CN107323698A - Satellite-rocket docking uses the load barrel structure of composite end frame - Google Patents
Satellite-rocket docking uses the load barrel structure of composite end frame Download PDFInfo
- Publication number
- CN107323698A CN107323698A CN201710353840.XA CN201710353840A CN107323698A CN 107323698 A CN107323698 A CN 107323698A CN 201710353840 A CN201710353840 A CN 201710353840A CN 107323698 A CN107323698 A CN 107323698A
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- Prior art keywords
- end frame
- cylinder
- mounting flange
- satellite
- composite
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 239000002131 composite material Substances 0.000 title claims abstract description 29
- 238000003032 molecular docking Methods 0.000 title claims abstract description 14
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 14
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 14
- 239000000835 fiber Substances 0.000 claims abstract description 14
- 238000005728 strengthening Methods 0.000 claims description 8
- 238000010276 construction Methods 0.000 claims description 4
- 235000006508 Nelumbo nucifera Nutrition 0.000 claims 1
- 240000002853 Nelumbo nucifera Species 0.000 claims 1
- 235000006510 Nelumbo pentapetala Nutrition 0.000 claims 1
- 239000000463 material Substances 0.000 abstract description 7
- 230000005540 biological transmission Effects 0.000 abstract description 4
- 229920000049 Carbon (fiber) Polymers 0.000 description 6
- 239000004917 carbon fiber Substances 0.000 description 6
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 6
- 229910000838 Al alloy Inorganic materials 0.000 description 3
- 239000004593 Epoxy Substances 0.000 description 3
- 229910001069 Ti alloy Inorganic materials 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000037452 priming Effects 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/646—Docking or rendezvous systems
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
The invention provides the load barrel structure that a kind of satellite-rocket docking uses composite end frame, it includes cylinder, upper end frame, lower end frame, mounting flange, upper end frame and lower end frame are all embedded in cylinder, and be integrally formed with cylinder, mounting flange is located at the lower section of upper end frame, lower end frame is located at the lower section of mounting flange, and mounting flange is located at the lower section of cylinder.All structural members of the load barrel structure of the present invention in addition to strengthens angle box all use carbon fibre composite, and thickness design is carried out to cylinder covering, the weight of structure is greatly reduced on the premise of bearing requirements are met, configuration is simple, power transmission is direct, technical maturity, by the different designs to cylinder covering and upper and lower side frame material parameter to adapt to different application demand, with wide applicability.
Description
Technical field
The present invention relates to a kind of satellite structure, in particular it relates to which a kind of satellite-rocket docking uses the load of composite end frame
Barrel structure.
Background technology
Bearing cylinder is widely used in all kinds of satellite configurations, and as main force support structure, Bearing cylinder is born entirely
The Main Load of satellite simultaneously provides the enough horizontal, longitudinal directions of satellite and torsional rigidity, is directly provided and carrier rocket by lower end frame
The loaded cylinder of interface, to ensure that precision and carrying etc. are required generally using material of the aluminium alloy as lower end frame, but this is significantly
Add the weight of loaded cylinder.According to statistics, during using aluminium alloy as lower end frame material, its weight account for loaded cylinder gross weight 20%~
30%, this causes satellite structure light-weight design to face great challenge.
The content of the invention
For defect of the prior art, it is an object of the invention to provide a kind of satellite-rocket docking using composite end frame
Load barrel structure, all structural members of its load barrel structure in addition to strengthens angle box all use carbon fibre composite, and to cylinder
Body covering carries out thickness design, and the weight of structure is greatly reduced on the premise of bearing requirements are met, and configuration is simple, power transmission
Directly, technical maturity, by the different designs to cylinder covering and upper and lower side frame material parameter to adapt to different application demand, has
There is wide applicability.
According to an aspect of the present invention there is provided the load barrel structure that a kind of satellite-rocket docking uses composite end frame, its
Be characterised by, it includes cylinder, upper end frame, lower end frame, mounting flange, upper end frame and lower end frame are all embedded in cylinder, and with cylinder
Body by integral forming, mounting flange is located at the lower section of upper end frame, and lower end frame is located at the lower section of mounting flange, and mounting flange is located at cylinder
Lower section.
Preferably, the cross section of the lower end frame is the thin wall circular of π fonts, using carbon fibre composite, is embedded in
Cylinder simultaneously carries out local strengthening by angle box pair and carrier rocket link position.
Preferably, the cross section of the upper end frame is the thin wall circular of π fonts, using carbon fibre composite, is embedded in
Cylinder simultaneously carries out local strengthening by angle box pair and load link position.
Preferably, the cylinder is thin-wall conical cylinder, and using honeycomb sandwich construction, interior exterior skin is complete for Varying-thickness laying
Carbon fibre composite and built-in pre-buried beam.
Preferably, the cross section of the mounting flange is T-shaped thin wall circular, using carbon fibre composite, is passed through
It is glued and is connected to cylinder inner and outer with screw connection manner.
