CN112591143B - Transition plate for accommodating flexible spacecraft - Google Patents
Transition plate for accommodating flexible spacecraft Download PDFInfo
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- CN112591143B CN112591143B CN202011468249.7A CN202011468249A CN112591143B CN 112591143 B CN112591143 B CN 112591143B CN 202011468249 A CN202011468249 A CN 202011468249A CN 112591143 B CN112591143 B CN 112591143B
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- transition plate
- flexible spacecraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/645—Separators
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
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- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Details Of Indoor Wiring (AREA)
- Electric Cable Arrangement Between Relatively Moving Parts (AREA)
Abstract
The invention discloses a transition plate structure for accommodating a flexible spacecraft. In the prior art, a non-flexible spacecraft is basically adopted, the structure of the non-flexible spacecraft has certain rigidity, and displacement change cannot occur, and the volume of the non-flexible spacecraft device and a data transmission and power supply system device cannot change after the non-flexible spacecraft device and the data transmission and power supply system device are installed and fixed, so that the non-flexible spacecraft device and the data transmission and power supply system device are usually integrated in a box. However, because the flexible spacecraft is adopted, the flexible spacecraft needs to be stored and fixed after being installed due to the inherent flexibility of the spacecraft, and if the flexible spacecraft is fixed in a box by adopting the prior art, the flexible spacecraft cannot be unfolded.
Description
Technical Field
The invention belongs to the field of flexible spacecraft structure design, and particularly relates to a transition plate structure for flexible spacecraft storage.
Background
The flexible spacecraft is a novel spacecraft taking a flexible thin film structure as a theme, and has wide application prospects in space missions such as space debris derailment, space attack and defense, space detection and the like. The fixed installation and successful storage of the flexible spacecraft are the prerequisites for ensuring the smooth work of the spacecraft.
However, in the current aerospace field, a non-flexible spacecraft is mainly adopted, the volume of the non-flexible spacecraft device and a data transmission and power supply system device of the non-flexible spacecraft device can not change after the non-flexible spacecraft device and the data transmission and power supply system device are installed and fixed, and the non-flexible spacecraft structure has certain rigidity and can not change in displacement, so that the non-flexible spacecraft and the data transmission and power supply system device can be integrated in a box. On the contrary, the flexible spacecraft is required to be stored and fixed after being installed due to the inherent flexibility of the flexible spacecraft, the existing installation mode cannot meet the storage requirement of the flexible spacecraft, and therefore, the transition plate installation structure for storing the flexible spacecraft is designed, and the flexible spacecraft has important significance.
Disclosure of Invention
In view of this, the present invention aims to provide a transition plate structure for flexible spacecraft stowage. The connection between the data transmission and power supply system device and the flexible spacecraft device can be realized, and the flexible spacecraft device has the characteristics of simple structure, small volume and light weight.
A transition plate structure for accommodating a flexible spacecraft is characterized in that a data transmission and power supply system device and the flexible spacecraft device are respectively arranged on two sides of the transition plate; the transition plate is of a rectangular flat plate structure, and a circle of countersunk unthreaded holes are formed in the center of the transition plate and used for mounting a data transmission and power supply system device; a row of through holes are respectively formed in the two long edge directions of the transition plate and used for mounting the flexible spacecraft device; the transition plate is divided into an upper side and a lower side by taking the axis parallel to the long edge as an axis; the axis parallel to the short edge is taken as an axis to divide the transition plate into a left side and a right side; the rectangular mounting hole and the threading groove of the electric connector are respectively arranged on the upper side and the lower side of the transition plate; the two sets of separating switch devices are respectively arranged on the left side and the right side of the transition plate, and the two sets of separating switch devices and the threading groove belong to the same side; cable tying holes are also arranged on four edge lines of the transition plate.
Preferably, T-shaped holes are formed in the left side and the right side of the transition plate, and inverted cone holes are formed in four corners of the transition plate; a flexible spacecraft storage box is sleeved outside the flexible spacecraft device and fixedly connected with the T-shaped hole; taper pins on the flexible spacecraft storage box are matched with the inverted taper holes for positioning.
Preferably, the T-shaped holes are located on both end portions of an axis parallel to the long side of the transition plate.
Preferably, four threaded holes are uniformly distributed around the T-shaped hole and used for mounting the nut collecting box.
Preferably, the cable binding hole is a hole with a concave structure, namely, the cable binding hole is formed by two through holes which are communicated with each other.
