CN105470619A - Satellite borne flat plate antenna articulated truss - Google Patents
Satellite borne flat plate antenna articulated truss Download PDFInfo
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- CN105470619A CN105470619A CN201510850867.0A CN201510850867A CN105470619A CN 105470619 A CN105470619 A CN 105470619A CN 201510850867 A CN201510850867 A CN 201510850867A CN 105470619 A CN105470619 A CN 105470619A
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Abstract
The invention discloses a satellite borne flat plate antenna articulated truss. The satellite borne flat plate antenna articulated truss comprises at least one group of rod components; each group of rod components includes a first supporting rod, a second supporting rod, a third supporting rod, a linkage supporting rod and an auxiliary supporting rod; one end of the first supporting rod is connected with a satellite platform through a satellite body supporting seat hinge; the other end of the first supporting rod is connected with one end of the second supporting rod through a multi-joint hinge; the other end of the second supporting rod is connected with an antenna inner plate through a first inter-rod hinge; one end of the third supporting rod is connected with an antenna outer plate through a frame supporting seat hinge; the other end of the third supporting rod is connected with one end of the linkage supporting rod through a second inter-rod hinge; the other end of the linkage supporting rod is connected with a multi-joint hinge; one end of the auxiliary supporting rod is connected with the third supporting rod through a third inter-rod hinge; and the other end of the auxiliary supporting rod is connected with the first inter-rod hinge. According to the satellite borne flat plate antenna articulated truss provided by the invention, a control system and a truss system are simplified, and inter-plate driving links can be reduced.
Description
Technical field
The present invention relates to aerospace craft technical field, be specifically related to a kind of spaceborne plate aerial radial type truss.
Background technology
At present, more to the investigation and application of satellite sun wing development agency both at home and abroad, solar wing all adopts passive mechanisms to launch, and without special required precision after launching in-orbit; And SAR plate aerial has a direct impact due to the electrical property of surface accuracy to antenna launching aft antenna, there are much relations to its image quality, for guaranteeing that SAR antenna launches the larger rigidity of rear maintenance in-orbit, usually adopt the scheme that leverage supports at the antenna back side.Foreign applications more typically has Canadian RADARSAT satellite, domesticly starts late in the development of radar satellite, and remote sensing radar satellite antenna is in-orbit close with RADARSAT structure.For design feature and the pattern of expansion of dull and stereotyped SAR antenna development, its main feature and weak point are mainly manifested in:
A, employing two have source mechanism to drive inside and outside two pieces of antenna plate to launch respectively, and truss leverage carries out servo-actuated, and such Control System Design is complicated, and Liang Tai mechanism has higher requirements to expansion timing and control precision;
B, employing one have source mechanism direct driven antenna inner panel, carry out driven antenna outside plate by setting up a set of special linkage simultaneously, truss leverage is also done servo-actuated, and the program overlaps independently leverage owing to having two, makes the motor coordination between leverage and coupling require higher;
Mechanism's weight is too increased while c, increase product are supporting.
Therefore, be necessary to provide a kind of spaceborne plate aerial radial type truss, to simplify the expansion of spacecraft two pieces of plate aerial expandable truss.
Summary of the invention
The object of the present invention is to provide a kind of spaceborne plate aerial radial type truss, to simplify the expansion of spacecraft two pieces of plate aerial expandable truss.
For solving the problem, the present invention proposes a kind of spaceborne plate aerial radial type truss, spaceborne plate aerial comprises antenna inner panel and antenna outside plate, and the side of described antenna inner panel connects on satellite platform by root hinge, and opposite side is connected with the side of described antenna outside plate by hinge between plate; Articulated truss at least comprises one group of rod member, often organizes rod member and comprises the first strut, the second strut, the 3rd strut, interlock strut and jury strut;
One end of described first strut is connected on described satellite platform by celestial body bearing hinge, and the other end is by one end of the second strut described in polylinker chain connection, and the other end of described second strut is by being hingedly connected on described antenna inner panel between the first bar;
One end of described 3rd strut is hingedly connected on described antenna outside plate by frame supporter, and the other end is by the one end of the strut that links described in chain connection between the second bar, and the other end of described interlock strut is connected on described polylinker hinge;
One end of described jury strut by being hingedly connected between the 3rd bar on described 3rd strut, and between described 3rd bar hinge between described frame supporter hinge, the second bar between hinge; The other end of described jury strut to be hinged between described first bar on hinge.