Compared with prior art, the present invention has following beneficial effect：Load barrel structure of the present invention is in addition to strengthens angle box
All structural members all use carbon fibre composite, and thickness design is carried out to cylinder covering, is meeting bearing requirements
On the premise of greatly reduce the weight of structure, configuration is simple, power transmission is direct, technical maturity, by cylinder covering and up and down
The different designs of frame material parameter are held to adapt to different application demand, with wide applicability.
Brief description of the drawings
By reading the detailed description made with reference to the following drawings to non-limiting example, further feature of the invention,
Objects and advantages will become more apparent upon：
Fig. 1 is the schematic diagram of the loaded cylinder of the present invention.
Fig. 2 is loaded cylinder part-structure schematic diagram of the invention.
Embodiment
With reference to specific embodiment, the present invention is described in detail.Following examples will be helpful to the technology of this area
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that to the ordinary skill of this area
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection domain.
As shown in Figure 1 to Figure 2, satellite-rocket docking of the present invention using composite end frame load barrel structure include cylinder 1, on
Frame 2, lower end frame 3, mounting flange 4 are held, upper end frame 2 and lower end frame 3 are all embedded in cylinder 1, and are integrally formed with cylinder 1, installed
Flange 4 is located at the lower section of upper end frame 2, and lower end frame 3 is located at the lower section of mounting flange 4, and mounting flange 4 is located at the lower section of cylinder 1.
The cross section of the lower end frame 3 is the thin wall circular of π fonts, using carbon fibre composite, is embedded in cylinder simultaneously
Local strengthening is carried out by angle box pair and carrier rocket link position.
The cross section of the upper end frame 2 is the thin wall circular of π fonts, using carbon fibre composite, is embedded in cylinder simultaneously
Local strengthening is carried out by angle box pair and load link position.
The cylinder 1 is thin-wall conical cylinder, using honeycomb sandwich construction, and interior exterior skin is the full carbon fiber of Varying-thickness laying
Composite and built-in pre-buried beam.
The cross section of the mounting flange 4 is T-shaped thin wall circular, using carbon fibre composite, by be glued with
Screw connection manner is connected to the inner and outer of cylinder 1.
Embodiment
The present embodiment is related to the load barrel structure that a kind of satellite-rocket docking uses composite end frame.
The loaded cylinder of the present embodiment is taper loaded cylinder, and its envelope size is Φ 3184mm × 1570mm, lower end frame interface
A diameter of Φ 3124mm, a diameter of Φ 1850mm of upper end frame interface, bearing capacity is 5t, by cylinder covering and upper and lower side frame
The different designs of material parameter are to adapt to different carrying demands.
Cylinder is honeycomb sandwich construction, and interior exterior skin is carbon fiber epoxy, and honeycomb core is 5A02 aluminium alloys, thickness
20mm；Interior exterior skin uses Varying-thickness laying, and thickness is by 0.7mm gradual changes to 0.9mm.
Upper end frame and lower end frame are all prepared using the pressurization of carbon fiber epoxy vacuum tank, and ply sequence is quasi-isotropic
Laying, is connected by way of being glued plus riveting with cylinder；Lower end frame is docked with carrier rocket using 12 priming systems, right
Connect position and local strengthening is carried out using titanium alloy TC 4 angle box；Upper end frame is connected with load, and titanium alloy TC 4 is used in docking location
Angle box carries out local strengthening.
Mounting flange is pressurizeed using carbon fiber epoxy vacuum tank and prepared, and ply sequence is quasi-isotropic laying, is led to
The mode for crossing glue connection added bolt connection is connected with cylinder, and sets reinforcement carbon fiber angle box in link position.
In summary, all structural members of the load barrel structure of the present invention in addition to strengthens angle box all use carbon fiber composite
Material, and thickness design is carried out to cylinder covering, the weight of structure, configuration are greatly reduced on the premise of bearing requirements are met
Simply, power transmission directly, technical maturity, by the different designs to cylinder covering and upper and lower side frame material parameter with adapt to it is different should
With demand, with wide applicability.
The specific embodiment of the present invention is described above.It is to be appreciated that the invention is not limited in above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring the substantive content of the present invention.
Claims (5)
1. a kind of satellite-rocket docking use composite end frame load barrel structure, it is characterised in that it include cylinder, upper end frame,
Lower end frame, mounting flange, upper end frame and lower end frame are all embedded in cylinder, and are integrally formed with cylinder, and mounting flange is located at upper end
The lower section of frame, lower end frame is located at the lower section of mounting flange, and mounting flange is located at the lower section of cylinder.
2. satellite-rocket docking according to claim 1 uses the load barrel structure of composite end frame, it is characterised in that described
The cross section of lower end frame is the thin wall circular of π fonts, using carbon fibre composite, is embedded in cylinder and by angle box pair and fortune
Carry rocket link position and carry out local strengthening.
3. satellite-rocket docking according to claim 1 uses the load barrel structure of composite end frame, it is characterised in that described
The cross section of upper end frame is the thin wall circular of π fonts, using carbon fibre composite, is embedded in cylinder and by angle box pair with carrying
Lotus link position carries out local strengthening.
