CN114659415B - Light cabin section structure of carrier - Google Patents
Light cabin section structure of carrier Download PDFInfo
- Publication number
- CN114659415B CN114659415B CN202210192067.4A CN202210192067A CN114659415B CN 114659415 B CN114659415 B CN 114659415B CN 202210192067 A CN202210192067 A CN 202210192067A CN 114659415 B CN114659415 B CN 114659415B
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- Prior art keywords
- reinforcing
- section shell
- cone
- box
- shell
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- 230000003014 reinforcing effect Effects 0.000 claims abstract description 105
- 230000002093 peripheral effect Effects 0.000 claims abstract description 33
- 230000000694 effects Effects 0.000 abstract description 2
- 230000010354 integration Effects 0.000 abstract 1
- 230000002787 reinforcement Effects 0.000 description 8
- 238000005728 strengthening Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 239000003292 glue Substances 0.000 description 2
- 239000013585 weight reducing agent Substances 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 229910001234 light alloy Inorganic materials 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000011208 reinforced composite material Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Body Structure For Vehicles (AREA)
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, 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, the inside of the cone section shell is provided with a second reinforcing structure, and the outer wall of the cone section shell is provided with a third reinforcing structure. The application has the following expected technical effects: the structural form of the skin and the stringer semi-hard shell is adopted, the shell structure of the integration of the column section shell and the cone section shell is matched with the combination of the first reinforcing structure, the second reinforcing structure and the third reinforcing structure, so that the integral 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 common carrier rocket shell section structure is mostly an independent column section or cone section structure, is a simple skin structure, has no other reinforcing structural design, has lower overall rigidity, and is difficult to meet the larger bearing requirement of the middle part in the cabin, thereby leading to poor carrying capacity and poor overall performance of the carrier rocket.
Disclosure of Invention
The application provides a lightweight cabin section structure of carrier to improve following technical problem: the common carrier rocket shell section structure is mostly an independent column section or cone section structure, is a simple skin structure, has no other reinforcing structural design, has lower overall rigidity, and is difficult to meet the larger bearing requirement of the middle part in the cabin, thereby leading to poor carrying capacity and poor overall performance of the carrier rocket.
The application provides a lightweight cabin section structure of carrier adopts following technical scheme:
the utility model provides a lightweight cabin section structure of carrier, includes integrated into one piece's column section casing and cone section casing, the junction of column section casing with cone section casing is provided with the middle end frame of annular design, the column section casing keep away from the tip inner peripheral wall of middle end frame is provided with the upper end frame of annular design, the cone section casing keep away from the tip inner peripheral wall of middle end frame is provided with the lower 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, the second reinforcing structure is arranged inside the cone section shell, and the third reinforcing structure is arranged on the outer wall of the cone 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.
Further, the first reinforcing boxes and the second reinforcing boxes are provided with a plurality of groups, the second reinforcing boxes are uniformly arranged around the inner peripheral wall of the column section shell at intervals, at least one first reinforcing box is arranged on each of two sides of each second reinforcing box, and the first reinforcing boxes and the second reinforcing boxes are arranged at equal intervals on the inner peripheral wall of the column section shell.
Further, the first reinforcing box and the second reinforcing box are both box body structures with flanging, the end part of the inner peripheral wall of the column section shell, which is far away from the first reinforcing box, is provided with a mounting interface, an engine nozzle or a weight reduction port, and the end part of the inner peripheral wall of the column section shell, which is far away from the second reinforcing box, is provided with a mounting interface, an engine nozzle or a weight reduction port.
Further, the second reinforced structure includes many strengthening ribs, polylith interior fagging and first mounting panel, the strengthening rib is fixed in the internal surface of cone section casing, the strengthening rib is followed the generating line of cone section casing is arranged, the one end of interior fagging is fixed in the internal surface of cone 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 reinforcing structure further comprises a supporting cylinder, wherein the supporting cylinder is located in the cone section shell and is arranged along the central axis of the cone section shell, and the other ends of the inner supporting plates are connected to the peripheral wall of the supporting cylinder.
Further, the inner supporting plates are in four and 8-shaped structures, and the cross sections of the inner supporting plates are I-shaped; the reinforcing rib is of a strip box-shaped structure provided with an opening, and a plurality of reinforcing plates are arranged inside the strip box-shaped structure.
