CN108438253A - A kind of microsatellite structure suitable for optics load - Google Patents
A kind of microsatellite structure suitable for optics load Download PDFInfo
- Publication number
- CN108438253A CN108438253A CN201810184540.8A CN201810184540A CN108438253A CN 108438253 A CN108438253 A CN 108438253A CN 201810184540 A CN201810184540 A CN 201810184540A CN 108438253 A CN108438253 A CN 108438253A
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- China
- Prior art keywords
- plate
- bottom plate
- load
- holder
- microsatellite
- 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.)
- Pending
Links
- 108091092878 Microsatellite Proteins 0.000 title claims abstract description 34
- 210000001503 joint Anatomy 0.000 claims abstract description 18
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 7
- 240000002853 Nelumbo nucifera Species 0.000 claims description 4
- 235000006508 Nelumbo nucifera Nutrition 0.000 claims description 4
- 235000006510 Nelumbo pentapetala Nutrition 0.000 claims description 4
- 239000007769 metal material Substances 0.000 claims description 4
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 3
- 230000001413 cellular effect Effects 0.000 claims description 3
- 230000008878 coupling Effects 0.000 claims description 3
- 238000010168 coupling process Methods 0.000 claims description 3
- 238000005859 coupling reaction Methods 0.000 claims description 3
- 239000003381 stabilizer Substances 0.000 claims description 3
- 238000003032 molecular docking Methods 0.000 claims 1
- 230000007547 defect Effects 0.000 abstract description 2
- 208000020442 loss of weight Diseases 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
- 229910052751 metal Inorganic materials 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000010276 construction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
Classifications
-
- 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
-
- 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
- B64G1/223—Modular spacecraft systems
Abstract
The invention discloses a kind of microsatellite structures suitable for optics load, including bottom plate, middle plate, top plate, side plate, holder, bulkhead, bottom plate to reinforce embedded part, butt joint ring and load；Bottom plate, middle plate, top plate and side plate are all made of rectangular plate-like structure, and the pre-buried bottom plate for reinforced structure reinforces embedded part in bottom plate, and plate upper surface installs the holder for being used to support load, and butt joint ring is installed in bottom plate lower surface；The through-hole for wearing load is equipped on middle plate and top plate；Bottom plate, middle plate and top plate, which are mutually parallel, and edge is vertical with four blocks of side plates is connected, and forms a boxlike configuration；Several bulkheads for reinforcing rigidity are installed between bottom plate and middle plate.The present invention reinforces the cooperation of embedded part, butt joint ring and load by bottom plate, middle plate, top plate, side plate, holder, bulkhead, bottom plate, shorten the Path of Force Transfer of optics load, the topology layout for optimizing whole star compensates for traditional microsatellite truss structure part collection and neutralizes the larger defect of quality.
Description
Technical field
The present invention relates to a kind of microsatellite structures suitable for optics load, are particularly suitable for 50~100kg optics load
The microsatellite of lotus belongs to microsatellite load fitting configuration technical field.
Background technology
Microsatellite structure compares conventional satellite, has the characteristics that space is small, equipment is more, density is big, integrated level is high, optics
Load microsatellite is due to the space requirement of light path design, density of equipment bigger in star.Optics load and whole star weight ratio simultaneously
It is worth larger, load is more concentrated.
Currently, using metal truss formula structure microsatellite (such as CubeSat etc.), providing equipment using metallic plate pacifies
Dress face carries out hollow out loss of weight in suitable position, forms single truss, several truss structures are grouped together to form whole star metal purlin
Rack and panel construction.It is this design be utilized it is relatively simple in metal truss structure design, and metal material be isotropic material, no
The advantages that local buckling easily occurs.But this structure has equipment mounting surface few simultaneously, the larger problem of density of material.In addition,
When some structure mounting surface number of devices is more, it should consider equipment installation interface and radiating surface requirement, consider loss of weight again
Hollow design causes design difficulty to increase, and also can further increase architecture quality and design complexities.
Invention content
Present invention solves the technical problem that being：Overcome the deficiencies in the prior art, the present invention provides one kind being suitable for optics
The microsatellite structure of load reinforces embedded part, butt joint ring and load by bottom plate, middle plate, top plate, side plate, holder, bulkhead, bottom plate
The cooperation of lotus shortens the Path of Force Transfer of optics load, optimizes the topology layout of whole star, compensates for traditional microsatellite truss
Constitutional detail collection neutralizes the larger defect of quality.
Technical solution of the invention is：
A kind of microsatellite structure suitable for optics load, including bottom plate, middle plate, top plate, side plate, holder, bulkhead, bottom
Plate reinforces embedded part, butt joint ring and load；Bottom plate, middle plate, top plate and side plate are all made of rectangular plate-like structure, pre-buried in bottom plate to be used for
The bottom plate of reinforced structure reinforces embedded part, and plate upper surface installs the holder for being used to support load, and butt joint ring is installed in bottom plate lower surface；
The through-hole for wearing load is equipped on middle plate and top plate；Bottom plate, middle plate and top plate be mutually parallel and edge with four pieces of sides
Plate is vertically connected, and forms a boxlike configuration；Several bulkheads for reinforcing rigidity are installed between bottom plate and middle plate.
A kind of above-mentioned microsatellite structure suitable for optics load, the bottom plate, middle plate, top plate and side plate are equal
For cellular board, holder, bulkhead, bottom plate reinforce embedded part and butt joint ring is all made of metal material.
A kind of above-mentioned microsatellite structure suitable for optics load, the bottom plate, middle plate and top plate are and side
Plate is threadedly coupled, and the center of middle plate and top plate is equipped with the through-hole for wearing load.
A kind of above-mentioned microsatellite structure suitable for optics load, the holder is titanium alloy frame, holder
It is connect with base thread；Cradle top surface is threadedly coupled with middle plate, and mid-stent is equipped with the platform for being equipped with load, side face
Several lightening holes are laid with, cradle top surface is equipped with the screw hole for mounting screw.
A kind of above-mentioned microsatellite structure suitable for optics load, the cradle top surface, which is equipped with, to be used for and middle plate
The pin hole of equipped positioning.
A kind of above-mentioned microsatellite structure suitable for optics load, the bulkhead is rectangular frame, bulkhead edge
Diagonal line is equipped with reinforcing rib, and bulkhead end face is equipped with for equipped stabilizer blade.
A kind of above-mentioned microsatellite structure suitable for optics load, the bulkhead be laid in bottom plate and middle plate it
Between, the coupling stiffness for improving bottom plate and middle plate.
A kind of above-mentioned microsatellite structure suitable for optics load, the bottom plate reinforces embedded part and uses cross beam
Structure；Bottom plate is reinforced in eight ends of embedded part, and each two end is threadedly coupled with one block of side plate.
A kind of above-mentioned microsatellite structure suitable for optics load, the holder and butt joint ring pass through bottom plate
Reinforce embedded part to connect with base thread.
A kind of above-mentioned microsatellite structure suitable for optics load, the load is cylindric optics load,
The weight range of load is set as 10~20kg.
Compared with the prior art, the invention has the advantages that：
【1】The present invention uses honeycomb plate structure, and equipment arrangement is more free, is not influenced by equipment loss of weight hollow design,
It is designed convenient for Zheng Xing configuration layouts；And be designed centered on optics load, remaining equipment is arranged around it, can be with
Optics load is set to be located at whole star center, mechanical condition is preferable.
【2】The present invention reinforces embedded part by holder, bulkhead and cross beam type bottom plate and bears concentrfated load, and directly with dock
Ring connects, and shortens Path of Force Transfer to the greatest extent, reduces the influence of concentrfated load.
【3】Compact overall structure of the present invention is suitable for various working environments, and service life is relatively long, in complex working condition
Under still can good operation, have the characteristics that applied widely, have good market application prospect.
