CN107221755B - Self-resilience reconfigurable satellite-borne deployable antenna - Google Patents
Self-resilience reconfigurable satellite-borne deployable antenna Download PDFInfo
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- CN107221755B CN107221755B CN201710267963.1A CN201710267963A CN107221755B CN 107221755 B CN107221755 B CN 107221755B CN 201710267963 A CN201710267963 A CN 201710267963A CN 107221755 B CN107221755 B CN 107221755B
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q15/00—Devices for reflection, refraction, diffraction or polarisation of waves radiated from an antenna, e.g. quasi-optical devices
- H01Q15/14—Reflecting surfaces; Equivalent structures
- H01Q15/16—Reflecting surfaces; Equivalent structures curved in two dimensions, e.g. paraboloidal
- H01Q15/161—Collapsible reflectors
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Abstract
The invention belongs to the technical field of antennas, and discloses a self-rebounding reconfigurable satellite-borne deployable antenna, which is provided with: a center hub; a plurality of variable parabolic radiation ribs are wound on the central wheel cylinder; the film reflecting surface is in the shape of a ring and is folded between the variable parabolic radiation ribs in a winding state. The variable parabolic radiation rib is made of enhanced polymer, and the unfolding structure only comprises the variable parabolic radiation rib and the windable carbon fiber central wheel cylinder, so that the structure is simple, the self-rebounding function can be realized, a complex unfolding and folding structure formed by the central wheel cylinder and the gear transmission mechanism of the traditional wound rib antenna is not needed, and the service reliability of the antenna is improved; the back surface of the reflecting film surface is attached with a shape memory actuator layer, deformation trends under the action of space heat radiation are mutually counteracted, the heat deformation of the film surface under the action of space heat radiation is effectively relieved, and the on-track precision of the reflecting film surface is improved; and the weight of the antenna can be effectively reduced by adopting a honeycomb structure.
Description
Technical Field
The invention belongs to the technical field of antennas, and particularly relates to a self-rebounding reconfigurable satellite-borne deployable antenna.
Background
The winding rib type antenna has the advantages of high storage rate, light structural weight, high unfolding reliability, simple mechanism design and the like. However, the rigid and flexible characteristics of the radiation rib are difficult to be considered, so that the profile accuracy and the on-track stability are poor, and the existing winding rib type antenna has some defects, such as poor surface accuracy of a reflection surface and poor rigidity and stability of an antenna structure. The reason for this is that the flexibility required for winding the thin-walled radiation rib is contradictory to the rigidity required for unwinding the thin-walled radiation rib, and both are difficult to be compatible. In addition, the accuracy of the reflecting surface cannot be ensured.
In summary, the problems of the prior art are as follows: the flexibility required by the existing winding rib type antenna thin-wall radiation rib during winding is contradictory to the rigidity required after unfolding, and the surface precision of the reflecting surface is poor.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides a self-rebounding reconfigurable satellite-borne deployable antenna.
The invention is realized in such a way that a self-rebounding reconfigurable spaceborne deployable antenna is provided with:
a center hub;
a plurality of variable parabolic radiation ribs are wound on the central wheel cylinder;
the film reflecting surface is in the shape of a ring and is folded between the variable parabolic radiation ribs in a winding state.
Further, the six modified parabolic radiating ribs are formed of a three-way shape memory polymer material.
Further, the thin film reflective surface comprises a metal reflective layer, a film layer and a shape memory actuator layer;
the metal reflecting layer and the film layer form a paraboloid at one time by using a thermoplastic hot-press molding method by using the film surface plated with the metal reflecting layer; the shape memory actuator layer is printed on the back of the reflective surface of the film.
Further, the shape memory actuator layer is of a honeycomb structure, and shape memory hinges are connected among honeycombs.
