CN102424115A - Spacecraft gridded composite bearing cylinder - Google Patents
Spacecraft gridded composite bearing cylinder Download PDFInfo
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- CN102424115A CN102424115A CN2011103624291A CN201110362429A CN102424115A CN 102424115 A CN102424115 A CN 102424115A CN 2011103624291 A CN2011103624291 A CN 2011103624291A CN 201110362429 A CN201110362429 A CN 201110362429A CN 102424115 A CN102424115 A CN 102424115A
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- end frame
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Abstract
The invention discloses a spacecraft gridded composited bearing cylinder, comprising an upper end frame, a lower end frame, a skin and a gridded rib, wherein the exterior of the gridded rib is wrapped with the skin to form an up-down through barrel, the upper edge and the lower edge of the barrel respectively comprise the upper end frame and the lower end frame; quantity of left rotating ribs and the quantity of right rotating ribs in the gridded rib are the same, and a prismatic grid is formed, wherein the rib angle is 30-45 degrees, and rib space is 80-150mm; the upper end frame and the lower end frame are formed by continuously flanging fibres of the skin and the gridded rib; and the upper end frame and the lower end frame respectively comprise a mounting interface for the bearing cylinder and a horizontal structural slab arranged outside. The spacecraft gridded composited bearing cylinder disclosed by the invention adopts a design form of skin+gridded rib composite bearing cylinder, structural mass is reduced by about 40% compared with an aluminium honeycomb interlayer bearing cylinder, important significance is realized during weight reduction of a satellite structure, and satellite platform bearing capacity is improved.
Description
Technical field
The present invention relates to aerospacecraft, be specially a kind of satellite network trellis composite material load-carrying tube.
Background technology
Loaded cylinder is the load-carrying construction that carries the satellite basic load, is whole satellite structure stack-mounted core, and it bears the basic load of whole spacecraft, directly the various piece of the loading transfer of carrier rocket to whole spacecraft.As whole spacecraft structure stack-mounted core, most of structure members all are that make up at the center with the loaded cylinder.Loaded cylinder can provide mounting interface and space for propellant tank, and benchmark and satellite assembling on ground, test, transportation, the bearing surface when storing and the mechanical interface of spacecraft and ground-support equipment of spacecraft design and processes can be provided again.
Before the present invention, center loaded cylinder version has sandwich structure (adopting carbon fiber covering aluminium honeycomb interlayer primary load bearing tube like wind and cloud three satellites), shell reinforced structure (adding the reinforcement tube that the aluminum alloy shell that adopts on satellite of reinforcement tube, remote sensing of carbon fiber stringer adds the aluminum alloy stringer like the carbon fiber shell that adopts on satellite of resource), ripple struction (like the carbon fiber bellows that adopts on the Dongfanghong-III satellite).It is big that the loaded cylinder of these structures has quality, and the defective that load-carrying capacity is more weak is relatively used to have certain deficiency in space industry.
Summary of the invention
Loaded cylinder quality in the prior art is big in order to overcome, the defective a little less than the load-carrying capacity, the invention provides the loaded cylinder that a mass is little, load-carrying capacity is strong.
To achieve these goals, the invention provides the latticed composite material load-carrying tube of a kind of spacecraft, comprise upper end frame, lower end frame, covering and grid ribs; Wherein,
The external packets of said grid ribs is wrapped with covering, forms cylindrical shell penetrating about in the of, and the upper edge of said cylindrical shell and lower edge include upper end frame and lower end frame respectively;
It is identical to revolve muscle quantity about in the said grid ribs, forms the prismatic grid, and the muscle angle is between 30 °～45 °, and the muscle spacing is between 80mm～150mm;
Said upper end frame and lower end frame form through the continuous flange of the fiber of said grid ribs and said covering; The mounting interface that comprises said loaded cylinder and exterior transversary plate on said upper end frame, the lower end frame.
