CN207466995U - Three unit cube star main force support structures - Google Patents
Three unit cube star main force support structures Download PDFInfo
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- CN207466995U CN207466995U CN201721541576.4U CN201721541576U CN207466995U CN 207466995 U CN207466995 U CN 207466995U CN 201721541576 U CN201721541576 U CN 201721541576U CN 207466995 U CN207466995 U CN 207466995U
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Abstract
The utility model discloses a kind of three unit cube star main force support structures, it is made of main frame, end cap, intermediate skeleton, screw rod, end nut, intermediate support, main frame is cuboid framework structure, two end caps are arranged on both ends of the main frame along long side direction, two intermediate skeleton parallel intervals are arranged on main frame centre position, intermediate support is arranged in parallel between intermediate skeleton, four screw rods are arranged in main frame, are passed through intermediate skeleton and intermediate support and are fixed on the end cap at main frame both ends；The utility model reduces the assembling difficulty of cube star, improves the integrality of interior layout.The utility model can ensure the depth of parallelism between guide rail since main frame is integral structure, and when transmitting is not stuck with satellite and the rocket separator, it is ensured that successful launch.
Description
Technical field
The utility model belongs to cube satellite technology field, specifically a kind of three units 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, MEMS device, cube
The development of star technology is substantially speeded up, and carries out space remote measurement using cube star, experiment is possibly realized.Cheap cost has promoted generation
Cube star research plan emerges in large numbers in the range of boundary.It wherein more and more comes from government, enterprise, particularly has powerful research strength
Academic institution.US and European has emitted a large amount of cubes of stars.
Cube satellite（Referred to as cube star）Belonging to micro-nano satellite scope, development is extremely rapid, normalized at present,
Modularization, commercialization.Cube star by the state Polytechnics in California and Stanford University's space system laboratory in
Joint proposes, while has formulated independent cube star within 1999（CubeSat）Design standard contributes to engineer small in progress
Its specific principle is followed during design of satellites, is substantially carried out the modularized design of satellite platform system, so as to shorten the R＆D cycle,
Save development cost.The purpose is to which university, institution of higher learning or the private enterprise is allowed to carry out inexpensive scientific research, emission space carries
Lotus carries out international cooperation, while student is allowed to obtain the practice experience of satellite development, transmitting and telemetering.
Cube star removes the rule of design of satellites and possesses outside some independent design standards, cube star and delivery
There is stringent interactive interface between rocket, while use special satellite and the rocket separating mechanism.Cube star is simple in structure, a unit cube
Star（1U Cubesat）Size is 100mm × 100mm × 100mm, and weight is no more than 1.33kg；The size of 2U cubes of star is
100mm × 100mm × 227mm, weight are no more than 2.66Kg；The size of 3U cubes of star be 100mm × 100mm × 340mm, weight
No more than 4kg, a cube of star task at most needed for two years from start to end, spent general to need 5 to 10 ten thousand in total
Euro.If task needs, a cube star can also be extended to 6U, 12U even 27U.
Have various cubes of star structures at present, including commercialization and independent development, cube star structure design skill
In a hundred flowers blossom, situation develops art.Such as：Space innovation scheme company（ISIS）It is one to be absorbed in by designing, manufacturing, changing
Cause the company that satellite system more minimizes into micro-nano satellite subsystem.Its unit cube star designed（100mm×
100mm×100mm）Main structure is made up of two modular big parts and four small parts connected the screw of M3*6；
On the other hand, many universities and organizational choice oneself also design and manufacture a cube star structure.
But for three unit cube stars（100mm×100mm×340mm）, it is connected by screw by framework, rib
Into main structural framework, since 4 guide rails are made of 2 parts even 4 parts, this is difficult to ensure the collimation between 4 guide rails.And
This is again extremely important for cube star, because this is concerning the success or failure emitted to cube star.The transmitting of cube star is logical
Satellite and the rocket separator-POD is crossed, a cube star is pushed in space under spring thrust effect.And contact of cube star with POD is just
It is being slidably matched between the channel-shaped guide rail being mutually parallel inside 4 guide rails and POD, therefore once flat between 4 guide rails of cube star
Row degree cannot be guaranteed, it is easy to the phenomenon that stuck occur, this just directly results in cube star and can not be pushed in space.This is just
Mean the failure of transmitting, all work are all nonsensical.
