CN102280716A - Body-mounted parabolic antenna for gas-filled satellite - Google Patents
Body-mounted parabolic antenna for gas-filled satellite Download PDFInfo
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- CN102280716A CN102280716A CN2011101207937A CN201110120793A CN102280716A CN 102280716 A CN102280716 A CN 102280716A CN 2011101207937 A CN2011101207937 A CN 2011101207937A CN 201110120793 A CN201110120793 A CN 201110120793A CN 102280716 A CN102280716 A CN 102280716A
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Abstract
The invention provides a body-mounted parabolic antenna for a gas-filled satellite. The parabolic antenna comprises an antenna reflection surface with a parabolic structure, a support ring, a support pipe, a guy cable, a feed source and a feed source support; the antenna reflection surface with the parabolic structure is fixed in the support ring; the lower end of the support pipe is connected with the support ring; the guy cable is connected between the support pipe and the antenna reflection surface with the parabolic structure; the feed source is arranged at the lower side of the antenna reflection surface with the parabolic structure; and the feed source support is connected between the feed source and the support ring. The body-mounted antenna provided by the invention is adopted, compared with the traditional antenna, as a mounting mode of satellite external accessories, the body-mounted antenna is beneficial to the increase of the effective aperture of the antenna, the larger the aperture of the antenna is, the more gain, the further detection distance and the better target discrimination can be obtained; and the body-mounted antenna is good for improving the general dynamic property of the satellite, is convenient for the operations of gesture regulation, orbital transfer and the like for the satellite in the space operation process, and is good for improving the general structure rigidity and vibration fundamental frequency of the satellite.
Description
Technical field
The present invention relates to a kind of body dress formula parabolic antenna that is used to inflate satellite, belong to the satellite technology field.
Background technology
The existing antenna that is used for satellite all is that the form with external annex is installed to satellite.Yet along with the continuous lifting of satellite function, increasing for the dimensional requirement of antenna aperture, the technology that this mounting means of antenna has caused satellites transmits on the one hand is a very big restriction for the increase of caliber size; On the other hand, antenna is as external annex, and size has brought the problem of the flexible increase of structure also to become more serious after improving thereupon.Because the structural vibration fundamental frequency is lower, makes the shape surface accuracy of satellite antenna be difficult to guarantee, thereby cause the precision of whole satellite receiving and transmitting signal and intensity to reduce greatly.
Summary of the invention
The objective of the invention is to cause antenna aperture to increase difficulty as the mounting means of satelloid outer attachment and make the structural vibration fundamental frequency reduce the precision of the whole satellite receiving and transmitting signal that causes and the problem that intensity reduces greatly, and then a kind of body dress formula parabolic antenna that is used to inflate satellite is provided in order to solve antenna.
The objective of the invention is to be achieved through the following technical solutions:
The present invention includes: the antenna reflective face of paraboloid structure, support ring, stay pipe, drag-line, feed and feed support, the support ring internal fixation has the antenna reflective face of paraboloid structure, the lower end of stay pipe is connected with support ring, be connected with drag-line between the antenna reflective face of stay pipe and paraboloid structure, feed is arranged on the downside of the antenna reflective face of paraboloid structure, is connected with the feed support between feed and the support ring.
The invention has the beneficial effects as follows: the invention solves antenna and cause antenna aperture to increase difficulty as the mounting means of satelloid outer attachment and make the structural vibration fundamental frequency reduce the precision of the whole satellite receiving and transmitting signal that causes and the problem that intensity reduces greatly.The present invention adopt body dress formula antenna than antenna in the past as the mounting means of satelloid outer attachment, very favourable to the effective aperture that increases antenna, and help improving the overall rigidity of structure of satellite, fundamental vibration frequency, improve the integral power characteristic of satellite greatly and improved the precision and the intensity of satellite receiving and transmitting signal.
Description of drawings
A kind of cross-sectional view that is used to inflate the body dress formula parabolic antenna of satellite that Fig. 1 is that the specific embodiment of the invention provides.
Embodiment
A kind of body dress formula parabolic antenna (see figure 1) that is used to inflate satellite that the specific embodiment of the invention provides, comprise: the antenna reflective face 1 of paraboloid structure, support ring 2, stay pipe 3, drag-line 4, feed 5 and feed support 6, support ring 2 internal fixation have the antenna reflective face 1 of paraboloid structure, the lower end of stay pipe 3 is connected with support ring 2, be connected with drag-line 4 between the antenna reflective face 1 of stay pipe 3 and paraboloid structure, feed 5 is arranged on the downside of the antenna reflective face 1 of paraboloid structure, is connected with feed support 6 between feed 5 and the support ring 2.
The antenna reflective face 1 of described paraboloid structure is made of the film of the surface metalation of parabolic shape or the film of wire netting or outer surface adhesion metal net.