In the technique scheme; Also comprise being used to provide said loaded cylinder and the satellite shaft stringer to the connecting interface of structural slab, said stringer is positioned at the outside of said covering, and is vertical with said upper and lower end frame; Its quantity has the 8-12 root, and the cross-sectional plane of every stringer is " T " font.
In the technique scheme, said stringer is received on the said covering through adhesive glue, and is aided with bolt-nut connection.
In the technique scheme, also comprise the outward flange of the connecting interface that is used to provide said loaded cylinder and exterior satellite transversary plate, said outward flange laterally is nested in the outside of said covering.
In the technique scheme, also comprise the inside flange of the connecting interface that is used to provide said loaded cylinder and exterior hydrazine bottle adapter plate, said inside flange is positioned at the inboard of said grid ribs, and is parallel with said upper and lower end frame.
In the technique scheme, the height of loaded cylinder is between 1320mm～1380mm, and barrel diameter is between 1100mm～1250mm.
In the technique scheme, said covering comprises 5～10 layers, and every layer thickness is 0.07mm, adopts symmetric mode shop layer; Each layer covering adopts carbon fiber composite material M55J to realize.
In the technique scheme, the periphery of said upper end frame and lower end frame adopts reinforcing fiber to strengthen.
In the technique scheme, said grid ribs adopts carbon fiber composite material T700 to realize.
Latticed composite material load-carrying tube of the present invention; Thickness, layering type that loaded cylinder is comprised mesh shape, the angle of cut, spacing, sectional dimension and covering according to the constraint conditions such as intensity, rigidity and stability of satellite platform etc. is optimized; Can reach technological characteristicss such as simple in structure, light weight and load-carrying capacity be strong; Architecture quality of the present invention reduces about 40% with respect to the aluminium honeycomb interlayer loaded cylinder with same load-carrying capacity; Significant to the satellite structure loss of weight, and improved the satellite platform load-carrying capacity.
Description of drawings
Fig. 1 is in a preferred embodiment, the block diagram of latticed composite material load-carrying tube of the present invention;
Fig. 2 is the grid ribs schematic perspective view;
Fig. 3 is the grid ribs partial enlarged drawing;
Fig. 4 is grid ribs sectional dimension figure;
Fig. 5 is a upper and lower end frame scheme drawing;
Fig. 6 is stringer and cylindrical shell connection diagram.
The specific embodiment
Below in conjunction with the accompanying drawing and the specific embodiment the present invention is further specified.
In one embodiment, loaded cylinder of the present invention comprises upper end frame (1), lower end frame (4), covering (6) and grid ribs (7).Wherein, the external packets of said grid ribs (7) is wrapped with covering (6), forms cylindrical shell penetrating about in the of, and the upper edge of said cylindrical shell and lower edge include upper end frame (1) and lower end frame (4) respectively.In the present embodiment, the height of formed loaded cylinder is between 1320mm～1380mm, and barrel diameter is between 1100mm～1250mm, and this height helps installing in the spacecraft miscellaneous part such as propellant tank with diameter range.But in other embodiments, the height of loaded cylinder and diameter also can be done corresponding adjustment as required.
Do further explanation with regard to the function and the realization of various piece below.
Covering (6) is wrapped in the periphery of said loaded cylinder, and it comprises 5～10 layers, and every layer thickness is 0.07mm, adopts symmetric mode shop layer.In the present embodiment, covering (6) can adopt carbon fiber composite material M55J to realize.
Grid ribs (7) is the base portion of loaded cylinder; In Fig. 2, provide the schematic perspective view of grid ribs (7), in Fig. 3, provided the partial enlarged drawing of grid ribs, as can be seen from the figure; The grid angle of cut (being the muscle angle) is between 30 °～45 °; The muscle spacing between 80mm～150mm, about to revolve muscle quantity identical, form the prismatic grid.Fig. 4 is the grid ribs schematic cross-section, and being shaped as of grid ribs cross section is trapezoidal, so that the demoulding.In the present embodiment, grid ribs (7) can adopt carbon fiber composite material T700 to realize, in other embodiments, also can adopt other light, high-strength materials.