Invention content
The purpose of this utility model is to provide a kind of three unit cube star main force support structures, the assembling for reducing cube star is difficult
Degree improves the integrality of interior layout, it is ensured that the depth of parallelism between guide rail, when transmitting be not stuck with satellite and the rocket separator, it is ensured that
Successful launch.
The utility model technical solution is：A kind of three unit cube star main force support structures, including main frame, intermediate branch
Frame, two intermediate quadrate frameworks, four screw rods, two rectangular end caps, eight end nuts；Main frame is cuboid, including four
Column and several connecting rods, connecting rod improve its overall stiffness for connecting adjacent two root posts；Two intermediate quadrates
Frame parallel interval is arranged in main frame, and lateral wall and the connecting rod of intermediate quadrate framework are connected, and intermediate support is arranged in parallel in
Between two intermediate quadrate frameworks, two rectangular end caps are located at the top and bottom of main frame respectively, square end outer side of lid wall with
Connecting rod is connected；Four screw rods are set respectively close to main frame four columns, between two intermediate quadrate frameworks and intermediate support
Gap coordinates, and four screw rods are connected by eight end nuts with two rectangular end caps.
The shape of two intermediate quadrate frameworks is matched with the shape that main frame connecting rod surrounds；Two rectangular end caps and master
The shape that frame connecting rod surrounds matches.
The through-hole for connecting solar array substrate is both provided on each face of the main frame.
The utility model compared with prior art, remarkable advantage：
（1）The utility model is integral structure due to main frame, it is ensured that the depth of parallelism between guide rail, it is ensured that is not divided with the satellite and the rocket
It is stuck from device, it is ensured that successful launch.
（2）The utility model light weight complies fully with the miniaturization of cube satellite, lightweight requirements, reduces and be to other
Quality of uniting and the limitation in space improve the functional density of cube star.
（3）The utility model structure outside dimension is 100mm × 100mm × 340mm, meets cube design of satellites standard,
Standard 3U-POD can be used to be detached for the satellite and the rocket.
（4）The utility model in the assembling process of cube star can first by Internal PCB and two rectangular end caps, two
Intermediate quadrate framework, intermediate square set, screw rod, end nut all assemble, then entirety is nested into main frame, this is greatly dropped
The low difficulty of assembling process, while also improve the integrality of interior layout.
（5）The structural intergrity of the utility model is good, and whole shock resistance antivibration kinetic force is strong, it can be ensured that cube star it is normal
Work.
（6）The utility model is simple in structure, and good reliability, processing cost is low, highly practical, is highly suitable for quick sound
It answers, the cube satellite that duty cycle is short.
Description of the drawings
Fig. 1 is the structure diagram of three unit cube star main force support structure of the utility model.
Fig. 2 is the main frame schematic diagram in three unit cube star main force support structure of the utility model.
Fig. 3 is the intermediate quadrate framework schematic diagram in three unit cube star main force support structure of the utility model.
Fig. 4 is the rectangular end cap schematic diagram in three unit cube star main force support structure of the utility model.
Fig. 5 is the end nut schematic diagram in three unit cube star main force support structure of the utility model.
Fig. 6 is the rectangular intermediate support schematic diagram in three unit cube star main force support structure of the utility model.
Specific embodiment
The utility model is described in further detail below in conjunction with the accompanying drawings.
With reference to Fig. 1 ~ Fig. 6, the utility model is a kind of three unit cube star main force support structures, including main frame 1, intermediate branch
The intermediate rectangular end cap 4 of screw rod 3, two of quadrate framework 2, four of 6, two, frame and eight end nuts 5；Main frame 1 is cuboid, is wrapped
Four columns and several connecting rods are included, four columns composition section is the rectangular of 100mm × 100mm, and connecting rod is used to connect
Adjacent two root posts improve its overall stiffness；The four columns of main frame 1, several connecting rods are Al7075 materials one
Processing and forming part.
