CN102975867A - Satellite module and modularized satellite - Google Patents
Satellite module and modularized satellite Download PDFInfo
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- CN102975867A CN102975867A CN2012104528370A CN201210452837A CN102975867A CN 102975867 A CN102975867 A CN 102975867A CN 2012104528370 A CN2012104528370 A CN 2012104528370A CN 201210452837 A CN201210452837 A CN 201210452837A CN 102975867 A CN102975867 A CN 102975867A
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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, relate in particular to a kind of standard interface that has, can realize that satellite modules is 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 cost, realize as required emission and the target that responds fast, satellite realizes that modularization is most important.The unit that the modular design of satellite is about to have the same requirements performance is incorporated in the module, and so that the structure of each module centers on standardized interface foundation, with guarantee any module each other machinery and electric aspect coupling, at last each module stack is formed a complete satellite.In recent years, both at home and abroad carrying out active research aspect the performance definition of modularization satellite and the design complexity.Result of study shows that the complexity of modular design is mainly reflected on the Interface design, the transmission exchange that interface must be able to provide intermodule to carry out data communication and machinery and electric energy, so 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 has been obtained a lot of major progress for the research of this respect.SCOUT(the Small by U.S. Department of Defense's subsidy, Smart Spacecraft for Observation and Utility Tasks) the SMART(Space Maintenance and Repair Technique that the FEBSS(the Flexible and Extensible Bus for Small Satellites of plan and Air Force Research Laboratory subsidy) all adopts in the works) platform, it is hexagonal octahedron that the satellite body profile is designed to the cross section, the standard interface of being connected with plate by corner post between the modules connects, and 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 that satellite modules expands at single direction, therefore multi-functional for the alerting ability and the satellite modules that increase the satellite modules expansion, satellite modules and assembly and connection mode have been carried out design and the improvement of multifunction, conveniency.
Summary of the invention
Technical matters to be solved by this invention is, the modularization satellite that a kind of satellite modules is provided and adopts this satellite modules to be assembled into, solving prior art Satellite module can only expand at single direction, and the alerting ability of expansion is not high, and the technical matters of assembling inconvenience between the 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 respectively a joint pin, the surface of described pipe link is disposed with a plurality of boss vertically, is equipped with on described pipe link and each the described boss for the first mounting hole that unit and structural slab is installed on the described pipe link.
Further, all boss are along pitman shaft to the surface that equidistantly is arranged in described pipe link.
Further, described pipe link surface is provided with a groove that is used for placing cable between the unit vertically.
In order to solve the problems of the technologies described above, the present invention also provides a kind of satellite modules, comprise a plurality of structural slabs be used to encapsulating described satellite modules, described satellite modules also comprises a plurality of connecting devices of the present invention and a plurality of ball-joint interface, and each described ball-joint interface is provided with a plurality of connecting bores; Between the pipe link of adjacent two described connecting devices mutually described joint pins vertical and by the pipe link two ends be connected with described connecting bore, and fix by captive nut; Mutually vertically and with described pipe link be connected between the adjacent two described structural slabs.
Further, described structural slab is provided with the second mounting hole, and matching in the position of described the first mounting hole on the position of described the second mounting hole and the described pipe link, and fixedly mounts by screw.
Further, described satellite modules is cube structure, and four jiaos of each described structural slab are equipped with a described ball-joint interface.
Further, be provided with keysets between the two parallel described pipe links that link to each other with same described structural slab, described keysets links to each other with described pipe link by the first mounting hole on the described boss, and described keysets is for laying the satellite unit.
Further, be provided with an auxiliary rod between the two described ball-joint interfaces on the diagonal line of described structural slab, described auxiliary rod is for the stable of maintenance satellite modules interface structure and/or for the cable of placing between the unit.
In order to solve the problems of the technologies described above, the present invention also provides a kind of modularization satellite, comprise a plurality of satellite modules of the present invention, share the pipe link of the one side of joining between two satellite modules, pipe link adjacent between two satellite modules is connected by the ball-joint interface that shares, and described structural slab is encapsulated in the outermost layer of described modularization satellite.
Further, be preset with the load frame that an annulus is arranged in the middle of one meter font in the base plate of the described modularization satellite bottom satellite and the rocket one described satellite modules of joining.
The invention has the advantages that: adopting has the truss structure of ball-joint interface as the satellite main structure, pipe link is provided with joint pin and mounting hole, and satellite modules has standardized interface, by being connected of ball-joint joint and pipe link, realize the multi-aspect expansion of satellite modules, expand flexible and easy to assemble.