The invention has the advantages and positive effects that: the variable parabolic radiation rib with the multi-degree-of-freedom variable function manufactured by the reinforced polymer is adopted, the whole unfolding structure only comprises the variable parabolic radiation rib and the windable carbon fiber central wheel cylinder, the structure is simple, the self-rebounding function can be realized, and the traditional winding is not neededThe rib-wound antenna is a complex unfolding and folding structure formed by a central wheel cylinder and a gear transmission mechanism, so that the service reliability of the antenna is improved. The back surface of the reflecting film surface is attached with a shape memory actuator layer, deformation trends under the action of space heat radiation are mutually counteracted, the heat deformation of the film surface under the action of space heat radiation is effectively relieved, and the on-track precision of the reflecting film surface is improved; the shape memory actuator layer adopts a honeycomb structure, and the weight of the antenna can be effectively reduced. According to the current technical development, the surface precision of the winding antenna is 0.5-2.5 mm, and the surface density is more than 0.7kg/m2The working frequency of the antenna can reach 1.6-40 GHz, and the requirements of low-frequency, medium-frequency and high-frequency wave bands can be met. The antenna type structure type and the in-orbit self-adjusting function greatly improve the accuracy of the antenna shape and surface, and the design target is 0.1 mm; with the improvement of the structural rigidity, the storage ratio can be less than 0.05; areal density of not more than 0.4kg/m2. Can meet the requirement of high-frequency wave band.
Drawings
Fig. 1 is a schematic structural diagram of a self-rebounding reconfigurable spaceborne deployable antenna provided by an embodiment of the invention;
FIG. 2 is a schematic diagram of a thin film reflective surface structure provided in an embodiment of the present invention;
in the figure: 1. a center wheel cylinder; 2. a variable parabolic radiation rib; 3. a thin film reflective surface; 3-1, a metal reflecting layer; 3-2, a film layer; 3-3, shape memory actuator layer.
FIG. 3 is a schematic diagram of a shape memory actuator layer structure according to an embodiment of the present invention;
in the figure: (a) a polymer honeycomb structure; (b) a shape memory hinge that resists bending.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail with reference to the following embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
The following detailed description of the principles of the invention is provided in connection with the accompanying drawings.
As shown in fig. 1, a self-rebounding reconfigurable spaceborne deployable antenna provided by an embodiment of the present invention includes: a central wheel cylinder 1, a variable parabolic radiation rib 2 and a film reflecting surface 3.
The variable parabolic radiation ribs 2 are wound on the central wheel cylinder 1, the film reflecting surface 3 is folded between the variable parabolic radiation ribs 2 in a winding state in an annular concave-convex shape,
the rib 2 of the variable-body parabolic radiation is designed and manufactured by adopting a three-way shape memory polymer material, and the film surface of the reflecting surface 3 of the film is divided into three layers, as shown in figure 2, and comprises a metal reflecting layer 3-1, a film layer 3-2 and a shape memory actuator layer 3-3. The metal reflecting layer 3-1 and the film layer 3-2 are formed into paraboloids at one time by a thermoplastic hot-press molding method by utilizing the film surface plated with the metal reflecting layer; the shape memory actuator layer 3-3 is printed on the back of the reflective surface 3 of the film. The shape memory actuator layer structure is shown in figure 3.
The working principle of the invention is as follows:
after the variable parabolic radiation ribs are adjusted and electrified for one time, the variable parabolic radiation ribs are gradually unfolded, and the film reflection surface is gradually rotated and unfolded under the traction of the six variable parabolic radiation ribs; after the variable parabolic radiation rib is unfolded, the variable parabolic radiation rib is continuously electrified and temperature-regulated, and the secondary variant of the variable parabolic radiation rib is folded along the width direction, namely the axial direction of the whole antenna, and is changed into a corrugated plate shape, so that the bending rigidity of the variable parabolic radiation rib is increased. The forming method of the metal reflecting layer and the film layer of the film reflecting surface is to form a paraboloid at one time by a thermoplastic hot-press forming method by utilizing the film surface plated with the metal reflecting layer, and the precision reaches 50 mu m of target precision. And then, placing the formed film on a high-precision substrate, and printing the shape memory actuator layer on the back surface of the film by adopting a manufacturing method of integrated injection molding. The shape memory actuator layer is of a honeycomb structure, each honeycomb is connected through the shape memory hinge, and the heat deformation trends of the shape memory hinges and the membrane surface under the action of space heat radiation are mutually offset, so that the heat deformation of the membrane surface under the action of space heat radiation is effectively relieved, and the purpose of improving the on-track shape control of the membrane surface is achieved.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (2)
1. The utility model provides a from resilience reconfigurable spaceborne deployable antenna which characterized in that, self-resilience reconfigurable spaceborne deployable antenna is provided with:
a center hub;
a plurality of variable parabolic radiation ribs are wound on the central wheel cylinder;
the film reflecting surface is in an annular concave-convex shape and is folded between the winding variable parabolic radiation ribs;
the shape memory actuator layer adopts a honeycomb structure, and each honeycomb is connected by a shape memory hinge;
after the variable parabolic radiation ribs are adjusted and electrified for one time, the variable parabolic radiation ribs are gradually unfolded, and the film reflection surface is gradually rotated and unfolded under the traction of the six variable parabolic radiation ribs; after the variable parabolic radiation rib is unfolded, the variable parabolic radiation rib is continuously electrified and temperature-regulated, and the secondary variable of the variable parabolic radiation rib is folded along the width direction, namely the axial direction of the whole antenna, and is changed into a corrugated plate shape, so that the bending rigidity of the variable parabolic radiation rib is increased;
the six deformable parabolic radiating ribs are formed of a three-way shape memory polymer material.
