CN114659415A - Lightweight cabin section structure of carrier - Google Patents
Lightweight cabin section structure of carrier Download PDFInfo
- Publication number
- CN114659415A CN114659415A CN202210192067.4A CN202210192067A CN114659415A CN 114659415 A CN114659415 A CN 114659415A CN 202210192067 A CN202210192067 A CN 202210192067A CN 114659415 A CN114659415 A CN 114659415A
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- section
- reinforcing
- shell
- end frame
- box
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Links
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 78
- 238000005728 strengthening Methods 0.000 claims abstract description 32
- 230000002093 peripheral effect Effects 0.000 claims abstract description 20
- 238000009434 installation Methods 0.000 claims description 11
- 235000017166 Bambusa arundinacea Nutrition 0.000 claims description 9
- 235000017491 Bambusa tulda Nutrition 0.000 claims description 9
- 241001330002 Bambuseae Species 0.000 claims description 9
- 235000015334 Phyllostachys viridis Nutrition 0.000 claims description 9
- 239000011425 bamboo Substances 0.000 claims description 9
- 230000002787 reinforcement Effects 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 3
- 210000003205 muscle Anatomy 0.000 description 4
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 238000004026 adhesive bonding Methods 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000011208 reinforced composite material Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
Abstract
The application relates to a lightweight cabin section structure of a carrier, which comprises a column section shell and a cone section shell which are integrally formed, wherein an annular middle end frame is arranged at the joint of the column section shell and the cone section shell, an annular upper end frame is arranged on the inner peripheral wall of the end part of the column section shell far away from the middle end frame, and a lower end frame is arranged on the inner peripheral wall of the end part of the cone section shell far away from the middle end frame; the internal perisporium of post section casing is provided with first additional strengthening, and first additional strengthening connects between upper end frame and middle end frame, and the inside of conic section casing is provided with the second additional strengthening, and the outer wall of conic section casing is provided with the third additional strengthening. The application has the following expected technical effects: the structural form of skin and stringer semi-hard shells, the shell structure integrating the column section shell and the cone section shell, and the combination of three reinforcing structures of a first reinforcing structure, a second reinforcing structure and a third reinforcing structure are adopted, so that the overall strength and rigidity of the cabin section are improved, the structural weight is reduced, and the carrying capacity of the carrier rocket is improved.
Description
Technical Field
The application relates to the technical field of carrier rocket structures, in particular to a lightweight cabin section structure of a carrier.
Background
The shell section structure of the common carrier rocket is mostly an independent column section or cone section structure and is a simple skin structure, no other reinforcing structure is designed in the shell section structure, the overall rigidity of the cabin section structure is low, and the requirement of large bearing of the middle part in the cabin section is difficult to meet, so that the carrier rocket is poor in carrying capacity and overall performance.
Disclosure of Invention
The application provides a lightweight cabin section structure of carrier to improve following technical problem: the shell section structure of the common carrier rocket is mostly an independent column section or cone section structure and is a simple skin structure, no other reinforcing structure is designed in the shell section structure, the overall rigidity of the cabin section structure is low, and the requirement of large bearing of the middle part in the cabin section is difficult to meet, so that the carrier rocket is poor in carrying capacity and overall performance.
The application provides a lightweight cabin section structure of carrier adopts following technical scheme:
a lightweight cabin section structure of a carrier comprises a column section shell and a cone section shell which are integrally formed, wherein an annular middle end frame is arranged at the joint of the column section shell and the cone section shell, an annular upper end frame is arranged on the inner peripheral wall of the end part of the column section shell, which is far away from the middle end frame, and a lower end frame is arranged on the inner peripheral wall of the end part of the cone section shell, which is far away from the middle end frame;
the inner peripheral wall of the column section shell is provided with a first reinforcing structure, the first reinforcing structure is connected between the upper end frame and the middle end frame, a second reinforcing structure is arranged inside the conical section shell, and a third reinforcing structure is arranged on the outer wall of the conical section shell.
