CN103545591A - A Sun Fancy Solid Deployable Antenna - Google Patents
A Sun Fancy Solid Deployable Antenna Download PDFInfo
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- CN103545591A CN103545591A CN201310552082.6A CN201310552082A CN103545591A CN 103545591 A CN103545591 A CN 103545591A CN 201310552082 A CN201310552082 A CN 201310552082A CN 103545591 A CN103545591 A CN 103545591A
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Abstract
The invention provides a sunflower type solid antenna capable of being spread. The sunflower type solid antenna capable of being spread aims at resolving the problems that mesh type and inflatable antenna molded surfaces are not high in precision and limited in working frequency at preset. According to the sunflower type solid antenna capable of being spread, a regular dodecagon plate body serves as a base, six driving shafts and six universal shafts are arranged in a staggered mode along the edge of the base, each driving shaft is connected with a corresponding edge on the base through the corresponding driving shaft support, the two ends of each driving shaft are respectively connected with one end of an adjacent universal shaft, each driving shaft is connected with the lower end of a main spherical shell, the other side of each auxiliary spherical shell is connected with the other side of an adjacent auxiliary spherical shell through a spherical hinge mechanism, the middle of each universal shaft is connected with the lower end of a connecting rod, and the upper end of each connecting rod is connected with the corresponding spherical hinge mechanism. The sunflower type solid antenna capable of being spread is used for the field of antennas.
Description
Technical field
The present invention relates to a kind of antenna, be specifically related to a kind of sun fancy solid deployable antenna.
Background technology
Developing Space cause is the important content of the long-term science and technology development planning of China, and a lot of great Space Science and Technology engineering of China all has close relationship with space deployable structure.At present, deployable antenna is widely used in the fields such as military affairs, space flight, information.Along with scientific and technological development, the deployable antenna of heavy caliber, high accuracy, lightweight is just becoming the development trend of deployable antenna.
According to the material of working face, deployable antenna can simply be divided into 3 classes: network type, gas-filled type and solid reflecting surface formula.The major defect of first two antenna is that profile precision is not high enough and operating frequency is restricted, and for the antenna of a diameter 10-15m, its profile precision is limited in about 2mmrms; Its working frequency range is limited in below 5GHz.During line working frequency range on the same day very high (such as 40GHz), grid type and gas-filled type folding exhibition antenna can not meet the requirement to antenna profile precision such as satellite, space shuttle, and solid reflector antenna is with the physical property of its solid card and the linked system of high rigidity, can provide very high profile precision.The maximum gauge of antenna when the restriction of delivery vehicle diameter has restricted transmitting greatly, much larger when the diameter while launching aft antenna work can be than transmitting.Thereby a rational gathering scheme need to be proposed, pursue as far as possible the little rate of taking in (maximum gauge after the maximum gauge after gathering/completely launches), with meeting spatial station, earth resource is surveyed, meteorology, oceanography, navigation, many-sided demand such as communication satellite.
Summary of the invention
The present invention is for the current grid type of solution and Inflatable antenna profile precision is not high and the restricted problem of operating frequency, and then proposes a kind of sun fancy solid deployable antenna.
The present invention addresses the above problem the technical scheme of taking to be: the present invention includes pedestal, six driving shafts, six driving shaft supports, six universal drive shafts, six cue ball shell parts, 12 secondary spherical shell parts, six connecting rods, 12 main hinges and a plurality of ball-and-socket hinge device, pedestal is dodecagon plate body, six driving shafts and six universal drive shafts are crisscross arranged along the edge of pedestal, and the axis of each a driving shaft all limit corresponding with pedestal is parallel, the axis of each universal drive shaft is all parallel with a corresponding limit of pedestal, each driving shaft respectively connects with one side corresponding on pedestal by a driving shaft support respectively, the two ends of each driving shaft are connected with one end of an adjoining universal drive shaft respectively, each driving shaft is connected with the lower end of a cue ball shell part respectively, the both sides of each spherical shell part are respectively connected with a side of a secondary spherical shell part by a main hinge respectively, the opposite side of each secondary spherical shell part is respectively connected with the opposite side of an adjoining secondary spherical shell part by a described ball-and-socket hinge device respectively, each is connected with the lower end of a connecting rod respectively at the middle part of each universal drive shaft, the upper end of each connecting rod connects with a corresponding described ball-and-socket hinge device respectively.
The invention has the beneficial effects as follows: the present invention proposes the external envelope disc face folding exhibition cutting scheme of expansion solid reflector antenna, realized the object that a parabola is slit into several cards; The present invention's mode that is connected through the hinge links together cue ball shell part and secondary spherical shell part, and has completed the spacing of system by ball-and-socket hinge device, thereby anti-locking system rotates over precalculated position; The present invention has reduced the degree of freedom of system, has guaranteed the uniqueness of the motion of system.Profile precision of the present invention is higher, and operating frequency is unrestricted.The present invention designs by telescopic formula, greatly reduces the volume under antenna non operating state.The present invention has designed and has used shaft coupling driving shaft and universal drive shaft to be connected into the structure of closed loop, has guaranteed each card to apply equal moment, with the synchronism that guarantees to launch simultaneously.