Two intermediate 2 parallel intervals of quadrate framework are arranged in main frame 1, what shape was surrounded with 1 connecting rod of main frame
Shape matches, and the lateral wall of intermediate quadrate framework 2 is connected with connecting rod by screw；Intermediate support 6 is arranged in parallel in two
Between intermediate quadrate framework 2；Two rectangular end caps 4 are located at the top and bottom of main frame 1 respectively, and there are four with holding nut for setting
The same stepped hole of 5 shapes, the one side for having branch angle for forming non-bulging rectangular 4 four edges of end cap of end nut 5, one of side
There is circular hole at two rectangular branch angles in four branch angles of shape end cap 4, for place satellite and the rocket separating switch by pressure cylinder and spring, four
While there is loss of weight design, two rectangular end caps 4 are matched with the shape that 1 connecting rod of main frame surrounds, and pass through four end nuts 5 and four
The screw thread of root screw rod 3 is connected, and rectangular 4 lateral wall of end cap is connected with connecting rod using screw；6, two centres of intermediate support are rectangular
Skeleton 2 and two rectangular end caps 4 are respectively Al7075 materials and are integrally formed processing part.
Four screw rods 3 are set respectively close to 1 four columns of main frame, between two intermediate quadrate frameworks 2 and intermediate support 6
Gap coordinates, and four screw rods 3 are connected by eight end nuts 5 and two rectangular end caps 4, end 5 shape of nut and the first square end
Four stepped holes on lid 4 match, and lower half portion is the screw thread coordinated with screw rod 3, and top half is Hexagon hole, convenient
It is installed using allen wrench.Hold nut 4 with 3 material of screw rod using titanium alloy, mechanical property needed for satisfaction.
The through-hole for connecting solar array substrate is both provided on each face of length direction of main frame 1；Two
Intermediate quadrate framework 2 is both provided with the threaded hole for connecting solar array substrate with the lateral wall of two rectangular end caps 4.
During assembling, by the way that nut 5 is held to be fixed on a rectangular end cap 4, pcb board is layered in screw rod 3 for four 3 one end of screw rod
On, intert two intermediate quadrate frameworks 2 and an intermediate support 6 between pcb board, screw rod 3 and the intermediate quadrate framework 2 passed through and
Intermediate support 6 is clearance fit, and 3 other end of screw rod is fixed on using end nut 5 on another rectangular end cap 4, then entirety is inserted in
Main frame 1；The through-hole for connecting solar array substrate is both provided on each face on 1 length direction of main frame, in
Between quadrate framework 2 and rectangular end cap 4 be provided with threaded hole for connecting solar array substrate, solar-electricity can be installed
Chi Zhen.
Embodiment
With reference to Fig. 1 ~ Fig. 6, the utility model is a kind of three unit cube star main force support structures, including main frame 1, intermediate branch
The intermediate rectangular end cap 4 of screw rod 3, two of quadrate framework 2, four of 6, two, frame and eight end nuts 5；Main frame 1 is cuboid, is wrapped
Four columns and several connecting rods are included, four columns composition section is the rectangular of 100mm × 100mm, and connecting rod is used to connect
Adjacent two root posts improve its overall stiffness；The four columns of main frame 1, several connecting rods are Al7075 materials one
Processing and forming part is process by a monoblock aluminium alloy.In the length that the four columns of main frame 1 are formed with several connecting rods
Heat-control multilayer material at rectangular emptying aperture is set, plays function of heat insulation.
Two intermediate 2 parallel intervals of quadrate framework are arranged in main frame 1, what shape was surrounded with 1 connecting rod of main frame
Shape matches, and the lateral wall of intermediate quadrate framework 2 is connected with connecting rod by screw；Intermediate support 6 is arranged in parallel in two
Between intermediate quadrate framework 2；Two rectangular end caps 4 are located at the top and bottom of main frame 1 respectively, and there are four with holding nut for setting
The same stepped hole of 5 shapes, the one side for having branch angle for forming non-bulging rectangular 4 four edges of end cap of end nut 5, one of side
There is circular hole at two rectangular branch angles in four branch angles of shape end cap 4, for place satellite and the rocket separating switch by pressure cylinder and spring, four
While there is loss of weight design, two rectangular end caps 4 are matched with the shape that 1 connecting rod of main frame surrounds, and pass through four end nuts 5 and four
The screw thread of root screw rod 3 is connected, and rectangular 4 lateral wall of end cap is connected with connecting rod using screw；6, two centres of intermediate support are rectangular
Skeleton 2 and two rectangular end caps 4 are respectively Al7075 materials and are integrally formed processing part.
