CN218242240U - Synthetic aperture radar antenna and solar wing fast unfolding device - Google Patents
Synthetic aperture radar antenna and solar wing fast unfolding device Download PDFInfo
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- CN218242240U CN218242240U CN202222076231.3U CN202222076231U CN218242240U CN 218242240 U CN218242240 U CN 218242240U CN 202222076231 U CN202222076231 U CN 202222076231U CN 218242240 U CN218242240 U CN 218242240U
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- wing
- solar cell
- star
- synthetic aperture
- phased array
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Abstract
The utility model relates to a satellite-borne synthetic aperture radar technical field specifically is a synthetic aperture radar antenna and solar wing expandes device fast, including the celestial body, solar cell wing and phased array antenna, the both sides on celestial body top are equipped with the solar cell wing, and the solar cell wing comprises main wing, fixed shell fragment one and flank, and the top terminal surface of main wing is equipped with fixed shell fragment one, and fixed shell fragment one is fixed mounting in celestial body top both sides, still is equipped with a flank respectively at two side end faces of main wing, and the flank is flexible material, and the outside of solar cell wing all is equipped with phased array antenna, and phased array antenna comprises main part, fixed shell fragment two, elastic connection board, curling portion and stopper, and the bottom terminal surface of main part is equipped with fixed shell fragment two, and phased array antenna passes through fixed shell fragment two fixed mounting on the terminal surface of celestial body bottom; the utility model discloses a flank of solar cell wing can accomodate into taking in the groove with the form of rolling up, the area of enveloping of reduction star that can be great.
Description
Technical Field
The utility model relates to a satellite-borne synthetic aperture radar technical field, concretely relates to synthetic aperture radar antenna and quick expansion device of solar wing.
Background
The satellite-borne Synthetic Aperture Radar (SAR) can acquire high-resolution images of ground targets all day long and all weather, and has extremely important application value in military affairs;
the small synthetic aperture radar satellite has the characteristics of light weight, small volume, low cost, high performance, easy multi-satellite networking and the like, and becomes an important development direction of the synthetic aperture radar satellite, and a synthetic aperture radar antenna extending out of a satellite is a main part of the synthetic aperture radar satellite and is also the largest part in volume in a synthetic aperture radar system, so that the folding volume of the radar antenna plays a great role in the miniaturization of the radar satellite.
SUMMERY OF THE UTILITY MODEL
Therefore, the utility model discloses it is made in view of above problem, the utility model discloses an aim at accomodates the groove through inwards setting up the side on four side edges of star, inwards sets up the top of two symmetries on the top end face of star and accomodates the groove for can produce less envelope area when the antenna is accomodate, it is great to solve the envelope area that exists among the prior art, the higher problem of the cost of transmission of satellite, the utility model discloses a realize above-mentioned purpose through following technical scheme:
the utility model provides a synthetic aperture radar antenna and quick device that expandes of solar wing, including the star, solar cell wing and phased array antenna, the both sides on star top are equipped with the solar cell wing, the solar cell wing comprises main wing, fixed shell fragment one and flank, the top terminal surface of main wing is equipped with fixed shell fragment one, fixed shell fragment one fixed mounting is in star top both sides, still be equipped with a flank respectively at two side terminal surfaces of main wing, and the flank is flexible material, the outside of solar cell wing all is equipped with the phased array antenna, the phased array antenna comprises main part, fixed shell fragment two, the elastic connection board, curling portion and stopper, the bottom terminal surface of main part is equipped with fixed shell fragment two, the phased array antenna passes through fixed shell fragment two fixed mounting on the terminal surface of star bottom, be equipped with the elastic connection board on the top terminal surface of main part, the other end of elastic connection board still is equipped with curling portion, curling portion is flexible material flexible crimping, curling portion is spacing to be installed at the star top.
Preferably, the outer contour of the star body is square, the four side ridge positions of the star body are respectively provided with a side accommodating groove, the top end face of the star body is symmetrically provided with two top accommodating grooves, the ridge positions of the star body at the outer ends of the two top accommodating grooves are respectively provided with an installation surface, and the two solar cell wings are respectively and symmetrically installed on the two installation surfaces.
Preferably, the joints of the elastic connecting plate and the main body part and the curling part as well as the joints of the second fixing elastic sheet and the main body part are provided with a plurality of limiting blocks which are symmetrically arranged.
Preferably, the side wings are wound into a roll and are limited and installed in the two side face accommodating grooves at the two ends of the installation face.
Preferably, the main wing is made of a plate-shaped material and is attached to one side wall surface of the star body.
Preferably, the main body is made of a plate-like material and is located outside the main wing.
Preferably, the curling part is wound into a roll and is limited and arranged in the top accommodating groove.
The utility model discloses beneficial effect:
1. the two ends of the solar cell wing are provided with the rollable side wings, and the four side ridge lines of the star body are provided with the side accommodating grooves inwards, so that the side wings at the two ends of the solar cell wing can be accommodated into the side accommodating grooves inwards in a rolling mode when being accommodated, the enveloping area of the star body can be greatly reduced, and the satellite launching cost is reduced;
2. through set up curling portion at phased array antenna end to inwards set up the top of two symmetries on the terminal surface of the top of star and accomodate the groove, make the curling portion at phased array antenna end can inwards accomodate into the top with the form of book when accomodating and accomodate the groove, can reduce the envelope volume of star, and then reduce satellite launch cost.
Drawings
Fig. 1 is a schematic view of the folded state of the present invention.
Fig. 2 is an exploded view of the present invention.
Fig. 3 is a partial sectional view of the whole structure of the present invention.
Fig. 4 is a schematic structural view of the star body of the present invention.
Fig. 5 is a top view of the overall structure of the present invention.
Fig. 6 isbase:Sub>A sectional view taken along linebase:Sub>A-base:Sub>A of fig. 5.
Fig. 7 is a schematic view of the expanded state of the present invention.
Description of reference numerals:
100. a star body; 110. a side receiving groove; 120. a top receiving groove; 130. a mounting surface; 200. a solar cell wing; 210. a main wing; 220. fixing the first elastic sheet; 230. a side wing; 300. a phased array antenna; 310. a main body part; 320. fixing the second elastic sheet; 330. an elastic connecting plate; 340. a curl portion; 350. and a limiting block.
Detailed Description
The preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings, however, the present invention can be implemented in various forms, and therefore, the present invention is not limited to the embodiments described hereinafter, and in addition, in order to describe the present invention more clearly, components which are not connected to the present invention will be omitted from the drawings;
as shown in fig. 1, a synthetic aperture radar antenna and solar wing fast unfolding apparatus includes: a star 100, a solar cell wing 200 and a phased array antenna 300;
as shown in fig. 2 to 6, the outer contour of the star 100 is square, a side accommodating groove 110 is respectively arranged at the ridge line position of four side surfaces of the star 100, two top accommodating grooves 120 are symmetrically arranged on the top end surface of the star 100, and an installation surface 130 is respectively arranged at the ridge line position of the star 100 at the outer end of the two top accommodating grooves 120;
the number of the solar cell wings 200 is two, the two solar cell wings 200 are respectively and symmetrically installed on the two installation surfaces 130 at the top end of the star body 100, each solar cell wing 200 is composed of a main wing 210, a first fixing elastic sheet 220 and a side wing 230, wherein the main wing 210 is made of a plate-shaped material, the first fixing elastic sheet 220 is arranged on the top end surface of the main wing 210, the main wing 210 and the first fixing elastic sheet 220 are initially vertically arranged, the whole solar cell wing 200 can be fixedly installed on the installation surface 130 at the top end of the star body 100 through the first fixing elastic sheet 220, the main wing 210 is attached to one side wall surface of the star body 100, the two side end surfaces of the main wing 210 are respectively provided with one side wing 230, the side wings 230 are made of a flexible material and can be deformed and curled, when the solar cell wings 200 are in a folding state, the first fixing elastic sheets 220 are bent, so that the main wing 210 is attached to the side surface of the star body 100 where the installation surface 130 is located, the side wings 230 at the two sides of the main wing 210 are wound into a roll and are limited and installed in the two side accommodating grooves 110 at the two ends of the installation surface 130;