Further, the first reinforcing structure comprises a first reinforcing box and a second reinforcing box, the length directions of the first reinforcing box and the second reinforcing box are parallel to the central axis direction of the column section shell, and the width of the second reinforcing box is larger than that of the first reinforcing box.
Furthermore, the first reinforcing boxes and the second reinforcing boxes are provided with multiple groups, the multiple groups of second reinforcing boxes are uniformly arranged around the inner peripheral wall of the column section shell at intervals, two sides of each second reinforcing box are respectively provided with at least one first reinforcing box, and the first reinforcing boxes and the second reinforcing boxes are arranged on the inner peripheral wall of the column section shell at equal intervals.
Furthermore, the first reinforcing box and the second reinforcing box are both box body structures with flanges, an installation interface, an engine nozzle or a weight reducing port is arranged at the end part, far away from the inner peripheral wall of the column section shell, of the first reinforcing box, and an installation interface, an engine nozzle or a weight reducing port is arranged at the end part, far away from the inner peripheral wall of the column section shell, of the second reinforcing box.
Further, the second additional strengthening includes many strengthening ribs, many inner supporting plates and first mounting panel, the strengthening rib is fixed in the internal surface of conic section casing, the strengthening rib is followed the generating line of conic section casing is arranged, the one end of interior fagging is fixed in the internal surface of conic section casing, the polylith the upper surface of interior fagging is located the coplanar, the polylith the upper surface of interior fagging all laminate and fixed connection in the lower surface of first mounting panel, first mounting panel is on a parallel with above-mentioned plane.
Further, the second additional strengthening still includes a support section of thick bamboo, a support section of thick bamboo is located the conic section casing and follows the central axis of conic section casing arranges, the polylith the other end of interior fagging all is connected to the periphery wall of a support section of thick bamboo.
Furthermore, the four inner supporting plates are of 8-shaped structures, and the cross sections of the inner supporting plates are I-shaped; the strengthening rib is for being equipped with open-ended rectangular box-shaped structure, just rectangular box-shaped structure's inside is provided with a plurality of gusset plates.
Further, the third additional strengthening includes outer fagging of polylith and ring muscle, polylith outer fagging is all followed the generating line of conic section casing is arranged, the polylith outer fagging winds the even interval arrangement of the periphery wall of conic section casing, outer fagging is the triangle-shaped form, the ring muscle is fixed in the periphery wall and the perpendicular to of conic section casing the generating line of conic section casing is arranged.
Further, the third additional strengthening still includes the second mounting panel, the second mounting panel with lower end frame parallel arrangement, the last fixed surface of second mounting panel connects in the polylith outer fagging.
Furthermore, a plurality of installing openings for installing instrument equipment are formed in the side wall of the conical section shell.
In summary, the present application includes at least one of the following beneficial technical effects:
1. the lightweight cabin section structure of the carrier adopts a structural form of skin and stringer semi-hard shells, and by designing a shell structure integrating a column section shell and a cone section shell and matching three reasonable reinforced structures of a first reinforced structure, a second reinforced structure and a third reinforced structure, the strength and the rigidity of the whole cabin section are improved, meanwhile, the structural weight is reduced, and the carrying capacity of the carrier rocket is improved;
2. install first mounting panel through interior backup pad, install the second mounting panel through outer backup pad, first mounting panel and second mounting panel provide one respectively and supply the fixed mounting plane of instrument equipment installation, and it is more convenient to install, and instrument equipment installation environment is better.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the description below are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
Fig. 1 is a schematic structural view of a lightweight deck section structure of a vehicle according to an embodiment of the present application.
Description of reference numerals:
1. a column section housing; 2. a conical section housing; 3. a middle end frame; 4. an upper end frame; 5. a lower end frame; 6. a first reinforcing box; 7. a second reinforcement box; 8. reinforcing ribs; 9. an inner supporting plate; 10. a first mounting plate; 11. a support cylinder; 12. an outer supporting plate; 13. a second mounting plate; 14. looping ribs; 15. and (7) installing a port.
Detailed Description
In order to make the technical problems, technical solutions and advantageous effects to be solved by the present application clearer, the present application is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present application and are not intended to limit the present application.
