CN105480437A - Solar wing layout structure of high-precision spacecraft - Google Patents
Solar wing layout structure of high-precision spacecraft Download PDFInfo
- Publication number
- CN105480437A CN105480437A CN201510860794.3A CN201510860794A CN105480437A CN 105480437 A CN105480437 A CN 105480437A CN 201510860794 A CN201510860794 A CN 201510860794A CN 105480437 A CN105480437 A CN 105480437A
- Authority
- CN
- China
- Prior art keywords
- solar wing
- platform
- spacecraft
- face
- side plate
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- 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
Landscapes
- 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 solar wing layout structure of a high-precision spacecraft. A top solar wing main plate and top solar wing side plates form a top solar wing which is fixedly installed on a platform top plate through bolts; an included angle between the top solar wing main plate and each top solar wing side plate is 120 degrees; the section of a spacecraft platform is in the shape of a regular hexagon, the top solar wing main plate is rectangular, each top solar wing side plate is triangular, and a bottom solar wing is installed at the bottom of a platform bottom plate; top solar wing honeycomb sandwich embedded parts are pre-embedded in the top solar wing main plate and the top solar wing side plates, and platform top plate honeycomb sandwich embedded parts are pre-embedded in the platform top plate; and a top solar wing pressing rod is installed among the top solar wing main plate, the top solar wing side plates and a payload. The solar wing layout structure disclosed by the invention can effectively improve the connection stiffness between the solar wing and the spacecraft platform so as to reduce the micro-vibration of the solar wing and improve the attitude stability of the spacecraft platform, and has the advantages of simple configuration, convenient connection and obvious effect.
Description
Technical field
The present invention relates to spacecraft field, specifically a kind of solar wing layout structure of high precision spacecraft, can be applied to the spacecraft had compared with lofty stance degree of stability.
Background technology
Along with China's spacecraft is towards the future development of high precision, high stability, its capacity weight carried requires more and more higher to the attitude stability of platform, need reduce the micro-vibration of spacecraft platform, to improve platform stance degree of stability as far as possible.
One of main source of the micro-vibration of spacecraft is solar wing flexible vibration.What current spacecraft platform adopted is substantially all the active sun wing, lower with the coupling stiffness of platform, will produce micro-vibration when spacecraft carries out Orbit Transformation or pose adjustment, thus reduces the attitude stability of platform.In addition, for reducing spacecraft weight as far as possible, solar wing adopts the light material as honeycomb sandwich panel and so on substantially, and this exacerbates micro-vibration further.Serious, when solar wing turnover sun shade, because Orbital heat flux change is violent, solar wing heat flutter may be caused, seriously reduce spacecraft platform stance degree of stability.Therefore, solar wing and platform coupling stiffness need be improved as far as possible, thus reduce the micro-vibration of solar wing, improve spacecraft platform stance degree of stability.
Summary of the invention
For defect of the prior art, the invention provides the solar wing layout structure of a kind of high precision spacecraft of knowing clearly, under the condition ensureing spacecraft energy resource supply balance under different gesture mode, improve the coupling stiffness of solar wing and spacecraft platform, thus improve platform stance degree of stability.
Object of the present invention is achieved through the following technical solutions: a kind of solar wing layout structure of high precision spacecraft, comprises end face solar wing mainboard, end face solar wing side plate, capacity weight, spacecraft platform, bottom surface solar wing, platform top, platform side plate, platform floor, end face solar wing compressor arm and bottom surface solar wing compressor arm; End face solar wing mainboard, end face solar wing side plate form end face solar wing, are mounted by means of bolts in platform top; Angle between end face solar wing mainboard and end face solar wing side plate is 120 degree; The cross section of spacecraft platform is regular hexagon, and end face solar wing mainboard is rectangle, and end face solar wing side plate is triangle, contributes to like this improving end face solar wing coupling stiffness, and bottom surface solar wing is arranged on bottom platform floor; In end face solar wing mainboard and end face solar wing side plate, be embedded with end face solar wing honeycomb interlayer embedded part, in platform top, be embedded with platform top honeycomb interlayer embedded part; End face solar wing compressor arm is arranged between end face solar wing mainboard, side plate and capacity weight; Bottom surface solar wing compressor arm is arranged between bottom surface solar wing and platform side plate; Contribute to like this strengthening solar wing coupling stiffness, improve spacecraft platform stance degree of stability further.
Wherein, capacity weight is installed on spacecraft top board.