Description of drawings
Fig. 1, the structural representation of the connecting device of satellite modules of the present invention;
Fig. 2, each parts relative position annexation scheme drawing of the described satellite modules of first specific embodiment of satellite modules of the present invention;
Fig. 3, the part of the described satellite modules of first specific embodiment of satellite modules of the present invention is disassembled rear scheme drawing;
Fig. 4, the assembling scheme drawing of the described satellite modules of first specific embodiment of satellite modules of the present invention;
Fig. 5, the assembling scheme drawing of the described satellite modules of second specific embodiment of satellite modules of the present invention;
Fig. 6, the part of modularization satellite of the present invention is disassembled rear scheme drawing;
Fig. 7, the assembling scheme drawing 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.
The specific embodiment
Below in conjunction with accompanying drawing to satellite modules provided by the invention and adopt the specific embodiment of the modularization satellite that this satellite modules is assembled into to elaborate.In order to increase satellite modules expansion alerting ability, the present invention adopts the truss structure that the ball-joint interface is arranged as the satellite main structure, is connected with pipe link by the connecting bore on the ball-joint interface and realizes the multi-aspect expansion of satellite modules.And truss structure to have quality light, good manufacturability, the advantage such as flexible and easy to assemble.
Provide at first by reference to the accompanying drawings the specific embodiment of the connecting device of satellite modules of the present invention.
It is the structural representation of the described connecting device of this specific embodiment shown in the accompanying drawing 1, Fig. 1 only schematically indicates the relative position relation of each parts, do not represent practical structures, connecting device adopts the cuboid structure in the present embodiment, in other embodiments the connecting device of the present invention form structure that also can adopt cylindrical and other to be convenient to connect.Described connecting device 10 comprises pipe link 101, described pipe link 101 two ends are extended with respectively a joint pin 102, the surface of described pipe link 101 is disposed with a plurality of boss 103 vertically, is equipped with on described pipe link 101 and each the described boss 103 for the first mounting hole 104 that unit (not shown) and structural slab (not shown) is installed on the described pipe link 101.Described connecting device 10 can adopt the light materials such as aluminium or aluminum magnesium alloy.
All boss 103 axially equidistantly are arranged in the surfaces of described pipe link 101 along pipe link 101, and the distance between the boss 103 can be according to the installation requirements setting of the standard interface of modularization unit; Also can be between adjacent or a plurality of boss 103 the keysets (not shown) of installation code, the modularization unit is placed on the keysets, like this, need not again to be designed at the satellite structure plate mounting hole of installation module unit, and the boss of equidistantly arranging and the setting of keysets, be convenient to the module interface of extension standards, make things convenient for the installation of unit.
In other embodiments, pipe link 101 surfaces are provided with one vertically for the groove 105 of placing cable between the unit.Cable between the unit can pass and be placed in the groove 105 from groove 105, so that the layout of cable is more neat, and need not clip position at structural slab design attached cable again.
Next provide by reference to the accompanying drawings first specific embodiment of satellite modules of the present invention.
It is the structural representation of the described satellite modules of this specific embodiment shown in the accompanying drawing 2-4, wherein Figure 2 shows that each parts relative position annexation scheme drawing of described satellite modules, the part that Figure 3 shows that described satellite modules is disassembled rear scheme drawing, Figure 4 shows that the assembling scheme drawing of described satellite modules.
With reference to the accompanying drawings 2, satellite modules of the present invention comprises a plurality of connecting devices 10, ball-joint interface 20 and structural slab 30.
The structural principle of described a plurality of connecting device 10 is described referring to accompanying drawing 1 is corresponding, between the pipe link 101 of adjacent two connecting devices 10 mutually described joint pins 102 vertical and by pipe link 101 two ends be connected with described ball-joint interface 20.
Described ball-joint interface 20 is provided with a plurality of connecting bores 201, interconnect by the connecting bore 201 on the ball-joint interface 20 between the pipe link 101 of each connecting device 10, and fix by captive nut, for example be connected the multi-aspect expansion of realization satellite modules by install and fix position that nut fixes each pipe link at joint pin with what guarantee structural slab and pipe link.Described connecting bore 201 can be screw, the double-screw bolt of corresponding described joint pin 102 for matching with screw on the ball-joint interface 20.The pipe link 101 of ball-joint interface 20 and connecting device 10 provides main load path for the assembling of modularization satellite.Ball-joint interface 20 can be selected 18 hole ball-joint interfaces.