Preferably, described satellite platform is provided with driving mechanism, described driving mechanism connects described root hinge.
Preferably, described truss includes two groups of rod members, and described two groups of rod members are separately positioned on the both sides of described antenna inner panel, antenna outside plate.
Preferably, described root hinge launches at described antenna inner panel the laggard row locking that puts in place;
Between described plate, hinge locks after described antenna shell plate development puts in place;
Between described second bar, hinge, polylinker hinge launch at rod member the laggard row locking that puts in place;
Between described first bar, between hinge, the 3rd bar, hinge and frame supporter hinge, celestial body bearing hinge do not lock after rod member expansion puts in place.
Preferably, described root hinge can open up angle is 90 °; Between described plate, hinge can open up angle is 180 °.
The present invention, owing to adopting above technical scheme, makes it compared with prior art, has following advantage and good effect:
1) one provided by the invention spaceborne plate aerial radial type truss, adopts a driving mechanism to drive whole truss, simplifies control system, reduces antenna expansion to the requirement launching timing and control precision;
2) one provided by the invention spaceborne plate aerial radial type truss, adopts a set of leverage to carry out antenna expansion and locking, avoids because the sports coordination that brings of the independent leverage of two covers is poor, mates and require high problem;
3) one provided by the invention spaceborne plate aerial radial type truss, decreases the quantity of source mechanism, transmission link eliminates drive push and pull system, achieves the lightweight of mechanism to a certain extent.
Accompanying drawing explanation
By reference to the accompanying drawings, by hereafter state detailed description, more clearly can understand above-mentioned and other feature and advantage of the present invention, wherein:
Fig. 1 is the spaceborne plate aerial radial type truss deployed configuration figure that the embodiment of the present invention provides;
Fig. 2 is the plane configuration figure of spaceborne plate aerial radial type truss under rounding state that the embodiment of the present invention provides;
Fig. 3 is the plane configuration figure of spaceborne plate aerial radial type truss in expansion process that the embodiment of the present invention provides;
Fig. 4 is that the spaceborne plate aerial radial type truss that the embodiment of the present invention provides is launching the plane configuration figure after putting in place.
Symbol description:
1-satellite platform 2-root hinge 3-driving mechanism
Hinge between 4-antenna inner panel 5-second strut 6-first bar
Hinge 8-jury strut 9-frame supporter hinge between 7-plate
Hinge between 10-antenna outside plate 11-the 3rd strut 12-the 3rd bar
Hinge 14-interlock strut 15-polylinker hinge between 13-second bar
16-first strut 17-celestial body bearing hinge.
Embodiment
See the accompanying drawing that the embodiment of the present invention is shown, hereafter in more detail the present invention will be described.But the present invention can realize in many different forms, and should not be construed as by the restriction in the embodiment of this proposition.On the contrary, it is abundant and complete open in order to reach for proposing these embodiments, and makes those skilled in the art understand scope of the present invention completely.In these accompanying drawings, for clarity sake, may be exaggerated size and the relative size in layer and region.
Please refer to Fig. 1-4, the invention provides a kind of spaceborne plate aerial radial type truss, for contraction and the expansion of spaceborne plate aerial; Spaceborne plate aerial comprises antenna inner panel 4 and antenna outside plate 10, and the side of antenna inner panel 4 is installed on satellite platform 1 by root hinge 2, and the opposite side of antenna inner panel 4 connects the side of antenna outside plate 10 by hinge between plate 7.
Wherein, it is 90 ° that root hinge 2 can open up angle, and between plate, hinge 7 can open up angle is 180 °.
