CN217848285U - Winding turnover type synthetic aperture radar satellite antenna unfolding structure - Google Patents
Winding turnover type synthetic aperture radar satellite antenna unfolding structure Download PDFInfo
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- CN217848285U CN217848285U CN202222150507.8U CN202222150507U CN217848285U CN 217848285 U CN217848285 U CN 217848285U CN 202222150507 U CN202222150507 U CN 202222150507U CN 217848285 U CN217848285 U CN 217848285U
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- antenna
- synthetic aperture
- aperture radar
- roll
- side antenna
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Abstract
The utility model relates to a satellite-borne synthetic aperture radar technical field specifically is a roll-up convertible synthetic aperture radar satellite antenna expansion structure, including the celestial body, middle part antenna, side antenna and spacing shell fragment, the bottom of celestial body is equipped with the spacing groove, the inside bottom face bilateral symmetry of spacing groove is provided with supports shell fragment one, the mobilizable middle part antenna of installing in spacing groove, the celestial body bottom is located below the spacing groove and is symmetrically fixed with the side antenna, the one end that the side antenna is close to spacing groove border position is equipped with the spread groove, the other end of side antenna is the free end, the side antenna is flexible memory material, and the free end of side antenna is rolled up the range upon range of embedding in the spacing groove and is located middle part antenna bottom, the bottom surface that is equipped with the one end of spread groove on the side antenna is fixed with the spacing shell fragment; the utility model discloses thrust that can utilize the middle part antenna when the side antenna expandes together expandes with the middle part antenna for the envelope area of antenna is littleer, and expansion efficiency is higher.
Description
Technical Field
The utility model relates to a satellite-borne synthetic aperture radar technical field, concretely relates to convertible synthetic aperture radar satellite antenna of coiling expandes structure.
Background
A satellite-borne Synthetic Aperture Radar (SAR) satellite is a modern radar satellite capable of acquiring high information of a ground target all day long and all weather, the SAR satellite mainly comprises a satellite body, a solar cell wing, a radar antenna and the like, the radar antenna is the largest part of the effective volume in the whole satellite, the existing SAR satellite antenna is usually folded outside the satellite body when being stored and folded, and the folding mode causes the enveloping area of the outer side of the satellite body to be larger, so that the satellite transmission cost is high.
SUMMERY OF THE UTILITY MODEL
Therefore, the utility model discloses a just make in view of above problem, the utility model discloses an aim at is through range upon range of middle part antenna lower extreme with side antenna winding to together imbed the celestial body bottom and together accomodate and expand with middle part antenna, make the area of envelope of antenna littleer, it is big to accomodate the area of envelope with the radar antenna who solves existence among the prior art, the higher problem of emission cost, the utility model discloses a through following technical scheme realize above-mentioned purpose:
the utility model provides a convertible synthetic aperture radar satellite antenna expansion structure of convoluteing, including the star, middle part antenna, side antenna and spacing shell fragment, the bottom of star is equipped with the spacing groove, the inside bottom face bilateral symmetry of spacing groove is provided with supports shell fragment one, the mobilizable middle part antenna of installing of spacing inslot portion, the star bottom is located spacing groove below symmetry and is fixed with the side antenna, the one end that the side antenna is close to spacing groove border position is equipped with the spread groove, the other end of side antenna is the free end, the side antenna is flexible memory material, and the free end of side antenna is convoluteed range upon range of embedding to the spacing inslot and is located middle part antenna bottom, the bottom surface that is equipped with the one end of spread groove on the side antenna is fixed with the spacing shell fragment.
Preferably, the side bottom of the both sides of limiting groove outside is equipped with the installation notch respectively the symmetry, and installation notch inside all installs and supports shell fragment two and stopper, supports shell fragment two and installs at the installation notch inner end, and the stopper is installed and is being supported two outer ends of shell fragment, supports two one ends of shell fragment and is fixed with the installation notch inner end, and the other end is fixed with the stopper side.
Preferably, a plurality of clamping grooves which are symmetrically arranged are arranged on two side wall surfaces of the limiting groove.
Preferably, the first supporting elastic piece is a strip-shaped elastic piece when not bent, the first supporting elastic piece is a U-shaped elastic piece when bent, one end of the first supporting elastic piece is embedded and fixed at the bottom end of the limiting groove, and the other end of the first supporting elastic piece is a free end and is abutted to the middle antenna.
Preferably, a plurality of clamping blocks corresponding to the clamping grooves at the two ends of the star body are arranged at the two ends of the middle antenna.
Preferably, the second supporting elastic sheet is in a bending and compressing state, and the outer side face of the limiting block is flush with the side face of the star body.
Preferably, the side antenna fixing end is bent, and the connecting groove corresponds to the clamping groove.
The utility model discloses beneficial effect:
1. the side antenna is wound and laminated at the lower end of the middle antenna, and is embedded into the bottom of the star body together with the middle antenna for storage, so that the side antenna can be unfolded together with the middle antenna by using the thrust of the middle antenna when being unfolded, and the storage and unfolding modes are carried out at the bottom of the star body, so that the envelope area of the antenna is smaller, the unfolding efficiency is higher, and the emission cost is lower;
2. through setting up stopper and spacing shell fragment, utilize the side antenna to expand the support between the stopper of spacing shell fragment after spacing and expansion and press the centre gripping for whole radar antenna position is more stable.
