CN103963997A - Small satellite polygonal force bearing barrel - Google Patents
Small satellite polygonal force bearing barrel Download PDFInfo
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- CN103963997A CN103963997A CN201410188592.4A CN201410188592A CN103963997A CN 103963997 A CN103963997 A CN 103963997A CN 201410188592 A CN201410188592 A CN 201410188592A CN 103963997 A CN103963997 A CN 103963997A
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- polygon
- cylindrical shell
- loaded cylinder
- satellite
- end frame
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Abstract
The invention discloses a small satellite polygonal force bearing barrel which comprises a barrel body. An upper end frame is glued at the top of the upper end of the barrel body in an embedded mode, a lower end frame is glued at the bottom of the lower end of the barrel body in an embedded mode, purlin strips are arranged at corners of the barrel body, a trepanning reinforcement frame is connected to the trepanning position of the barrel body in a glued mode, and a reinforcement corner box is arranged at the upper end of the lower end frame. The small satellite polygonal force bearing barrel solves the problems that the mass of the force bearing barrel is large, inconvenience is brought to installation on the surface of the barrel body, and the structural mode is complex, and has the advantages of being simple in structure, light in weight, multiple in installation face and the like.
Description
Technical field
The present invention relates to the load-carrying construction of satellite Main Load, be specifically related to one and be applied to grapefruit satellite polygon loaded cylinder.
Background technology
Loaded cylinder is the load-carrying construction of carrying satellite Main Load, it is the core of satellite structure assembling, the interface that can directly provide the system attachment faces such as propelling, satellite to be connected separation with carrier rocket, can provide for satellite structure again benchmark and test, the support of transport and the interface of ground-support equipment of design, manufacture, assembling, precision measure.Therefore, loaded cylinder is the crucial main force support structure that affects the performances such as satellite platform structural strength, rigidity and whole star dynamic response characteristic.
Summary of the invention
In order to solve the deficiencies such as in prior art, loaded cylinder quality is large, drum surface installation is inconvenient, version is complicated, the object of the present invention is to provide a kind of grapefruit satellite polygon loaded cylinder.The anti-loaded cylinder of boring of honeycomb sandwich construction that the invention provides a kind of integrated, lightweight, polygon design, is used for solving the problems of the technologies described above.
In order to reach foregoing invention object, the technical scheme that the present invention adopts for its technical matters of solution is to provide a kind of grapefruit satellite polygon loaded cylinder, comprise cylindrical shell, described cylindrical shell upper end top embedding glue has a upper end frame, described cylindrical shell lower end bottom embedding glue has a lower end frame, the corner of cylindrical shell is provided with stringer, and cylindrical shell tapping glueds joint has opening strengthening frame, frame upper end, described lower end to be provided with reinforcement angle box.
As preferably, described cylindrical shell is polygon plane, comprises inside panel, exterior skin and honeycomb core.
As preferably, the laying order of described inside panel and described exterior skin is (± 45 °/0 ° 3/ ± 45) symmetrical laying.
As preferably, described opening strengthening part, strengthen angle box, stringer all selects high intensity carbon fiber material T700S-12K mold pressing to form.
As preferably, described upper end frame is polygon, and reinforcing material is T700S-12K, and basis material is AG-80 epoxy resin, and for connection platform construction, described lower end frame is circular, and material is aluminum alloy, for the satellite and the rocket burbling area as 660 type bands.
As preferably, the profile of described stringer is T-shape.
As preferably, described cylindrical shell is the anti-taper of circle under upper polygon.
The present invention is due to covering, honeycomb, end frame, stringer etc. are carried out to specific selection, cylindrical shell, upper and lower side frame profile and connection mode are carried out to customized design, covering has been carried out to laying optimization, therefore, not only reach the requirement of integrated, lightweight, high rigidity, the aspect such as easy for installation, and loaded cylinder can bear the load weight of about 450KG, obtained simple in structure, integrated, quality light, have the beneficial effects such as more attachment face, application prospect is extensive.
Brief description of the drawings
Describe the present invention in detail below in conjunction with the drawings and specific embodiments;
Fig. 1 is structural representation of the present invention;
Fig. 2 is mount structure schematic diagram in upper end in Fig. 1;
Fig. 3 is opening strengthening part structural representation in Fig. 1;
Fig. 4 is stringer structural representation in Fig. 1;
Fig. 5 strengthens angle box structural representation in Fig. 1.
In figure, be labeled as: 1. upper end frame, 2. cylindrical shell, 3. lower end frame, 4. stringer, 5. strengthen angle box, 6. opening reinforcement.