Further, the third reinforcing structure comprises a plurality of outer supporting plates and ring ribs, the outer supporting plates are arranged along the bus of the cone-section shell, the outer supporting plates are uniformly arranged around the outer peripheral wall of the cone-section shell at intervals, the outer supporting plates are triangular, and the ring ribs are fixed on the outer peripheral wall of the cone-section shell and perpendicular to the bus of the cone-section shell.
Further, the third reinforcing structure further comprises a second mounting plate, the second mounting plate and the lower end frame are arranged in parallel, and the upper surface of the second mounting plate is fixedly connected to the plurality of outer support plates.
Further, a plurality of mounting openings for mounting instruments and equipment are formed in the side wall of the cone section shell.
In summary, the present application includes at least one of the following beneficial technical effects:
1. the light cabin structure of the carrier adopts the structural form of a skin and a stringer semi-hard shell, and by designing a shell structure integrating a column section shell and a cone section shell and combining three reasonable reinforcement structures of a first reinforcement structure, a second reinforcement structure and a third reinforcement structure, the integral strength and the integral rigidity of the cabin are improved, the structural weight is reduced, and the carrying capacity of the carrier rocket is improved;
2. the first mounting plate is mounted through the inner supporting plate, the second mounting plate is mounted through the outer supporting plate, the first mounting plate and the second mounting plate respectively provide a mounting plane for mounting and fixing the instrument and equipment, the mounting is more convenient, and the mounting environment of the instrument and equipment is better.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic structural view of a lightweight class structure of a vehicle according to an embodiment of the present application.
Reference numerals illustrate:
1. a column section housing; 2. a cone 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 reinforcing box; 8. reinforcing ribs; 9. an inner support plate; 10. a first mounting plate; 11. a support cylinder; 12. an outer support plate; 13. a second mounting plate; 14. a ring rib; 15. and (5) an installation port.
Detailed Description
In order to make the technical problems, technical schemes and beneficial effects to be solved by the present application more clear, 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 for purposes of illustration only and are not intended to limit the present application.
It will be understood that when an element is referred to as being "mounted" 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 is to be understood that the terms "length," "width," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate or are based on the orientation or positional relationship shown in the drawings, merely to facilitate description of the present application and simplify description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be configured and operated in a particular orientation, and therefore should not be construed as limiting the present application.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present application, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.
The present application is described in further detail below in conjunction with fig. 1.
The embodiment of the application discloses a lightweight cabin section structure of a carrier. Referring to fig. 1, the lightweight cabin section structure of the carrier comprises a column section shell 1 and a cone section shell 2, wherein an annular middle end frame 3 is arranged at the joint of the column section shell 1 and the cone section shell 2, an annular upper end frame 4 is arranged on the inner peripheral wall of the end part of the column section shell 1, which is 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 cone section shell 2, which is far away from the middle end frame 3, and the column section shell 1, the cone section shell 2, the upper end frame 4, the middle end frame 3 and the lower end frame 5 are integrally formed.
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, the inside of the cone section shell 2 is provided with a second reinforcing structure, and the outer wall of the cone section shell 2 is provided with a third reinforcing structure.
The first reinforcing structure includes 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 casing 1, and the width of the second reinforcing box 7 is larger than the width of the first reinforcing box 6.
The first reinforcing boxes 6 and the second reinforcing boxes 7 are provided with a plurality of groups, the second reinforcing boxes 7 of the plurality of groups are uniformly arranged at intervals around the inner peripheral wall of the column section shell 1, at least one first reinforcing box 6 is arranged on two sides of each second reinforcing box 7, and the first reinforcing boxes 6 and the second reinforcing boxes 7 are arranged at equal intervals on the inner peripheral wall of the column section shell 1.
The first reinforcing box 6 and the second reinforcing box 7 are box body structures with flanging, the end part of the inner peripheral wall of the first reinforcing box 6, which is far away from the column section shell 1, is provided with a mounting interface, an engine nozzle or a weight reducing port, the end part of the inner peripheral wall of the second reinforcing box 7, which is far away from the column section shell 1, is provided with a mounting interface, an engine nozzle or a weight reducing port, and the number and the positions of the mounting interface, the engine nozzle or the weight reducing port can be configured as required.
