CN105480437B - A kind of solar wing layout structure of high-precision spacecraft - Google Patents
A kind of solar wing layout structure of high-precision spacecraft Download PDFInfo
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- CN105480437B CN105480437B CN201510860794.3A CN201510860794A CN105480437B CN 105480437 B CN105480437 B CN 105480437B CN 201510860794 A CN201510860794 A CN 201510860794A CN 105480437 B CN105480437 B CN 105480437B
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- solar wing
- top surface
- surface solar
- platform
- side plate
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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
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
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- Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Photovoltaic Devices (AREA)
Abstract
The invention discloses a kind of solar wing layout structure of high-precision spacecraft, top surface solar wing mainboard, top surface solar wing side plate form top surface solar wing, are mounted by means of bolts in platform top；Angle between top surface solar wing mainboard and top surface solar wing side plate is 120 degree；The section of spacecraft platform is regular hexagon, and top surface solar wing mainboard is rectangle, and top surface solar wing side plate is triangle, and bottom surface solar wing is arranged on platform floor bottom；Top surface solar wing honeycomb interlayer embedded part is embedded with top surface solar wing mainboard and top surface solar wing side plate, platform top honeycomb interlayer embedded part is embedded with platform top；Top surface solar wing compressor arm is arranged between top surface solar wing mainboard, side plate and payload.The present invention can effectively improve the coupling stiffness of solar wing and spacecraft platform, and then reduce solar wing micro-vibration, improve spacecraft platform stance stability, have the advantages of simple configuration, easy to connect, significant effect.
Description
Technical field
The present invention relates to spacecraft field, specifically a kind of solar wing layout structure of high-precision spacecraft, can apply
To the spacecraft with compared with lofty stance stability.
Background technology
As China's spacecraft develops towards the direction of high accuracy, high stability, the payload that it is carried is to platform
Attitude stability requires more and more higher, need to reduce spacecraft platform micro-vibration as far as possible, to improve platform stance stability.
One of main source of spacecraft micro-vibration is solar wing flexible vibration.Current spacecraft platform use substantially all
It is the active sun wing, it is relatively low with the coupling stiffness of platform, it will produce micro- shake when spacecraft carries out Orbit Transformation or pose adjustment
It is dynamic, so as to reduce the attitude stability of platform.In addition, to reduce spacecraft weight as far as possible, solar wing uses honeycomb such as to press from both sides substantially
The light material of laminate etc, this has been further exacerbated by micro-vibration.Serious, when solar wing enters sunny shade, due to outer
Changes of heat flux is violent, may result in solar wing heat flutter, serious to reduce spacecraft platform stance stability.Therefore, need to try one's best
Solar wing and platform coupling stiffness are improved, so as to reduce solar wing micro-vibration, improves spacecraft platform stance stability.
The content of the invention
For in the prior art the defects of, the invention provides a kind of solar wing layout structure of high-precision spacecraft,
The connection that solar wing and spacecraft platform are improved under conditions of spacecraft energy resource supply balance under ensureing different gesture modes is firm
Degree, so as to improve platform stance stability.
The purpose of the present invention is achieved through the following technical solutions：A kind of solar wing layout structure of high-precision spacecraft,
Including top surface solar wing mainboard, top surface solar wing side plate, payload, spacecraft platform, bottom surface solar wing, platform top, flat
Platform side plate, platform floor, top surface solar wing compressor arm and bottom surface solar wing compressor arm；Top surface solar wing mainboard, top surface solar wing
Side plate forms top surface solar wing, is mounted by means of bolts in platform top；Top surface solar wing mainboard and top surface sun flank
Angle between plate is 120 degree；The section of spacecraft platform is regular hexagon, and top surface solar wing mainboard is rectangle, the top surface sun
Flank plate is triangle, is so favorably improved top surface solar wing coupling stiffness, and bottom surface solar wing is arranged on platform floor bottom；
Top surface solar wing honeycomb interlayer embedded part is embedded with top surface solar wing mainboard and top surface solar wing side plate, it is pre- in platform top
It is embedded with platform top honeycomb interlayer embedded part；Top surface solar wing compressor arm is arranged on top surface solar wing mainboard, side plate and payload
Between；Bottom surface solar wing compressor arm is arranged between bottom surface solar wing and platform side plate；So contribute to strengthen solar wing connection
Rigidity, further improve spacecraft platform stance stability.
Wherein, payload is installed on spacecraft top plate.
Wherein, bottom surface solar wing is rectangle, shares 3 pieces, is compressed respectively on platform side plate in Spacecraft Launch,
It is connected through the hinge between plate, deploys and lock after in-orbit.
Wherein, top surface solar wing mainboard, top surface solar wing side plate and platform top are honeycomb sandwich construction, are so helped
In mitigation construction weight.
Compared with prior art, the present invention has advantages below：
The coupling stiffness of solar wing and spacecraft platform can be effectively improved, and then reduces solar wing micro-vibration, improves space flight
Device platform stance stability, there is the advantages of simple configuration, easy to connect, significant effect.
Brief description of the drawings
Fig. 1 is a kind of positive structure schematic of the solar wing layout structure of high-precision spacecraft of the embodiment of the present invention.
Fig. 2 is a kind of side structure schematic diagram of the solar wing layout structure of high-precision spacecraft of the embodiment of the present invention.
Fig. 3 is spacecraft top surface solar wing and deck roof in a kind of solar wing layout structure of high-precision spacecraft of embodiment
The structural representation of plate connection.
Embodiment
With reference to specific embodiment, the present invention is described in detail.Following examples will be helpful to the technology of this area
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill to this area
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection domain.