Has the beneficial effects that:
1. in the prior art, a non-flexible spacecraft is basically adopted, the structure of the non-flexible spacecraft has certain rigidity, and displacement change cannot occur, and the volume of the non-flexible spacecraft device and a data transmission and power supply system device cannot change after the non-flexible spacecraft device and the data transmission and power supply system device are installed and fixed, so that the non-flexible spacecraft device and the data transmission and power supply system device can be integrated in a box. However, because the flexible spacecraft is adopted, the flexible spacecraft needs to be stored and fixed after being installed due to the inherent flexibility of the spacecraft, and if the flexible spacecraft is fixed in a box by adopting the prior art, the flexible spacecraft cannot be unfolded, so that the novel flat satellite structure of the transition plate has the advantages of low cost, high functional density and short development period;
2. the transition plate designed by the invention realizes the fixed installation between the flexible spacecraft and the data transmission and power supply system device, and ensures the smooth development of the on-orbit task of the flexible spacecraft. The device has the advantages of simple structure, small volume and light weight while providing more load mounting platforms.
3. In order to avoid secondary disasters, the nut collecting box is arranged on the transition plate and used for collecting separated nuts after the separation of the electric explosion bolts arranged on the transition plate.
Drawings
Fig. 1 is a schematic view of the distribution of transition plates suitable for flexible spacecraft stowage according to the present invention.
FIG. 2 is a schematic structural diagram of a transition plate suitable for accommodating a flexible spacecraft, according to the invention;
fig. 3 is a partial structural schematic diagram of a disconnecting switch device in a transition plate suitable for accommodating a flexible spacecraft, according to the invention.
Fig. 4 is a schematic view of a partial structure of a cable binding hole in a transition plate suitable for accommodating a flexible spacecraft, according to the present invention.
Wherein, 1-a rectangular wire slot; 2-inverted taper hole; 3-cable binding holes; 3-1-a groove structure; 4-disconnecting the switching device; 5-a threaded hole; 6-T shaped holes; 7-a threading slot; 8-a nut collection box; 9-countersunk unthreaded hole; 10-a data transmission and power system device; 11-a through hole; 20-a transition plate; 30-a flexible spacecraft device; 40-flexible spacecraft storage box.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and examples.
The invention provides a transition plate structure for accommodating a flexible spacecraft, as shown in fig. 1, a transition plate 20 is a flat plate structure with a certain thickness and is positioned at the middle connection part of a data transmission and power supply system device 10 and a flexible spacecraft device 30. As shown in fig. 2, the transition plate 20 is a rectangular plate with a certain thickness, wherein a circle of countersunk unthreaded holes 9 matching the size of the data transmission and power supply system device 10 is formed in the center of the transition plate 20, and the data transmission and power supply system device 10 is fixed in the center of the upper portion of the transition plate 20 through the matching of countersunk screws and the countersunk unthreaded holes 9. A row of through holes 11 are respectively arranged in the two long side directions of the transition plate 20 and used for installing the flexible spacecraft device 30 on the lower side of the transition plate 20 through screws; the transition plate 20 is divided into an upper side and a lower side by taking the axis parallel to the long edge as an axis; the rectangular mounting hole 1 and the threading groove 7 of the connector are respectively arranged at the upper side and the lower side of the transition plate; the rectangular mounting hole 1 of the electric connector is used for mounting the electric connector; the four edge lines of the transition plate 20 are also provided with cable binding holes 3, namely: on crossing cab apron 20's minor face direction, one side is equipped with one row of cable ligature hole 3, and the opposite side is equipped with two rows of cable ligature holes 3, is equipped with one row of cable ligature hole 3 in two long edge directions respectively, as shown in fig. 4, cable ligature hole 3 is the character cut in bas relief structure hole, and concrete structure is: the cable binding hole 3 is composed of two through holes, and the thickness of a plate spaced between the two through holes is smaller than that of the transition plate 20. The cable passes through the cable binding hole 3 to realize fixing. The reason why the cable binding holes 3 on the transition plate 20 are arranged is that: because the data transmission and power supply system device 10 is a cuboid structure, and the front, the back and one of the side surfaces thereof are all provided with electric connectors, a row of cable binding holes 3 are respectively arranged on the transition plate 20 corresponding to the front and the back of the data transmission and power supply system device 10 in the two long edge directions for wiring. A row of cable binding holes 3 are arranged in the short side direction of the transition plate 20 corresponding to the side surface of the electric connector on the data transmission and power supply system device 10 for wiring; the transition plate 20 is divided into a left side and a right side by taking the axis parallel to the short edge as an axis; two sets of separation switch devices 4 are symmetrically arranged on the left side and the right side of the transition plate 20, the two sets of separation switch devices 4 and the threading groove 7 belong to the same side, and in order to ensure that the separation switch devices 4 are electrified with the data transmission and power supply system device 10, a row of cable binding holes 3 are required to be arranged between the separation switch devices 4 and the rectangular mounting holes 1 and the threading groove 7 of the electric connector along the long edge and short edge directions of the transition plate. However, since the two long side directions are provided with the row of cable binding holes 3, in order to save space, only one row of cable binding holes 3 need to be respectively arranged in the short side direction.