The second reinforced structure comprises a plurality of reinforcing ribs 8, a plurality of inner supporting plates 9 and a first mounting plate 10, wherein the reinforcing ribs 8 are fixed on the inner surface of the cone section shell 2, the reinforcing ribs 8 are arranged along the bus of the cone section shell 2, one ends of the inner supporting plates 9 are fixed on the inner surface of the cone section shell 2, the upper surfaces of the inner supporting plates 9 are located on the same plane, the upper surfaces of the inner supporting plates 9 are all attached to and fixedly connected with the lower surface of the first mounting plate 10, and the first mounting plate 10 is parallel to the 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 glue and externally connecting bolts, so that the structures of the first reinforcing box 6 and the second reinforcing box 7 are firmer and are not easy to loosen; the reinforcing ribs 8 and the inner supporting plates 9 are all installed on the inner wall of the cone section shell 2 in a mode of bonding with glue and externally connecting with bolts, and then the structures of the reinforcing ribs 8 and the inner supporting plates 9 are firmer and are not easy to loosen.
The second reinforcing structure further comprises a supporting cylinder 11, wherein the supporting cylinder 11 is positioned in the cone section shell 2 and is arranged along the central axis of the cone section shell 2, and the other ends of the inner supporting plates 9 are connected to the peripheral wall of the supporting cylinder 11.
The inner supporting plates 9 are in four and 8-shaped structures, and the cross sections of the inner supporting plates 9 are I-shaped; the reinforcing rib 8 is a strip box-shaped structure provided with an opening, and a plurality of reinforcing plates are arranged inside the strip box-shaped structure and perpendicular to the length direction of the strip box-shaped structure.
The third reinforcing structure comprises a plurality of outer supporting plates 12 and ring ribs 14, wherein the outer supporting plates 12 are arranged along the bus of the cone-section shell 2, the outer supporting plates 12 are uniformly arranged at intervals around the outer peripheral wall of the cone-section shell 2, the outer supporting plates 12 are triangular, and the ring ribs 14 are fixed on the outer peripheral wall of the cone-section shell 2 and are perpendicular to the bus of the cone-section shell 2.
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 with the plurality of outer supporting plates 12.
The side wall of the cone section shell 2 is provided with a plurality of mounting ports 15 for mounting instruments and 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 according to requirements.
All structures except the first mounting plate 10 and the second mounting plate 13 of the light cabin structure of the carrier are made of carbon fiber reinforced composite materials, so that the light cabin structure has the advantages of good structural strength and rigidity and light weight. The first mounting plate 10 and the second mounting plate 13 are square, 45-degree chamfers are arranged at four corners, and the first mounting plate 10 and the second mounting plate 13 are made of light alloy materials.
The implementation principle of the lightweight cabin section structure of the carrier provided by the embodiment of the application is as follows: the light cabin structure of the carrier adopts the structural form of a skin and a stringer semi-hard shell, and by designing a shell structure integrating the column section shell 1 and the cone section shell 2 and combining three reasonable reinforcement structures of a first reinforcement structure, a second reinforcement structure and a third reinforcement structure, the strength and the rigidity of the whole cabin are improved, the structural weight is reduced, and the carrying capacity of the carrier rocket is improved; the first mounting plate 10 is mounted through the inner supporting plate 9, the second mounting plate 13 is mounted through the outer supporting plate 12, the first mounting plate 10 and the second mounting plate 13 respectively provide a mounting plane for mounting and fixing the instrument and the equipment, the mounting is more convenient, and the mounting environment of the instrument and the equipment is better.
The foregoing description of the preferred embodiments of the present invention is not intended to limit the invention to the particular forms disclosed, but on the contrary, the intention is to cover all modifications, equivalents, and alternatives falling within the spirit and scope of the invention.