Four screw rods 3 are set respectively close to 1 four columns of main frame, between two intermediate quadrate frameworks 2 and intermediate support 6
Gap coordinates, and four screw rods 3 are connected by eight end nuts 5 and two rectangular end caps 4, end 5 shape of nut and the first square end
Four stepped holes on lid 4 match, and lower half portion is the screw thread coordinated with screw rod 3, and top half is Hexagon hole, convenient
It is installed using allen wrench.Hold nut 4 with 3 material of screw rod using titanium alloy, mechanical property needed for satisfaction.
The through-hole for connecting solar array substrate is both provided on each face of length direction of main frame 1；Two
Intermediate quadrate framework 2 is both provided with the threaded hole for connecting solar array substrate with the lateral wall of two rectangular end caps 4.
During assembling, by the way that nut 5 is held to be fixed on a rectangular end cap 4, pcb board is layered in screw rod 3 for four 3 one end of screw rod
On, intert two intermediate quadrate frameworks 2 and an intermediate support 6 between pcb board, screw rod 3 and the intermediate quadrate framework 2 passed through and
Intermediate support 6 is clearance fit, and 3 other end of screw rod is fixed on using end nut 5 on another rectangular end cap 4, then entirety is inserted in
Main frame 1；The through-hole for connecting solar array substrate is both provided on each face on 1 length direction of main frame, in
Between quadrate framework 2 and rectangular end cap 4 be provided with threaded hole for connecting solar array substrate, solar-electricity can be installed
Chi Zhen.
Claims (3)
1. a kind of three unit cube star main force support structures, it is characterised in that：Including main frame（1）, intermediate support（6）, in two
Between quadrate framework（2）, four pieces screw rods（3）, two rectangular end caps（4）With eight end nuts（5）；Main frame（1）For cuboid, packet
Four columns and several connecting rods are included, connecting rod improves its overall stiffness for connecting adjacent two root posts；Two centres
Quadrate framework（2）Parallel interval is arranged on main frame（1）It is interior, intermediate quadrate framework（2）Lateral wall be connected with connecting rod, it is intermediate
Stent（6）It is arranged in parallel in two intermediate quadrate frameworks（2）Between, two rectangular end caps（4）It is located at main frame respectively（1）Top
Portion and bottom, rectangular end cap（4）Lateral wall is connected with connecting rod；Four screw rods（3）Respectively close to main frame（1）Four columns are set
It puts, with two intermediate quadrate frameworks（2）And intermediate support（6）Clearance fit, and four screw rods（3）Pass through eight end nuts（5）
With two rectangular end caps（4）It is connected.
2. three units cube star main force support structure according to claim 1, it is characterised in that：Described two intermediate quadrates
Frame（2）Shape and main frame（1）The shape that connecting rod surrounds matches；Two rectangular end caps（4）With main frame（1）Connecting rod
The shape surrounded matches.
3. three units cube star main force support structure according to claim 1, it is characterised in that：The main frame（1）It is each
The through-hole for connecting solar array substrate is both provided on a face.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721541576.4U CN207466995U (en) | 2017-11-17 | 2017-11-17 | Three unit cube star main force support structures |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721541576.4U CN207466995U (en) | 2017-11-17 | 2017-11-17 | Three unit cube star main force support structures |
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| Publication Number | Publication Date |
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| CN207466995U true CN207466995U (en) | 2018-06-08 |
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ID=62261191
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| Application Number | Title | Priority Date | Filing Date |
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| CN201721541576.4U Active CN207466995U (en) | 2017-11-17 | 2017-11-17 | Three unit cube star main force support structures |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107878782A (en) * | 2017-11-17 | 2018-04-06 | 南京理工大学 | Three unit cube star main force support structures |
| CN111470069A (en) * | 2020-04-08 | 2020-07-31 | 上海卫星工程研究所 | Lower end frame structure suitable for satellite bearing cylinder |
-
2017
- 2017-11-17 CN CN201721541576.4U patent/CN207466995U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107878782A (en) * | 2017-11-17 | 2018-04-06 | 南京理工大学 | Three unit cube star main force support structures |
| CN111470069A (en) * | 2020-04-08 | 2020-07-31 | 上海卫星工程研究所 | Lower end frame structure suitable for satellite bearing cylinder |
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