CN102975867B - Satellite module and modularized satellite - Google Patents
Satellite module and modularized satellite Download PDFInfo
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- CN102975867B CN102975867B CN201210452837.0A CN201210452837A CN102975867B CN 102975867 B CN102975867 B CN 102975867B CN 201210452837 A CN201210452837 A CN 201210452837A CN 102975867 B CN102975867 B CN 102975867B
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- pipe link
- satellite modules
- structural slab
- ball
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Abstract
The invention relates to a satellite module which is provided with a standardization interface and can achieve multi-direction expansion, and a modularization satellite which is assembled by the satellite module. The satellite module comprises structural plates, connecting devices and globe joint interfaces. The connecting device comprises a connecting rod, connecting pillars extend at both ends of each connecting rods, a plurality of bosses are axially arranged on the surface of each connecting rod, and first mounting holes which are used for arranging single machines and structure plates on the connecting rods are arranged in the connecting rods and the bosses. Each global joint interface is provided with a plurality of connecting holes. Adjacent connecting rods are mutually perpendicular and connected with the connecting holes by the connecting pillars, and fixed by fixing nuts. Two adjacent structural plates are mutually perpendicular and connected with the connecting rods. A truss structure with the global joint interfaces is adopted as a satellite main structure, the connecting rods are provided with the connecting pillars and the mounting holes, so that the satellite module can achieve the multi-direction expansion through connection of the global joint and the connection rods, and is easy to dissemble and assemble.
Description
Technical field
The present invention relates to space technology Satellite technical field, particularly relate to one and there is standard interface, satellite modules can be realized at the satellite modules of multi-aspect expansion and the modularization satellite that adopts this satellite modules to be assembled into.
Background technology
In order to reduce costs, realize the target of launching as required and responding fast, it is most important that satellite realizes modularization.The unit that the modular design of satellite is about to have same requirements performance is incorporated in a module, and the structure of each module is set up around standardized interface, with ensure any module each other machinery and electrically in coupling, finally each module stack is formed a complete satellite.In recent years, in the behavioral definition and design complexity of modularization satellite, active research has been carried out both at home and abroad.Result of study shows, the complexity of modular design is mainly reflected in Interface design, and the transmission that interface must be able to provide intermodule to carry out data communication and machinery and electric energy exchanges, and therefore the standardized designs of module interface has become the emphasis of research.The standardized designs of satellite modules mechanical interface and Modular Structure Design are again one of gordian techniquies of research, and recent domestic achieves a lot of major progress for the research of this respect.The SCOUT(the Small subsidized by U.S. Department of Defense, Smart Spacecraft for Observation and Utility Tasks) the FEBSS(the Flexible and Extensible Bus for Small Satellites of plan and Air Force Research Laboratory subsidy) the SMART(Space Maintenance and Repair Technique that all adopts in the works) platform, satellite body profile being designed to cross section is hexagonal octahedron, be connected with the standard interface on plate by corner post between modules, it is model's achievement that the research of satellite platform Modular Structure Design obtains.But, the design of above-mentioned standard interface can only realize satellite modules and expand at single direction, therefore alerting ability and satellite modules in order to increase satellite modules expansion are multi-functional, have carried out multifunction, the design of conveniency and improvement to satellite modules and assembly and connection mode.
Summary of the invention
Technical matters to be solved by this invention is, the modularization satellite a kind of satellite modules being provided and adopting this satellite modules to be assembled into, solve prior art Satellite module to expand at single direction, the alerting ability of expansion is not high, and assembles the technical matters of inconvenience between satellite modules.
In order to solve the problems of the technologies described above, the invention provides a kind of connecting device, comprise a pipe link, described pipe link two ends are extended with a joint pin respectively, the surface of described pipe link is disposed with multiple boss vertically, described pipe link and boss described in each is equipped with the first mounting hole for unit and structural slab being arranged on described pipe link.
Further, all boss are along pitman shaft to the surface being equidistantly arranged in described pipe link.
Further, described pipe link surface is provided with one vertically for placing the groove of cable between unit.
