CN103693212A - Controlled-unfolding coiled stretching arm for unfolding satellite load - Google Patents
Controlled-unfolding coiled stretching arm for unfolding satellite load Download PDFInfo
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- CN103693212A CN103693212A CN201310658700.5A CN201310658700A CN103693212A CN 103693212 A CN103693212 A CN 103693212A CN 201310658700 A CN201310658700 A CN 201310658700A CN 103693212 A CN103693212 A CN 103693212A
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- extending arm
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Abstract
The invention discloses a controlled-unfolding coiled stretching arm for unfolding a satellite load. The stretching arm mainly comprises a stretching arm main body, a bottom storage tube, a Y-shaped top plate and an unfolding control assembly, wherein one end of the stretching arm main body is connected with the storage tube, the other end of the stretching arm main body is connected with the Y-shaped top plate, a driving unit in the unfolding control assembly is mounted at the bottom of the storage tube, and an unfolding control cable is connected to the Y-shaped top plate. The stretching arm has the characteristics of high storage ratio, light weight, high reliability and the like, can realize the linear-direction short-distance or middle/far-distance unfolding, is applicable to the unfolding of satellite loads, such as magnetometers, antennae and gravity gradient counterweights and has wide application adaptability.
Description
Technical field
The present invention relates to a kind of extending arm, particularly relate to a kind of satellite load and stretch with controlled expansion coiling extending arm.
Background technology
Along with the development of space technology, Modern Satellite structure is increasingly sophisticated, and function is on the increase, and the layout of Satellite Payloads has been proposed to many-sided requirement.As satellite load such as magnetometer, antenna and gravity gradient counterweights, at launching phase, need be pressed on celestial body surface, to be launched enter the orbit after, according to specify to require to unlock and extend to the assigned address of determinative star body certain distance, thereby realize its design function., stretch on the basis of function meeting load, satellite is day by day harsh to the lightweight requirements of each each auxiliary equipment of system meanwhile, to the envelope of extending apparatus, take in than having proposed requirements at the higher level with weight.Therefore, conventional expansion mode has been difficult to adapt to above each generic request.
Summary of the invention
Technical matters to be solved by this invention is to provide a kind of satellite load and stretches with controlled expansion coiling extending arm, it has features such as taking in greatly ratio, lightweight and high reliability, this type extending arm can realize in rectilinear direction realize from short range to, launch at a distance, be applicable to the satellite load such as magnetometer, antenna and gravity gradient counterweight and stretch, have a wide range of applications comformability.
The present invention solves above-mentioned technical matters by following technical proposals: a kind of satellite load stretches with controlled expansion coiling extending arm, it is characterized in that, it is mainly comprised of extending arm main body, bottom admission extinguisher, Y shape top board, expansion control assembly, extending arm main body one end connects admission extinguisher, the other end connects Y shape top board, launch driver element in control assembly and be installed to admission extinguisher bottom, launch to control drag-line and be connected to Y shape top board.
Preferably, described extending arm main body is mainly by Suo Zucheng between rod member and bar.
Preferably, described bottom admission extinguisher is for storing the extending arm main body of receiving state and the mounting interface that launches control assembly being provided.
Preferably, described Y shape top board is used for connecting launch to control drag-line, and provides customizable mounting interface for satellite load.
Preferably, described expansion control assembly comprises expansion control drag-line, launches to control drag-line one end and is connected to Y shape top board, and the retarder of usining connects motor as propulsion source, realizes the controlled expansion of extending arm by the release rate of control drag-line.
Positive progressive effect of the present invention is: one, and extending arm main body of the present invention adopts the material with large elastic deformability to make, and the expansion of extending arm is without supporting corresponding expansion actuating device, thus the lightweight of implementation; Two, the present invention adopts lightweight, Miniaturization Design, makes this type extending arm have the higher ratio of taking in, and can be stored in completely in the admission extinguisher of bottom; Three, Y shape top board can be satellite load customizable mounting interface is provided, and meets the installation requirement of all kinds of satellite load; Four, launch to control employing retarder and connect motor driving, expansion process is stablized controlled.
Accompanying drawing explanation
Fig. 1 is that satellite load of the present invention stretches the schematic diagram with controlled expansion coiling extending arm receiving state;
Fig. 2 is that satellite load of the present invention stretches with controlled expansion coiling extending arm deployed condition schematic diagram.
The specific embodiment
Below in conjunction with accompanying drawing, provide preferred embodiment of the present invention, to describe technical scheme of the present invention in detail.