Described a plurality of structural slab 30 is used for encapsulating satellite modules of the present invention.Four jiaos of each described structural slab 30 are provided with a described ball-joint interface 20.Described structural slab 30 is provided with a plurality of the second mounting holes 301, and the position of described the first mounting hole 104 arranges and the position setting of described the second mounting hole 301 is complementary.Structural slab 30 can be installed on the described connecting device 10 by described the second mounting hole 301.Described the first mounting hole 104 and the second mounting hole 301 all can be screw, pass through the screw captive joint between two screws.During installation, the location matches of the second mounting hole 301 on the described structural slab 30 and the first mounting hole 104 on the described pipe link 101 is good, by screw described structural slab 30 is installed on the described connecting device 10, for example is installed on the end face adjacent or relative with described boss 103 place end faces on the described connecting device 10.The intraware (for example each unit) of the design of structural slab 30 in order to structurally to support satellite modules, and required Rigidity and strength and the holding frequency requirement of assembly total weight that provides support and comprise.
Preferably, described satellite modules is coupled together 12 pipe links 101 by 8 ball-joint interfaces 20 and forms a cube structure, and cube structure is outside with structural slab 30 encapsulation, as shown in Figure 3 and Figure 4.
Continue with reference to the accompanying drawings 3 and shown in Figure 4, be provided with an auxiliary rod 40 between the two described ball-joint interfaces 20 on the diagonal line of described structural slab 30, described auxiliary rod 40 can be extended with respectively for two ends the polished rod of a double-screw bolt, be used for playing the supplemental support effect, auxiliary rod 40 intensity can be set according to actual load needs.Described auxiliary rod 40 also can be provided with one for the form of placing the groove (not shown) of cable between the unit for an end face, cable between the unit can pass and be placed on wherein from the groove of described auxiliary rod 40, so that described auxiliary rod 40 plays the effect of similar concentrator, when auxiliary rod 40 intensity met the demands, auxiliary rod 40 can be used for the cable between stablizing of maintenance satellite modules interface structure and the placement unit simultaneously.
Be provided with the keysets (not shown) between the pipe link 101 of the two parallel described connecting devices 10 that link to each other with same described structural slab 20, described keysets links to each other with described pipe link 101 by the first mounting hole 104 on the described boss 103, and described keysets is used for laying the satellite unit.The mounting hole of array can be set on the keysets, arrange with coupling 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 installed on pipe link 101 or the keysets, the design of structural slab 30 just need not structurally to support the intraware (for example each unit) of satellite modules, and the required Rigidity and strength of assembly total weight that provides support and comprise, only need to satisfy the demands such as thermal control and block radiation be used to encapsulating satellite modules of the present invention.
Next provide by reference to the accompanying drawings second specific embodiment of satellite modules of the present invention.
It is the assembling scheme drawing of the described satellite modules of this specific embodiment shown in the accompanying drawing 5, different from first specific embodiment of satellite modules of the present invention is, in the present embodiment, pipe link 101 surfaces of connecting device 10 are provided with one vertically for the groove 105 of placing cable between the unit.Unit 50 can be directly installed on the pipe link 101, and in other embodiments, unit 50 also can be installed on the keysets of array mounting hole.Cable 501 between the unit can pass and be placed in the groove 105 from groove 105, so that the layout of cable 501 is more neat, and need not clip position at structural slab 30 design attached cables again.
Next provide by reference to the accompanying drawings the specific embodiment of modularization satellite of the present invention.
Accompanying drawing 6 and shown in Figure 7 be the structural representation of the described modularization satellite of this specific embodiment, Figure 6 shows that wherein the part of described modularization satellite is disassembled rear scheme drawing, Figure 7 shows that the assembling scheme drawing of described modularization satellite.
With reference to the accompanying drawings 6, the described modularization satellite of this specific embodiment comprises a plurality of 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, sharing pipe link 101 adjacent between pipe link 101, two satellite modules of the connecting device 10 that joins between two satellite modules is connected by the ball-joint interface 20 that shares.
For example can select 18 hole ball-joint joints, main by the screw for example of the connecting bore 201(on the ball-joint interface 20 at each angle between each satellite modules) with the joint pin 102(at corresponding pipe link 101 two ends double-screw bolt for example) couple together.Be connected (for example the adopting screw to connect) of structural slab 30 and pipe link 101 is auxiliary load paths, and it is so that lock between the module, improves the shearing strength value of junction and strengthens the EMI integraty of shell; In other embodiments, also can adopt auxiliary rod (this figure does not show) as auxiliary load path.