Upper end frame (1), lower end frame (4) are the upper and lower edge of loaded cylinder, and they can directly utilize grid ribs and the continuous flange of covering fiber to form, thereby guarantee the continuity of end frame and cylindrical shell fiber, have improved the bonded assembly reliability.As shown in Figure 5, also can adopt reinforcing fiber to strengthen in the periphery of upper and lower end frame, to guarantee end frame thickness and connection reliability, in the present embodiment, described reinforcing fiber is the T300 carbon cloth.The upper and lower end frame adopts end frame and cylindrical shell co-curing technology moulding (as solidifying with vacuum bag hot pressing pot process), guarantees the compactness of goods.The mounting interface of loaded cylinder and transversary plate also is provided on upper end frame, the lower end frame.
In another embodiment, said loaded cylinder also comprises stringer (5), and said stringer (5) is positioned at the outside of said covering (6); Vertical with the upper and lower end frame; Its quantity has the 8-12 root, and the cross-sectional plane of every stringer is " T " font, is used to provide loaded cylinder and the satellite shaft connecting interface to structural slab.Said stringer (5) can be received on the covering of loaded cylinder through adhesive glue, and is as shown in Figure 6, for guaranteeing the bonded assembly reliability, also can be aided with bolt-nut and connect.Stringer (5) can adopt carbon fiber composite material T700 to realize in the present embodiment.
In yet another embodiment, on the basis of preceding two embodiment, said loaded cylinder also comprises outward flange (2), and said outward flange (2) laterally is nested in the outside of said covering (6), is used to provide the connecting interface of loaded cylinder and exterior satellite transversary plate.Said outward flange (2) can be connected on the covering of loaded cylinder through adhesive glue, for guaranteeing the bonded assembly reliability, also can be aided with bolt-nut and connect.In the present embodiment, outward flange (2) can adopt carbon fiber composite material T700 to realize.
In another embodiment; On the basis of embodiment before, said loaded cylinder also comprises inside flange (3), and said inside flange (3) is positioned at the inboard of said grid ribs (7); Parallel with said upper and lower end frame, be used to provide the connecting interface of loaded cylinder and hydrazine bottle adapter plate.Said inside flange (3) can glued joint the grid ribs (7) of loaded cylinder through adhesion agent, for guaranteeing the bonded assembly reliability, also can be aided with bolt-nut and connect.In the present embodiment, inside flange (3) can adopt carbon fiber composite material T700 to realize.
As a preferred embodiment, as shown in Figure 1, loaded cylinder of the present invention comprises upper end frame (1), outward flange (2), inside flange (3), lower end frame (4), stringer (5), covering (6) and grid ribs (7); Wherein, the external packets of said grid ribs (7) is wrapped with covering (6), forms cylindrical shell penetrating about in the of, and the upper edge of said cylindrical shell and lower edge include upper end frame (1) and lower end frame (4) respectively; The outside of said covering (6) laterally is nested with outward flange (2), vertically is connected with stringer (5); The inboard of said grid ribs (7) is horizontally connected with inside flange (3).
The latticed composite material load-carrying barrel structure of the present invention is suitably adjusted mesh parameter, covering parameter, just can satisfy the carrying needs of different loads, thereby can improve the comformability to load.Find through the experiment contrast; Remove auxiliary components such as interior outward flange, stringer; The mass ratio of loaded cylinder of the present invention has the aluminium honeycomb interlayer loaded cylinder loss of weight about 80% of same load-carrying capacity; Even auxiliary components such as interior outward flange, stringer are taken into account, it is about 40% that the mass ratio of loaded cylinder of the present invention has the aluminium honeycomb interlayer loaded cylinder loss of weight of same load-carrying capacity, is significant for the satellite structure loss of weight.
Claims (9)
1. the latticed composite material load-carrying tube of spacecraft is characterized in that, comprises upper end frame (1), lower end frame (4), covering (6) and grid ribs (7); Wherein,
The external packets of said grid ribs (7) is wrapped with covering (6), forms cylindrical shell penetrating about in the of, and the upper edge of said cylindrical shell and lower edge include upper end frame (1) and lower end frame (4) respectively;
It is identical to revolve muscle quantity about in the said grid ribs (7), forms the prismatic grid, and the muscle angle is between 30 °～45 °, and the muscle spacing is between 80mm～150mm;
Said upper end frame (1) forms through the fiber continuous flange of said grid ribs (7) with said covering (6) with lower end frame (4); The mounting interface that comprises said loaded cylinder and exterior transversary plate on said upper end frame (1), the lower end frame (4).
2. the latticed composite material load-carrying tube of spacecraft according to claim 1; It is characterized in that; Also comprise being used to provide said loaded cylinder and the satellite shaft stringer (5) to the connecting interface of structural slab, said stringer (5) is positioned at the outside of said covering (6), and is vertical with said upper and lower end frame; Its quantity has the 8-12 root, and the cross-sectional plane of every stringer is " T " font.
3. the latticed composite material load-carrying tube of spacecraft according to claim 2 is characterized in that said stringer (5) is received on the said covering (6) through adhesive glue, and is aided with bolt-nut connection.
4. the latticed composite material load-carrying tube of spacecraft according to claim 1 and 2; It is characterized in that; Also comprise the outward flange (2) of the connecting interface that is used to provide said loaded cylinder and exterior satellite transversary plate, said outward flange (2) laterally is nested in the outside of said covering (6).
5. according to claim 1 or the latticed composite material load-carrying tube of 2 or 4 described spacecrafts; It is characterized in that; The inside flange (3) that also comprises the connecting interface that is used to provide said loaded cylinder and exterior hydrazine bottle adapter plate; Said inside flange (3) is positioned at the inboard of said grid ribs (7), and is parallel with said upper and lower end frame.
6. according to claim 1 or the latticed composite material load-carrying tube of 2 or 4 or 5 described spacecrafts, it is characterized in that the height of loaded cylinder is between 1320mm～1380mm, barrel diameter is between 1100mm～1250mm.
7. according to claim 1 or the latticed composite material load-carrying tube of 2 or 4 or 5 described spacecrafts, it is characterized in that said covering (6) comprises 5～10 layers, every layer thickness is 0.07mm, adopts symmetric mode shop layer; Each layer covering (6) adopts carbon fiber composite material M55J to realize.
8. according to claim 1 or the latticed composite material load-carrying tube of 2 or 4 or 5 described spacecrafts, it is characterized in that said upper end frame (1) adopts reinforcing fiber to strengthen with the periphery of lower end frame (4).