Spaceborne plate aerial radial type truss at least includes one group of rod member, in the present embodiment in order to the stability ensureing that spaceborne plate aerial launches, shrink, preferably be provided with two groups of rod members, and be symmetricly set on the both sides of antenna inner panel 4 and antenna outside plate 10 between two groups of bars; Certainly, radial type truss also only can be provided with one group of rod member, also can be provided with rod member more than two, sets as the case may be, is not restricted herein.
In the present embodiment, often organize rod member and include the first strut 16, second strut 5, the 3rd strut 11, interlock strut 14 and jury strut 8.
Concrete, one end of the first strut 16 is installed on satellite platform 1 by celestial body bearing hinge 17, and celestial body bearing hinge 17 and root hinge 2 are all arranged on the same side of satellite platform 1; The other end of the first strut 16 connects one end of the second strut 5 by polylinker hinge 15, the other end of the second strut 5 is connected on antenna inner panel 4 by hinge 6 between the first bar, and between preferred first bar, hinge 6 is near the other end of antenna inner panel 4.
One end of 3rd strut 11 is connected on antenna outside plate 10 by frame supporter hinge 9, and preferred frame supporter hinge 9 is near the other end of antenna outside plate 10; The other end of the 3rd strut 11 connects one end of interlock strut 14 by hinge 13 between the second bar, the other end of interlock strut 14 is connected on polylinker hinge 15.
Jury strut 8 is also provided with between 3rd strut 11 and the second strut 5, one end of jury strut 8 is connected on the 3rd strut 11 by hinge 12 between the 3rd bar, and between the 3rd bar hinge 12 between frame supporter hinge 9 and the second bar between hinge 13, particular location can adjust as the case may be, is not restricted herein; The other end of jury strut 8 to be also connected between the first bar on hinge 6.
In the present embodiment, satellite platform 1 is also provided with driving mechanism 3, driving mechanism 3 connects root hinge 2.Driving mechanism 3 is unique active matrix driving of whole hinged truss, and other hinges have passive drive and launch function; Driving mechanism 3 starts and drives antenna inner panels 4 to overturn by root hinged 2, thus drive remaining rod member, hinge moves.
In the present embodiment, root hinge 2 launches at antenna inner panel 4 the laggard row locking that puts in place; Between plate, hinge 7 launches at antenna outside plate 10 the laggard row locking that puts in place; Between the second bar, hinge 13, polylinker hinge 15 launch at rod member the laggard row locking that puts in place; Between the first bar, between hinge 6, the 3rd bar, hinge 12 and frame supporter hinge 9, celestial body bearing hinge 17 do not lock after rod member expansion puts in place.Above-described each lock function, by adding latch-up structure to realize on each hinge, is not restricted herein.
Spaceborne plate aerial radial type truss provided by the invention, adopts a driving mechanism to drive whole truss, simplifies control system, reduces antenna expansion to the requirement launching timing and control precision; And the present invention adopts a set of leverage to carry out antenna expansion and locking, avoid because the sports coordination that brings of the independent leverage of two covers is poor, mate and require high problem; In addition, The present invention reduces the quantity of source mechanism, transmission link eliminates drive push and pull system, achieve the lightweight of mechanism to a certain extent.Below with regard to the expansion process of a kind of spaceborne plate aerial radial type truss provided by the invention, be described further, specifically comprise the steps:
During rounding state, first strut 16, second strut 5, the 3rd strut 11, interlock strut 14, jury strut 8 are arranged in the both sides of antenna inner panel 4, antenna outside plate 10, folding draw in around satellite platform 1 and antenna inner panel 4, antenna outside plate 10, between root hinge 2, plate between hinge 7, first bar between hinge 6, the 3rd bar between hinge 12, second bar hinge 13, polylinker hinge 15 be all in active connection state, as shown in Figure 2;
In expansion process, under the effect of driving mechanism 3 active matrix driving root hinge 2, antenna inner panel 4 does gyration around root hinge 2; Synchronously, under the effect of polylinker hinge 15 passive drive, the second strut 5 drives interlock strut 14, jury strut 8 and the 3rd strut 11, and then between driven antenna outside plate 10 winding board, gyration done by hinge 7, as shown in Figure 3;
After expansion puts in place, hinge 7 between root hinge 2, plate, between polylinker hinge 15 and the second bar, hinge 13 all locks, driving mechanism 3 quits work, now antenna inner panel 4 relative satellite platform 1 rotates 90 °, antenna outside plate 10 relative antenna inner panel 4 correspondence rotates 180 °, antenna inner panel 4 and antenna outside plate 10 are in a working face, and whole truss forms a Stable structure, as shown in Figure 4.