Wherein, bottom surface solar wing is rectangle, has 3 pieces, compresses respectively and is arranged on platform side plate, be connected through the hinge between plate, launch afterwards in-orbit and lock when Spacecraft Launch.
Wherein, end face solar wing mainboard, end face solar wing side plate and platform top are honeycomb sandwich construction, contribute to like this alleviating structural weight.
Compared with prior art, the present invention has the following advantages:
Effectively can improve the coupling stiffness of solar wing and spacecraft platform, and then reduce solar wing micro-vibration, improve spacecraft platform stance degree of stability, have that configuration is simple, easy to connect, the advantage of Be very effective.
Accompanying drawing explanation
Fig. 1 is the Facad structure schematic diagram of the solar wing layout structure of a kind of high precision spacecraft of the embodiment of the present invention.
Fig. 2 is the construction profile schematic diagram of the solar wing layout structure of a kind of high precision spacecraft of the embodiment of the present invention.
Fig. 3 is the structural representation that in the solar wing layout structure of a kind of high precision spacecraft of embodiment, spacecraft end face solar wing is connected with platform top.
Detailed description of the invention
Below in conjunction with specific embodiment, the present invention is described in detail.Following examples will contribute to those skilled in the art and understand the present invention further, but not limit the present invention in any form.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, some distortion and improvement can also be made.These all belong to protection scope of the present invention.
As Figure 1-3, embodiments provide a kind of solar wing layout structure of high precision spacecraft, comprise end face solar wing mainboard 1, end face solar wing side plate 2, capacity weight 3, spacecraft platform 4, bottom surface solar wing 5, platform top 6, platform side plate 7, platform floor 8, end face solar wing compressor arm 9 and bottom surface solar wing compressor arm 10; End face solar wing mainboard 1, end face solar wing side plate 2 form end face solar wing, are fixedly mounted in platform top 6 by bolt 13; Angle between end face solar wing mainboard 1 and end face solar wing side plate 2 is 120 degree; The cross section of spacecraft platform 4 is regular hexagon, and end face solar wing mainboard 1 is rectangle, and end face solar wing side plate 2 is triangle, contributes to like this improving end face solar wing coupling stiffness, and bottom surface solar wing 5 is arranged on bottom platform floor 8; In end face solar wing mainboard 1 and end face solar wing side plate 2, be embedded with end face solar wing honeycomb interlayer embedded part 11, in platform top 6, be embedded with platform top honeycomb interlayer embedded part 12; End face solar wing compressor arm 9 is arranged between end face solar wing mainboard 1, side plate 2 and capacity weight 3; Bottom surface solar wing compressor arm 10 is arranged between bottom surface solar wing 5 and platform side plate 7; Contribute to like this strengthening solar wing coupling stiffness, improve spacecraft platform stance degree of stability further.
Capacity weight 3 is installed on spacecraft top board 6.
Bottom surface solar wing 5 is rectangle, has 3 pieces, compresses respectively and is arranged on platform side plate 7, be connected through the hinge between plate, launch afterwards in-orbit and lock when Spacecraft Launch.
End face solar wing mainboard 1, end face solar wing side plate 2 are honeycomb sandwich construction with platform top 6, contribute to like this alleviating structural weight.
Above specific embodiments of the invention are described.It is to be appreciated that the present invention is not limited to above-mentioned particular implementation, those skilled in the art can make various distortion or amendment within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (4)
1. the solar wing layout structure of a high precision spacecraft, it is characterized in that, comprise end face solar wing mainboard, end face solar wing side plate, capacity weight, spacecraft platform, bottom surface solar wing, platform top, platform side plate, platform floor, end face solar wing compressor arm and bottom surface solar wing compressor arm; End face solar wing mainboard, end face solar wing side plate form end face solar wing, are mounted by means of bolts in platform top; Angle between end face solar wing mainboard and end face solar wing side plate is 120 degree; The cross section of spacecraft platform is regular hexagon, and end face solar wing mainboard is rectangle, and end face solar wing side plate is triangle, and bottom surface solar wing is arranged on bottom platform floor; In end face solar wing mainboard and end face solar wing side plate, be embedded with end face solar wing honeycomb interlayer embedded part, in platform top, be embedded with platform top honeycomb interlayer embedded part; End face solar wing compressor arm is arranged between end face solar wing mainboard, side plate and capacity weight; Bottom surface solar wing compressor arm is arranged between bottom surface solar wing and platform side plate.