Drawings
Fig. 1 is a schematic view of the folded state of the present invention.
Fig. 2 is an exploded view of the structure of the present invention.
Fig. 3 is a partially enlarged schematic view of a portion a in fig. 2.
Fig. 4 is a half-sectional schematic view of the folded state of the present invention.
Fig. 5 is a schematic structural diagram of the middle side antenna of the present invention.
Fig. 6 is a schematic structural diagram of the expanded state of the middle phased array antenna according to the present invention.
Fig. 7 is a schematic view of the expanded state of the present invention.
Fig. 8 is a half-section schematic view of the unfolded state of the present invention.
Description of reference numerals:
100. a star body; 110. a limiting groove; 120. a card slot; 130. supporting the elastic sheet I; 140. installing a notch; 150. supporting a second elastic sheet; 160. a limiting block; 200. a middle antenna; 210. a clamping block; 300. a side antenna; 310. connecting grooves; 400. spacing shell fragment.
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 not connected to the present invention will be omitted from the drawings;
as shown in fig. 1, a roll-over-roll type synthetic aperture radar satellite antenna deployment structure includes: the star body 100, the middle antenna 200, the side antenna 300 and the limiting elastic sheet 400;
as shown in fig. 2 to 4, the outer contour of the star body 100 is square, the bottom end face of the star body 100 is provided with a limiting groove 110, the left and right side wall faces of the limiting groove 110 are provided with a plurality of clamping grooves 120 which are symmetrically arranged, two sides of the inner bottom end face of the limiting groove 110 are further symmetrically provided with two first supporting spring pieces 130, the first supporting spring pieces 130 are strip-shaped spring pieces when not being bent, the first supporting spring pieces 130 are U-shaped spring pieces when being bent, one end of each first supporting spring piece 130 is embedded and fixed at the bottom end of the limiting groove 110, the other end of each first supporting spring piece is a free end, the bottom end positions of the side faces of the two sides of the outer portion of the limiting groove 110 are further symmetrically provided with two mounting notches 140, and each mounting notch 140 is internally provided with a second supporting spring piece 150 and a limiting block 160, wherein the second supporting spring pieces 150 are mounted at the inner ends of the mounting notches 140, the limiting blocks 160 are mounted at the outer ends of the second supporting spring pieces 150, one end of the second supporting spring pieces 150 is fixed with the inner ends of the mounting notches 140, the other ends of the limiting blocks 160 are fixed with the side faces of the limiting blocks 160, and when the satellite body 100 is in a launching state, the limiting block 150 is in which is completely embedded in the mounting notches 160;
as shown in fig. 2 and 4, the central antenna 200 is a plate-shaped structure, two ends of the central antenna 200 are provided with a plurality of locking blocks 210 corresponding to the locking slots 120 at two ends of the star 100, and the central antenna 200 is movably mounted at the bottom end of the limiting slot 110 by the locking blocks 210 on the central antenna and the limiting slot 110 at the lower end of the star 100 matching with each other;
as shown in fig. 2, 4, and 5, the side antenna 300 is made of a flexible memory material, the number of the side antenna 300 is two, two side antennas 300 are symmetrically installed at the bottom end of the limiting groove 110 at the lower end of the star 100, one end of the side antenna 300 is provided with a plurality of connecting grooves 310 corresponding to the plurality of clamping grooves 120 at the lower end of the star 100, one end of the side antenna 300 provided with the connecting grooves 310 is fixedly installed at the lower end of the star 100, and when the side antenna 300 is fixed, the connecting grooves 310 correspond to the clamping grooves 120, the other end of the side antenna 300 is a free end, a limiting elastic sheet 400 is further fixedly installed on the bottom surface of the end of the side antenna 300 provided with the connecting grooves 310, the limiting elastic sheet 400 is in a strip-shaped structure when the side antenna 300 is unfolded, the limiting elastic sheet 400 below the fixed end of the side antenna 300 is bent into a U-shaped structure, then the fixed end of the side antenna 300 is bent, and the free end of the side antenna 300 is laminated by winding and then completely embedded into the limiting groove 110.