In sum, spaceborne plate aerial radial type truss provided by the invention, comprise: hinge between hinge, the 3rd bar, interlock strut, polylinker hinge, the first strut, celestial body bearing hinge between hinge, jury strut, frame supporter hinge, antenna outside plate, the 3rd strut, the second bar between hinge, plate between satellite platform, root hinge, driving mechanism, antenna inner panel, the second strut, the first bar, this arrangement simplifies control system and leverage truss, decrease the driving link between plate; Simultaneously, also disclose the expansion process of spaceborne plate aerial radial type truss, in expansion process under the driving effect of driving mechanism and polylinker hinge, by truss change of configuration, complete a kind of expansion and locking of spaceborne plate aerial radial type truss, ensure that linkage mechanism launches timing and sports coordination, uniqueness preferably, be easy to the lightweight realizing mechanism simultaneously, can be used for the expansion of spacecraft two pieces of plate aerials.
Those skilled in the art should be understood that the present invention can not depart from the spirit or scope of itself with many other concrete forms realizations.Although described case study on implementation of the present invention, the present invention should be understood and should not be restricted to these embodiments, within the spirit and scope of the present invention that those skilled in the art can define as appended claims, make change and amendment.
Claims (5)
1. a spaceborne plate aerial radial type truss, spaceborne plate aerial comprises antenna inner panel and antenna outside plate, the side of described antenna inner panel connects on satellite platform by root hinge, opposite side is connected with the side of described antenna outside plate by hinge between plate, it is characterized in that, articulated truss at least comprises one group of rod member, often organizes rod member and comprises the first strut, the second strut, the 3rd strut, interlock strut and jury strut;
One end of described first strut is connected on described satellite platform by celestial body bearing hinge, and the other end is by one end of the second strut described in polylinker chain connection, and the other end of described second strut is by being hingedly connected on described antenna inner panel between the first bar;
One end of described 3rd strut is hingedly connected on described antenna outside plate by frame supporter, and the other end is by the one end of the strut that links described in chain connection between the second bar, and the other end of described interlock strut is connected on described polylinker hinge;
One end of described jury strut by being hingedly connected between the 3rd bar on described 3rd strut, and between described 3rd bar hinge between described frame supporter hinge, the second bar between hinge; The other end of described jury strut to be hinged between described first bar on hinge.
2. spaceborne plate aerial radial type truss according to claim 1, it is characterized in that, described satellite platform is provided with driving mechanism, and described driving mechanism connects described root hinge.
3. spaceborne plate aerial radial type truss according to claim 1, it is characterized in that, described truss includes two groups of rod members, and described two groups of rod members are separately positioned on the both sides of described antenna inner panel, antenna outside plate.
4. spaceborne plate aerial radial type truss according to claim 1, is characterized in that, described root hinge launches at described antenna inner panel the laggard row locking that puts in place;
Between described plate, hinge locks after described antenna shell plate development puts in place;
Between described second bar, hinge, polylinker hinge launch at rod member the laggard row locking that puts in place;
Between described first bar, between hinge, the 3rd bar, hinge and frame supporter hinge, celestial body bearing hinge do not lock after rod member expansion puts in place.