9. according to claim 1 or the latticed composite material load-carrying tube of 2 or 4 or 5 described spacecrafts, it is characterized in that said grid ribs (7) adopts carbon fiber composite material T700 to realize.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011103624291A CN102424115A (en) | 2011-11-15 | 2011-11-15 | Spacecraft gridded composite bearing cylinder |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2011103624291A CN102424115A (en) | 2011-11-15 | 2011-11-15 | Spacecraft gridded composite bearing cylinder |
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| CN102424115A true CN102424115A (en) | 2012-04-25 |
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| CN2011103624291A Pending CN102424115A (en) | 2011-11-15 | 2011-11-15 | Spacecraft gridded composite bearing cylinder |
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Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102729482A (en) * | 2012-06-29 | 2012-10-17 | 中国人民解放军国防科学技术大学 | Composite heatproof bearing cylinder and preparation method thereof |
| CN102748999A (en) * | 2012-07-30 | 2012-10-24 | 上海宇航系统工程研究所 | Carbon fiber layer shell reinforced supporting cabin |
| CN102881991A (en) * | 2012-09-29 | 2013-01-16 | 西安空间无线电技术研究所 | High-carrying-capacity composite material insert |
| CN102937396A (en) * | 2012-11-02 | 2013-02-20 | 大连理工大学 | Double-scale grid stiffened cylindrical shell structure |
| CN103448918A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | Composite end frame spliced with bearing cylinder body fibers and bearing cylinder |
| CN103963997A (en) * | 2014-05-06 | 2014-08-06 | 上海卫星工程研究所 | Small satellite polygonal force bearing barrel |
| CN104290918A (en) * | 2014-09-12 | 2015-01-21 | 上海卫星工程研究所 | Miniaturized orbit tug satellite configuration and layout design method |
| CN104589663A (en) * | 2014-11-26 | 2015-05-06 | 上海复合材料科技有限公司 | Forming method for latticed composite material bearing cylinder applicable to satellite |
| CN104608915A (en) * | 2015-01-30 | 2015-05-13 | 中国人民解放军国防科学技术大学 | Multilayer grating bearing cylinder and preparation method thereof |
| CN106628259A (en) * | 2016-11-16 | 2017-05-10 | 上海卫星工程研究所 | Serial type high-rigidity integrated bearing structure |
| CN107226219A (en) * | 2017-06-28 | 2017-10-03 | 北京蓝箭空间科技有限公司 | A kind of anti-torsion row's hungry ghosts who spit fire's structure of vehicle thermal release interstage section |
| CN109080852A (en) * | 2018-06-20 | 2018-12-25 | 上海卫星工程研究所 | Covering aperture reinforcement loaded cylinder |
| WO2019000932A1 (en) * | 2017-06-28 | 2019-01-03 | 北京蓝箭空间科技有限公司 | Inter-stage segment structure for carrier and carrier |
| CN109854413A (en) * | 2019-03-13 | 2019-06-07 | 北京星际荣耀空间科技有限公司 | Tank cylinder section, tank and rocket |
| CN110395408A (en) * | 2019-07-03 | 2019-11-01 | 北京空间飞行器总体设计部 | A kind of interface structure of grid type load-carrying construction |
| CN111947018A (en) * | 2020-09-25 | 2020-11-17 | 天津爱思达新材料科技有限公司 | Composite material gas cylinder with internal grid ribs and winding forming method thereof |
| CN112123812A (en) * | 2020-08-05 | 2020-12-25 | 上海复合材料科技有限公司 | Large-size light composite material barrel with flange and integrated forming method thereof |
| CN116518795A (en) * | 2023-07-03 | 2023-08-01 | 江苏亨睿航空工业有限公司 | Carbon fiber composite satellite supporting cabin and preparation method thereof |
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| CN102729482A (en) * | 2012-06-29 | 2012-10-17 | 中国人民解放军国防科学技术大学 | Composite heatproof bearing cylinder and preparation method thereof |
| CN102729482B (en) * | 2012-06-29 | 2014-06-25 | 中国人民解放军国防科学技术大学 | Composite heatproof bearing cylinder and preparation method thereof |