It will be understood that when an element is referred to as being "secured to" or "disposed on" another element, it can be directly on the other element or be indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or be indirectly connected to the other element.
It will be understood that the terms "length," "width," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like, as used herein, refer to an orientation or positional relationship indicated in the drawings that is solely for the purpose of facilitating the description and simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be considered as limiting the present application.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present application, "a plurality" means two or more unless specifically limited otherwise.
The present application is described in further detail below with reference to fig. 1.
The embodiment of the application discloses lightweight cabin section structure of delivery ware. Referring to fig. 1, the lightweight cabin section structure of carrier includes column casing 1 and conic section casing 2, the junction of column casing 1 and conic section casing 2 is provided with the middle end frame 3 of annular design, the end internal perisporium that middle end frame 3 was kept away from to column casing 1 is provided with the upper end frame 4 of annular design, the end internal perisporium that middle end frame 3 was kept away from to conic section casing 2 is provided with lower end frame 5, column casing 1, conic section casing 2, upper end frame 4, middle end frame 3, 5 integrated into one piece of lower end frame.
The internal perisporium of column casing 1 is provided with first additional strengthening, and first additional strengthening is connected between upper end frame 4 and middle end frame 3, and the inside of conic section casing 2 is provided with the second additional strengthening, and the outer wall of conic section casing 2 is provided with the third additional strengthening.
The first reinforcing structure comprises a first reinforcing box 6 and a second reinforcing box 7, the length directions of the first reinforcing box 6 and the second reinforcing box 7 are parallel to the central axis direction of the column section shell 1, and the width of the second reinforcing box 7 is larger than that of the first reinforcing box 6.
The first reinforcing boxes 6 and the second reinforcing boxes 7 are provided with multiple groups, the multiple groups of second reinforcing boxes 7 are uniformly arranged around the inner peripheral wall of the column section shell 1 at intervals, two sides of each second reinforcing box 7 are respectively provided with at least one first reinforcing box 6, and the first reinforcing boxes 6 and the second reinforcing boxes 7 are arranged on the inner peripheral wall of the column section shell 1 at equal intervals.
The first reinforcing box 6 and the second reinforcing box 7 are both of box body structures with flanges, the end part, away from the inner peripheral wall of the column section shell 1, of the first reinforcing box 6 is provided with an installation interface, an engine nozzle or a weight reducing port, the end part, away from the inner peripheral wall of the column section shell 1, of the second reinforcing box 7 is provided with an installation interface, an engine nozzle or a weight reducing port, and the number and the positions of the installation interface, the engine nozzle or the weight reducing port can be configured as required.
Second additional strengthening includes many strengthening ribs 8, vaulting board 9 and first mounting panel 10 in the polylith, strengthening rib 8 is fixed in the internal surface of conic section casing 2, strengthening rib 8 is arranged along the generating line of conic section casing 2, the one end of interior vaulting board 9 is fixed in the internal surface of conic section casing 2, the upper surface of vaulting board 9 is located the coplanar in the polylith, the upper surface of vaulting board 9 is all laminated and fixed connection in the lower surface of first mounting panel 10 in the polylith, first mounting panel 10 is on a parallel with above-mentioned plane.
The first reinforcing box 6 and the second reinforcing box 7 are both arranged on the inner wall of the column section shell 1 in a mode of bonding with glue and connecting with bolts, so that the first reinforcing box 6 and the second reinforcing box 7 are firmer in structure and are not easy to loosen; the strengthening rib 8 and interior fagging 9 are all installed on the 2 inner walls of conic section casing through the mode of glue bonding plus bolted connection, and then the structure of strengthening rib 8 and interior fagging 9 is more firm, difficult not hard up.
The second additional strengthening still includes a support section of thick bamboo 11, and a support section of thick bamboo 11 is located conic section casing 2 and arranges along conic section casing 2's the central axis, and the other end of polylith inner stay board 9 all is connected to the periphery wall of a support section of thick bamboo 11.
The four inner supporting plates 9 are of 8-shaped structures, and the cross sections of the inner supporting plates 9 are I-shaped; the reinforcing ribs 8 are of a long-strip box-shaped structure provided with an opening, a plurality of reinforcing plates are arranged inside the long-strip box-shaped structure, and the reinforcing plates are arranged in a direction perpendicular to the length direction of the long-strip box-shaped structure.
The third additional strengthening includes outer fagging 12 of polylith and ring muscle 14, and outer fagging 12 of polylith all arranges along the generating line of conic section casing 2, and outer fagging 12 of polylith is arranged around the even interval of the periphery wall of conic section casing 2, and outer fagging 12 is the triangle-shaped form, and ring muscle 14 is fixed in the periphery wall of conic section casing 2 and is arranged perpendicular to conic section casing 2's generating line.
The third reinforcing structure further comprises a second mounting plate 13, the second mounting plate 13 and the lower end frame 5 are arranged in parallel, and the upper surface of the second mounting plate 13 is fixedly connected to the outer supporting plates 12.
The side wall of the conical section shell 2 is provided with a plurality of mounting ports 15 for mounting instrument equipment, and the side wall of the column section shell 1 can be provided with an engine spray pipe nozzle, an antenna window and the like as required.
All structures of the light cabin section structure of the carrier except the first mounting plate 10 and the second mounting plate 13 are made of carbon fiber reinforced composite materials, so that the light cabin section structure has the advantages of good structural strength and rigidity and light weight. First mounting panel 10 and second mounting panel 13 are the square and the four corners is provided with 45 degrees chamfers, and the preparation material of first mounting panel 10 and second mounting panel 13 is the alloy material of light moreover.
The implementation principle of the lightweight cabin section structure of the carrier in the embodiment of the application is as follows: the lightweight cabin section structure of the carrier adopts a structural form of skin and stringer semi-hard shells, and by designing a shell structure integrating a column section shell 1 and a cone section shell 2 and matching three reasonable reinforced structures of a first reinforced structure, a second reinforced structure and a third reinforced structure, the strength and the rigidity of the whole cabin section are improved, meanwhile, the structural weight is reduced, and the carrying capacity of the carrier rocket is improved; install first mounting panel 10 through interior fagging 9, install second mounting panel 13 through outer fagging 12, first mounting panel 10 and second mounting panel 13 provide a fixed mounting plane of confession instrument equipment installation respectively, and it is more convenient to install, and instrument equipment installation environment is better.
The above description is only exemplary of the present application and should not be taken as limiting the present application, as any modification, equivalent replacement, or improvement made within the spirit and principle of the present application should be included in the protection scope of the present application.
Claims (10)
1. The utility model provides a lightweight cabin section structure of delivery ware which characterized in that: the device comprises a column section shell (1) and a conical section shell (2) which are integrally formed, wherein a middle end frame (3) with an annular design is arranged at the joint of the column section shell (1) and the conical section shell (2), an upper end frame (4) with an annular design is arranged on the inner peripheral wall of the end part of the column section shell (1) far away from the middle end frame (3), and a lower end frame (5) is arranged on the inner peripheral wall of the end part of the conical section shell (2) far away from the middle end frame (3);
the inner peripheral wall of the column section shell (1) is provided with a first reinforcing structure, the first reinforcing structure is connected between the upper end frame (4) and the middle end frame (3), a second reinforcing structure is arranged inside the conical section shell (2), and a third reinforcing structure is arranged on the outer wall of the conical section shell (2).
2. A light weight deck section structure of a vehicle according to claim 1, wherein: the first reinforcing structure comprises a first reinforcing box (6) and a second reinforcing box (7), the length direction of the first reinforcing box (6) and the length direction of the second reinforcing box (7) are parallel to the central axis direction of the column section shell (1), and the width of the second reinforcing box (7) is larger than that of the first reinforcing box (6).
3. A light-weight deck section structure of a vehicle according to claim 2, wherein: the first reinforcing box (6) and the second reinforcing box (7) are provided with multiple groups, the multiple groups are formed in a manner that the second reinforcing box (7) winds the inner peripheral wall of the column section shell (1) in an even interval arrangement mode, each group is formed in a manner that two sides of the second reinforcing box (7) are respectively provided with at least one first reinforcing box (6), and the first reinforcing box (6) and the second reinforcing box (7) are arranged in an equidistant mode on the inner peripheral wall of the column section shell (1).
4. A light-weight deck section structure of a vehicle according to claim 2, wherein: the first reinforcing box (6) and the second reinforcing box (7) are both box body structures with turned-over edges, an installation interface, an engine nozzle or a weight reducing opening is formed in the end portion, far away from the inner peripheral wall of the column section shell (1), of the first reinforcing box (6), and an installation interface, an engine nozzle or a weight reducing opening is formed in the end portion, far away from the inner peripheral wall of the column section shell (1), of the second reinforcing box (7).
5. A light-weight deck section structure of a vehicle according to claim 1, wherein: bracing plate (9) and first mounting panel (10) in second additional strengthening includes many strengthening ribs (8), polylith, strengthening rib (8) are fixed in the internal surface of conic section casing (2), strengthening rib (8) are followed the generating line of conic section casing (2) is arranged, the one end of interior fagging (9) is fixed in the internal surface of conic section casing (2), the polylith the upper surface of interior fagging (9) is located the coplanar, the polylith the upper surface of interior fagging (9) all laminate and fixed connection in the lower surface of first mounting panel (10), first mounting panel (10) are on a parallel with above-mentioned plane.
6. A light-weight deck section structure of a vehicle according to claim 5, wherein: the second additional strengthening still includes a support section of thick bamboo (11), a support section of thick bamboo (11) are located in conic section casing (2) and along the central axis of conic section casing (2) arranges, the polylith the other end of interior fagging (9) all is connected to the periphery wall of a support section of thick bamboo (11).
7. A light-weight deck section structure of a vehicle according to claim 5, wherein: the four inner supporting plates (9) are of 8-shaped structures, and the cross sections of the inner supporting plates (9) are I-shaped; strengthening rib (8) are for being equipped with open-ended rectangular box-shaped structure, just rectangular box-shaped structure's inside is provided with a plurality of gusset plates.
8. A light weight deck section structure of a vehicle according to claim 1, wherein: the third additional strengthening includes outer fagging (12) of polylith and hoop reinforcement (14), polylith outer fagging (12) are all followed the generating line of conic section casing (2) is arranged, the polylith outer fagging (12) are wound the even interval arrangement of periphery wall of conic section casing (2), outer fagging (12) are the triangle-shaped form, hoop reinforcement (14) are fixed in the periphery wall and the perpendicular to of conic section casing (2) the generating line of conic section casing (2) is arranged.
9. A light-weight deck section structure of a vehicle according to claim 8, wherein: the third additional strengthening still includes second mounting panel (13), second mounting panel (13) with lower end frame (5) parallel arrangement, the last fixed surface of second mounting panel (13) connects in the polylith outer fagging (12).
