CN104241868B - The Spacial Inflatable Deploying Antenna reflecting surface not affected by solar light pressure - Google Patents
The Spacial Inflatable Deploying Antenna reflecting surface not affected by solar light pressure Download PDFInfo
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- CN104241868B CN104241868B CN201410523560.5A CN201410523560A CN104241868B CN 104241868 B CN104241868 B CN 104241868B CN 201410523560 A CN201410523560 A CN 201410523560A CN 104241868 B CN104241868 B CN 104241868B
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Abstract
The invention provides a kind of Spacial Inflatable Deploying Antenna reflecting surface not affected by solar light pressure.The present invention by gold-plated or nickel plating molybdenum filament net, can rigidifying rack and lens blooming face is bonding forms a seal air cavity, it is connected by constant force spring between inflated supporting ring and seal air cavity, the opening of elastic clip is arranged on the outside of supporting sleeve, and the opening of elastic clip is provided with blasting bolt.After Spacial Inflatable Deploying Antenna reflecting surface of the present invention launches, respectively inflated supporting ring, seal air cavity are inflated at planned orbit, antenna reflective face structure is launched into fixing planform, solidification can be irradiated with or after being heating and curing by space rigidifying material in space, blasting bolt explosive damage, elastic clip in supporting sleeve is no longer to connecting rope Constrained effect, on satellite, motor action will connect rope and extract out from connecting ring, it is achieved seal air cavity and gold-plated or nickel plating molybdenum filament net and can separate by rigidifying rack.The most i.e. can obtain the antenna reflective face that design requires.
Description
Technical field
The present invention relates to a kind of Spacial Inflatable Deploying Antenna reflecting surface not affected by solar light pressure, belong to inflatable space antenna reflecting surface technical field.
Background technology
At present, large space reflecting surface of deployable antenna mainly machinery expansion mode in too aerial applications, there is hinge too much to cause launching reliability reduction and the size-constrained problem processed of FOLD AND PACK, inflation is utilized to drive the film antenna reflecting surface launched to launch reliability higher, the size-constrained system of FOLD AND PACK is less, but large-scale membrane structure is affected seriously by solar light pressure in spatial environments, and then the attitude in-orbit of satellite is had a negative impact.
Summary of the invention
The invention aims to solve the problem that above-mentioned prior art exists, the most large-scale membrane structure is affected seriously by solar light pressure in spatial environments, and then has a negative impact the attitude in-orbit of satellite.And then a kind of Spacial Inflatable Deploying Antenna reflecting surface not affected by solar light pressure is provided.
It is an object of the invention to be achieved through the following technical solutions:
nullA kind of Spacial Inflatable Deploying Antenna reflecting surface not affected by solar light pressure，Including: inflated supporting ring、Constant force spring、Can rigidifying rack、Blasting bolt、Supporting sleeve、Lens blooming face、Gold-plated or nickel plating molybdenum filament net、Connect rope、Connect ring one、Connect ring two and elastic clip，By gold-plated or nickel plating molybdenum filament net、Can rigidifying rack and lens blooming face one seal air cavity of bonding formation，Inflated supporting ring is arranged on the outside of seal air cavity，Inflated supporting ring and seal air cavity are that concentric circular is arranged，It is connected by constant force spring between inflated supporting ring and seal air cavity，Supporting sleeve with can the center at rigidifying rack rear portion be connected，Elastic clip it is provided with in supporting sleeve，The opening of elastic clip is arranged on the outside of supporting sleeve，The opening of elastic clip is provided with blasting bolt，Connection ring one it is bonded with on described seal air cavity upper surface，At node, connection ring two can be crossed with gold-plated or nickel plating molybdenum filament Netcom is connected by rigidifying rack，Described connection rope is also cross multiple connection rings one and connects ring two，Connect rope to collect in supporting sleeve.
After the inflatable space antenna reflecting surface of the space rigidifying made is folded, pack with closing；After launching, respectively inflated supporting ring, seal air cavity are inflated at planned orbit, antenna reflective face structure is launched into fixing planform, solidification can be irradiated with or after being heating and curing by space rigidifying material in space, blasting bolt explosive damage, elastic clip in supporting sleeve is no longer to connecting rope Constrained effect, and on satellite, motor action will connect rope and extract out from connecting ring, it is achieved seal air cavity and gold-plated or nickel plating molybdenum filament net and can separate by rigidifying rack.The most i.e. can obtain the antenna reflective face that design requires.
The present invention compared with prior art has a following useful technique effect: the present invention has that folding volume is little, launch the advantages such as reliability is high, lightweight, and the antenna reflective face structure after space environment solidifies can be prevented effectively from solar light pressure and be applied to inflate lens face and the harmful effect that produces antenna and satellite.The present invention has broad application prospects in the communications field.
Accompanying drawing explanation
Fig. 1 is the structural representation of the Spacial Inflatable Deploying Antenna reflecting surface that the present invention is not affected by solar light pressure；
Fig. 2 is the A-A sectional view of Fig. 1；
Fig. 3 is the partial enlarged drawing of Fig. 1；
Fig. 4 is the profile of supporting sleeve 5.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is described in further detail: the present embodiment is implemented under premised on technical solution of the present invention, gives detailed embodiment, but protection scope of the present invention is not limited to following embodiment.
nullAs shown in Fig. 1 ~ Fig. 4，A kind of Spacial Inflatable Deploying Antenna reflecting surface not affected by solar light pressure involved by the present embodiment，Including: inflated supporting ring 1、Constant force spring 2、Inflatable rigidifying rack 3、Blasting bolt 4、Supporting sleeve 5、Lens blooming face 6、Gold-plated or nickel plating molybdenum filament net 7、Connect rope 8、Connect ring 1、Connect ring 2 10 and elastic clip 11，By gold-plated or nickel plating molybdenum filament net 7、Can rigidifying rack 3 and lens blooming face 6 one seal air cavity of bonding formation，Inflated supporting ring 1 is arranged on the outside of seal air cavity，Inflated supporting ring 1 and seal air cavity are that concentric circular is arranged，It is connected by constant force spring 2 between inflated supporting ring 1 and seal air cavity，Supporting sleeve 5 with can the center at rigidifying rack 3 rear portion be connected，Elastic clip 11 it is provided with in supporting sleeve 5，The opening of elastic clip 11 is arranged on the outside of supporting sleeve 5，The opening of elastic clip 11 is provided with blasting bolt 4，Connection ring 1 it is bonded with on described seal air cavity upper surface，Can be connected by connecting ring 2 10 with gold-plated or nickel plating molybdenum filament net 7 at node by rigidifying rack 3，Described connection rope 8 is also cross multiple connection rings 1 and connects ring 2 10，Connect rope 8 to collect in supporting sleeve 5.
Described gold-plated or nickel plating molybdenum filament net 7 is as the face of antenna receiving signal.
The lens arrangement that air cavity is dual paraboloid in described lens blooming face 6.
Described inflated supporting ring 1 is made up of Kapton or Mylar material.
Described can the material of rigidifying rack 3 be ultraviolet rigidifying material or heat cure rigidifying material, its medium ultraviolet rigidifying material is to fill cationic photopolymerization to cause the aliphatic epoxy resin/quartz fiber reinforced composite material of firming agent, and heat cure rigidifying material is made up of carbon fiber, aramid fiber and the resistance wire shuffling of heat-setting pre-epoxy resin dipping.
Gold-plated or nickel plating molybdenum filament net 7 and can covering on the upper surface of seal air cavity by rigidifying rack 3.Gold-plated or the nickel plating molybdenum filament net 7 of reception signal is in can be between rigidifying rack 3 and seal air cavity.All connection ropes collect in supporting sleeve 5, and supporting sleeve 5 is outside the blasting bolt 4 elastic clip 11 in fastening support sleeve pipe 5, retrain connection rope 8 with this.Supporting sleeve 5 is rigid supporting rod, is reflecting surface and the extending arm connection member on satellite.
Claims (4)
- null1. the Spacial Inflatable Deploying Antenna reflecting surface not affected by solar light pressure，It is characterized in that，Including: inflated supporting ring (1)、Constant force spring (2)、Can rigidifying rack (3)、Blasting bolt (4)、Supporting sleeve (5)、Lens blooming face (6)、Gold-plated or nickel plating molybdenum filament net (7)、Connect rope (8)、Connect ring one (9)、Connect ring two (10) and elastic clip (11)，By gold-plated or nickel plating molybdenum filament net (7)、Can rigidifying rack (3) and one seal air cavity of lens blooming face (6) bonding formation，Inflated supporting ring (1) is arranged on the outside of seal air cavity，Inflated supporting ring (1) and seal air cavity are that concentric circular is arranged，It is connected by constant force spring (2) between inflated supporting ring (1) and seal air cavity，Supporting sleeve (5) with can the center at rigidifying rack (3) rear portion be connected，Elastic clip (11) it is provided with in supporting sleeve (5)，The opening of elastic clip (11) is arranged on the outside of supporting sleeve (5)，The opening of elastic clip (11) is provided with blasting bolt (4)，Connection ring one (9) it is bonded with on described seal air cavity upper surface，Can be connected by connecting ring two (10) with gold-plated or nickel plating molybdenum filament net (7) at node by rigidifying rack (3)，Described connection rope (8) is also cross multiple connection rings one (9) and connects ring two (10)，Connect rope (8) to collect in supporting sleeve (5)；After first the antenna reflective face made being folded, pack with closing, after launching, respectively inflated supporting ring (1), seal air cavity are inflated at planned orbit；After launching, respectively inflated supporting ring (1), seal air cavity are inflated at planned orbit, antenna reflective face structure is launched in fixing planform, solidification can be irradiated with or after being heating and curing by tempering rack (3) in space, blasting bolt (4) explosive damage, elastic clip (11) in supporting sleeve (5) is no longer to connecting rope (8) Constrained effect, connect rope (8) from connecting ring one (9) and connecting extraction ring two (10), it is achieved seal air cavity and gold-plated or nickel plating molybdenum filament net (7) and can separate by tempering rack (3)；Described gold-plated or nickel plating molybdenum filament net (7) is as the face of antenna receiving signal.
- The Spacial Inflatable Deploying Antenna reflecting surface not affected by solar light pressure the most according to claim 1, it is characterised in that the lens arrangement that air cavity is dual paraboloid of described lens blooming face (6).
- The Spacial Inflatable Deploying Antenna reflecting surface not affected by solar light pressure the most according to claim 1, it is characterised in that described inflated supporting ring (1) is made up of Kapton or Mylar material.
- The Spacial Inflatable Deploying Antenna reflecting surface not affected by solar light pressure the most according to claim 1, it is characterized in that, described can the material of rigidifying rack (3) be ultraviolet rigidifying material or heat cure rigidifying material, its medium ultraviolet rigidifying material is to fill cationic photopolymerization to cause the aliphatic epoxy resin/quartz fiber reinforced composite material of firming agent, and heat cure rigidifying material is made up of carbon fiber, aramid fiber and the resistance wire shuffling of heat-setting pre-epoxy resin dipping.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410523560.5A CN104241868B (en) | 2014-10-08 | 2014-10-08 | The Spacial Inflatable Deploying Antenna reflecting surface not affected by solar light pressure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410523560.5A CN104241868B (en) | 2014-10-08 | 2014-10-08 | The Spacial Inflatable Deploying Antenna reflecting surface not affected by solar light pressure |
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| Publication Number | Publication Date |
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| CN104241868A CN104241868A (en) | 2014-12-24 |
| CN104241868B true CN104241868B (en) | 2016-08-03 |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107238993B (en) * | 2017-07-13 | 2019-07-16 | 西安电子科技大学 | A kind of deployable large-scale inflating thin film shading cover structure in space |
| CN109167179B (en) * | 2018-11-02 | 2024-02-27 | 中国电子科技集团公司第五十四研究所 | FAST center inflatable FAST-assembling reflecting surface |
| CN111555011B (en) * | 2018-12-29 | 2023-01-24 | 长沙天仪空间科技研究院有限公司 | Deployable inflatable antenna suitable for satellite |
| CN110065652A (en) * | 2019-03-29 | 2019-07-30 | 上海卫星工程研究所 | Spacecraft stores the method for folding than folding and inflatable deployment structure with plane |
| CN112909483A (en) * | 2021-01-15 | 2021-06-04 | 大连理工大学 | Inflated and expanded shell film reflector antenna reflector |
| CN116960638B (en) * | 2023-09-19 | 2024-01-12 | 广东福顺天际通信有限公司 | Reflector with adjustable reflecting surface |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| GB2120857B (en) * | 1982-04-28 | 1985-10-30 | British Aerospace | Reflectors |
| CN102280716B (en) * | 2011-05-11 | 2013-10-16 | 哈尔滨工业大学 | Body-mounted parabolic antenna for gas-filled satellite |
| CN103943966B (en) * | 2014-04-28 | 2016-02-24 | 哈尔滨工业大学 | Inflated supporting pipe mixes with hinge to support and launches spaceborne parabolic-cylinder antenna |
| CN104022337B (en) * | 2014-06-17 | 2016-05-18 | 哈尔滨工业大学 | Modular space curved surface folding exhibition antenna mechanism based on rib mechanism |
| CN104064878B (en) * | 2014-07-10 | 2016-07-06 | 哈尔滨工业大学 | The reflecting surface of a kind of inflating expanded parabolic-cylinder antenna launches setting mechanism |
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