Accompanying drawing explanation
Fig. 1 is the vertical view after the present invention launches, and Fig. 2 is A place enlarged drawing in Fig. 1, and Fig. 3 is the front view of the present invention while not launching, and Fig. 4 is the vertical view of Fig. 3, and Fig. 5 is B place enlarged drawing in Fig. 3, and Fig. 6 is the vertical view of pedestal, and Fig. 7 is the left view of Fig. 6.
Embodiment
Embodiment one: present embodiment is described in conjunction with Fig. 1 to Fig. 7, described in present embodiment, a kind of sun fancy solid deployable antenna comprises pedestal 1, six driving shafts 2, six driving shaft supports 3, six universal drive shafts 4, six cue ball shell parts 5, 12 secondary spherical shell parts 6, six connecting rods 7, 12 main hinges 8 and a plurality of ball-and-socket hinge device, pedestal 1 is dodecagon plate body, six driving shafts 2 and six universal drive shafts 4 are crisscross arranged along the edge of pedestal 1, and the axis of each a driving shaft 2 all limit corresponding with pedestal 1 is parallel, the axis of each universal drive shaft 4 is all parallel with a corresponding limit of pedestal 1, each driving shaft 2 respectively connects with one side corresponding on pedestal 1 by a driving shaft support 3 respectively, the two ends of each driving shaft 2 are connected with one end of an adjoining universal drive shaft 4 respectively, each driving shaft 2 is connected with the lower end of a cue ball shell part 5 respectively, the both sides of each spherical shell part 5 are respectively connected with a side of a secondary spherical shell part 6 by a main hinge 8 respectively, the opposite side of each secondary spherical shell part 6 is respectively connected with the opposite side of an adjoining secondary spherical shell part 6 by a described ball-and-socket hinge device respectively, each is connected with the lower end of a connecting rod 7 respectively at the middle part of each universal drive shaft 4, the upper end of each connecting rod 7 connects with a corresponding described ball-and-socket hinge device respectively.
Embodiment two: present embodiment is described in conjunction with Fig. 1 and Fig. 2, described in present embodiment, described in each of a kind of sun fancy solid deployable antenna, ball-and-socket hinge device comprises secondary spherical shell part the first hinge seat 9, secondary spherical shell part the second hinge seat 10, chain connection piece 11, two secondary spherical shell part the first hinge-rods 12, secondary spherical shell part the second hinge-rod 13 and connecting rod link bar 14, secondary spherical shell part the first hinge seat 9 is connected with chain connection piece 11 by two secondary spherical shell part the first hinge-rods 12, secondary spherical shell part the second hinge seat 10 is connected with chain connection piece 11 by secondary spherical shell part the second hinge-rod 13, chain connection piece 11 connects with the upper end of a corresponding connecting rod 7 by connecting rod link bar 14.
The technique effect of present embodiment is: so arrange, to meet two kinds of coupled motions conditions of two bracket panel faces that each ball pivot is connected: bracket panel face moves around the System of Rotating about Fixed Axis on base together with master face around the System of Rotating about Fixed Axis motion on master face and bracket panel face, and bracket panel face is connected with adjacent bracket panel face.Other composition and annexation are identical with embodiment one.
Embodiment three: in conjunction with Fig. 1, Fig. 3, Fig. 4, Fig. 6 and Fig. 7, present embodiment is described, each universal drive shaft 4 two ends of a kind of sun fancy solid deployable antenna are respectively connected with one end of adjacent driving shaft 2 by a universal joint 15 respectively described in present embodiment.
The technique effect of present embodiment is: so arrange, driving shaft 2 and universal drive shaft are connected into dodecagonal closing structure, make the moment that drive unit applies structure be delivered on a 50-50 basis and side by side on each ball-and-socket hinge device, and then act on two bracket panel faces that are attached thereto, with the synchronism that guarantees to launch.Other composition and annexation are identical with embodiment one or two.
Embodiment four: present embodiment is described in conjunction with Fig. 1 and Fig. 2, described in present embodiment, on a kind of pedestal 1 of sun fancy solid deployable antenna, the middle part on one side corresponding with cue ball shell part 5 is provided with side by side two and supports flap 16, two support flaps 16 connect by rotating shaft 17, and rotating shaft 17 is arranged on the middle part at pedestal 1 edge by axle bed.
The technique effect of present embodiment is: so arrange, six master faces are arranged on orthohexagonal limit, and realize master face around the fixed-axis rotation on pedestal 1.Other composition and annexation are identical with embodiment three.
Embodiment five: in conjunction with Fig. 5, present embodiment is described, a kind of middle part of each cue ball shell part 5 lower end of sun fancy solid deployable antenna is provided with gap 5-1 described in present embodiment.
The effect of present embodiment is: so arrange in ， mechanism gathering process, the inner wall edge that the axle part in ball-and-socket hinge device rotates to gap 5-1 is blocked, and has played the position-limiting action while having drawn in.Other composition and annexation are identical with embodiment one.