2. the solar wing layout structure of a kind of high precision spacecraft according to claim 1, it is characterized in that, capacity weight 3 is installed on spacecraft top board 6.
3. the solar wing layout structure of a kind of high precision spacecraft according to claim 1, is characterized in that, bottom surface solar wing is rectangle, have 3 pieces, compress respectively when Spacecraft Launch and be arranged on platform side plate, be connected through the hinge between plate, launch afterwards in-orbit and lock.
4. the solar wing layout structure of a kind of high precision spacecraft according to claim 1, is characterized in that, end face solar wing mainboard 1, end face 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 true CN105480437A (en) | 2016-04-13 |
| CN105480437B CN105480437B (en) | 2017-12-29 |
Family
ID=55667790
Family Applications (1)
| 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 |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105480437B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106777638A (en) * | 2016-12-08 | 2017-05-31 | 上海宇航系统工程研究所 | A kind of trim layout design method of eccentric spacecraft propulsion cabin zero |
| CN110703588A (en) * | 2019-11-15 | 2020-01-17 | 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 |
Citations (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 |
| 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 |
| US8757554B1 (en) * | 2009-09-09 | 2014-06-24 | MMA Design, LLC | Deployable and tracked solar array mechanism for nano-satellites |
| CN104044757A (en) * | 2014-05-30 | 2014-09-17 | 西北工业大学 | Automatic draw-pull type solar panel mechanism of miniature satellite |
| US20150008290A1 (en) * | 2013-07-08 | 2015-01-08 | Bigelow Aerospace LLC | Docking node transporter tug |
-
2015
- 2015-11-30 CN CN201510860794.3A patent/CN105480437B/en active Active
Patent Citations (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 |
| US20150008290A1 (en) * | 2013-07-08 | 2015-01-08 | Bigelow Aerospace LLC | Docking node transporter tug |
| CN104044757A (en) * | 2014-05-30 | 2014-09-17 | 西北工业大学 | Automatic draw-pull type solar panel mechanism of miniature satellite |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106777638A (en) * | 2016-12-08 | 2017-05-31 | 上海宇航系统工程研究所 | A kind of trim layout design method of eccentric spacecraft propulsion cabin zero |
| 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 |
| CN110703588A (en) * | 2019-11-15 | 2020-01-17 | 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105480437B (en) | 2017-12-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106907418B (en) | Phonon crystal negative poisson's ratio honeycomb vibration isolation anti-impact device | |
| CN103899004B (en) | One is energy consumer stage by stage | |
| CN109898681B (en) | High-bearing-capacity tensile energy-consumption shock insulation device | |
| CN102433969B (en) | Skin structure of composite big plate type square cabin and method for reducing thermal deformation of skin | |
| CN206298959U (en) | A kind of new steel structure slide energy-dissipating and shock-absorbing bean column node device | |
| CN105508142A (en) | Multi-girder structure large size wind power blade and production method thereof | |
| CN105480437A (en) | Solar wing layout structure of high-precision spacecraft | |
| CN102704615A (en) | Square cabin composite plate | |
| CN203806149U (en) | Hexagonal frame main bearing satellite structure | |
| CN202518458U (en) | Stiffened wallboard fatigue test transition section | |
| CN206678932U (en) | A kind of lever aids in buffering type automobile bumper | |
| CN206117572U (en) | Solar cell panel mounting bracket that multi -angle was adjusted | |
| CN205498542U (en) | Balanced bracing strut of disconnected | |
| CN208563560U (en) | The structural system of flatbed super high-rise building | |
| CN208039627U (en) | Lower pair of installing Cable-clamp device of pre- tensile state | |
| CN101787737B (en) | Structure node meeting spatial constraint requirements in different directions simultaneously | |
| CN102882008B (en) | Low-expansion mesh reflector using composite material connectors | |
| CN107769701A (en) | A kind of solar cell board mounting stand | |
| CN105156873B (en) | A kind of profile | |
| CN106739278A (en) | A kind of composite metal making sheet | |
| CN204263860U (en) | Bump rubber supporting structure and a kind of automobile after a kind of | |
| CN206004578U (en) | A kind of mounting bracket system | |
| CN208815708U (en) | A kind of lightweight wallboard | |
| CN204937468U (en) | A kind of reinforcement structure installing airframe antenna additional | |
| CN103573005A (en) | Composite material pole tower reinforcement device and reinforcement method thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |