CN105083590B - Multiunit cubesat main load-bearing structure - Google Patents
Multiunit cubesat main load-bearing structure Download PDFInfo
- Publication number
- CN105083590B CN105083590B CN201510557584.7A CN201510557584A CN105083590B CN 105083590 B CN105083590 B CN 105083590B CN 201510557584 A CN201510557584 A CN 201510557584A CN 105083590 B CN105083590 B CN 105083590B
- Authority
- CN
- China
- Prior art keywords
- main frame
- middle skeleton
- end cap
- main
- cube star
- 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.)
- Active
Links
Landscapes
- Photovoltaic Devices (AREA)
Abstract
The invention discloses a multiunit cubesat main load-bearing structure. A main frame is of a rectangular frame structure and provided with rib plates matched with the shape of the long-edge section of the main frame in the direction of the long edges. End covers are arranged at the two ends of the main frame in the direction of the long edges, and the profile of the end covers is matched with the shape enclosed by the main frame. A middle skeleton is arranged at the positions corresponding to the rib plates in the main frame, and the profile of the middle skeleton is matched with the shape enclosed by the rib plates. Four threaded rods are arranged in the main frame in the direction of the long edges, penetrate through the middle skeleton and are fixed to the end covers at the two ends of the main frame. According to the multiunit cubic-star main load-bearing structure, due to the fact that the main frame is of an integrated structure, parallelism among guide rails can be guaranteed, the main load-bearing structure cannot be clamped by a launcher in the launching process, and successful launch is guaranteed; in the cubesat assembling process, internal PCBs can be assembled with the end covers, the middle skeleton, the threaded rods and nuts firstly, and then the assembled whole body is arranged in the main frame in a sleeving mode; the difficulty of the assembling process is greatly lowered, and the internal layout integrity is improved.
Description
Technical field
The invention belongs to cube technical field, particularly a kind of multiple-unit cube star main force support structure.
Background technology
In recent years, along with the fast development of the science and technology such as communication, photoelectric cell, material, sensor, applicating fluid, cube
The development of star technology substantially speeds up, and is remotely measured using a cube star, tests and be possibly realized.Cheap cost has promoted world's model
In enclosing, cube star research plan emerges in large numbers.Wherein more and more from government, enterprise, particularly have powerful research strength
Art mechanism.US and European has launched a large amount of cubes of stars.
Various cubes of star structures are had at present, including commercial and independent development, cube star structure design skill
In a hundred flowers blossom, situation develops art.For example：Space innovation scheme company (ISIS) is one and is absorbed in by designing, manufacturing, change
Enter the company that micro-nano satellite subsystem causes satellite system more miniaturization.Cube star structure of its design is modular by two
The finding of big part and four connections constitutes the main structure of a unit cube star by the screw of M3*6；On the other hand,
There are many universities and organizational choice oneself to design and manufacture a cube star structure.
But for double unit cube stars, all it is that main structural framework is connected by screw into by framework, rib, due to 4
Guide rail is made up of 2 parts even 4 parts, and this is difficult to ensure the collimation between 4 guide rails.And this is for cube star
It is extremely important, because this concerns cube success or failure for star transmitting.The transmitting of cube star is by discharger-POD, in spring
A cube star is pushed in space under thrust.And mutually put down inside contact of cube star with POD exactly 4 guide rails and POD
Being slidably matched between capable channel-shaped guide rail, once therefore the depth of parallelism between 4 guide rails of cube star cannot be guaranteed, it is easy to occur
Stuck phenomenon, this just directly results in cube star and cannot be pushed in space.This means that the failure of transmitting, all work
It is all nonsensical.
The content of the invention
It is an object of the invention to provide a kind of depth of parallelism for ensureing four tracks of cube star, it can be ensured that successful launch
Multiple-unit cube star main force support structure
The technical solution for realizing the object of the invention is：
A kind of multiple-unit cube star main force support structure, including main frame, end cap, middle skeleton and screw rod, main frame is length
Cube frame structure, arranges the gusset being engaged with main frame long side direction cross sectional shape on its long side direction, and end cap is arranged
In main frame along the two ends of long side direction, its profile is closed with the matching form that main frame is surrounded, and intermedium frame is arranged on main frame
Position corresponding to inner reinforced plate, its profile are closed with the matching form that gusset is surrounded, and four screw rods are arranged on main frame along long side direction
In frame, which passes through middle skeleton and is fixed on the end cap at main frame two ends.
The present invention compared with prior art, its remarkable advantage：
(1) it is of the invention as main frame is integrative-structure, therefore the depth of parallelism between guide rail can be ensured, it is ensured that not with transmitting dress
Put stuck, it is ensured that successful launch.
(2) present invention can first by Internal PCB and end cap, middle skeleton, screw rod, spiral shell in the assembling process of cube star
Cap is all assembled, then entirety is nested in main frame, and this greatly reduces the difficulty of assembling process, while also improving inside
The integrity of layout.
Below in conjunction with the accompanying drawings the present invention is described in further detail.
Description of the drawings
Fig. 1 is the structural representation of multiple-unit cube star main force support structure of the present invention.
Specific embodiment
With reference to Fig. 1：
A kind of multiple-unit cube star main force support structure of the present invention, including main frame 1, end cap 2, middle skeleton 3 and screw rod 4,
Main frame 1 is cuboid framework structure, arranges the muscle being engaged with 1 long side direction cross sectional shape of main frame on its long side direction
Plate, end cap 2 are arranged on main frame 1 along the two ends of long side direction, and its profile is closed with the matching form that main frame 1 is surrounded, intermedium
Frame 3 is arranged on the position corresponding to 1 inner reinforced plate of main frame, and its profile is closed with the matching form that gusset is surrounded, and four screw rods 4 are along length
Edge direction is arranged in main frame 1, and which passes through middle skeleton 3 and is fixed on the end cap 2 at 1 two ends of main frame.
, through middle skeleton 3 and one of end cap 2, its two ends is respectively by screw thread and another end cap and spiral shell for screw rod 4
Cap 5 is connected, and the middle skeleton 3 and end cap 2 that wherein screw rod 4 is passed through with which coordinates for gap.
End cap 2 and middle skeleton 3 are coordinated with 1 gap of main frame.
The screwed hole for connecting solar array substrate is provided with each face of main frame 1.
Embodiment：
With reference to Fig. 1：
A kind of pair of unit cube star main force support structure, including main frame 1, end cap 2, middle skeleton 3, screw rod 4 and nut 5,
Middle part on its long side direction arranges the gusset being engaged with 1 long side direction cross sectional shape of main frame, and end cap 2 is arranged on main frame
Frame 1 is closed with the matching form that main frame 1 is surrounded along the two ends of long side direction, its profile, and middle skeleton 3 is arranged in main frame 1
Position corresponding to gusset, the matching form that its profile and gusset are surrounded are closed, end cap 2 and centre skeleton 3 with 1 gap of main frame
Coordinate；Four screw rods 4 are arranged in main frame 1 along long side direction, and screw rod 4 passes through middle skeleton 3 and one of end cap 2, its
Two ends are connected with another end cap and nut 5 by screw thread respectively, and the middle skeleton 3 and end cap 2 that wherein screw rod 4 is passed through with which is
Gap coordinates；The screwed hole for connecting solar array substrate is provided with each face of main frame 1.
Claims (5)
1. a kind of multiple-unit cube star main force support structure, it is characterised in that：Including main frame (1), end cap (2), middle skeleton (3)
With screw rod (4), main frame (1) is cuboid framework structure, is arranged and main frame (1) long side direction section on its long side direction
The gusset that matching form is closed, end cap (2) are arranged on main frame (1) along the two ends of long side direction, and its profile is surrounded with main frame (1)
Matching form close, middle skeleton (3) are arranged on the position corresponding to main frame (1) inner reinforced plate, and its profile is surrounded with gusset
Matching form is closed, and four screw rods (4) are arranged in main frame (1) along long side direction, and which passes through middle skeleton (3) and is fixed on master
On the end cap (2) at framework (1) two ends.
2. multiple-unit cube star main force support structure according to claim 1, it is characterised in that：Described screw rod (4) is passed through
Middle skeleton (3) and one of end cap (2), its two ends are connected with another end cap and nut (5) by screw thread respectively, wherein
The middle skeleton (3) and end cap (2) that screw rod (4) is passed through with which coordinates for gap.
3. multiple-unit cube star main force support structure according to claim 1 and 2, it is characterised in that：Described end cap (2) and
Middle skeleton (3) are coordinated with main frame (1) gap.
4. multiple-unit cube star main force support structure according to claim 1 and 2, it is characterised in that：Described main frame (1)
Each face on be provided with screwed hole for connecting solar array substrate.