1) film of surface metalation can reflection electromagnetic wave, and has good air-tightness, its execution mode is: after emission is entered the orbit, the metallized film reflecting surface is inflating expanded, thereby forms parabolic film reflecting surface, simultaneously, the connection drag-line that is installed between support ring and the reflecting surface has certain tension effect to parabola, thereby can better control the shape and the precision of parabolic reflector, and can further improve the rigidity of structure of reflecting surface, improve its dynamic performance.Its execution mode is: support ring is at first inflating expanded and draw back the metallized film reflecting surface, the support ring electric heating is just changed, the metallized film reflecting surface is inflating expanded, simultaneously, inflating expanded and the tension drag-line of stay pipe, the moulding of the further tension metal reflecting surface of drag-line, metallize then reflecting surface and stay pipe electric heating are just changed, thereby form the metallized film reflecting surface of rigid support and firmization.
2) wire netting that is adopted is special-purpose antenna reflective face wire netting, and the wire netting reflecting surface can reflection electromagnetic wave, and has good elasticity, but does not have air-tightness.Its embodiment is: the wire netting reflecting surface is installed on the inflation ring, after emission is entered the orbit, inflation encircles inflating expanded and draws back the wire netting reflecting surface and becomes flat state substantially, the electric heating of inflation ring is just changed, then stay pipe inflating expanded and the tension drag-line, drag-line tension metal reflecting surface is shaped to the parabolic shape antenna reflective face, and simultaneously, the stay pipe electric heating has just changed into type and fixed-type parabolic wire netting reflecting surface.
3) film of outer surface adhesion metal net had both had the air-tightness of film, can be inflating expanded, has the ELECTROMAGNETIC REFLECTION characteristic of wire netting and certain elasticity again, its embodiment is: after emission is entered the orbit, support ring is at first inflating expanded and draw back the film reflecting surface of adhesion metal net, the support ring electric heating is just changed, the film reflecting surface of adhesion metal net is inflating expanded, simultaneously, inflating expanded and the tension drag-line of stay pipe, the film reflecting surface moulding of the further tensioning adhesion metal of drag-line net, the stay pipe electric heating is just changed then, thereby forms the film reflecting surface of the adhesion metal net of rigid support and firmization.
The edge of the antenna reflective face 1 of 2 pairs of paraboloid structures of described support ring supports, and is connected with the inner surface of inflation satellite shell 9.Drag-line 4 is used to connect the antenna reflective face 1 of stay pipe 3 and paraboloid structure, and drag-line 4 is positioned at the below of stay pipe 3, perpendicular to the upper surface of the antenna reflective face 1 of paraboloid structure.Feed 5 is positioned at the focus place of the antenna reflective face 1 of paraboloid structure, is connected with support ring 3 by feed support 6.The upper end of stay pipe 3 is connected with the satellite nuclear 7 of inflation satellite, is connected with housings support pipe 8 between satellite nuclear 7 and the inflation satellite shell 9.
The antenna reflective face 1 of described paraboloid structure, support ring 2 and stay pipe 3 constitute for can just changing flexible composite, and collapsible, expansion, structure have just been changed, and be identical with inflation satellite material.Under the unaerated deployed condition, body dress formula antenna and inflation satellite all are flexible state.After the inflation of inflation satellite, reflecting surface is along with the inflation satellite launches, and the expansion of stay pipe has further driven the antenna expansion, and drag-line helps guaranteeing the parabolic shape antenna structure.Form after structure is solidified and reach the parabolic antenna that required shape surface accuracy requires, the transmitting-receiving electromagnetic wave.
Antenna aperture of the present invention is big, the rigidity of structure is high, the integral power performance is good, the overall integrated level height of satellite, detection performance is good, folding efficiency is high, the emission volume little, total quality is light.Antenna aperture can obtain bigger gain, farther detection range and better target discrimination greatly.Body dress formula antenna helps improving the overall dynamics of satellite, is convenient to the attitude adjustment of satellite during space motion, becomes operation such as rail.The fundamental vibration frequency of body dress formula antenna improves, thereby greatly reduces structure owing to vibrate and cause the possibility damaged, has guaranteed the shape surface accuracy of satellite antenna, and the precision of whole satellite receiving and transmitting signal and intensity can improve greatly.
The above; only be the preferable embodiment of the present invention; these embodiments all are based on the different implementations under the general idea of the present invention; and protection scope of the present invention is not limited thereto; anyly be familiar with those skilled in the art in the technical scope that the present invention discloses; the variation that can expect easily or replacement all should be encompassed within protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with the protection range of claims.
Claims (4)
1. body dress formula parabolic antenna that is used to inflate satellite, it is characterized in that, comprise: the antenna reflective face of paraboloid structure (1), support ring (2), stay pipe (3), drag-line (4), feed (5) and feed support (6), support ring (2) internal fixation has the antenna reflective face (1) of paraboloid structure, the lower end of stay pipe (3) is connected with support ring (2), be connected with drag-line (4) between the antenna reflective face (1) of stay pipe (3) and paraboloid structure, feed (5) is arranged on the downside of the antenna reflective face (1) of paraboloid structure, is connected with feed support (6) between feed (5) and the support ring (2).
2. a kind of body dress formula parabolic antenna that is used to inflate satellite according to claim 1, it is characterized in that the antenna reflective face of described paraboloid structure (1) is made of the film of the surface metalation of parabolic shape or the film of wire netting or outer surface adhesion metal net.
3. a kind of body dress formula parabolic antenna that is used to inflate satellite according to claim 1 is characterized in that described support ring (2) supports the edge of the antenna reflective face (1) of paraboloid structure.
4. a kind of body dress formula parabolic antenna that is used to inflate satellite according to claim 1 is characterized in that the antenna reflective face of described paraboloid structure (1), support ring (2) and stay pipe (3) constitute for can just changing flexible composite.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110120793 CN102280716B (en) | 2011-05-11 | 2011-05-11 | Body-mounted parabolic antenna for gas-filled satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110120793 CN102280716B (en) | 2011-05-11 | 2011-05-11 | Body-mounted parabolic antenna for gas-filled satellite |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102280716A true CN102280716A (en) | 2011-12-14 |
| CN102280716B CN102280716B (en) | 2013-10-16 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201110120793 Expired - Fee Related CN102280716B (en) | 2011-05-11 | 2011-05-11 | Body-mounted parabolic antenna for gas-filled satellite |
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| Country | Link |
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| CN (1) | CN102280716B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103151596A (en) * | 2013-01-31 | 2013-06-12 | 哈尔滨工业大学 | Inflatable radial rib antenna tail rod connecting piece for spacecraft |
| CN104241868A (en) * | 2014-10-08 | 2014-12-24 | 哈尔滨工业大学 | Space inflation deployable antenna reflector without influence of sunlight pressures |
| CN106246799A (en) * | 2016-07-29 | 2016-12-21 | 上海交通大学 | Object under dynamic balance state and vibration control thereof and attitude adjusting method |
| CN112909483A (en) * | 2021-01-15 | 2021-06-04 | 大连理工大学 | Inflated and expanded shell film reflector antenna reflector |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103682668B (en) * | 2013-12-18 | 2015-06-17 | 哈尔滨工业大学 | Bending-forming-based parabolic cylinder antenna reflector and method for reflector to achieve parabolic cylinder |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2120857A (en) * | 1982-04-28 | 1983-12-07 | British Aerospace | Reflectors |
| US6318674B1 (en) * | 2000-03-02 | 2001-11-20 | The Aerospace Corporation | Power sphere deployment method |
| CN102011922A (en) * | 2010-12-03 | 2011-04-13 | 西安电子科技大学 | Deployable surface device with fixed truss structure |
-
2011
- 2011-05-11 CN CN 201110120793 patent/CN102280716B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2120857A (en) * | 1982-04-28 | 1983-12-07 | British Aerospace | Reflectors |
| US6318674B1 (en) * | 2000-03-02 | 2001-11-20 | The Aerospace Corporation | Power sphere deployment method |
| CN102011922A (en) * | 2010-12-03 | 2011-04-13 | 西安电子科技大学 | Deployable surface device with fixed truss structure |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103151596A (en) * | 2013-01-31 | 2013-06-12 | 哈尔滨工业大学 | Inflatable radial rib antenna tail rod connecting piece for spacecraft |
| CN104241868A (en) * | 2014-10-08 | 2014-12-24 | 哈尔滨工业大学 | Space inflation deployable antenna reflector without influence of sunlight pressures |
| CN106246799A (en) * | 2016-07-29 | 2016-12-21 | 上海交通大学 | Object under dynamic balance state and vibration control thereof and attitude adjusting method |
| CN106246799B (en) * | 2016-07-29 | 2018-11-16 | 上海交通大学 | Object and its vibration control and attitude adjusting method under dynamic balance state |
| CN112909483A (en) * | 2021-01-15 | 2021-06-04 | 大连理工大学 | Inflated and expanded shell film reflector antenna reflector |
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| Publication number | Publication date |
|---|---|
| CN102280716B (en) | 2013-10-16 |
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| C53 | Correction of patent of invention or patent application | ||
| CB03 | Change of inventor or designer information |
Inventor after: Miao Changqing Inventor after: Dong Hao Inventor after: Wei Jianzheng Inventor after: Wang Changguo Inventor after: Wang Youshan Inventor after: Du Xingwen Inventor before: Miao Changqing Inventor before: Liu Chang Inventor before: Wei Jianzheng Inventor before: Tian Shuang Inventor before: Wang Changguo Inventor before: Wang Youshan Inventor before: Du Xingwen |
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Free format text: CORRECT: INVENTOR; FROM: MIAO CHANGQING LIU CHANG WEI JIANZHENG TIAN SHUANG WANG CHANGGUO WANG YOUSHAN DU XINGWEN TO: MIAO CHANGQING DONG HAO WEI JIANZHENG WANG CHANGGUO WANG YOUSHAN DU XINGWEN |
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Granted publication date: 20131016 Termination date: 20140511 |