As Figure 1-3, the embodiments of the invention provide a kind of solar wing layout structure of high-precision spacecraft, including top
It is face solar wing mainboard 1, top surface solar wing side plate 2, payload 3, spacecraft platform 4, bottom surface solar wing 5, platform top 6, flat
Platform side plate 7, platform floor 8, top surface solar wing compressor arm 9 and bottom surface solar wing compressor arm 10；Top surface solar wing mainboard 1, top surface
Solar wing side plate 2 forms top surface solar wing, is fixedly mounted on by bolt 13 in platform top 6；Top surface solar wing mainboard 1 and top
Angle between face solar wing side plate 2 is 120 degree；The section of spacecraft platform 4 is regular hexagon, and top surface solar wing mainboard 1 is
Rectangle, top surface solar wing side plate 2 are triangle, are so favorably improved top surface solar wing coupling stiffness, and bottom surface solar wing 5 is installed
In the bottom of platform floor 8；Top surface solar wing honeycomb interlayer is embedded with top surface solar wing mainboard 1 and top surface solar wing side plate 2
Embedded part 11, platform top honeycomb interlayer embedded part 12 is embedded with platform top 6；Top surface solar wing compressor arm 9 is arranged on top surface
Between solar wing mainboard 1, side plate 2 and payload 3；Bottom surface solar wing compressor arm 10 is arranged on bottom surface solar wing 5 and platform side
Between plate 7；So contribute to strengthen solar wing coupling stiffness, further improve spacecraft platform stance stability.
Payload 3 is installed on spacecraft top plate 6.
Bottom surface solar wing 5 is rectangle, shares 3 pieces, is compressed respectively on platform side plate 7 in Spacecraft Launch, plate
Between be connected through the hinge, deploy and lock after in-orbit.
Top surface solar wing mainboard 1, top surface solar wing side plate 2 and platform top 6 are honeycomb sandwich construction, are so contributed to
Mitigate construction weight.
The specific embodiment of the present invention is described above.It is to be appreciated that the invention is not limited in above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring the substantive content of the present invention.
Claims (4)
1. a kind of solar wing layout structure of high-precision spacecraft, it is characterised in that including top surface solar wing mainboard, the top surface sun
Flank plate, payload, spacecraft platform, bottom surface solar wing, platform top, platform side plate, platform floor, top surface solar wing pressure
Tight bar and bottom surface solar wing compressor arm；Top surface solar wing mainboard, top surface solar wing side plate form top surface solar wing, are consolidated by bolt
Dingan County is in platform top；Angle between top surface solar wing mainboard and top surface solar wing side plate is 120 degree；Spacecraft platform
Section be regular hexagon, top surface solar wing mainboard is rectangle, and top surface solar wing side plate is triangle, and bottom surface solar wing is arranged on
Platform floor bottom；Top surface solar wing honeycomb interlayer embedded part is embedded with top surface solar wing mainboard and top surface solar wing side plate,
Platform top honeycomb interlayer embedded part is embedded with platform top；Top surface solar wing compressor arm be arranged on top surface solar wing mainboard,
Between side plate and payload；Bottom surface solar wing compressor arm is arranged between bottom surface solar wing and platform side plate.
A kind of 2. solar wing layout structure of high-precision spacecraft according to claim 1, it is characterised in that payload
(3) it is installed in platform top (6).
A kind of 3. solar wing layout structure of high-precision spacecraft according to claim 1, it is characterised in that the bottom surface sun
The wing is rectangle, shares 3 pieces, compresses on platform side plate in Spacecraft Launch, is connected through the hinge between plate respectively, in-orbit
After deploy and lock.
A kind of 4. solar wing layout structure of high-precision spacecraft according to claim 1, it is characterised in that the top surface sun
Wing mainboard (1), top surface solar wing side plate and platform top are honeycomb sandwich construction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510860794.3A CN105480437B (en) | 2015-11-30 | 2015-11-30 | A kind of solar wing layout structure of high-precision spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510860794.3A CN105480437B (en) | 2015-11-30 | 2015-11-30 | A kind of solar wing layout structure of high-precision spacecraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105480437A CN105480437A (en) | 2016-04-13 |
| CN105480437B true CN105480437B (en) | 2017-12-29 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510860794.3A Active CN105480437B (en) | 2015-11-30 | 2015-11-30 | A kind of solar wing layout structure of high-precision spacecraft |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106777638B (en) * | 2016-12-08 | 2020-06-26 | 上海宇航系统工程研究所 | Zero-trim layout design method for propulsion cabin of eccentric spacecraft |
| CN110703588B (en) * | 2019-11-15 | 2022-09-13 | 上海航天控制技术研究所 | Space station solar wing reliable redundancy control system and method based on multi-instruction input |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6888513B1 (en) * | 2001-10-18 | 2005-05-03 | Raytheon Company | Method and apparatus for storage and deployment of folded panel structures |
| US8757554B1 (en) * | 2009-09-09 | 2014-06-24 | MMA Design, LLC | Deployable and tracked solar array mechanism for nano-satellites |
| CN102372092A (en) * | 2010-08-17 | 2012-03-14 | 上海卫星工程研究所 | Configuration for low-earth-orbit remote sensing satellite and mounting method thereof |
| US9567116B2 (en) * | 2013-07-08 | 2017-02-14 | Bigelow Aerospace | Docking node transporter tug |
| CN104044757B (en) * | 2014-05-30 | 2016-06-29 | 西北工业大学 | A kind of automatic drawing and pulling type solar panels mechanism of microsatellite |
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| Publication number | Publication date |
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| CN105480437A (en) | 2016-04-13 |
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