The utility model discloses theory of operation:
when a satellite is launched, a shell is sleeved outside the star body 100, the middle antenna 200 is located at the lowest end of the limiting groove 110, the middle antenna 200 bends the first supporting elastic sheet 130 into a U-shaped state, the two side antennas 300 are both in a folded state and embedded and installed inside the limiting groove 110, the folded state is shown in fig. 1 and 4, when the satellite is launched to a predetermined orbit to be unfolded, the shell on the outer side falls off, the plurality of limiting blocks 160 on the star body 100 are separated from the limit of the outer part of the star body 100, then each limiting block 160 starts to turn outwards under the elastic force of each second supporting elastic sheet 150 until the outer end side face of the limiting block 160 is clamped by the bottom end face of the installing notch 140, the limiting blocks 160 stop turning, meanwhile, the side antennas 300 at the bottom of the star body 100 are also separated from the limit of the outer part of the star body 100, then the middle antenna 200 at the bottom of the limiting groove 110 starts to push the side antennas 300 to move outwards along the clamping grooves 120 under the elastic force of the first supporting elastic sheets 130, meanwhile, the fixed end of the side antenna 300 with the connecting slot 310 also starts to drive the whole side antenna 300 to turn outwards under the elastic force of the limiting elastic sheet 400, after the free end of the side antenna 300 wound and laminated is separated from the limit of the limiting slot 110, the free end of the side antenna 300 wound and laminated starts to unfold under the memory elasticity of the material of the side antenna 300 until the limiting elastic sheet 400 below the fixed end of the side antenna 300 is completely straightened and presses the side antenna 300 against the bottom end face of the limiting block 160, the fixed end of the side antenna 300 stops turning over, at this time, the free end of the side antenna 300 laminated is completely unfolded, the supporting elastic sheet one 130 at the bottom of the limiting slot 110 is completely straightened and presses against the bottom end of the middle antenna 200, and the middle antenna 200 is completely meshed with the connecting slots 310 on the two side antennas 300 through the clamping blocks 210 at the two ends, the entire side antenna 300 and the middle antenna 200 are completely unfolded as shown in fig. 6, 7 and 8.
Claims (7)
1. The utility model provides a convertible synthetic aperture radar satellite antenna of coiling expandes structure, includes star (100), middle part antenna (200), side antenna (300) and spacing shell fragment (400), its characterized in that: the bottom of the star body (100) is provided with a limiting groove (110), two sides of the inner bottom end face of the limiting groove (110) are symmetrically provided with first supporting elastic pieces (130), a middle antenna (200) is movably arranged in the limiting groove (110), the bottom end of the star body (100) is located below the limiting groove (110) and is symmetrically fixed with a side antenna (300), one end, close to the edge of the limiting groove (110), of the side antenna (300) is provided with a connecting groove (310), the other end of the side antenna (300) is a free end, the side antenna (300) is made of a flexible memory material, the free end of the side antenna (300) is wound, stacked, embedded into the limiting groove (110) and located at the bottom end of the middle antenna (200), and the bottom face, at one end of the connecting groove (310) on the side antenna (300), is provided with a limiting elastic piece (400).
2. The roll-to-roll synthetic aperture radar satellite antenna deployment structure of claim 1, wherein: the side bottom of the two sides of the outer portion of the limiting groove (110) is symmetrically provided with mounting notches (140) respectively, two supporting elastic pieces (150) and a limiting block (160) are mounted inside the mounting notches (140), the two supporting elastic pieces (150) are mounted at the inner end of the mounting notches (140), the limiting block (160) is mounted at the outer end of the two supporting elastic pieces (150), one end of each supporting elastic piece (150) is fixed to the inner end of the corresponding mounting notch (140), and the other end of each supporting elastic piece is fixed to the side face of the limiting block (160).
3. The roll-to-roll synthetic aperture radar satellite antenna deployment structure of claim 1, wherein: and a plurality of symmetrically arranged clamping grooves (120) are formed in the two side wall surfaces of the limiting groove (110).
4. The roll-over synthetic aperture radar satellite antenna deployment structure of claim 3, wherein: the first supporting elastic piece (130) is a strip-shaped elastic piece when not bent and is a U-shaped elastic piece when bent, one end of the first supporting elastic piece (130) is embedded and fixed at the bottom end of the limiting groove (110), and the other end of the first supporting elastic piece (130) is a free end and is abutted to the middle antenna (200).
5. The roll-over synthetic aperture radar satellite antenna deployment structure of claim 3, wherein: and a plurality of clamping blocks (210) corresponding to the clamping grooves (120) at the two ends of the star body (100) are arranged at the two ends of the middle antenna (200).
6. The roll-over synthetic aperture radar satellite antenna deployment structure of claim 2, wherein: the second supporting elastic sheet (150) is in a bending compression state, and the outer side face of the limiting block (160) is flush with the side face of the star body (100).
7. The roll-to-roll synthetic aperture radar satellite antenna deployment structure of claim 3, wherein: the fixed end of the side antenna (300) is bent, and the connecting groove (310) corresponds to the position of the clamping groove (120).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222150507.8U CN217848285U (en) | 2022-08-16 | 2022-08-16 | Winding turnover type synthetic aperture radar satellite antenna unfolding structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222150507.8U CN217848285U (en) | 2022-08-16 | 2022-08-16 | Winding turnover type synthetic aperture radar satellite antenna unfolding structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217848285U true CN217848285U (en) | 2022-11-18 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222150507.8U Active CN217848285U (en) | 2022-08-16 | 2022-08-16 | Winding turnover type synthetic aperture radar satellite antenna unfolding structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217848285U (en) |
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2022
- 2022-08-16 CN CN202222150507.8U patent/CN217848285U/en active Active
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