Description of the drawings
Attached drawing is used to provide further understanding of the present invention, and is constituted part of this application, the embodiment of the present invention and
It illustrates, for explaining the present invention, not constituting improper limitations of the present invention.In the accompanying drawings：
Fig. 1 is the structural diagram of the present invention
Fig. 2 is the structure chart of bottom plate, holder and bulkhead
Fig. 3 is the application schematic diagram of the present invention
Wherein：1 bottom plate；Plate in 2；3 top plates；4 side plates；5 holders；6 bulkheads；7 bottom plates reinforce embedded part；8 butt joint rings；9 load；
Specific implementation mode
To make the solution of the present invention more be illustrated, explanation and specific embodiment are made the present invention further below in conjunction with the accompanying drawings
Description：
As shown in Figures 1 to 3, a kind of microsatellite structure suitable for optics load, including bottom plate 1, middle plate 2, top plate 3,
Side plate 4, holder 5, bulkhead 6, bottom plate reinforce embedded part 7, butt joint ring 8 and load 9；Bottom plate 1, middle plate 2, top plate 3 and side plate 4 are all made of
Rectangular plate-like structure, the pre-buried bottom plate for reinforced structure reinforces embedded part 7 in bottom plate 1, and the installation of 1 upper surface of bottom plate is used to support load
Butt joint ring 8 is installed in the holder 5 of lotus 9,1 lower surface of bottom plate；The through-hole for wearing load 9 is equipped on middle plate 2 and top plate 3；Bottom
Plate 1, middle plate 2 and top plate 3, which are mutually parallel, and edge is vertical with four blocks of side plates 4 is connected, and forms a boxlike configuration；Bottom plate 1 with
Several bulkheads 6 for reinforcing rigidity are installed between middle plate 2.
Preferably, bottom plate 1, middle plate 2, top plate 3 and side plate 4 are cellular board, and holder 5, bulkhead 6, bottom plate reinforce 7 and of embedded part
Butt joint ring 8 is all made of metal material.
Preferably, bottom plate 1, middle plate 2 and top plate 3 are threadedly coupled with side plate 4, and the center of middle plate 2 and top plate 3 is all provided with useful
In the through-hole for wearing load 9.
Preferably, holder 5 is titanium alloy frame, and holder 5 is threadedly coupled with bottom plate 1；5 top surface of holder connects with 2 screw thread of middle plate
It connects, 5 middle part of holder is equipped with the platform for being equipped with load 9, and 5 side of holder is laid with several lightening holes, and 5 top surface of holder is equipped with
Screw hole for mounting screw.
Preferably, 5 top surface of holder is equipped with for the pin hole with the equipped positioning of middle plate 2.
Preferably, bulkhead 6 is rectangular frame, and bulkhead 6 is diagonally equipped with reinforcing rib, and 6 end face of bulkhead is equipped with for being equipped with
Stabilizer blade.
Preferably, bulkhead 6 is laid between bottom plate 1 and middle plate 2, the coupling stiffness for improving bottom plate 1 and middle plate 2.
Preferably, bottom plate reinforces embedded part 7 using nine-squares beam structure；Bottom plate is reinforced in eight ends of embedded part 7, each two end
Head is threadedly coupled with one block of side plate 4.
Preferably, holder 5 and butt joint ring 8 are threadedly coupled by bottom plate reinforcement embedded part 7 with bottom plate 1, and holder 5, bottom plate add
Strong embedded part 7, butt joint ring 8 form stable force transferring structure together with bottom plate 1.
Preferably, load 9 is cylindric optics load, and the weight range of load 9 is set as 10~20kg.
The present invention operation principle be：
When microsatellite is in launching phase or working condition, stress that load 9 is born by holder 5, bottom plate 1, every
Frame 6 and bottom plate reinforce the cooperation of embedded part 7, are transferred directly to butt joint ring 9, you can effectively reduce the influence of concentrfated load 9.
The content not being described in detail in description of the invention is known to the skilled person technology.