In order to solve the problems of the technologies described above, present invention also offers a kind of satellite modules, comprise multiple structural slab for encapsulating described satellite modules, described satellite modules also comprises multiple connecting device of the present invention and multiple ball-joint interface, and described in each, ball-joint interface is provided with multiple connecting bore; Mutually vertical and be connected with described connecting bore by the described joint pin at pipe link two ends between the pipe link of connecting device described in adjacent two, and fixed by captive nut; Mutually vertical and be connected with described pipe link between structural slab described in adjacent two.
Further, described structural slab is provided with the second mounting hole, and matching with the position of described first mounting hole on described pipe link in the position of described second mounting hole, and is fixedly mounted by screw.
Further, described satellite modules is cube structure, and the corner of structural slab described in each is equipped with ball-joint interface described in.
Further, be provided with keysets between the described pipe link parallel with same described structural slab is connected two, described keysets is connected with described pipe link by the first mounting hole on described boss, and described keysets is used for laying satellite unit.
Further, be provided with an auxiliary rod described on the diagonal line of described structural slab two between ball-joint interface, described auxiliary rod is for keeping the stable of satellite modules interface structure and/or for placing the cable between unit.
In order to solve the problems of the technologies described above, present invention also offers a kind of modularization satellite, comprise multiple satellite modules of the present invention, the pipe link of the one side that connects is shared between two satellite modules, pipe link adjacent between two satellite modules is connected by the ball-joint interface shared, and described structural slab is encapsulated in the outermost layer of described modularization satellite.
Further, the described modularization satellite bottom satellite and the rocket connect one described in satellite modules base plate in be preset with the load frame having an annulus in the middle of one meter of font.
The invention has the advantages that: adopt and have the truss structure of ball-joint interface as satellite main structure, pipe link is provided with joint pin and mounting hole, and satellite modules has standardized interface, by the connection of ball-joint joint and pipe link, realize the multi-aspect expansion of satellite modules, expand flexible and easy to assemble.
Accompanying drawing explanation
Fig. 1, the structural representation of the connecting device of satellite modules of the present invention;
Fig. 2, each parts relative position annexation schematic diagram of satellite modules described in the first detailed description of the invention of satellite modules of the present invention;
Fig. 3, described in the first detailed description of the invention of satellite modules of the present invention, the part of satellite modules disassembles rear schematic diagram;
Fig. 4, the assembling schematic diagram of satellite modules described in the first detailed description of the invention of satellite modules of the present invention;
Fig. 5, the assembling schematic diagram of satellite modules described in the second detailed description of the invention of satellite modules of the present invention;
Fig. 6, the part of modularization satellite of the present invention disassembles rear schematic diagram;
Fig. 7, the assembling schematic diagram of modularization satellite of the present invention;
Fig. 8, the structural representation of the load frame of modularization satellite of the present invention.
[primary clustering nomenclature]
10, connecting device; 101, pipe link; 102, joint pin;
103, boss; 104, the first mounting hole; 105, groove;
20, ball-joint interface; 201, connecting bore; 30, structural slab;
301, the second mounting hole; 40, auxiliary rod; 50, unit;
501, cable; 80, load frame.
Detailed description of the invention
Elaborate below in conjunction with the detailed description of the invention of accompanying drawing to satellite modules provided by the invention and the modularization satellite that adopts this satellite modules to be assembled into.In order to increase satellite modules expansion alerting ability, the present invention adopts has the truss structure of ball-joint interface as satellite main structure, to be connected to realize the multi-aspect expansion of satellite modules by the connecting bore on ball-joint interface with pipe link.And truss structure to have quality light, good manufacturability, the advantage such as flexible and easy to assemble.
First the detailed description of the invention of the connecting device of satellite modules of the present invention is provided by reference to the accompanying drawings.
It is the structural representation of connecting device described in this detailed description of the invention shown in accompanying drawing 1, Fig. 1 only schematically indicates the relative position relation of each parts, do not represent practical structures, in present embodiment, connecting device adopts cuboid structure, in other embodiments connecting device of the present invention also can adopt cylindrical and other be convenient to the form structure that connects.Described connecting device 10 comprises pipe link 101, described pipe link 101 two ends are extended with a joint pin 102 respectively, the surface of described pipe link 101 is disposed with multiple boss 103 vertically, described pipe link 101 and boss 103 described in each is equipped with the first mounting hole 104 for unit (not shown) and structural slab (not shown) being arranged on described pipe link 101.Described connecting device 10 can adopt the light material such as aluminium or aluminum magnesium alloy.