10. A light-weight deck section structure of a vehicle according to any one of claims 1-9, wherein: the side wall of the conical section shell (2) is provided with a plurality of mounting ports (15) for mounting instrument equipment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210192067.4A CN114659415B (en) | 2022-03-01 | 2022-03-01 | Light cabin section structure of carrier |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210192067.4A CN114659415B (en) | 2022-03-01 | 2022-03-01 | Light cabin section structure of carrier |
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| Publication Number | Publication Date |
|---|---|
| CN114659415A true CN114659415A (en) | 2022-06-24 |
| CN114659415B CN114659415B (en) | 2024-02-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210192067.4A Active CN114659415B (en) | 2022-03-01 | 2022-03-01 | Light cabin section structure of carrier |
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| CN (1) | CN114659415B (en) |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2072953C1 (en) * | 1993-06-09 | 1997-02-10 | Юрий Семенович Соломонов | Rocket compartment-platform for attachment of payload components |
| US20120141703A1 (en) * | 2009-12-30 | 2012-06-07 | Ima Materialforschung Und Anwendungstechnik Gmbh | Aircraft or spacecraft casing |
| CN105122964B (en) * | 2007-12-25 | 2012-07-25 | 上海卫星工程研究所 | Grapefruit satellite platform loaded cylinder |
| US20140134389A1 (en) * | 2012-11-13 | 2014-05-15 | Airbus Operations Gmbh | Shell structure of a fuselage |
| WO2015006809A1 (en) * | 2013-07-16 | 2015-01-22 | G & G Mining Fabrication Pty Ltd | A bucket for an earth moving machine |
| CN106864773A (en) * | 2017-03-31 | 2017-06-20 | 陕西蓝箭航天技术有限公司 | A kind of instrument cabin structure of vehicle |
| CN109018445A (en) * | 2018-09-12 | 2018-12-18 | 北京航空航天大学 | Moonlet vehicle |
| RU186237U1 (en) * | 2018-04-18 | 2019-01-11 | Федеральное государственное автономное образовательное учреждение высшего образования "Национальный исследовательский Томский государственный университет" (НИ ТГУ) | Adapter in the form of a polyhedral conical shell made of composite materials |
| CN110466801A (en) * | 2019-05-24 | 2019-11-19 | 上海宇航系统工程研究所 | A kind of aircraft section structure |
| CN212290392U (en) * | 2020-10-14 | 2021-01-05 | 中国长征火箭有限公司 | Composite cabin section structure and aircraft |
| CN212290307U (en) * | 2020-10-27 | 2021-01-05 | 中国长征火箭有限公司 | Composite material shell and aircraft |
| CN113091527A (en) * | 2021-04-28 | 2021-07-09 | 北京星途探索科技有限公司 | Covering purlin strip type shell structure |
-
2022
- 2022-03-01 CN CN202210192067.4A patent/CN114659415B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2072953C1 (en) * | 1993-06-09 | 1997-02-10 | Юрий Семенович Соломонов | Rocket compartment-platform for attachment of payload components |
| CN105122964B (en) * | 2007-12-25 | 2012-07-25 | 上海卫星工程研究所 | Grapefruit satellite platform loaded cylinder |
| US20120141703A1 (en) * | 2009-12-30 | 2012-06-07 | Ima Materialforschung Und Anwendungstechnik Gmbh | Aircraft or spacecraft casing |
| US20140134389A1 (en) * | 2012-11-13 | 2014-05-15 | Airbus Operations Gmbh | Shell structure of a fuselage |
| WO2015006809A1 (en) * | 2013-07-16 | 2015-01-22 | G & G Mining Fabrication Pty Ltd | A bucket for an earth moving machine |
| CN106864773A (en) * | 2017-03-31 | 2017-06-20 | 陕西蓝箭航天技术有限公司 | A kind of instrument cabin structure of vehicle |
| RU186237U1 (en) * | 2018-04-18 | 2019-01-11 | Федеральное государственное автономное образовательное учреждение высшего образования "Национальный исследовательский Томский государственный университет" (НИ ТГУ) | Adapter in the form of a polyhedral conical shell made of composite materials |
| CN109018445A (en) * | 2018-09-12 | 2018-12-18 | 北京航空航天大学 | Moonlet vehicle |
| CN110466801A (en) * | 2019-05-24 | 2019-11-19 | 上海宇航系统工程研究所 | A kind of aircraft section structure |
| CN212290392U (en) * | 2020-10-14 | 2021-01-05 | 中国长征火箭有限公司 | Composite cabin section structure and aircraft |
| CN212290307U (en) * | 2020-10-27 | 2021-01-05 | 中国长征火箭有限公司 | Composite material shell and aircraft |
| CN113091527A (en) * | 2021-04-28 | 2021-07-09 | 北京星途探索科技有限公司 | Covering purlin strip type shell structure |
Non-Patent Citations (1)
| Title |
|---|
| 陈献平等: "轻质箭体结构优化设计", 导弹与航天运载技术, no. 02, pages 17 - 21 * |
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| Publication number | Publication date |
|---|---|
| CN114659415B (en) | 2024-02-09 |
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