the phased array antenna 300 is two, the two phased array antennas 300 are respectively and symmetrically installed on the outer sides of the two solar cell wings 200, each phased array antenna 300 is composed of a main body portion 310, a second fixing elastic sheet 320, an elastic connecting plate 330, a curling portion 340 and a limiting block 350, the main body portion 310 is made of a plate-shaped material, the second fixing elastic sheet 320 is arranged on the end face of the bottom end of the main body portion 310, the whole phased array antenna 300 can be fixedly installed on the end face of the bottom end of the star body 100 through the second fixing elastic sheet 320, the elastic connecting plate 330 is arranged on the end face of the top end of the main body portion 310, and the main body portion 310, the elastic connecting plate 330 and the second fixing elastic sheet 320 are initially and vertically arranged;
the other end of the elastic connecting plate 330 is further provided with a curling part 340, the curling part 340 is a flexible material and can be deformed and curled, a plurality of stopper 350 which are symmetrically arranged are arranged at the joint of the elastic connecting plate 330 and the main body part 310 and the curling part 340 and the joint of the two fixed spring pieces 320 and the main body part 310, when the phased array antenna 300 is in a folded state, the two fixed spring pieces 320 and the elastic connecting plate 330 are bent, so that the main body part 310 is attached to the surface of the main wing 210, the curling part 340 on the top end side of the main body part 310 is wound into a roll and is in limited installation in the top accommodating groove 120, after the phased array antenna 300 is separated from the external limitation of the star body 100, the curling part 340 and the main body part 310 on the phased array antenna 300 are turned outwards under the elastic force of the two elastic connecting plate 330 and the two fixed spring pieces 320, when the curling part 340 is turned out of the top accommodating groove 120, the curling part 340 starts to be gradually unfolded under the elastic force of the own until the stopper 350 on the two fixed stopper 320 is abutted against the main body part 310, when the curling part 350 on the bottom end of the main body part 310 is abutted against the stopper 310, the curling part 340, and the curling part 340 is completely parallel to the star body part 310, and the bottom end of the curling part 310 is completely turned parallel to the star body part 100.
The utility model discloses the theory of operation:
when a satellite is launched, a shell is sleeved outside the satellite body 100, the solar cell wings 200 and the phased array antennas 300 are in a folded state, the two solar cell wings 200 are symmetrically stacked on two sides of the satellite body 100, the two phased array antennas 300 are symmetrically stacked outside the two solar cell wings 200, at this time, the main wings 210 on the solar cell wings 200 are bonded on the side surfaces of the satellite body 100 where the mounting surface 130 is located, the side wings 230 on two sides of the main wings 210 are wound into a roll and are limitedly mounted in the two side receiving grooves 110 at two ends of the mounting surface 130, the main body part 310 is bonded on the main wings 210, the elastic connecting plate 330 at the top end of the main body part 310 is wound into a roll and is limitedly mounted in the top receiving groove 120, the folded state is shown in fig. 1 and 3, when the satellite is launched to a predetermined orbit to be unfolded, the shell on the outer side falls off, the phased array antenna 300 is separated from the limitation outside the satellite body 100, and then the curled part 340 and the main body part 310 on the phased array antenna 300, will turn over outwards under the elastic force of the elastic connecting plate 330 and the second fixed elastic sheet 320 respectively, when the curling part 340 turns over out of the top receiving groove 120, the curling part 340 will begin to unfold gradually under its own elastic force until the stoppers 350 at the two ends of the elastic connecting plate 330 abut against, the stoppers 350 on the second fixed elastic sheet 320 abut against the stoppers 350 at the bottom end of the main body 310, the curling part 340 stops turning over with the main body 310, at this time, the main body 310 is parallel to the bottom end face of the star 100, and the curling part 340 is unfolded completely and parallel to the main body 310, and at the same time, the side wings 230 on the solar cell wing 200 will begin to unfold gradually under its own elastic force, after the phased array antenna 300 is unfolded completely, the main wing 210 on the solar cell wing 200 will break away from the restriction of the phased array antenna 300, so the main wing 210 on the solar cell wing 200 will begin to turn over outwards under the elastic force of the first fixed elastic sheet 220, until the first fixed elastic piece 220 is restored to the flat state, the main wing 210 stops turning over, at this time, the main wing 210 is parallel to the top end surface of the star 100, the side wing 230 is parallel to the main wing 210, the solar cell wing 200 is unfolded, at this time, the solar cell wing 200 and the phased array antenna 300 are completely unfolded, and the unfolded state is shown in fig. 7.