All boss 103 are axially equidistantly arranged in the surface of described pipe link 101 along pipe link 101, the distance between boss 103 can be arranged according to the installation requirements of the standard interface of modularization unit; Also can between adjacent or multiple boss 103 the keysets (not shown) of installation code, modularization unit is placed on keysets, like this, without the need to being again designed for the mounting hole of installation of modular unit on satellite structure plate, and the equidistantly boss of arrangement and the setting of keysets, be convenient to the module interface of extension standards, facilitate the installation of unit.
In other embodiments, pipe link 101 surface is provided with one vertically for placing the groove 105 of cable between unit.Cable between unit can pass and be placed in groove 105 from groove 105, makes the layout of cable more neat, and without the need to designing the clip position of attached cable again on structural slab.
Next the first detailed description of the invention of satellite modules of the present invention is provided by reference to the accompanying drawings.
It is the structural representation of satellite modules described in this detailed description of the invention shown in accompanying drawing 2-4, wherein Figure 2 shows that each parts relative position annexation schematic diagram of described satellite modules, Figure 3 shows that the part of described satellite modules disassembles rear schematic diagram, Figure 4 shows that the assembling schematic diagram of described satellite modules.
With reference to accompanying drawing 2, satellite modules of the present invention comprises multiple connecting device 10, ball-joint interface 20 and structural slab 30.
The structural principle of described multiple connecting device 10 describes see accompanying drawing 1 correspondence, mutually vertical and be connected with described ball-joint interface 20 by the described joint pin 102 at pipe link 101 two ends between the pipe link 101 of adjacent two connecting devices 10.
Described ball-joint interface 20 is provided with multiple connecting bore 201, be interconnected by the connecting bore 201 on ball-joint interface 20 between the pipe link 101 of each connecting device 10, and fixed by captive nut, such as fixing the position of each pipe link to ensure the connection of structural slab and pipe link by installing captive nut on joint pin, realizing the multi-aspect expansion of satellite modules.Described connecting bore 201 can be screw, and corresponding described joint pin 102 is the stud matched with screw on ball-joint interface 20.The pipe link 101 of ball-joint interface 20 and connecting device 10 is that the assembling of modularization satellite provides main load path.Ball-joint interface 20 can select 18 hole ball-joint interfaces.
Described multiple structural slab 30, for encapsulating satellite modules of the present invention.The corner of structural slab 30 described in each is provided with ball-joint interface 20 described in.Described structural slab 30 is provided with multiple second mounting hole 301, and the position setting of described first mounting hole 104 arranges with the position of described second mounting hole 301 and matches.Structural slab 30 can be arranged on described connecting device 10 by described second mounting hole 301.Described first mounting hole 104 and the second mounting hole 301 can be all screw, are fixedly connected with between two screws by screw.During installation, by good with the location matches of the first mounting hole 104 on described pipe link 101 for the second mounting hole 301 on described structural slab 30, by screw, described structural slab 30 is arranged on described connecting device 10, such as, is arranged on an end face adjacent or relative with described boss 103 place end face on described connecting device 10.The design of structural slab 30 is in order to structurally to support the intraware of satellite modules (such as each unit), and the Rigidity and strength needed for assembly total weight providing support comprised and holding frequency requirement.
Preferably, 12 pipe links 101 to be coupled together by 8 ball-joint interfaces 20 and form a cube structure by described satellite modules, and cube structure outside structural slab 30 encapsulates, as shown in Figure 3 and Figure 4.
