CN102490910A - Composite sandwich-structured bearing cylinder for spacecrafts - Google Patents
Composite sandwich-structured bearing cylinder for spacecrafts Download PDFInfo
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- CN102490910A CN102490910A CN2011103624520A CN201110362452A CN102490910A CN 102490910 A CN102490910 A CN 102490910A CN 2011103624520 A CN2011103624520 A CN 2011103624520A CN 201110362452 A CN201110362452 A CN 201110362452A CN 102490910 A CN102490910 A CN 102490910A
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Abstract
The invention relates to a composite sandwich-structured bearing cylinder for spacecrafts, which comprises an upper end frame (1), an outer flange (2), an inner flange (3), a lower end frame (4), purlins (5), an outer skin (6), an inner skin (7), a honeycomb core (8), a stepped hole insert (9), a threaded hole insert (10), a glue film (11), Styrofoam (12), screws (13) and nuts (14). The composite sandwich-structured bearing cylinder for spacecrafts is designed according to connection requirements of different structures, designs of parting surfaces and end frames are reduced, and weight of a satellite structure can be reduced.
Description
Technical field
The present invention relates to a kind of loaded cylinder, particularly a kind of spacecraft composite material sandwich structure loaded cylinder.
Background technology
Loaded cylinder is as the main force support structure of spacecraft; It is spacecraft structure stack-mounted core component; It not only bears the basic load of whole spacecraft, and the benchmark of spacecraft design and processes is provided, and also will assemble on ground, tests, transports, the mechanical interface of the bearing surface when storing and spacecraft and ground-support equipment; Usually also utilize the loaded cylinder inner space, for propellant tank provides mounting interface and space.
Before the present invention, mostly the loaded cylinder of spacecraft is versions such as bare hull, Corrugated Shells, grid reinforcement shell, stringer reinforcement shell, and material is main with aluminum alloy also, and redundancy structure is many and structural weight is big.
The present invention has designed the composite material sandwich structure loaded cylinder; Adopt carbon fiber composite material covering, aluminium honeycomb core to alleviate structural weight greatly,, inside and outside cylindrical shell, gluedd joint butt flange and stringer respectively simultaneously according to structure connection needs; For guaranteeing to glued joint reliability; To glueing joint regional separation screw, be aided with mechanical connection, in case anti-avulsion glue.The present invention, the loss of weight of favourable and spacecraft structure improves the spacecraft structure overall performance.
Summary of the invention
For rigidity and the weight issue that solves the spacecraft main force support structure; The object of the present invention is to provide spacecraft composite material sandwich structure loaded cylinder; Utilize the present invention, not only reach and improve spacecraft structure rigidity, alleviate spacecraft structure weight; And can improve the ability that satellite carries capacity weight, improve the ratio performance of satellite.
In order to reach the foregoing invention purpose; The technical scheme that the present invention is adopted for its technical matters of solution provides a kind of spacecraft composite material sandwich structure loaded cylinder; It is characterized in that comprising: upper end frame [1], outward flange [2], inside flange [3], lower end frame [4], stringer [5]; Said loaded cylinder is the column tube of both ends open, and its upper limb glueds joint upper end frame [1], the fixing lower end frame [4] that glueds joint of lower edge, and the outside face of said loaded cylinder is along circumferentially glueing joint outward flange [2]; The inside face of said loaded cylinder is along circumferentially glueing joint inside flange [3], and the outside face of said loaded cylinder is provided with stringer vertically.
The cylindrical shell of wherein said loaded cylinder comprises exterior skin [6], inside panel [7], honeycomb core [8]; Said exterior skin; Inside panel and honeycomb core solidify splicing through glued membrane [11]; In the said cylindrical shell along the direction of vertical drum surface pre-buried or after bury and be used for and a plurality of stepped hole insertss of other structure bonded assembly [9] and tapped bore inserts [10], said stepped hole inserts [9] and tapped bore inserts [10] be filling-foam glue [12] on every side, with honeycomb core [8] splicing be one.
Mechanical joints with other framing member is all arranged on wherein said upper end frame [1], the lower end frame [4], the connecting interface with other framing member is all arranged on said outward flange [2], inside flange [3] and the stringer [5].
Wherein screw [13] is screwed into tapped bore inserts [10] or screw [13] is passed exterior skin [6], lower end frame [4], inside panel [7], use nut [14] to connect again to strengthen being connected of said upper end frame [1], outward flange [2], inside flange [3], lower end frame [4] and stringer [5].
Wherein said upper end frame [1], lower end frame [4] can be aluminum alloy materials, titanium alloy material, magnesium alloy materials or carbon fiber composite material; Described outward flange [2], inside flange [3], stringer [5] can be aluminum alloy materials, titanium alloy material, magnesium alloy materials or carbon fiber composite material; Described exterior skin [6], inside panel [7] are aluminum alloy materials or carbon fiber composite material; Described honeycomb core [8] is aluminium honeycomb core material or aramid fiber paper substrate honeycomb core, and described stepped hole inserts [9], tapped bore inserts [10] are aluminum alloy materials, magnesium alloy materials, titanium alloy material or the metal matrix composite that comprises aluminium base carborundum etc.
Wherein said glued membrane [11] is middle temperature structural adhesion or thermal structure glue; Film thickness is 0.1mm to 0.5mm; Described foamed glue [12] is middle temperature foamed glue or high temperature foamed glue, is filled in stepped hole inserts [9], tapped bore inserts [10] on every side in the 10mm scope.
Described screw [13], nut [14] can be titanium alloy material, alloy steel material or aluminum alloy materials.
Spacecraft composite material sandwich structure loaded cylinder of the present invention; Owing to take technique scheme, therefore, solved the low and big problem of weight of rigidity of spacecraft main force support structure; Through on cylindrical shell, glueing joint end frame, flange and stringer, realized and being connected of other framing members of spacecraft; Through at cylindrical shell embedded set inserts, realized that the installation of instrument and equipment on cylindrical shell is with fixing; Be spirally connected and when end frame, flange and stringer glued joint, be aided with, effectively avoided the influence of covering degumming problem.Adopt the composite material sandwich structure loaded cylinder, not only improve spacecraft structure rigidity, alleviate spacecraft structure weight, and can improve the ability that satellite carries capacity weight, improve the ratio performance of satellite.
Description of drawings
Fig. 1 is a spacecraft composite material sandwich structure loaded cylinder block diagram;
Fig. 2 illustrates cylindrical shell longitdinal cross-section diagram and internal structure;
Fig. 3 illustrates the partial view of stringer on cylindrical shell;
1-upper end frame wherein, 2-outward flange, 3-inside flange, 4-lower end frame, 5-stringer, 6-exterior skin, 7-inside panel, 8-honeycomb core, 9-stepped hole inserts, 10-tapped bore inserts, 11-glued membrane, 12-foamed glue, 13-screw, 14-nut.
The specific embodiment
Below in conjunction with description of drawings the preferred embodiments of the present invention.
Fig. 1 is a spacecraft composite material sandwich structure loaded cylinder block diagram; Fig. 2 can see the barrel structure for the present invention is a spacecraft composite material sandwich structure loaded cylinder longitdinal cross-section diagram, and Fig. 3 is the partial view of stringer on cylindrical shell.
Shown in the embodiment of accompanying drawing, this device comprises: upper end frame 1, outward flange 2, inside flange 3, lower end frame 4, stringer 5, exterior skin 6, inside panel 7, honeycomb core 8, stepped hole inserts 9, tapped bore inserts 10, glued membrane 11, foamed glue 12, screw 13, nut 14.Upper end frame [1], outward flange [2], inside flange [3], lower end frame [4], stringer [5]; Said loaded cylinder is the column tube of both ends open; Its upper limb glueds joint upper end frame [1], the fixing lower end frame [4] that glueds joint of lower edge; The outside face of said loaded cylinder is along circumferentially glueing joint outward flange [2], and the inside face of said loaded cylinder is along circumferentially glueing joint inside flange [3], and the outside face of said loaded cylinder is provided with stringer vertically.
The cylindrical shell of wherein said loaded cylinder comprises exterior skin [6], inside panel [7], honeycomb core [8]; Said exterior skin; Inside panel and honeycomb core solidify splicing through glued membrane [11]; In the said cylindrical shell along the direction of vertical drum surface pre-buried or after bury and be used for and a plurality of stepped hole insertss of other structure bonded assembly [9] and tapped bore inserts [10], said stepped hole inserts [9] and tapped bore inserts [10] be filling-foam glue [12] on every side, with honeycomb core [8] splicing be one.
Mechanical joints with other framing member is all arranged on wherein said upper end frame [1], the lower end frame [4], the connecting interface with other framing member is all arranged on said outward flange [2], inside flange [3] and the stringer [5].Upper end frame 1, lower end frame 4 is all unrestricted with the diameter and the quantity of the connecting bore of other framing member, can confirm according to the spacecraft structure design demand, and the hole is processed in cylindrical shell and solidifies and forward and backwardly all can implement;
For guaranteeing the connection of parts such as upper end frame 1, outward flange 2, inside flange 3, lower end frame 4, stringer 5; Adopt screw 13 auxiliary reinforcements; Screw [13] is screwed into tapped bore inserts [10] or screw [13] is passed exterior skin [6], lower end frame [4], inside panel [7], use nut [14] to connect again to strengthen the connection reliability of said upper end frame [1], outward flange [2], inside flange [3], lower end frame [4] and stringer [5].Screw 13, nut 14 can be titanium alloy material, alloy steel material or aluminum alloy materials, and screw 13, the model of nut 14, specification are not limit.
Wherein said upper end frame [1], lower end frame [4] can be aluminum alloy materials, titanium alloy material, magnesium alloy materials or carbon fiber composite material; Described outward flange [2], inside flange [3], stringer [5] can be aluminum alloy materials, titanium alloy material, magnesium alloy materials or carbon fiber composite material; Outward flange 2, inside flange 3, stringer 5 position and the quantity on loaded cylinder is unrestricted; All can confirm according to the spacecraft structure design demand; Outward flange 2, inside flange 3, stringer 5 is unrestricted with the diameter and the quantity of the connecting bore of other framing member, all can confirm according to the spacecraft structure design demand, and the hole is processed in cylindrical shell and solidifies and forward and backwardly all can implement.
Described exterior skin [6], inside panel [7] are aluminum alloy materials or carbon fiber composite material, and described honeycomb core [8] is aluminium honeycomb core material or aramid fiber paper substrate honeycomb core, and honeycomb thickness and core lattice size are not limit; Described stepped hole inserts [9], tapped bore inserts [10] are aluminum alloy materials, magnesium alloy materials, titanium alloy material or the metal matrix composite that comprises aluminium base carborundum etc.
Wherein said glued membrane [11] is middle temperature structural adhesion or thermal structure glue; Film thickness is 0.1mm to 0.5mm; Described foamed glue [12] is middle temperature foamed glue or high temperature foamed glue, is filled in stepped hole inserts [9], tapped bore inserts [10] on every side in the 10mm scope.
From the above mentioned, spacecraft composite material sandwich structure loaded cylinder of the present invention glueds joint end frame, flange and stringer on cylindrical shell, has realized and being connected of other framing members of spacecraft; At cylindrical shell embedded set inserts, realized that the installation of instrument and equipment on cylindrical shell is with fixing; Be spirally connected and when end frame, flange and stringer glued joint, be aided with, effectively avoided the influence of covering degumming problem.
Claims (7)
1. spacecraft composite material sandwich structure loaded cylinder; It is characterized in that comprising: upper end frame [1], outward flange [2], inside flange [3], lower end frame [4], stringer [5]; Said loaded cylinder is the column tube of both ends open, and its upper limb glueds joint upper end frame [1], the fixing lower end frame [4] that glueds joint of lower edge, and the outside face of said loaded cylinder is along circumferentially glueing joint outward flange [2]; The inside face of said loaded cylinder is along circumferentially glueing joint inside flange [3], and the outside face of said loaded cylinder is provided with stringer vertically.
2. spacecraft composite material sandwich structure loaded cylinder as claimed in claim 1; The cylindrical shell that it is characterized in that said loaded cylinder comprises exterior skin [6], inside panel [7], honeycomb core [8]; Said exterior skin; Inside panel and honeycomb core solidify splicing through glued membrane [11]; In the said cylindrical shell along the direction of vertical drum surface pre-buried or after bury and be used for and a plurality of stepped hole insertss of other structure bonded assembly [9] and tapped bore inserts [10], said stepped hole inserts [9] and tapped bore inserts [10] be filling-foam glue [12] on every side, with honeycomb core [8] splicing be one.
3. spacecraft composite material sandwich structure loaded cylinder as claimed in claim 1; It is characterized in that all having on said upper end frame [1], the lower end frame [4] mechanical joints with other framing member, the connecting interface with other framing member is all arranged on said outward flange [2], inside flange [3] and the stringer [5].
4. spacecraft composite material sandwich structure loaded cylinder as claimed in claim 2; It is characterized in that screw [13] is screwed into tapped bore inserts [10] or screw [13] is passed exterior skin [6], lower end frame [4], inside panel [7], use nut [14] to connect again to strengthen being connected of said upper end frame [1], outward flange [2], inside flange [3], lower end frame [4] and stringer [5].
5. spacecraft composite material sandwich structure loaded cylinder as claimed in claim 4; It is characterized in that: described upper end frame [1], lower end frame [4] can be aluminum alloy materials, titanium alloy material, magnesium alloy materials or carbon fiber composite material; Described outward flange [2], inside flange [3], stringer [5] can be aluminum alloy materials, titanium alloy material, magnesium alloy materials or carbon fiber composite material; Described exterior skin [6], inside panel [7] are aluminum alloy materials or carbon fiber composite material; Described honeycomb core [8] is aluminium honeycomb core material or aramid fiber paper substrate honeycomb core, and described stepped hole inserts [9], tapped bore inserts [10] are aluminum alloy materials, magnesium alloy materials, titanium alloy material or the metal matrix composite that comprises aluminium base carborundum etc.
6. spacecraft composite material sandwich structure loaded cylinder as claimed in claim 2; It is characterized in that: described glued membrane [11] is middle temperature structural adhesion or thermal structure glue; Film thickness is 0.1mm to 0.5mm; Described foamed glue [12] is middle temperature foamed glue or high temperature foamed glue, is filled in stepped hole inserts [9], tapped bore inserts [10] on every side in the 10mm scope.
7. spacecraft composite material sandwich structure loaded cylinder according to claim 1 is characterized in that: described screw [13], nut [14] can be titanium alloy material, alloy steel material or aluminum alloy materials.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN2011103624520A CN102490910A (en) | 2011-11-15 | 2011-11-15 | Composite sandwich-structured bearing cylinder for spacecrafts |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2011103624520A CN102490910A (en) | 2011-11-15 | 2011-11-15 | Composite sandwich-structured bearing cylinder for spacecrafts |
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| CN102490910A true CN102490910A (en) | 2012-06-13 |
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| CN2011103624520A Pending CN102490910A (en) | 2011-11-15 | 2011-11-15 | Composite sandwich-structured bearing cylinder for spacecrafts |
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| 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 |
| CN103605252A (en) * | 2013-11-29 | 2014-02-26 | 中国科学院长春光学精密机械与物理研究所 | Integrated structure of center force bearing barrel and light shield |
| CN103963997A (en) * | 2014-05-06 | 2014-08-06 | 上海卫星工程研究所 | Small satellite polygonal force bearing barrel |
| CN104527995A (en) * | 2014-12-09 | 2015-04-22 | 中国科学院上海技术物理研究所 | Antistatic metal honeycomb core composite material veneer structure |
| 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 |
| CN104698509A (en) * | 2013-12-10 | 2015-06-10 | 上海卫星工程研究所 | Geostationary orbit meteorological satellite |
| CN105480435A (en) * | 2015-12-02 | 2016-04-13 | 上海宇航系统工程研究所 | Large honeycomb sandwich bearing cylinder |
| CN105881888A (en) * | 2016-04-07 | 2016-08-24 | 山东英特力新材料有限公司 | Method for mounting equipment on composite material sandwich panel |
| CN106482589A (en) * | 2016-12-13 | 2017-03-08 | 中国运载火箭技术研究院 | A kind of stringer housing |
| CN107323698A (en) * | 2017-05-18 | 2017-11-07 | 上海卫星工程研究所 | Satellite-rocket docking uses the load barrel structure of composite end frame |
| CN107538758A (en) * | 2017-09-08 | 2018-01-05 | 陕西飞机工业（集团）有限公司 | A kind of composite material connection method |
| CN108725844A (en) * | 2018-06-26 | 2018-11-02 | 北京蓝箭空间科技有限公司 | The control cabin structure of space launch vehicle |
| CN110104213A (en) * | 2019-04-23 | 2019-08-09 | 上海宇航系统工程研究所 | A kind of wall-hanging satellite adapter |
| CN111422377A (en) * | 2020-03-10 | 2020-07-17 | 上海卫星工程研究所 | Structure suitable for satellite and facilitating assembly of double-layer flange type bearing cylinder and laminate |
| CN111475918A (en) * | 2020-03-10 | 2020-07-31 | 上海卫星工程研究所 | Method for quickly creating bearing cylinder three-dimensional model |
| CN111846290A (en) * | 2020-08-06 | 2020-10-30 | 北京中科宇航技术有限公司 | Carrier rocket and launching support tail section thereof |
| CN111927910A (en) * | 2020-06-18 | 2020-11-13 | 北京遥感设备研究所 | Aluminum-magnesium alloy integrated multifunctional integrated structure |
| RU2747562C1 (en) * | 2020-08-26 | 2021-05-06 | Акционерное общество «Информационные спутниковые системы» имени академика М.Ф.Решетнёва» | Support unit of the honeycomb panel and the method for assembling the support unit |
| CN117516297A (en) * | 2023-12-04 | 2024-02-06 | 北京中科宇航技术有限公司 | Inverted cone structure of rocket fairing |
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| 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 |
| CN102881991B (en) * | 2012-09-29 | 2014-10-08 | 西安空间无线电技术研究所 | High-carrying-capacity composite material insert |
| CN103605252B (en) * | 2013-11-29 | 2016-07-06 | 中国科学院长春光学精密机械与物理研究所 | Bearing cylinder and shade integral structure |
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| 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 |
| CN104527995A (en) * | 2014-12-09 | 2015-04-22 | 中国科学院上海技术物理研究所 | Antistatic metal honeycomb core composite material veneer structure |
| CN104527995B (en) * | 2014-12-09 | 2016-08-24 | 中国科学院上海技术物理研究所 | A kind of metal honeycomb core composite single plate structure of antistatic |
| 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 |
| CN105480435A (en) * | 2015-12-02 | 2016-04-13 | 上海宇航系统工程研究所 | Large honeycomb sandwich bearing cylinder |
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| CN107323698A (en) * | 2017-05-18 | 2017-11-07 | 上海卫星工程研究所 | Satellite-rocket docking uses the load barrel structure of composite end frame |
| CN107538758A (en) * | 2017-09-08 | 2018-01-05 | 陕西飞机工业（集团）有限公司 | A kind of composite material connection method |
| CN108725844A (en) * | 2018-06-26 | 2018-11-02 | 北京蓝箭空间科技有限公司 | The control cabin structure of space launch vehicle |
| CN110104213A (en) * | 2019-04-23 | 2019-08-09 | 上海宇航系统工程研究所 | A kind of wall-hanging satellite adapter |
| CN110104213B (en) * | 2019-04-23 | 2022-08-12 | 上海宇航系统工程研究所 | Wall-mounted satellite adapter |
| CN111422377B (en) * | 2020-03-10 | 2021-10-15 | 上海卫星工程研究所 | Structure suitable for satellite and facilitating assembly of double-layer flange type bearing cylinder and laminate |
| CN111475918A (en) * | 2020-03-10 | 2020-07-31 | 上海卫星工程研究所 | Method for quickly creating bearing cylinder three-dimensional model |
| CN111422377A (en) * | 2020-03-10 | 2020-07-17 | 上海卫星工程研究所 | Structure suitable for satellite and facilitating assembly of double-layer flange type bearing cylinder and laminate |
| CN111927910A (en) * | 2020-06-18 | 2020-11-13 | 北京遥感设备研究所 | Aluminum-magnesium alloy integrated multifunctional integrated structure |
| CN111846290A (en) * | 2020-08-06 | 2020-10-30 | 北京中科宇航技术有限公司 | Carrier rocket and launching support tail section thereof |
| RU2747562C1 (en) * | 2020-08-26 | 2021-05-06 | Акционерное общество «Информационные спутниковые системы» имени академика М.Ф.Решетнёва» | Support unit of the honeycomb panel and the method for assembling the support unit |
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Application publication date: 20120613 |