continuous Tracking in antenna hemisphere work spatial domain, realize the demand of satellite-signal and the uninterrupted continuous operation of data.It is convenient easy to separate owing to the equation of motion of finding the solution parallel institution is counter, is easy to realize SERVO CONTROL.
In order to achieve the above object; Design of the present invention is: utilize parallel institution have that rigidity is big, precision is high, speed is fast, bearing capacity is big, simple in structure, in light weight and control distinct advantages such as convenient; And the equation of motion of parallel institution counter separate find the solution convenient easily, be easy to realize SERVO CONTROL.Be applied to the design of remote sensing remote measurement low orbit satellite antenna, given full play to the characteristics of parallel institution.Adopt space six-degree-of-freedom parallel connection mechanism (Stewart platform mechanism) as antenna mount; Adopt space six cover linear telescopic drive units to connect upper and lower two platforms; Connect formation Stewart platform mechanism through ball pivot or universal hinge (Hooke's hinge), realize the six-degree-of-freedom parallel connection mechanism antenna mount.Upper mounting plate connects through flange-interface and various forms of antenna reflector, and lower platform and ground are fixed, and also can connect with other carriers (as: skeletons such as vehicle, naval vessel and aircraft) to constitute motor-driven antenna system.Through to the analysis of spatial mechanism of space six-degree-of-freedom parallel connection mechanism (Stewart platform mechanism), comprehensive and theoretical derivation; Rationally choose bar length, collapsing length and the space angle of six cover linear drive apparatus; Solving on a large scale, the rotational angle movement position does not have unusual position problem, realization space remote sensing, remote sensing telemetering antenna hemisphere spatial domain Continuous Tracking antenna structure system.The antenna system that this invention and corresponding feed system and servo-control system constitute; Realize the telemetered signal and the data in the effective spatial domains of aircraft such as satellite, carrier rocket; Satisfactorily resolve the top and followed the tracks of " blind area " problem, realized the antenna system of " crossing the top " Continuous Tracking.
According to the foregoing invention design, the present invention adopts following technical proposals:
A kind of parallel antenna structure system; Connecting an antenna mount by an antenna reflector constitutes; The structure that it is characterized in that said antenna mount is: six servomotors drive six linear telescopic drive units respectively; The upper end of these six linear telescopic drive units and a upper mounting plate are hinged, and lower end and a lower platform are hinged, and constitute six-degree-of-freedom parallel connection mechanism.
Every adjacent two upper ends of six above-mentioned linear telescopic drive units are hinged through a projection of ball pivot or universal hinge and said upper mounting plate bottom surface, and every adjacent two lower ends are through a projection hinge of ball pivot or universal hinge and said and a lower platform upper surface.
Above-mentioned upper and lower two platforms are triangle, and upper and lower two triangle position differs 60 °, and the installation that is parallel to each other.
Above-mentioned upper mounting plate is fixedly connected with antenna reflector, and said lower platform is connected with ground frame or antenna carrier frame.
The structure of above-mentioned antenna reflector is: a centerbody is with back frame structure outward, and the back frame structure upper surface lays reflector panel, and centerbody is installed subreflector through a supporting construction.
The invention has the beneficial effects as follows: can solve classical pitching-orientation type (EL-AZ type) antenna satisfactorily and cross zenith " blind awl district " spatial domain Continuous Tracking satellite problem, realize the demand of space remote sensing, satellite remote sensing telemetered signal and satellite communication signal and the uninterrupted continuous operation of information at antenna.And the antenna of same bore, technical indicator; The weight of antenna structure system of the present invention is starkly lower than classical pitching-orientation type (EL-AZ type) antenna weight; Especially more obvious when large aperture antenna; Be merely the 70%-50% of pitching-orientation type (EL-AZ type) antenna weight, saved production cost greatly.
Description of drawings
Fig. 1: the structured flowchart that is antenna system.
Fig. 2: the structural representation that is parallel antenna structure system of the present invention.
Fig. 3: the antenna level that is antenna structure system shown in Figure 2 refers to flat attitude sketch map.
Fig. 4: the sketch map that is antenna structure system antenna reflector of the present invention.
Fig. 5: the vertical view that is Fig. 4.
Fig. 6: the structural representation that is antenna structure system antenna mount of the present invention.
Fig. 7: the vertical view that is Fig. 6.
Fig. 8: the upward view that is Fig. 6.
Embodiment
A preferred embodiment of the present invention accompanying drawings is following:
At Fig. 1 antenna system 1 being shown is made up of antenna structure system 2 and corresponding feed system 3, servo-control system 4 and corresponding supporting electronic equipment thereof jointly; Realize automatic tracking satellite and aircraft, accomplish satellite or aircraft signal and data passes, analysis and processing.