Continue with reference to shown in accompanying drawing 3 and Fig. 4, an auxiliary rod 40 is provided with between ball-joint interface 20 described on the diagonal line of described structural slab 30 two, described auxiliary rod 40 can be the polished rod that two ends are extended with a stud respectively, for playing supplemental support effect, auxiliary rod 40 intensity can need setting according to actual load.Described auxiliary rod 40 also can be provided with one for placing the form of the groove (not shown) of cable between unit for face, one end, cable between unit can pass and be placed on wherein from the groove of described auxiliary rod 40, described auxiliary rod 40 is made to play the effect of similar concentrator, when auxiliary rod 40 intensity meets the demands, auxiliary rod 40 can simultaneously for the cable keeping the stable of satellite modules interface structure and place between unit.
Keysets (not shown) is provided with between the pipe link 101 of the described connecting device 10 parallel with same described structural slab 20 is connected two, described keysets is connected with described pipe link 101 by the first mounting hole 104 on described boss 103, and described keysets is used for laying satellite unit.Keysets can be arranged the mounting hole of array, arrange to mate non-standard interface unit interface, realize the smooth installation of non-standard interface unit.Thus, standard interface module unit non-standard interface unit all can be arranged on pipe link 101 or keysets, the design of structural slab 30 is just without the need to structurally supporting the intraware of satellite modules (such as each unit), and the Rigidity and strength needed for assembly total weight providing support comprised, only need, for encapsulating satellite modules of the present invention, to meet the demand such as thermal control and block radiation.
Next the second detailed description of the invention of satellite modules of the present invention is provided by reference to the accompanying drawings.
It is the assembling schematic diagram of satellite modules described in this detailed description of the invention shown in accompanying drawing 5, with the first detailed description of the invention of satellite modules of the present invention unlike, in the present embodiment, pipe link 101 surface of connecting device 10 is provided with one vertically for placing the groove 105 of cable between unit.Unit 50 can be directly installed on pipe link 101, and in other embodiments, unit 50 also can be arranged on the keysets of array mounting hole.Cable 501 between unit can pass and be placed in groove 105 from groove 105, makes the layout of cable 501 more neat, and without the need to designing the clip position of attached cable again on structural slab 30.
Next the detailed description of the invention of modularization satellite of the present invention is provided by reference to the accompanying drawings.
Be the structural representation of modularization satellite described in this detailed description of the invention shown in accompanying drawing 6 and Fig. 7, wherein Figure 6 shows that the part of described modularization satellite disassembles rear schematic diagram, Figure 7 shows that the assembling schematic diagram of described modularization satellite.
With reference to accompanying drawing 6, described in this detailed description of the invention, modularization satellite comprises multiple satellite modules, each satellite modules has standard interface, can continue according to demand to increase satellite modules to carry out the expansion of satellite function, share pipe link 101 adjacent between pipe link 101, two satellite modules of the connecting device 10 that connects between two satellite modules to be connected by the ball-joint interface 20 shared.
Such as can select 18 hole ball-joint joints, mainly through the connecting bore 201(such as screw on the ball-joint interface 20 at each angle between each satellite modules) with the joint pin 102(such as stud at corresponding pipe link 101 two ends) couple together.Structural slab 30 is auxiliary load paths with the connection (such as adopting screw to connect) of pipe link 101, and it makes to lock between module, and the shearing strength value of raising junction also strengthens the EMI integraty of shell; In other embodiments, auxiliary rod (this figure does not show) also can be adopted as auxiliary load path.
Satellite modules can for having standard interface cube structure, can be connected with corresponding pipe link by the ball-joint interface 20 at each angle according to demand, continue to increase module to carry out the expansion of satellite function, because the structure of each satellite modules is set up around standardized interface, can ensure any satellite modules each other machinery and electrically in coupling, multiple satellite modules stackingly can be extended to the complete modularization satellite of a cuboid or a large cube structure, gesture stability in satellite structure, thermal control, communications and data process, the unit such as power supply and propelling can be arranged on the pipe link in each satellite modules, or by arranging keysets, the unit of various performance is arranged on the keysets arranged between pipe link, the satellite modules being in modularization inside satellite adopts pipe link as load path, auxiliary rod can also be adopted as auxiliary load path, the outside outermost layer of modularization satellite adopts structural slab 30 to encapsulate, play the effect of thermal control and block radiation, as shown in Figure 7.