5. spaceborne plate aerial radial type truss according to claim 1, it is characterized in that, it is 90 ° that described root hinge can open up angle; Between described plate, hinge can open up angle is 180 °.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510850867.0A CN105470619B (en) | 2015-11-30 | 2015-11-30 | A kind of spaceborne plate aerial radial type truss |
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| CN201510850867.0A CN105470619B (en) | 2015-11-30 | 2015-11-30 | A kind of spaceborne plate aerial radial type truss |
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| CN105470619A true CN105470619A (en) | 2016-04-06 |
| CN105470619B CN105470619B (en) | 2018-04-06 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106025488A (en) * | 2016-05-28 | 2016-10-12 | 上海大学 | Two-dimensional planar antenna unfolding apparatus |
| CN106058422A (en) * | 2016-07-15 | 2016-10-26 | 上海宇航系统工程研究所 | Low-area-ratio spaceborne planar antenna support truss and assembling and adjusting method thereof |
| CN106129578A (en) * | 2016-07-15 | 2016-11-16 | 上海宇航系统工程研究所 | A kind of spaceborne flat plane antenna sub-truss |
| CN106229601A (en) * | 2016-07-15 | 2016-12-14 | 上海宇航系统工程研究所 | A kind of spacecraft flat plane antenna synchronizes deployable trusses and Method of Adjustment |
| CN106374184A (en) * | 2016-08-30 | 2017-02-01 | 西安空间无线电技术研究所 | Folding and unfolding device and folding and unfolding method of satellite-borne dipole antenna array |
| CN107331940A (en) * | 2017-05-27 | 2017-11-07 | 上海卫星工程研究所 | Adapt to the antisymmetry high rigidity mixed structure that spaceborne big front antenna H types are installed |
| CN113675574A (en) * | 2021-08-10 | 2021-11-19 | 燕山大学 | Bidirectional flat plate folding and unfolding unit and bidirectional flat plate folding and unfolding antenna mechanism |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106025488A (en) * | 2016-05-28 | 2016-10-12 | 上海大学 | Two-dimensional planar antenna unfolding apparatus |
| CN106025488B (en) * | 2016-05-28 | 2019-02-22 | 上海大学 | A kind of two-dimensional flat plate antenna expanding unit |
| CN106058422A (en) * | 2016-07-15 | 2016-10-26 | 上海宇航系统工程研究所 | Low-area-ratio spaceborne planar antenna support truss and assembling and adjusting method thereof |
| CN106129578A (en) * | 2016-07-15 | 2016-11-16 | 上海宇航系统工程研究所 | A kind of spaceborne flat plane antenna sub-truss |
| CN106229601A (en) * | 2016-07-15 | 2016-12-14 | 上海宇航系统工程研究所 | A kind of spacecraft flat plane antenna synchronizes deployable trusses and Method of Adjustment |
| CN106129578B (en) * | 2016-07-15 | 2019-05-24 | 上海宇航系统工程研究所 | A kind of spaceborne flat plane antenna sub-truss |
| CN106229601B (en) * | 2016-07-15 | 2019-05-28 | 上海宇航系统工程研究所 | A kind of synchronous deployable trusses of spacecraft flat plane antenna and Method of Adjustment |
| CN106374184A (en) * | 2016-08-30 | 2017-02-01 | 西安空间无线电技术研究所 | Folding and unfolding device and folding and unfolding method of satellite-borne dipole antenna array |
| CN106374184B (en) * | 2016-08-30 | 2018-12-21 | 西安空间无线电技术研究所 | A kind of the gathering expanding unit and its gathering method of deploying of spaceborne antenna dipole array |
| CN107331940A (en) * | 2017-05-27 | 2017-11-07 | 上海卫星工程研究所 | Adapt to the antisymmetry high rigidity mixed structure that spaceborne big front antenna H types are installed |
| CN107331940B (en) * | 2017-05-27 | 2019-08-02 | 上海卫星工程研究所 | Adapt to the antisymmetry high rigidity mixed structure of spaceborne big front antenna H-type installation |
| CN113675574A (en) * | 2021-08-10 | 2021-11-19 | 燕山大学 | Bidirectional flat plate folding and unfolding unit and bidirectional flat plate folding and unfolding antenna mechanism |
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