Claims (10)
1. a kind of microsatellite structure suitable for optics load, it is characterised in that：Including bottom plate (1), middle plate (2), top plate
(3), side plate (4), holder (5), bulkhead (6), bottom plate reinforce embedded part (7), butt joint ring (8) and load (9)；Bottom plate (1), middle plate
(2), top plate (3) and side plate (4) are all made of rectangular plate-like structure, and the pre-buried bottom plate for reinforced structure is reinforced burying in bottom plate (1)
The holder (5) for being used to support load (9) is installed in part (7), bottom plate (1) upper surface, and butt joint ring (8) is installed in bottom plate (1) lower surface；In
The through-hole for wearing load (9) is equipped on plate (2) and top plate (3)；Bottom plate (1), middle plate (2) and top plate (3) are mutually parallel
And edge is vertical with four blocks side plate (4) connected, forms a boxlike configuration；It is equipped between bottom plate (1) and middle plate (2) several
A bulkhead (6) for reinforcing rigidity.
2. a kind of microsatellite structure suitable for optics load according to claim 1, it is characterised in that：The bottom plate
(1), middle plate (2), top plate (3) and side plate (4) are cellular board, and holder (5), bulkhead (6), bottom plate reinforce embedded part (7) and docking
Ring (8) is all made of metal material.
3. a kind of microsatellite structure suitable for optics load according to claim 2, it is characterised in that：The bottom plate
(1), middle plate (2) and top plate (3) are threadedly coupled with side plate (4), and the center of middle plate (2) and top plate (3) is equipped with for wearing
The through-hole of load (9).
4. a kind of microsatellite structure suitable for optics load according to claim 1, it is characterised in that：The holder
(5) it is titanium alloy frame, holder (5) is threadedly coupled with bottom plate (1)；Holder (5) top surface is threadedly coupled with middle plate (2), holder (5)
Middle part is equipped with the platform for being equipped with load (9), and holder (5) side is laid with several lightening holes, and holder (5) top surface, which is equipped with, to be used
In the screw hole of mounting screw.
5. a kind of microsatellite structure suitable for optics load according to claim 4, it is characterised in that：The holder
(5) top surface is equipped with for the pin hole with the equipped positioning of middle plate (2).
6. a kind of microsatellite structure suitable for optics load according to claim 1, it is characterised in that：The bulkhead
(6) it is rectangular frame, diagonally equipped with reinforcing rib, bulkhead (6) end face is equipped with for equipped stabilizer blade bulkhead (6).
7. a kind of microsatellite structure suitable for optics load according to claim 6, it is characterised in that：The bulkhead
(6) it is laid between bottom plate (1) and middle plate (2), the coupling stiffness for improving bottom plate (1) and middle plate (2).
8. a kind of microsatellite structure suitable for optics load according to claim 1, it is characterised in that：The bottom plate
Reinforce embedded part (7) and uses nine-squares beam structure；Bottom plate is reinforced in eight ends of embedded part (7), each two end and one piece of side plate (4)
It is threadedly coupled.
9. a kind of microsatellite structure suitable for optics load according to claim 1, it is characterised in that：The holder
(5) embedded part (7) is reinforced by bottom plate and is threadedly coupled with bottom plate (1) with butt joint ring (8).