Preferably, a spacecraft storage box 40 is also mounted on the transition plate 20. In this case, the transition plate is further provided with T-shaped holes 6 on both left and right sides in the above-described structure, and the T-shaped holes 6 are preferably located on both end portions of an axis parallel to the long side of the transition plate 20. Four corners of the transition plate 20 are respectively provided with inverted cone holes 2; the flexible spacecraft storage box 40 covers the flexible spacecraft device 30 and is fixedly locked through an electric explosion bolt arranged on the T-shaped hole 6; taper pins on the flexible spacecraft storage box 40 are matched with the inverted taper holes 2, so that the positioning accuracy is guaranteed, meanwhile, the transition plate 20 is convenient to separate from the flexible spacecraft storage box 40, and smooth release of the flexible spacecraft is guaranteed. In order to avoid secondary disasters caused by free flying of partial nuts after the electro-explosive bolts are separated, four threaded holes 5 are formed around each T-shaped hole 6 and used for mounting a nut collecting box 8 of the nut separating part of the electro-explosive bolts on the transition plate 20; the flexible spacecraft storage box 40 and the transition plate 20 jointly form a storage container of the flexible spacecraft.
As shown in fig. 3, when the flexible ball spacecraft is in the stowed state, the separation switch device 4 is always in the closed state. After the electric explosion bolt unblock, flexible spacecraft receiver 40 with cross cab apron 20 separation, flexible spacecraft receiver 40 no longer sticiss disconnect-switch device 4 this moment for disconnect-switch opens, data transmission and electrical power generating system device 10 begins work, flexible spacecraft device 30 through the cable realize with the connection between the data transmission and the electrical power generating system device 10, the connection cable passes through threading groove 7 and installs the electric connector on rectangular wire casing 1 and fix cross on cab apron 20, in order to avoid connecting the influence of cable free state to surrounding components down, cross and be equipped with several cable binding hole 3 on the cab apron 20, be in simultaneously the bottom of cable binding hole 3 is equipped with a groove structure 3-1, ensures cross cab apron 20 with flexible spacecraft receiver 40 closely laminates the container of constituteing flexible spacecraft jointly.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. A transition plate structure for accommodating a flexible spacecraft is characterized in that a data transmission and power supply system device (10) and a flexible spacecraft device (30) are respectively arranged on two surfaces of a transition plate (20); the transition plate (20) is of a rectangular flat plate structure, and a circle of countersunk unthreaded hole (9) is formed in the center of the transition plate (20) and used for mounting a data transmission and power supply system device (10); a row of through holes (11) are respectively formed in the two long edge directions of the transition plate (20) and used for mounting the flexible spacecraft device (30); the transition plate (20) is divided into an upper side and a lower side by taking the axis parallel to the long edge as an axis; the axis parallel to the short edge is taken as an axis to divide the transition plate into a left side and a right side; the rectangular mounting hole (1) and the threading groove (7) of the electric connector are respectively arranged at the upper side and the lower side of the transition plate; the two sets of separating switch devices (4) are respectively arranged on the left side and the right side of the transition plate, and the two sets of separating switch devices (4) and the threading groove (7) belong to the same side; cable binding holes (3) are also formed in the four side lines of the transition plate (20);
when the flexible ball spacecraft is in the storage state, the disconnecting switch device (4) is always in the closed state, and after the flexible spacecraft storage box is separated from the transition plate (20), the flexible spacecraft storage box does not press the disconnecting switch device (4) any more, so that the disconnecting switch is opened, and the data transmission and power supply system device (10) starts to work.
2. The transition plate structure of claim 1, wherein: t-shaped holes (6) are arranged on the left side and the right side of the transition plate (20), and inverted cone holes (2) are arranged at four corners of the transition plate; a flexible spacecraft storage box (40) is sleeved outside the flexible spacecraft device (30), and the flexible spacecraft storage box (40) is fixedly connected with the T-shaped hole (6); taper pins on the flexible spacecraft storage box (40) are matched with the inverted taper holes for positioning.