Detailed description of the invention
For technological means, creation characteristic that the present invention is realized, reach object and effect is easy to understand, below in conjunction with detailed description of the invention, further set forth the present invention.
In the present embodiment, loaded cylinder whole height 320 ㎜.Upper end frame is that the length of side is the polygon of 510 ㎜, and lower end frame diameter is 660 ㎜.
As shown in Figure 1, this device comprises cylindrical shell 2, described cylindrical shell 2 top, upper end embedding glue have a upper end frame 1, described cylindrical shell 2 lower end bottom embedding glue have a lower end frame 3, six corners of described cylindrical shell 2 are provided with six stringers 4, described cylindrical shell 2 tappings glued joint opening strengthening part 6, and frame 3 upper ends, described lower end are provided with six and strengthen angle box 5.
Wherein, described cylindrical shell 2 is hexagon, comprises inside panel, exterior skin and honeycomb core; Inside panel, exterior skin are carbon/epoxy composite material, and reinforcing material is M55J-6k carbon fiber, and basis material is epoxy AG-80 resin matrix, and laying order is ± 45 °/0 °
3/ ± 45 symmetrical layings; Honeycomb core adopts material to be LF2Y, highly to be the porose durability aluminium honeycomb that 6.5mm, specification are 4-0.04; Inside panel, exterior skin and aluminium honeycomb core adopt the J78B adhesion agent of thickness 0.15mm to glued joint, and under 90 DEG C of high temperature, solidify, and form cylindrical shell 2; The inside and outside surface of cylindrical shell is for installing the instrument of the systems such as propelling.
Wherein, described lower end frame 3 is circular, and material is aluminum alloy, as the satellite and the rocket burbling area of 660 type bands, simultaneously for propulsion module dashboard provides mounting interface.
As shown in Figure 2, described upper end frame 1 is hexagon, selects high intensity carbon fiber material T700S-12K, and basis material is AG-80 epoxy resin, forms through mold pressing, and the oad of described upper end frame 1 is that external diameter is the hexagon of φ 1020mm, and wall thickness is 6mm.
As shown in Figure 3, described opening reinforcement 6 selects high intensity carbon fiber material T700S-12K mold pressing to form, and glueds joint, for the reinforcement to tapping by the tapping of Redux420 adhesion agent and cylindrical shell 2.
As shown in Figure 4, described stringer 4 profiles are T-shape, select high intensity carbon fiber material T700S-12K mold pressing to form, and are connected on six corners of cylindrical shell 2 by Redux420 adhesive glue, and to loaded cylinder, corner strengthens.
As shown in Figure 5, described reinforcement angle box 5 selects high intensity carbon fiber material T700S-12K mold pressing to form, and is connected on lower end frame 1 by Redux420 adhesive glue, and loaded cylinder lower end frame is strengthened.
In addition,, as long as the thickness of cylindrical shell is suitably adjusted, just can meet the carrying needs of different quality satellite, thereby improve the comformability to load.
In sum, prove through the tests such as whole star mode, vibration, noise and loaded cylinder static test, grapefruit satellite polygon loaded cylinder of the present invention has reached simple in structure, integrated, high rigidity, has been convenient to the objects such as installation, can realize the carrying of 450KG left and right, has met preferably the requirement of system.
The above is the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, do not departing under the prerequisite of principle of the present invention; can also make some improvements and modifications, these improvements and modifications also should be considered as protection scope of the present invention.
Claims (7)
1. a grapefruit satellite polygon loaded cylinder, comprise cylindrical shell (2), it is characterized in that: described cylindrical shell (2) top, upper end embedding glue has a upper end frame (1), described cylindrical shell (2) lower end bottom embedding glue has a lower end frame (3), the corner of cylindrical shell (2) is provided with stringer (4), cylindrical shell (2) tapping glueds joint has opening strengthening frame (6), described lower end frame (3) upper end to be provided with reinforcement angle box (5).
2. a kind of grapefruit satellite polygon loaded cylinder according to claim 1, is characterized in that: described cylindrical shell (2) is polygon plane, comprises inside panel, exterior skin and honeycomb core.
3. a kind of grapefruit satellite polygon loaded cylinder according to claim 2, is characterized in that: the laying order of described inside panel and described exterior skin is (± 45 °/0 ° 3/ ± 45) symmetrical laying.
4. a kind of grapefruit satellite polygon loaded cylinder according to claim 1, is characterized in that: described opening strengthening part (6), reinforcement angle box (5), stringer (4) all select high intensity carbon fiber material T700S-12K mold pressing to form.