2. The self-rebounding reconfigurable spaceborne deployable antenna of claim 1, wherein the thin film reflective surface comprises a metallic reflective layer, a film layer, and a shape memory actuator layer;
the metal reflecting layer and the film layer form a paraboloid at one time by using a thermoplastic hot-press molding method by using the film surface plated with the metal reflecting layer; the shape memory actuator layer is printed on the back of the reflective surface of the film.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710267963.1A CN107221755B (en) | 2017-04-22 | 2017-04-22 | Self-resilience reconfigurable satellite-borne deployable antenna |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710267963.1A CN107221755B (en) | 2017-04-22 | 2017-04-22 | Self-resilience reconfigurable satellite-borne deployable antenna |
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| Publication Number | Publication Date |
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| CN107221755A CN107221755A (en) | 2017-09-29 |
| CN107221755B true CN107221755B (en) | 2020-09-01 |
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| CN201710267963.1A Active CN107221755B (en) | 2017-04-22 | 2017-04-22 | Self-resilience reconfigurable satellite-borne deployable antenna |
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| CN107768797B (en) * | 2017-10-19 | 2020-04-03 | 西北工业大学 | Satellite-borne solid surface deployable antenna |
| US11381001B2 (en) * | 2017-10-30 | 2022-07-05 | Institute For Q-Shu Pioneers Of Space, Inc. | Reflector, deployable antenna, and spacecraft |
| CN108365348B (en) * | 2018-02-02 | 2020-03-31 | 西安电子科技大学 | Flexible rib deployable antenna device with active shape surface adjusting function |
| CN109004362A (en) * | 2018-06-20 | 2018-12-14 | 上海卫星工程研究所 | It is a kind of based on multi-point displacement adjust satellite antenna in rail type face active control device |
| GB201810641D0 (en) | 2018-06-28 | 2018-08-15 | Oxford Space Systems | Deployable reflector for an antenna |
| CN110350322B (en) * | 2019-07-22 | 2020-10-02 | 哈尔滨工业大学 | Intelligent expansion type antenna reflecting surface radially supported by multi-stable curved beam |
| CN111092288B (en) * | 2020-01-09 | 2021-04-20 | 天津大学 | Single-degree-of-freedom parabolic cylinder deployable surface antenna |
| CN113078440B (en) * | 2021-04-07 | 2022-03-04 | 西北工业大学 | Memory alloy actuator of large-scale satellite-borne netted reflector antenna |
| CN116505224B (en) * | 2023-06-29 | 2023-09-05 | 齐鲁空天信息研究院 | Antenna and aerospace device composed of expandable winding ribs |
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| CN101872904B (en) * | 2010-06-30 | 2012-12-19 | 哈尔滨工业大学 | Deformable antenna reflection surface |
| CN103662099B (en) * | 2012-09-20 | 2015-12-09 | 中国科学院沈阳自动化研究所 | A kind of deployable space structures |
| CN103441322A (en) * | 2013-09-09 | 2013-12-11 | 西北工业大学 | Extendable tower-shaped satellite antenna framework structure |
| CN106025568B (en) * | 2016-05-23 | 2018-08-31 | 西安电子科技大学 | A kind of inflating thin film reflecting surface device with shape adjustment function |
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