Claims (5)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310552082.6A CN103545591A (en) | 2013-11-08 | 2013-11-08 | A Sun Fancy Solid Deployable Antenna |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310552082.6A CN103545591A (en) | 2013-11-08 | 2013-11-08 | A Sun Fancy Solid Deployable Antenna |
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| CN103545591A true CN103545591A (en) | 2014-01-29 |
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| CN201310552082.6A Pending CN103545591A (en) | 2013-11-08 | 2013-11-08 | A Sun Fancy Solid Deployable Antenna |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104124507A (en) * | 2014-08-04 | 2014-10-29 | 江苏中寰卫星导航通信有限公司 | Wide-area antenna |
| CN104765122A (en) * | 2015-04-29 | 2015-07-08 | 哈尔滨工业大学 | Telescopic truss type binary optical space camera and on-orbit work method thereof |
| CN106654516A (en) * | 2016-11-16 | 2017-05-10 | 上海卫星工程研究所 | High-precision measuring device and high-precision measuring method suitable for multipoint distribution deployable antennas |
| CN107479161A (en) * | 2016-10-26 | 2017-12-15 | 哈尔滨工业大学 | The extensible primary mirror mechanism of space large caliber |
| CN107742772A (en) * | 2017-09-25 | 2018-02-27 | 上海卫星工程研究所 | The deployable solid surface antenna development mechanism of petal type |
| CN107768796A (en) * | 2017-09-25 | 2018-03-06 | 上海卫星工程研究所 | The deployable spaceborne parabola antenna of petal type |
| CN107768797A (en) * | 2017-10-19 | 2018-03-06 | 西北工业大学 | A kind of spaceborne solid face deployable antenna |
| CN110289474A (en) * | 2019-07-03 | 2019-09-27 | 海南大学 | Spherical satellite antenna and manufacturing method of spherical satellite antenna |
| CN113241513A (en) * | 2021-05-11 | 2021-08-10 | 北京航空航天大学 | Folding and unfolding assembly and antenna supporting mechanism with same |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7271775B1 (en) * | 2006-10-19 | 2007-09-18 | Bae Systems Information And Electronic Systems Integration Inc. | Deployable compact multi mode notch/loop hybrid antenna |
-
2013
- 2013-11-08 CN CN201310552082.6A patent/CN103545591A/en active Pending
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7271775B1 (en) * | 2006-10-19 | 2007-09-18 | Bae Systems Information And Electronic Systems Integration Inc. | Deployable compact multi mode notch/loop hybrid antenna |
Non-Patent Citations (1)
| Title |
|---|
| 郭宏伟等: "太阳花式固体反射面折展天线参数分析与设计", 《中国空间科学学会2013年空间光学与机电技术研讨会》, 1 November 2013 (2013-11-01), pages 222 - 227 * |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104124507A (en) * | 2014-08-04 | 2014-10-29 | 江苏中寰卫星导航通信有限公司 | Wide-area antenna |
| CN104765122A (en) * | 2015-04-29 | 2015-07-08 | 哈尔滨工业大学 | Telescopic truss type binary optical space camera and on-orbit work method thereof |
| CN107479161A (en) * | 2016-10-26 | 2017-12-15 | 哈尔滨工业大学 | The extensible primary mirror mechanism of space large caliber |
| CN107479161B (en) * | 2016-10-26 | 2020-10-16 | 哈尔滨工业大学 | Large-caliber expandable primary mirror mechanism in space |
| CN106654516A (en) * | 2016-11-16 | 2017-05-10 | 上海卫星工程研究所 | High-precision measuring device and high-precision measuring method suitable for multipoint distribution deployable antennas |
| CN106654516B (en) * | 2016-11-16 | 2019-03-29 | 上海卫星工程研究所 | High precision measuring device and method suitable for multiple spot distribution deployable antenna |
| CN107742772B (en) * | 2017-09-25 | 2019-10-29 | 上海卫星工程研究所 | The deployable solid surface antenna unfolding mechanism of petal type |
| CN107742772A (en) * | 2017-09-25 | 2018-02-27 | 上海卫星工程研究所 | The deployable solid surface antenna development mechanism of petal type |
| CN107768796A (en) * | 2017-09-25 | 2018-03-06 | 上海卫星工程研究所 | The deployable spaceborne parabola antenna of petal type |
| CN107768796B (en) * | 2017-09-25 | 2019-09-17 | 上海卫星工程研究所 | The deployable spaceborne parabola antenna of petal type |
| CN107768797A (en) * | 2017-10-19 | 2018-03-06 | 西北工业大学 | A kind of spaceborne solid face deployable antenna |
| CN107768797B (en) * | 2017-10-19 | 2020-04-03 | 西北工业大学 | A spaceborne fixed surface deployable antenna |
| CN110289474B (en) * | 2019-07-03 | 2020-09-01 | 海南大学 | Spherical satellite antenna and preparation method thereof |
| CN110289474A (en) * | 2019-07-03 | 2019-09-27 | 海南大学 | Spherical satellite antenna and manufacturing method of spherical satellite antenna |
| CN113241513A (en) * | 2021-05-11 | 2021-08-10 | 北京航空航天大学 | Folding and unfolding assembly and antenna supporting mechanism with same |
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Application publication date: 20140129 |