Referring to Fig. 2 and Fig. 3, this parallel antenna structure system is made up of antenna reflector 5 and antenna mount 6.
Referring to Fig. 4 and Fig. 5, this antenna structure system antenna reflector 5 is made up of subreflector (the no subreflector that feedovers, only the rear feed pattern has subreflector) and supporting construction 7, main reflector panel 8, back frame structure 9 and centerbody 10.
Referring to Fig. 6, Fig. 7 and Fig. 8, this antenna structure system antenna mount 6 is made up of upper mounting plate 11, six cover linear telescopic drive units 12 and servomotor 13, lower platform 14 and ground frame 15.Servo-control system realizes that to drive upper mounting plate 11 antenna reflector points to the satellite or the aircraft of required tracking, realizes signal, information exchange or reception by feed system according to tracer request instruction servomotor 13 driving spaces six cover linear telescopic devices 12.
Above-mentioned linear telescopic drive unit 12 and servomotor 13 thereof can be worm drive (as: screw-and-nut mechanisms), and its nut is directly driven by servomotor or passes through its rotation of actuator drives, thereby the screw rod straight line is moved; Also can be that direct the driving perhaps of servomotor provides power oil through oil pump of actuator drives, piston rod moved as straight line by the power oil driving oil cylinder.
Claims (1)
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| Application Number | Priority Date | Filing Date | Title |
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| CN2008100363989A CN101262086B (en) | 2008-04-21 | 2008-04-21 | Parallel antenna structure system |
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| CN2008100363989A CN101262086B (en) | 2008-04-21 | 2008-04-21 | Parallel antenna structure system |
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| CN101262086A CN101262086A (en) | 2008-09-10 |
| CN101262086B true CN101262086B (en) | 2012-08-08 |
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Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101630776B (en) * | 2009-07-29 | 2013-03-20 | 中国科学院国家天文台南京天文光学技术研究所 | Easily adjusted reflection panel back frame structure and reflection panel supporting structure |
| CN101924266B (en) * | 2010-06-12 | 2013-07-17 | 上海大学 | Spherical three-degree-of-freedom parallel mechanism antenna structure system |
| CN102904017B (en) * | 2012-06-28 | 2016-04-06 | 上海创投机电工程有限公司 | Hemispherical work spatial domain parallel antenna structure system |
| CN102832438B (en) * | 2012-08-28 | 2014-07-16 | 西北工业大学 | Regular-triangle-unit planar array deployable mechanism |
| CN103779665B (en) * | 2013-09-18 | 2017-02-22 | 贵州振华天通设备有限公司 | Connecting method and connecting structure for improving the main reflector accuracy of antenna |
| CN105186142A (en) * | 2015-09-28 | 2015-12-23 | 上海创投机电工程有限公司 | 3/6-SPU type parallel mechanism based antenna structural system |
| CN106450653B (en) * | 2016-09-08 | 2023-05-09 | 中国电子科技集团公司第五十四研究所 | Parallel six-degree-of-freedom redundancy driving antenna structure system |
| CN111509388B (en) * | 2020-04-30 | 2022-03-15 | 庆安集团有限公司 | Ground radar antenna system |
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| CN1546875A (en) * | 2003-11-29 | 2004-11-17 | 浙江大学 | Generalized Loading System Based on Parallel Six Degrees of Freedom Platform |
| CN1814416A (en) * | 2006-02-28 | 2006-08-09 | 浙江工业大学 | Six-degree-of-freedom steel band parallel robot mechanisw |
| CN1909285A (en) * | 2006-08-14 | 2007-02-07 | 西安电子科技大学 | Multiple-wave feed automatic switch and drive device for large-scale flexible radio telescope antenna |
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|---|---|---|---|---|
| CN1546875A (en) * | 2003-11-29 | 2004-11-17 | 浙江大学 | Generalized Loading System Based on Parallel Six Degrees of Freedom Platform |
| CN1814416A (en) * | 2006-02-28 | 2006-08-09 | 浙江工业大学 | Six-degree-of-freedom steel band parallel robot mechanisw |
| CN1909285A (en) * | 2006-08-14 | 2007-02-07 | 西安电子科技大学 | Multiple-wave feed automatic switch and drive device for large-scale flexible radio telescope antenna |
Non-Patent Citations (1)
| Title |
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| 管涛.在天线伺服系统中的虚拟轴技术.《机械》.2006,第33卷第88-90页. * |
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