Claims (7)
1. The utility model provides a synthetic aperture radar antenna and quick device that expandes of solar wing, includes star (100), solar cell wing (200) and phased array antenna (300), its characterized in that: the solar cell wing (200) is arranged on two sides of the top end of the star body (100), the solar cell wing (200) is composed of a main wing (210), a first fixing elastic sheet (220) and a side wing (230), the first fixing elastic sheet (220) is arranged on the top end face of the main wing (210), the first fixing elastic sheet (220) is fixedly installed on two sides of the top end of the star body (100), two side end faces of the main wing (210) are respectively provided with a side wing (230), the side wings (230) are made of flexible materials, a phased array antenna (300) is arranged on the outer side of the solar cell wing (200), the phased array antenna (300) is composed of a main body portion (310), a second fixing elastic sheet (320), an elastic connecting plate (330), a curling portion (340) and a limiting block (350), the bottom end face of the main body portion (310) is provided with a second fixing elastic sheet (320), the phased array antenna (300) is fixedly installed on the end face of the bottom end of the star body (100) through the second fixing elastic sheet (320), the top end face of the main body portion (310) is provided with the elastic connecting plate (330), the other end face of the elastic connecting plate (330) is further provided with a curling portion (340), the curling portion (340), and the curling portion (340) is installed on the top of the star body (100) made of the limiting block (100).
2. The synthetic aperture radar antenna and solar wing fast deployment apparatus of claim 1, wherein: the outer contour of the star body (100) is square, the four side ridge positions of the star body (100) are respectively provided with a side accommodating groove (110), the top end face of the star body (100) is symmetrically provided with two top accommodating grooves (120), the ridge positions of the star body (100) at the outer ends of the two top accommodating grooves (120) are respectively provided with an installation surface (130), and the two solar cell wings (200) are respectively and symmetrically installed on the two installation surfaces (130).
3. The synthetic aperture radar antenna and solar wing fast deployment apparatus of claim 1, wherein: the joints of the elastic connecting plate (330) and the main body part (310) and the curling part (340) and the joints of the second fixed elastic sheet (320) and the main body part (310) are provided with a plurality of symmetrically arranged limiting blocks (350).
4. The synthetic aperture radar antenna and solar wing fast deployment apparatus of claim 2, wherein: the side wing (230) is wound into a roll and is limited and arranged in the two side accommodating grooves (110) at the two ends of the mounting surface (130).
5. The apparatus of claim 1, wherein the apparatus comprises: the main wing (210) is made of a plate-shaped material, and the main wing (210) is attached to one side wall surface of the star body (100).
6. The synthetic aperture radar antenna and solar wing fast deployment apparatus of claim 1, wherein: the main body part (310) is made of a plate-shaped material and is positioned outside the main wing (210).
7. The synthetic aperture radar antenna and solar wing fast deployment apparatus of claim 2, wherein: the curling part (340) is wound into a roll and is limited and arranged in the top accommodating groove (120).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222076231.3U CN218242240U (en) | 2022-08-09 | 2022-08-09 | Synthetic aperture radar antenna and solar wing fast unfolding device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222076231.3U CN218242240U (en) | 2022-08-09 | 2022-08-09 | Synthetic aperture radar antenna and solar wing fast unfolding device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218242240U true CN218242240U (en) | 2023-01-06 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222076231.3U Active CN218242240U (en) | 2022-08-09 | 2022-08-09 | Synthetic aperture radar antenna and solar wing fast unfolding device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218242240U (en) |
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- 2022-08-09 CN CN202222076231.3U patent/CN218242240U/en active Active
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