| WO2014019328A1 (en) * | 2012-07-30 | 2014-02-06 | 上海宇航系统工程研究所 | Carbon fiber layer thin shell reinforced supporting cabin |
| CN102748999A (en) * | 2012-07-30 | 2012-10-24 | 上海宇航系统工程研究所 | Carbon fiber layer shell reinforced supporting cabin |
| CN102881991A (en) * | 2012-09-29 | 2013-01-16 | 西安空间无线电技术研究所 | High-carrying-capacity composite material insert |
| CN102937396A (en) * | 2012-11-02 | 2013-02-20 | 大连理工大学 | Double-scale grid stiffened cylindrical shell structure |
| CN103448918A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | Composite end frame spliced with bearing cylinder body fibers and bearing cylinder |
| CN103448918B (en) * | 2013-08-08 | 2016-08-10 | 上海卫星工程研究所 | With loaded cylinder canister fabric continuous print composite end frame and loaded cylinder |
| CN103963997A (en) * | 2014-05-06 | 2014-08-06 | 上海卫星工程研究所 | Small satellite polygonal force bearing barrel |
| CN104290918A (en) * | 2014-09-12 | 2015-01-21 | 上海卫星工程研究所 | Miniaturized orbit tug satellite configuration and layout design method |
| CN104290918B (en) * | 2014-09-12 | 2016-07-27 | 上海卫星工程研究所 | Miniaturization track towboat satellite configuration and layout design method |
| CN104589663A (en) * | 2014-11-26 | 2015-05-06 | 上海复合材料科技有限公司 | Forming method for latticed composite material bearing cylinder applicable to satellite |
| CN104589663B (en) * | 2014-11-26 | 2017-05-03 | 上海复合材料科技有限公司 | Forming method for latticed composite material bearing cylinder applicable to satellite |
| CN104608915A (en) * | 2015-01-30 | 2015-05-13 | 中国人民解放军国防科学技术大学 | Multilayer grating bearing cylinder and preparation method thereof |
| CN106628259A (en) * | 2016-11-16 | 2017-05-10 | 上海卫星工程研究所 | Serial type high-rigidity integrated bearing structure |
| WO2019000932A1 (en) * | 2017-06-28 | 2019-01-03 | 北京蓝箭空间科技有限公司 | Inter-stage segment structure for carrier and carrier |
| CN107226219B (en) * | 2017-06-28 | 2018-05-22 | 北京蓝箭空间科技有限公司 | A kind of anti-torsion row's hungry ghosts who spit fire's structure of vehicle thermal release interstage section |
| CN107226219A (en) * | 2017-06-28 | 2017-10-03 | 北京蓝箭空间科技有限公司 | A kind of anti-torsion row's hungry ghosts who spit fire's structure of vehicle thermal release interstage section |
| CN109080852B (en) * | 2018-06-20 | 2020-07-14 | 上海卫星工程研究所 | Skin perforated reinforced bearing cylinder |
| CN109080852A (en) * | 2018-06-20 | 2018-12-25 | 上海卫星工程研究所 | Covering aperture reinforcement loaded cylinder |
| CN109854413A (en) * | 2019-03-13 | 2019-06-07 | 北京星际荣耀空间科技有限公司 | Tank cylinder section, tank and rocket |
| CN109854413B (en) * | 2019-03-13 | 2024-03-01 | 北京星际荣耀空间科技股份有限公司 | Tank section, tank and rocket |
| CN110395408A (en) * | 2019-07-03 | 2019-11-01 | 北京空间飞行器总体设计部 | A kind of interface structure of grid type load-carrying construction |
| CN110395408B (en) * | 2019-07-03 | 2020-11-20 | 北京空间飞行器总体设计部 | Interface structure of grid type force bearing structure |
| CN112123812A (en) * | 2020-08-05 | 2020-12-25 | 上海复合材料科技有限公司 | Large-size light composite material barrel with flange and integrated forming method thereof |
| CN111947018A (en) * | 2020-09-25 | 2020-11-17 | 天津爱思达新材料科技有限公司 | Composite material gas cylinder with internal grid ribs and winding forming method thereof |
| CN111947018B (en) * | 2020-09-25 | 2022-01-07 | 天津爱思达新材料科技有限公司 | Winding forming method of composite material gas cylinder with internal grid ribs |
| CN116518795A (en) * | 2023-07-03 | 2023-08-01 | 江苏亨睿航空工业有限公司 | Carbon fiber composite satellite supporting cabin and preparation method thereof |
| CN116518795B (en) * | 2023-07-03 | 2023-09-15 | 江苏亨睿航空工业有限公司 | Carbon fiber composite satellite supporting cabin and preparation method thereof |
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Application publication date: 20120425 |