10. a kind of microsatellite structure suitable for optics load according to claim 1, it is characterised in that：The load
Lotus (9) is cylindric optics load, and the weight range of load (9) is set as 10~20kg.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810184540.8A CN108438253A (en) | 2018-03-06 | 2018-03-06 | A kind of microsatellite structure suitable for optics load |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810184540.8A CN108438253A (en) | 2018-03-06 | 2018-03-06 | A kind of microsatellite structure suitable for optics load |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108438253A true CN108438253A (en) | 2018-08-24 |
Family
ID=63193374
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810184540.8A Pending CN108438253A (en) | 2018-03-06 | 2018-03-06 | A kind of microsatellite structure suitable for optics load |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108438253A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109229422A (en) * | 2018-11-14 | 2019-01-18 | 长光卫星技术有限公司 | A kind of deck board formula satellite configuration and its assembly method |
| CN111152938A (en) * | 2020-04-08 | 2020-05-15 | 北京前沿探索深空科技有限公司 | Satellite structure |
| CN111703592A (en) * | 2020-05-27 | 2020-09-25 | 长光卫星技术有限公司 | Large commercial remote sensing satellite platform configuration and assembly method |
| CN111806726A (en) * | 2019-05-23 | 2020-10-23 | 上海微小卫星工程中心 | Main framework of small high-orbit satellite common platform |
| CN112550761A (en) * | 2020-12-21 | 2021-03-26 | 中国人民解放军国防科技大学 | Integrated truss type minisatellite main bearing structure and design optimization method |
| CN113562195A (en) * | 2021-08-17 | 2021-10-29 | 北京微纳星空科技有限公司 | Box board frame combined satellite configuration |
| CN114408214A (en) * | 2021-12-23 | 2022-04-29 | 航天东方红卫星有限公司 | High-bearing earth observation small satellite configuration suitable for multi-optical large-mass load |
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| CN102009746A (en) * | 2010-11-08 | 2011-04-13 | 航天东方红卫星有限公司 | Octagonal battery-equipped array upright post micro satellite configuration |
| US8531524B2 (en) * | 2010-12-15 | 2013-09-10 | Skybox Imaging, Inc. | Integrated antenna system for imaging microsatellites |
| CN104443431A (en) * | 2014-10-23 | 2015-03-25 | 上海卫星工程研究所 | Triangular satellite configuration and system and assembly method |
| CN105235916A (en) * | 2015-10-27 | 2016-01-13 | 上海微小卫星工程中心 | Integration satellite compact in layout |
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2018
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| US5755406A (en) * | 1995-12-22 | 1998-05-26 | Hughes Electronics | Modular, independent subsystem design satellite bus and variable communication payload configurations and missions |
| CN102009746A (en) * | 2010-11-08 | 2011-04-13 | 航天东方红卫星有限公司 | Octagonal battery-equipped array upright post micro satellite configuration |
| US8531524B2 (en) * | 2010-12-15 | 2013-09-10 | Skybox Imaging, Inc. | Integrated antenna system for imaging microsatellites |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109229422A (en) * | 2018-11-14 | 2019-01-18 | 长光卫星技术有限公司 | A kind of deck board formula satellite configuration and its assembly method |
| CN111806726A (en) * | 2019-05-23 | 2020-10-23 | 上海微小卫星工程中心 | Main framework of small high-orbit satellite common platform |
| CN111806726B (en) * | 2019-05-23 | 2022-03-15 | 上海微小卫星工程中心 | Main framework of small high-orbit satellite common platform |
| CN111152938A (en) * | 2020-04-08 | 2020-05-15 | 北京前沿探索深空科技有限公司 | Satellite structure |
| CN111152938B (en) * | 2020-04-08 | 2020-08-07 | 北京前沿探索深空科技有限公司 | Satellite structure |
| CN111703592A (en) * | 2020-05-27 | 2020-09-25 | 长光卫星技术有限公司 | Large commercial remote sensing satellite platform configuration and assembly method |
| CN111703592B (en) * | 2020-05-27 | 2022-01-07 | 长光卫星技术有限公司 | Large commercial remote sensing satellite platform configuration and assembly method |
| CN112550761A (en) * | 2020-12-21 | 2021-03-26 | 中国人民解放军国防科技大学 | Integrated truss type minisatellite main bearing structure and design optimization method |
| CN113562195A (en) * | 2021-08-17 | 2021-10-29 | 北京微纳星空科技有限公司 | Box board frame combined satellite configuration |
| CN114408214A (en) * | 2021-12-23 | 2022-04-29 | 航天东方红卫星有限公司 | High-bearing earth observation small satellite configuration suitable for multi-optical large-mass load |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180824 |
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| RJ01 | Rejection of invention patent application after publication |