As depicted in figs. 1 and 2, satellite load of the present invention stretches with controlled expansion coiling extending arm and mainly extending arm main body 1, bottom admission extinguisher 2, Y shape top board 3, expansion control assembly 4, consists of, extending arm main body one end connects admission extinguisher, the other end connects Y shape top board, launch driver element in control assembly and be installed to admission extinguisher bottom, launch to control drag-line and be connected to Y shape top board.
Described extending arm main body is mainly by Suo Zucheng between rod member and bar.Wherein each rod member adopts the material with large elastic deformability to make, and when coiling is drawn in, the strain energy of storage is launched power as it, makes it without can independently launching under restrained condition, without external power supply, thus the lightweight of implementation.After extending arm launches, under the cooperation of rope between bar, keep structural stability, and guarantee rigidity requirement.
Described bottom admission extinguisher is for storing the extending arm main body of receiving state and the mounting interface that launches control assembly being provided.
Described Y shape top board is used for connecting launch to control drag-line, and provides customizable mounting interface for satellite load.
Described expansion control assembly comprises expansion control drag-line, launches to control drag-line one end and is connected to Y shape top board, and the retarder of usining connects motor as propulsion source, realizes the controlled expansion of extending arm by the release rate of control drag-line.
In sum, this extending arm can realize in rectilinear direction realize from short range to, launch at a distance, and there is features such as taking in greatly ratio, lightweight and high reliability, be a kind ofly on spacecraft, to have the space of stronger using value can open up extending arm.
Those skilled in the art can carry out various remodeling and change to the present invention.Therefore, the present invention has covered various remodeling and the change in the scope that falls into appending claims and equivalent thereof.
Claims (5)
1. a satellite load stretches with controlled expansion coiling extending arm, it is characterized in that, it is mainly comprised of extending arm main body, bottom admission extinguisher, Y shape top board, expansion control assembly, extending arm main body one end connects admission extinguisher, the other end connects Y shape top board, launch driver element in control assembly and be installed to admission extinguisher bottom, launch to control drag-line and be connected to Y shape top board.
2. satellite load as claimed in claim 1 stretches with controlled expansion coiling extending arm, it is characterized in that, described extending arm main body is mainly by Suo Zucheng between rod member and bar.
3. satellite load as claimed in claim 1 stretches with controlled expansion coiling extending arm, it is characterized in that, described bottom admission extinguisher is for storing the extending arm main body of receiving state and the mounting interface that launches control assembly being provided.
4. satellite load as claimed in claim 1 stretches with controlled expansion coiling extending arm, it is characterized in that, described Y shape top board is used for connecting and launches control drag-line, and provides customizable mounting interface for satellite load.
5. satellite load as claimed in claim 1 stretches with controlled expansion coiling extending arm, it is characterized in that, described expansion control assembly comprises expansion control drag-line, launch to control drag-line one end and be connected to Y shape top board, the retarder of usining connects motor as propulsion source, realizes the controlled expansion of extending arm by controlling the release rate of drag-line.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310658700.5A CN103693212A (en) | 2013-12-06 | 2013-12-06 | Controlled-unfolding coiled stretching arm for unfolding satellite load |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310658700.5A CN103693212A (en) | 2013-12-06 | 2013-12-06 | Controlled-unfolding coiled stretching arm for unfolding satellite load |
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| CN103693212A true CN103693212A (en) | 2014-04-02 |
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| CN201310658700.5A Pending CN103693212A (en) | 2013-12-06 | 2013-12-06 | Controlled-unfolding coiled stretching arm for unfolding satellite load |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105564668A (en) * | 2016-01-22 | 2016-05-11 | 上海交通大学 | Coiling type telescopic arm capable of achieving segmental, sequential and progressive expanding |
| CN106364700A (en) * | 2016-08-29 | 2017-02-01 | 南京航空航天大学 | Space deployable mechanism designed on basis of posterior wing deployable mechanism of dermaptera insect earwigs |
| CN106410362A (en) * | 2016-11-09 | 2017-02-15 | 上海卫星工程研究所 | Stretching forming mechanism of parabolic cylinder |
| CN106945850A (en) * | 2017-01-24 | 2017-07-14 | 重庆大学 | Satellite load packaging type prestress thin wall taper gravity gradient boom |
| CN109818151A (en) * | 2019-02-19 | 2019-05-28 | 上海卫星工程研究所 | Spaceborne unfolded reticular antenna |
| CN110901954A (en) * | 2019-11-04 | 2020-03-24 | 上海宇航***工程研究所 | High-rigidity coiled stretching mechanism |
| CN113895652A (en) * | 2021-09-16 | 2022-01-07 | 大连理工大学 | Truss type stretching arm capable of being unfolded and folded |
| CN117284498A (en) * | 2023-11-24 | 2023-12-26 | 北京航空航天大学 | Coiled extension type optical load with optical path offset compensation mechanism |
| CN117289446A (en) * | 2023-11-24 | 2023-12-26 | 北京航空航天大学 | Space long-focus closed-loop imaging system capable of automatically focusing |
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| CN1474069A (en) * | 2003-05-22 | 2004-02-11 | 上海交通大学 | High-rigidity synchronously spreading folded space extension arm |
| CN102322463A (en) * | 2011-08-18 | 2012-01-18 | 哈尔滨工业大学 | Connecting structure between main support pipes and oblique tensile pipes of inflating and extending truss structure |
| CN102381491A (en) * | 2011-08-18 | 2012-03-21 | 哈尔滨工业大学 | Unfolding control device for three-dimensional inflatable unfolding truss structure |
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2013
- 2013-12-06 CN CN201310658700.5A patent/CN103693212A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN1474069A (en) * | 2003-05-22 | 2004-02-11 | 上海交通大学 | High-rigidity synchronously spreading folded space extension arm |
| CN102322463A (en) * | 2011-08-18 | 2012-01-18 | 哈尔滨工业大学 | Connecting structure between main support pipes and oblique tensile pipes of inflating and extending truss structure |
| CN102381491A (en) * | 2011-08-18 | 2012-03-21 | 哈尔滨工业大学 | Unfolding control device for three-dimensional inflatable unfolding truss structure |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105564668B (en) * | 2016-01-22 | 2017-10-03 | 上海交通大学 | A kind of coiling extending arm for being segmented asymptotic expansion successively |
| CN105564668A (en) * | 2016-01-22 | 2016-05-11 | 上海交通大学 | Coiling type telescopic arm capable of achieving segmental, sequential and progressive expanding |
| CN106364700A (en) * | 2016-08-29 | 2017-02-01 | 南京航空航天大学 | Space deployable mechanism designed on basis of posterior wing deployable mechanism of dermaptera insect earwigs |
| CN106410362A (en) * | 2016-11-09 | 2017-02-15 | 上海卫星工程研究所 | Stretching forming mechanism of parabolic cylinder |
| CN106945850B (en) * | 2017-01-24 | 2021-07-02 | 重庆大学 | Satellite load wrapped type prestress thin-wall conical gravity gradient rod |
| CN106945850A (en) * | 2017-01-24 | 2017-07-14 | 重庆大学 | Satellite load packaging type prestress thin wall taper gravity gradient boom |
| CN109818151A (en) * | 2019-02-19 | 2019-05-28 | 上海卫星工程研究所 | Spaceborne unfolded reticular antenna |
| CN109818151B (en) * | 2019-02-19 | 2021-05-21 | 上海卫星工程研究所 | Satellite-borne deployable mesh antenna |
| CN110901954A (en) * | 2019-11-04 | 2020-03-24 | 上海宇航***工程研究所 | High-rigidity coiled stretching mechanism |
| CN110901954B (en) * | 2019-11-04 | 2021-12-07 | 上海宇航***工程研究所 | High-rigidity coiled stretching mechanism |
| CN113895652A (en) * | 2021-09-16 | 2022-01-07 | 大连理工大学 | Truss type stretching arm capable of being unfolded and folded |
| CN113895652B (en) * | 2021-09-16 | 2023-08-04 | 大连理工大学 | Truss type extension arm capable of being unfolded and folded |
| CN117284498A (en) * | 2023-11-24 | 2023-12-26 | 北京航空航天大学 | Coiled extension type optical load with optical path offset compensation mechanism |
| CN117289446A (en) * | 2023-11-24 | 2023-12-26 | 北京航空航天大学 | Space long-focus closed-loop imaging system capable of automatically focusing |
| CN117289446B (en) * | 2023-11-24 | 2024-01-19 | 北京航空航天大学 | Space long-focus closed-loop imaging system capable of automatically focusing |
| CN117284498B (en) * | 2023-11-24 | 2024-02-09 | 北京航空航天大学 | Coiled extension type optical load with optical path offset compensation mechanism |
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Application publication date: 20140402 |