5. a kind of grapefruit satellite polygon loaded cylinder according to claim 1, it is characterized in that: described upper end frame (1) is polygon, reinforcing material is T700S-12K, basis material is AG-80 epoxy resin, for connection platform construction, described lower end frame (3) is circular, and material is aluminum alloy, for the satellite and the rocket burbling area as 660 type bands.
6. a kind of grapefruit satellite polygon loaded cylinder according to claim 1, is characterized in that: the profile of described stringer (4) is T-shape.
7. a kind of grapefruit satellite polygon loaded cylinder according to claim 1, is characterized in that: described cylindrical shell (2) is the anti-taper of circle under upper polygon.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410188592.4A CN103963997A (en) | 2014-05-06 | 2014-05-06 | Small satellite polygonal force bearing barrel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410188592.4A CN103963997A (en) | 2014-05-06 | 2014-05-06 | Small satellite polygonal force bearing barrel |
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| CN103963997A true CN103963997A (en) | 2014-08-06 |
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| CN201410188592.4A Pending CN103963997A (en) | 2014-05-06 | 2014-05-06 | Small satellite polygonal force bearing barrel |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104309824A (en) * | 2014-09-12 | 2015-01-28 | 上海卫星工程研究所 | Satellite configuration of embedded compound eye camera load |
| CN104369874A (en) * | 2014-10-28 | 2015-02-25 | 上海卫星工程研究所 | Integrated heat control device for aircraft with complex external strength bearing cylinder structure |
| CN105438503A (en) * | 2015-11-30 | 2016-03-30 | 中国空间技术研究院 | Satellite and rocket docking device |
| CN105480435A (en) * | 2015-12-02 | 2016-04-13 | 上海宇航系统工程研究所 | Large honeycomb sandwich bearing cylinder |
| CN105527685A (en) * | 2016-01-28 | 2016-04-27 | 长光卫星技术有限公司 | Main bearing member for optical minimal satellite and common structure of optical camera |
| 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 |
| CN107323694A (en) * | 2017-05-18 | 2017-11-07 | 上海卫星工程研究所 | Modular satellite booster cabin |
| CN109015510A (en) * | 2018-07-26 | 2018-12-18 | 北京卫星环境工程研究所 | The stringer installation method of sealed compartment time structure Instrumental mounting platform |
| CN109080852A (en) * | 2018-06-20 | 2018-12-25 | 上海卫星工程研究所 | Covering aperture reinforcement loaded cylinder |
| CN111409875A (en) * | 2020-03-19 | 2020-07-14 | 上海卫星工程研究所 | Composite material bearing structure suitable for space vehicle separation cabin section |
| 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 |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104309824A (en) * | 2014-09-12 | 2015-01-28 | 上海卫星工程研究所 | Satellite configuration of embedded compound eye camera load |
| CN104369874A (en) * | 2014-10-28 | 2015-02-25 | 上海卫星工程研究所 | Integrated heat control device for aircraft with complex external strength bearing cylinder structure |
| CN104369874B (en) * | 2014-10-28 | 2016-08-24 | 上海卫星工程研究所 | The outer loaded cylinder aircraft integration thermal controls apparatus of complex configuration |
| CN105438503B (en) * | 2015-11-30 | 2018-02-09 | 中国空间技术研究院 | A kind of satellite-rocket docking device |
| CN105438503A (en) * | 2015-11-30 | 2016-03-30 | 中国空间技术研究院 | Satellite and rocket docking device |
| CN105480435A (en) * | 2015-12-02 | 2016-04-13 | 上海宇航系统工程研究所 | Large honeycomb sandwich bearing cylinder |
| CN105527685A (en) * | 2016-01-28 | 2016-04-27 | 长光卫星技术有限公司 | Main bearing member for optical minimal satellite and common structure of optical camera |
| 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 |
| CN107323694A (en) * | 2017-05-18 | 2017-11-07 | 上海卫星工程研究所 | Modular satellite booster cabin |
| CN109080852A (en) * | 2018-06-20 | 2018-12-25 | 上海卫星工程研究所 | Covering aperture reinforcement loaded cylinder |
| CN109015510A (en) * | 2018-07-26 | 2018-12-18 | 北京卫星环境工程研究所 | The stringer installation method of sealed compartment time structure Instrumental mounting platform |
| 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 |
| CN111409875A (en) * | 2020-03-19 | 2020-07-14 | 上海卫星工程研究所 | Composite material bearing structure suitable for space vehicle separation cabin section |
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Application publication date: 20140806 |
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