Satellite modules can be for having the standard interface cube structure, the ball-joint interface 20 that can pass through according to demand each angle links to each other with corresponding pipe link, 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 guarantee any satellite modules each other machinery and electric aspect the coupling, a plurality of satellite modules can stackingly be extended to the complete modularization satellite of a cuboid or a large cube structure, attitude control in the satellite structure, thermal control, communications and data is processed, the unit such as power supply and propelling can be installed on the pipe link in each satellite modules, perhaps by keysets is set, the unit of various performances is installed on the keysets that arranges between the pipe link, the satellite modules that is in the modularization inside satellite adopts pipe link as the load path, can also adopt auxiliary rod as auxiliary load path, the outside outermost layer of modularization satellite adopts structural slab 30 encapsulation, play the effect of thermal control and block radiation, as shown in Figure 7.
Can design this body profile of microsatellite is cuboid, by a plurality of stacking forming of cube satellite modules with standard interface.Because the use of 18 hole ball-joint joints, satellite modules can be carried out the expansion of a plurality of directions, so also can be used for a plurality of satellite modules are stacked into microsatellite.
Preferably, consider being connected 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 had any different.For the power that makes whole satellite passes on the adapter effectively, the load frame 80 of an annulus is arranged, as shown in Figure 8 in the base plate that the satellite and the rocket join (being the base plate of a satellite modules of the bottom) in the middle of the pre-buried rice font.
The above only is preferred implementation of the present invention; should be pointed out that for those skilled in the art, under the prerequisite that does not break away from the principle 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 (10)
1. connecting device, comprise a pipe link, it is characterized in that, described pipe link two ends are extended with respectively a joint pin, the surface of described pipe link is disposed with a plurality of boss vertically, is equipped with on described pipe link and each the described boss for the first mounting hole that unit and structural slab is installed on the described pipe link.
2. connecting device according to claim 1 is characterized in that, all boss are along pitman shaft to the surface that equidistantly is arranged in described pipe link.
3. connecting device according to claim 1 is characterized in that, described pipe link surface is provided with one vertically for the groove of placing cable between the unit.
4. satellite modules, comprise a plurality of structural slabs be used to encapsulating described satellite modules, it is characterized in that described satellite modules comprises the described connecting device of a plurality of claim 1～3 any one and a plurality of ball-joint interface, each described ball-joint interface is provided with a plurality of connecting bores; Between the pipe link of adjacent two described connecting devices mutually described joint pins vertical and by the pipe link two ends be connected with described connecting bore, and fix by captive nut; Mutually vertically and with described pipe link be connected between the adjacent two described structural slabs.
5. satellite modules according to claim 4 is characterized in that, described structural slab is provided with the second mounting hole, and matching in the position of described the first mounting hole on the position of described the second mounting hole and the described pipe link, and fixedly mounts by screw.
6. satellite modules according to claim 4 is characterized in that, described satellite modules is cube structure, and four jiaos of each described structural slab are equipped with a described ball-joint interface.
7. satellite modules according to claim 6, it is characterized in that, be provided with keysets between the two parallel described pipe links that link to each other with same described structural slab, described keysets links to each other with described pipe link by the first mounting hole on the described boss, and described keysets is for laying the satellite unit.
8. satellite modules according to claim 6, it is characterized in that, be provided with an auxiliary rod between the two described ball-joint interfaces on the diagonal line of described structural slab, described auxiliary rod is for the stable of maintenance satellite modules interface structure and/or for the cable of placing between the unit.
9. modularization satellite, it is characterized in that, comprise the described satellite modules of a plurality of claim 4～8 any one, share the pipe link of the one side of joining between two satellite modules, pipe link adjacent between two satellite modules is connected by the ball-joint interface that shares, and described structural slab is encapsulated in the outermost layer of described modularization satellite.
10. modularization satellite according to claim 9 is characterized in that, is preset with the middle load frame that an annulus is arranged of one meter font in the base plate of the described satellite modules that the described modularization satellite bottom satellite and the rocket join.
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| CN201210452837.0A CN102975867B (en) | 2012-11-13 | 2012-11-13 | Satellite module and modularized satellite |
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| CN201210452837.0A CN102975867B (en) | 2012-11-13 | 2012-11-13 | Satellite module and modularized satellite |
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| 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 |
| CN104176272A (en) * | 2014-08-06 | 2014-12-03 | 上海卫星工程研究所 | Eight rod connection type non-contact satellite platform configuration |
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| CN103448917A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | Quick assembly service capsule of high-orbit satellite platform and application of quick assembly service capsule |
| CN103434660B (en) * | 2013-08-31 | 2015-10-28 | 西北工业大学 | Small plate-type spacecraft |
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