Claims (7)
1. A lightweight cabin section structure of a carrier, characterized in that: the novel column section type conical section type column comprises a column section shell (1) and a conical section shell (2) which are integrally formed, wherein an annular middle end frame (3) is arranged at the joint of the column section shell (1) and the conical section shell (2), an annular upper end frame (4) 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), the interior of the cone section shell (2) is provided with a second reinforcing structure, and the outer wall of the cone section shell (2) is provided with a third reinforcing structure;
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 second reinforcing structure comprises a plurality of reinforcing ribs (8), a plurality of inner supporting plates (9) and a first mounting plate (10), wherein the reinforcing ribs (8) are fixed on the inner surface of the cone section shell (2), the reinforcing ribs (8) are arranged along a bus of the cone section shell (2), one ends of the inner supporting plates (9) are fixed on the inner surface of the cone section shell (2), the upper surfaces of the inner supporting plates (9) are positioned on the same plane, the upper surfaces of the inner supporting plates (9) are respectively attached to and fixedly connected with the lower surface of the first mounting plate (10), and the first mounting plate (10) is parallel to the plane; the third reinforced structure comprises a plurality of outer supporting plates (12) and annular ribs (14), the outer supporting plates (12) are all arranged along the bus of the cone-section shell (2), the outer supporting plates (12) are uniformly arranged at intervals around the outer peripheral wall of the cone-section shell (2), the outer supporting plates (12) are triangular, and the annular ribs (14) are fixed on the outer peripheral wall of the cone-section shell (2) and are perpendicular to the bus of the cone-section shell (2).
2. The lightweight class structure of a vehicle of claim 1, wherein: the first reinforcing boxes (6) and the second reinforcing boxes (7) are provided with a plurality of groups, the second reinforcing boxes (7) are uniformly arranged around the inner peripheral wall of the column section shell (1) at intervals, at least one first reinforcing box (6) is arranged on two sides of each second reinforcing box (7), and the first reinforcing boxes (6) and the second reinforcing boxes (7) are arranged at equal intervals on the inner peripheral wall of the column section shell (1).
3. The lightweight class structure of a vehicle of claim 1, wherein: the first reinforcing box (6) and the second reinforcing box (7) are of box body structures with flanging, the first reinforcing box (6) is far away from the end part of the inner peripheral wall of the column section shell (1) and is provided with a mounting interface, an engine nozzle or a weight reducing port, and the second reinforcing box (7) is far away from the end part of the inner peripheral wall of the column section shell (1) and is provided with a mounting interface, an engine nozzle or a weight reducing port.
4. The lightweight class structure of a vehicle of claim 1, wherein: the second reinforcing structure further comprises a supporting cylinder (11), wherein the supporting cylinder (11) is positioned in the cone section shell (2) and is arranged along the central axis of the cone section shell (2), and the other ends of the inner supporting plates (9) are connected to the peripheral wall of the supporting cylinder (11).
5. The lightweight class structure of a vehicle of claim 1, wherein: the inner supporting plates (9) are in four and 8-shaped structures, and the cross sections of the inner supporting plates (9) are I-shaped; the reinforcing rib (8) is of a strip box-shaped structure with an opening, and a plurality of reinforcing plates are arranged inside the strip box-shaped structure.
6. The lightweight class structure of a vehicle of claim 1, wherein: 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 plurality of outer support plates (12).
7. The lightweight class structure of a vehicle according to any of claims 1-6, characterized in that the side wall of the cone section housing (2) is provided with a plurality of mounting openings (15) for mounting of instruments and 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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114659415A CN114659415A (en) | 2022-06-24 |
| CN114659415B true CN114659415B (en) | 2024-02-09 |
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ID=82027246
Family Applications (1)
| 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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| Country | Link |
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| CN (1) | CN114659415B (en) |
Citations (10)
| 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 |
| 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 |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102009060876A1 (en) * | 2009-12-30 | 2011-07-14 | IMA Materialforschung und Anwendungstechnik GmbH, 01109 | Aircraft or spacecraft cover |
| EP2730495B1 (en) * | 2012-11-13 | 2016-04-27 | Airbus Operations GmbH | Shell structure of a fuselage |
-
2022
- 2022-03-01 CN CN202210192067.4A patent/CN114659415B/en active Active
Patent Citations (10)
| 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 |
| 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 |
|---|
| 轻质箭体结构优化设计;陈献平等;导弹与航天运载技术(02);第17-21，43页 * |
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| CN114659415A (en) | 2022-06-24 |
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