4. satellite-rocket docking according to claim 1 uses the load barrel structure of composite end frame, it is characterised in that described
Cylinder is thin-wall conical cylinder, and using honeycomb sandwich construction, interior exterior skin is simultaneously interior for the full carbon fibre composite of Varying-thickness laying
Put pre-buried beam.
5. satellite-rocket docking according to claim 1 uses the load barrel structure of composite end frame, it is characterised in that described
The cross section of mounting flange is T-shaped thin wall circular, using carbon fibre composite, is connected to by being glued with screw connection manner
Cylinder inner and outer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710353840.XA CN107323698A (en) | 2017-05-18 | 2017-05-18 | Satellite-rocket docking uses the load barrel structure of composite end frame |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710353840.XA CN107323698A (en) | 2017-05-18 | 2017-05-18 | Satellite-rocket docking uses the load barrel structure of composite end frame |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107323698A true CN107323698A (en) | 2017-11-07 |
Family
ID=60192920
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710353840.XA Pending CN107323698A (en) | 2017-05-18 | 2017-05-18 | Satellite-rocket docking uses the load barrel structure of composite end frame |
Country Status (1)
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|---|---|
| CN (1) | CN107323698A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107792399A (en) * | 2017-09-25 | 2018-03-13 | 上海卫星工程研究所 | Tank test formula satellite platform structure |
| CN109823576A (en) * | 2019-02-20 | 2019-05-31 | 上海卫星工程研究所 | Bearer connection structure for planetary landing device |
| CN109835504A (en) * | 2019-02-26 | 2019-06-04 | 北京空间飞行器总体设计部 | A kind of tapered loaded cylinder of high-mechanic |
| CN109911246A (en) * | 2019-02-20 | 2019-06-21 | 上海卫星工程研究所 | Spacecraft composite structure is connected suitable for point type |
| 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 |
| CN114103158A (en) * | 2021-10-25 | 2022-03-01 | 湖北三江航天江北机械工程有限公司 | Forming method of special-shaped composite skirt of solid rocket engine |
| CN114162350A (en) * | 2021-12-01 | 2022-03-11 | 上海宇航系统工程研究所 | Sun orientation device main structure suitable for space station |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102490910A (en) * | 2011-11-15 | 2012-06-13 | 上海卫星工程研究所 | Composite sandwich-structured bearing cylinder for spacecrafts |
| CN203007475U (en) * | 2012-12-20 | 2013-06-19 | 湖南金博复合材料科技有限公司 | Composite material guide cylinder |
| CN103448919A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | Carbon-fiber skin and stringer reinforced bearing cylinder for satellite structure |
| CN103963997A (en) * | 2014-05-06 | 2014-08-06 | 上海卫星工程研究所 | Small satellite polygonal force bearing barrel |
| CN105594316B (en) * | 2013-02-05 | 2015-07-15 | 上海卫星工程研究所 | Grapefruit satellite hexagon honeycomb sandwich construction loaded cylinder |
-
2017
- 2017-05-18 CN CN201710353840.XA patent/CN107323698A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102490910A (en) * | 2011-11-15 | 2012-06-13 | 上海卫星工程研究所 | Composite sandwich-structured bearing cylinder for spacecrafts |
| CN203007475U (en) * | 2012-12-20 | 2013-06-19 | 湖南金博复合材料科技有限公司 | Composite material guide cylinder |
| CN105594316B (en) * | 2013-02-05 | 2015-07-15 | 上海卫星工程研究所 | Grapefruit satellite hexagon honeycomb sandwich construction loaded cylinder |
| CN103448919A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | Carbon-fiber skin and stringer reinforced bearing cylinder for satellite structure |
| CN103963997A (en) * | 2014-05-06 | 2014-08-06 | 上海卫星工程研究所 | Small satellite polygonal force bearing barrel |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107792399A (en) * | 2017-09-25 | 2018-03-13 | 上海卫星工程研究所 | Tank test formula satellite platform structure |
| CN109823576A (en) * | 2019-02-20 | 2019-05-31 | 上海卫星工程研究所 | Bearer connection structure for planetary landing device |
| CN109911246A (en) * | 2019-02-20 | 2019-06-21 | 上海卫星工程研究所 | Spacecraft composite structure is connected suitable for point type |
| CN109835504A (en) * | 2019-02-26 | 2019-06-04 | 北京空间飞行器总体设计部 | A kind of tapered loaded cylinder of high-mechanic |
| 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 |
| CN114103158A (en) * | 2021-10-25 | 2022-03-01 | 湖北三江航天江北机械工程有限公司 | Forming method of special-shaped composite skirt of solid rocket engine |
| CN114162350A (en) * | 2021-12-01 | 2022-03-11 | 上海宇航系统工程研究所 | Sun orientation device main structure suitable for space station |
| CN114162350B (en) * | 2021-12-01 | 2023-09-29 | 上海宇航系统工程研究所 | Main structure of sun alignment orientation device suitable for space station |
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| PB01 | Publication | ||
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| RJ01 | Rejection of invention patent application after publication | ||
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Application publication date: 20171107 |