3. The transition plate structure of claim 2, characterized in that the T-shaped holes (6) are located on both ends of the axis parallel to the long sides of the transition plate (20).
4. The transition plate structure of claim 2, characterized in that four threaded holes (5) are uniformly distributed around the T-shaped hole (6) for mounting nut collection boxes (8).
5. The transition plate structure of claim 1, wherein the cable binding hole (3) is a female-shaped structure hole, i.e., is formed by two through holes communicating with each other.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011468249.7A CN112591143B (en) | 2020-12-14 | 2020-12-14 | Transition plate for accommodating flexible spacecraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011468249.7A CN112591143B (en) | 2020-12-14 | 2020-12-14 | Transition plate for accommodating flexible spacecraft |
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| Publication Number | Publication Date |
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| CN112591143A CN112591143A (en) | 2021-04-02 |
| CN112591143B true CN112591143B (en) | 2022-11-08 |
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| CN202011468249.7A Active CN112591143B (en) | 2020-12-14 | 2020-12-14 | Transition plate for accommodating flexible spacecraft |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103241393A (en) * | 2013-05-17 | 2013-08-14 | 哈尔滨工业大学 | Spacecraft space firm docking method |
| CN105119097A (en) * | 2015-09-21 | 2015-12-02 | 上海卫星工程研究所 | Spaceflight power bus fixing device |
| CN205770212U (en) * | 2016-05-25 | 2016-12-07 | 南京理工大学 | A kind of micro-nano satellite braking sail leaves the right or normal track device |
| EP3536617A1 (en) * | 2018-06-26 | 2019-09-11 | Airbus Defence and Space SAS | A flexible radiative fin for a spacecraft |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3544041A (en) * | 1967-11-07 | 1970-12-01 | Communications Satellite Corp | Deployable flexible solar array |
| JPH1059298A (en) * | 1996-08-23 | 1998-03-03 | Toshiba Corp | Flexible solar battery paddle |
| JP2000177699A (en) * | 1998-12-21 | 2000-06-27 | Mitsubishi Electric Corp | On-board satellite holding and releasing device |
| JP3944571B2 (en) * | 2002-10-17 | 2007-07-11 | 独立行政法人 宇宙航空研究開発機構 | Thin film unfolding structure, thin film unfolding method therefor, thin film unfolding unit and thin film unfolding system |
| DE102004063115B3 (en) * | 2004-12-23 | 2006-05-04 | Eads Space Transportation Gmbh | Spin-stabilized vessel dropping device for spacecraft, has central rope roll placed on ring which serves as holding ring, in which vessel is set in translatory motion when vessel, placed on holding ring, rotates along with holding ring |
| US9550584B1 (en) * | 2010-09-30 | 2017-01-24 | MMA Design, LLC | Deployable thin membrane apparatus |
| CN203337789U (en) * | 2013-07-04 | 2013-12-11 | 上海航天设备制造总厂 | Shut-off switch pressing device |
| CN105836162B (en) * | 2016-05-25 | 2018-03-09 | 南京理工大学 | A kind of micro-nano satellite braking sail leaves the right or normal track device |
| CN106184817A (en) * | 2016-07-08 | 2016-12-07 | 北京空间飞行器总体设计部 | Towards the spacecraft plane deployable supporting construction of load Two-Dimensional Quadratic and using method |
| CN106516172B (en) * | 2016-11-23 | 2019-06-07 | 上海卫星工程研究所 | A kind of device for the more star On-orbit releases of micro-nano satellite |
| CN106584438B (en) * | 2017-01-24 | 2022-11-15 | 重庆大学 | Spacecraft prestress conical thin-wall three-rod parallel space unfolding mechanism |
-
2020
- 2020-12-14 CN CN202011468249.7A patent/CN112591143B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103241393A (en) * | 2013-05-17 | 2013-08-14 | 哈尔滨工业大学 | Spacecraft space firm docking method |
| CN105119097A (en) * | 2015-09-21 | 2015-12-02 | 上海卫星工程研究所 | Spaceflight power bus fixing device |
| CN205770212U (en) * | 2016-05-25 | 2016-12-07 | 南京理工大学 | A kind of micro-nano satellite braking sail leaves the right or normal track device |
| EP3536617A1 (en) * | 2018-06-26 | 2019-09-11 | Airbus Defence and Space SAS | A flexible radiative fin for a spacecraft |
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| CN112591143A (en) | 2021-04-02 |
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