Can design this body profile of microsatellite is cuboid, forms by multiple cube satellite modules with standard interface is stacking.Due to the use of 18 hole ball-joint joints, satellite modules can carry out the expansion of multiple directions, therefore also can be used for multiple satellite modules to be stacked into microsatellite.
Preferably, consider the connection of satellite and rocket adapter, the base plate of a satellite modules of the modularization satellite bottom and the production-release design plate of other satellite modules are slightly distinguished.In order to make the power of whole satellite effectively pass on adapter, there is the load frame 80 of an annulus in the base plate (i.e. the base plate of a satellite modules of the bottom) that the satellite and the rocket connect in the middle of a pre-buried rice font, as shown in Figure 8.
The above is only the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, under the premise without departing from the principles of the invention; can also make some improvements and modifications, these improvements and modifications also should be considered as protection scope of the present invention.
Claims (9)
1. a satellite modules, comprising multiple structural slab for encapsulating described satellite modules, it is characterized in that, described satellite modules comprises multiple connecting device and multiple ball-joint interface, and described in each, ball-joint interface is provided with multiple connecting bore;
Described connecting device comprises a pipe link, described pipe link two ends are extended with a joint pin respectively, the surface of described pipe link is disposed with multiple boss vertically, described pipe link and boss described in each is equipped with the first mounting hole for unit and structural slab being arranged on described pipe link;
Mutually vertical and be connected with described connecting bore by the described joint pin at pipe link two ends between the pipe link of connecting device described in adjacent two, and fixed by captive nut;
Mutually vertical and be connected with described pipe link between structural slab described in adjacent two.
2. satellite modules according to claim 1, is characterized in that, all boss are along pitman shaft to the surface being equidistantly arranged in described pipe link.
3. satellite modules according to claim 1, is characterized in that, described pipe link surface is provided with one vertically for placing the groove of cable between unit.
4. the satellite modules according to claim 1-3 any one, it is characterized in that, described structural slab is provided with the second mounting hole, and matching with the position of described first mounting hole on described pipe link in the position of described second mounting hole, and is fixedly mounted by screw.
5. the satellite modules according to claim 1-3 any one, is characterized in that, described satellite modules is cube structure, and the corner of structural slab described in each is equipped with ball-joint interface described in.
6. satellite modules according to claim 5, it is characterized in that, be provided with keysets between the described pipe link parallel with same described structural slab is connected two, described keysets is connected with described pipe link by the first mounting hole on described boss, and described keysets is used for laying satellite unit.
7. satellite modules according to claim 5, it is characterized in that, be provided with an auxiliary rod between ball-joint interface described on the diagonal line of described structural slab two, described auxiliary rod is for keeping the stable of satellite modules interface structure and/or for placing the cable between unit.
8. a modularization satellite, it is characterized in that, comprise the satellite modules described in multiple claim 1-3 any one, the pipe link of the one side that connects is shared between two satellite modules, pipe link adjacent between two satellite modules is connected by the ball-joint interface shared, and described structural slab is encapsulated in the outermost layer of described modularization satellite.
9. modularization satellite according to claim 8, is characterized in that, the described modularization satellite bottom satellite and the rocket connect one described in satellite modules base plate in be preset with the load frame having an annulus in the middle of one meter of font.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210452837.0A CN102975867B (en) | 2012-11-13 | 2012-11-13 | Satellite module and modularized satellite |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210452837.0A CN102975867B (en) | 2012-11-13 | 2012-11-13 | Satellite module and modularized satellite |
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| Publication Number | Publication Date |
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| CN102975867A CN102975867A (en) | 2013-03-20 |
| CN102975867B true CN102975867B (en) | 2014-12-31 |
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| CN111071482B (en) * | 2019-11-27 | 2021-04-02 | 西北工业大学 | Standardized and modularized cube star unit and method |
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| CN112124627A (en) * | 2020-09-28 | 2020-12-25 | 中国科学院微小卫星创新研究院 | Flexible satellite platform structure |
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| CN117622518A (en) * | 2023-12-20 | 2024-03-01 | 北华航天工业学院 | Main structure device of spacecraft platform |
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| CN102975867A (en) | 2013-03-20 |
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