5. multiple-unit cube star main force support structure according to claim 3, it is characterised in that：Described main frame (1)
The screwed hole for connecting solar array substrate is provided with each face.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510557584.7A CN105083590B (en) | 2015-09-02 | 2015-09-02 | Multiunit cubesat main load-bearing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510557584.7A CN105083590B (en) | 2015-09-02 | 2015-09-02 | Multiunit cubesat main load-bearing structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105083590A CN105083590A (en) | 2015-11-25 |
| CN105083590B true CN105083590B (en) | 2017-03-22 |
Family
ID=54565104
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510557584.7A Active CN105083590B (en) | 2015-09-02 | 2015-09-02 | Multiunit cubesat main load-bearing structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105083590B (en) |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105667836B (en) * | 2016-03-03 | 2018-08-07 | 航天东方红卫星有限公司 | A kind of satellite pole structure |
| CN105883003A (en) * | 2016-04-28 | 2016-08-24 | 南京理工大学 | Multi-unit cubic star main load-bearing structure based on carbon fiber composite |
| CN107985635B (en) * | 2017-11-15 | 2019-11-29 | 上海宇航系统工程研究所 | A kind of cube star On-orbit release device |
| CN107878782A (en) * | 2017-11-17 | 2018-04-06 | 南京理工大学 | Three unit cube star main force support structures |
| CN107902107B (en) * | 2017-11-17 | 2023-09-05 | 南京理工大学 | Six-unit cube star main bearing structure |
| CN108528761A (en) * | 2018-03-19 | 2018-09-14 | 西北工业大学 | A kind of 12U cubes of star structure |
| CN108482710A (en) * | 2018-03-19 | 2018-09-04 | 西北工业大学 | A kind of 2U cubes of star structure |
| CN109103677A (en) * | 2018-08-23 | 2018-12-28 | 西北工业大学 | A kind of cube star unit quickly assembled with pluggable mode |
| CN111071482B (en) * | 2019-11-27 | 2021-04-02 | 西北工业大学 | Standardized and modularized cube star unit and method |
| CN118062256A (en) * | 2024-04-15 | 2024-05-24 | 哈尔滨工业大学 | Flat plate type satellite configuration |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101381003A (en) * | 2008-09-19 | 2009-03-11 | 航天东方红卫星有限公司 | Main load-carrying structure of spacecraft |
| RU2457157C1 (en) * | 2010-12-07 | 2012-07-27 | Федеральное государственное унитарное предприятие "Государственный космический научно-производственный центр имени М.В. Хруничева (ФГУП "ГКНПЦ им. М.В. Хруничева") | Micro-satellite for earth surface remote sensing |
| CN103863577A (en) * | 2014-02-25 | 2014-06-18 | 上海微小卫星工程中心 | Frame panel type satellite configuration and modular satellite |
| CN103963998A (en) * | 2014-05-06 | 2014-08-06 | 上海卫星工程研究所 | Main force-bearing satellite structure with hexagonal framework |
| CN104044757A (en) * | 2014-05-30 | 2014-09-17 | 西北工业大学 | Automatic draw-pull type solar panel mechanism of miniature satellite |
| CN205060040U (en) * | 2015-09-02 | 2016-03-02 | 南京理工大学 | Polycell cube star primary load bearing structure |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9637248B2 (en) * | 2013-03-15 | 2017-05-02 | The Boeing Company | Component deployment system |
-
2015
- 2015-09-02 CN CN201510557584.7A patent/CN105083590B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101381003A (en) * | 2008-09-19 | 2009-03-11 | 航天东方红卫星有限公司 | Main load-carrying structure of spacecraft |
| RU2457157C1 (en) * | 2010-12-07 | 2012-07-27 | Федеральное государственное унитарное предприятие "Государственный космический научно-производственный центр имени М.В. Хруничева (ФГУП "ГКНПЦ им. М.В. Хруничева") | Micro-satellite for earth surface remote sensing |
| CN103863577A (en) * | 2014-02-25 | 2014-06-18 | 上海微小卫星工程中心 | Frame panel type satellite configuration and modular satellite |
| CN103963998A (en) * | 2014-05-06 | 2014-08-06 | 上海卫星工程研究所 | Main force-bearing satellite structure with hexagonal framework |
| CN104044757A (en) * | 2014-05-30 | 2014-09-17 | 西北工业大学 | Automatic draw-pull type solar panel mechanism of miniature satellite |
| CN205060040U (en) * | 2015-09-02 | 2016-03-02 | 南京理工大学 | Polycell cube star primary load bearing structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105083590A (en) | 2015-11-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105083590B (en) | Multiunit cubesat main load-bearing structure | |
| US10407190B2 (en) | Method for arranging a plurality of spacecraft under the fairing of a launcher, assembly resulting from such a method and dispenser suited to such an assembly | |
| CN104443431B (en) | Triangle satellite configuration | |
| CN104058102B (en) | Eight bar interconnection system noncontact satellite platform configuration and assembly methods | |
| CN105799950A (en) | Single-degree-of-freedom overconstrained shear-type deployable unit and space deployable mechanisms composed of same | |
| CN104260903A (en) | Propelling module structure with independent high-rail satellite platform function | |
| CN107902107B (en) | Six-unit cube star main bearing structure | |
| CN103831213A (en) | Screen dispensing operation fixture | |
| CN205060040U (en) | Polycell cube star primary load bearing structure | |
| CN204433058U (en) | The full landform in low latitude collapsible scouting operation one unmanned plane | |
| CN103699069A (en) | Advanced electronic integrated system for microsatellite | |
| CN107054693A (en) | Single-degree-of-freedom is asymmetric to cut hinge formula deployable mechanism unit | |
| CN207466995U (en) | Three unit cube star main force support structures | |
| CN106586039A (en) | Spatial anti-error capturing and docking device | |
| CN103241392A (en) | Attached device of deep-space week-gravitation celestial body and method for constructing attached device | |
| CN103853869B (en) | A kind of aircraft separates emulation mode | |
| CN107878782A (en) | Three unit cube star main force support structures | |
| RU178000U1 (en) | Spatial advertising element | |
| CN103560314B (en) | Reinforcing framework of flexible parabolic antenna | |
| CN102723021A (en) | Multifunctional movable space geometry analytical model | |
| CN202331943U (en) | English learning module | |
| CN203160797U (en) | Steel structure tower | |
| CN203282461U (en) | Storage rack | |
| CN207773527U (en) | Six unit cube star main force support structures | |
| CN203873279U (en) | Stainless steel storage rack unit placed in classroom |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |