CN212290307U - Composite material shell and aircraft - Google Patents
Composite material shell and aircraft Download PDFInfo
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- CN212290307U CN212290307U CN202022407622.XU CN202022407622U CN212290307U CN 212290307 U CN212290307 U CN 212290307U CN 202022407622 U CN202022407622 U CN 202022407622U CN 212290307 U CN212290307 U CN 212290307U
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Abstract
The utility model relates to a high-end equipment manufacture technical field provides a combined material casing and aircraft, wherein, the combined material casing includes: the composite light shell comprises an epoxy resin-based carbon fiber unidirectional tape which is integrally laid, cured and molded: the composite material light shell comprises a skin area, an upper end frame area and a lower end frame area which are positioned at two ends of the skin area, an upper end frame transition area which is in transition extension from the upper end frame area to the skin area, a lower end frame transition area which is in transition extension from the lower end frame area to the skin area, and annular reinforcing rib areas which are circumferentially arranged along the inner side surfaces of the upper end frame area and the lower end frame area respectively, composite material stringers are connected to the inner wall of the composite material light shell in a co-curing molding mode along the axial direction of the composite material light shell, and the composite material stringers are arranged at intervals. The utility model discloses when guaranteeing casing main structure bulk strength and rigidity, realized the product and effectively subtract the effect of heavy.
Description
Technical Field
The utility model relates to a high-end equipment manufacturing technical field, more specifically say, relate to a combined material casing and aircraft.
Background
The structural design of a cabin shell of an aircraft (such as a rocket or a missile) generally comprises three types, namely an optical cylinder structure, a skin stringer structure and a grid stiffened structure. The light cylinder structure process is simplest, but the bearing efficiency is lowest. The skin-stringer structure cabin section is high in designability, good in stability and highest in axial load bearing efficiency, is suitable for a structure designed according to stability, stress strength and rigidity, and has a good weight advantage. As a cabin shell mainly bearing axial load, the requirements of stress strength and rigidity are guaranteed, and meanwhile, the weight is further reduced to improve the missile range or the effective load of a rocket.
For this reason, it is a technical challenge those skilled in the art are working to solve when the development of composite materials is well-established, how to more economically improve the load efficiency of the nacelle section casing.
SUMMERY OF THE UTILITY MODEL
In view of the above-mentioned problems in the prior art, an object of the present invention is to provide a composite shell and an aircraft.
In a first aspect, the present invention provides a composite material housing, comprising: a composite light hull and a number of composite stringers, the composite light hull comprising: the composite material stringer comprises a skin area, an upper end frame area and a lower end frame area which are positioned at two ends of the skin area, an upper end frame transition area extending from the upper end frame area to the skin area in a transition mode, a lower end frame transition area extending from the lower end frame area to the skin area in a transition mode, and a circumferential reinforcing rib area circumferentially arranged along the inner side faces of the upper end frame area and the lower end frame area respectively, wherein the skin area, the upper end frame area, the lower end frame area, the upper end frame transition area, the lower end frame transition area and the circumferential reinforcing rib area are epoxy resin-based carbon fiber unidirectional tapes which are integrally laid and cured, composite material stringers are integrally connected to the inner wall of the composite material optical shell in an axial co-curing mode of the composite material optical shell, and the composite material stringers are arranged at intervals.
In some embodiments, the composite stringer is a T-shaped stringer comprising a rim plate and a web plate, the web plate being attached to an inner wall of the composite light hull, the rim plate being perpendicular to the web plate.
In some embodiments, the platform comprises at least 10 layers of epoxy-based carbon fiber unidirectional tape, and the 10 layers of epoxy-based carbon fiber unidirectional tape have a ply sequence [ ± 45/0/90/0]S(ii) a The web plate at least comprises 16 layers of epoxy resin-based carbon fiber unidirectional tapes, and the layering sequence of the 16 layers of epoxy resin-based carbon fiber unidirectional tapes is [ +/-45/0/90/0/+/-45/0]S。
In some embodiments, in the composite light shell, the skin region includes a first layer and a second layer, the epoxy resin-based carbon fiber unidirectional tape in the first layer continuously passes through an upper end frame transition region to an upper end frame region position along the outer side of the composite light shell, and the epoxy resin-based carbon fiber unidirectional tape in the second layer continuously passes through a lower end frame transition region along the inner side of the composite light shell, and joins after bypassing the circumferential reinforcing rib region.
In some embodiments, the skin region includes at least 14 layers of epoxy-based carbon fiber unidirectional tape; the first layer comprises 7 layers of epoxy resin-based carbon fiber unidirectional tapes, the second layer comprises 7 layers of epoxy resin-based carbon fiber unidirectional tapes, the epoxy resin-based carbon fiber unidirectional tapes in the first layer and the second layer are of symmetrical structures, and the paving sequence of the epoxy resin-based carbon fiber unidirectional tapes in the first layer and the second layer is [ +/-45/0/90/0/90/0 ].
In some embodiments, the epoxy resin-based carbon fiber unidirectional tape in the second layer continuously passes through the lower end frame transition region along the inner side of the composite light shell and joins after bypassing the circumferential reinforcing rib region, specifically including: 7 layers of epoxy resin-based carbon fiber one-way belts in the second layer are separated from the annular reinforcing rib area through the lower end frame transition area continuously along the inner side of the composite material light shell, wherein 2 layers of epoxy resin-based carbon fiber one-way belts bypass the annular reinforcing rib area and then are converged with the other 5 layers of epoxy resin-based carbon fiber one-way belts on the inner side of the annular reinforcing rib.
In some embodiments, the upper and lower end frame regions each comprise 52 layers of epoxy-based carbon fiber unidirectional tape,the 52-layer epoxy resin-based carbon fiber unidirectional tape comprises 14 layers of epoxy resin-based carbon fiber unidirectional tapes of a first layer and a second layer of the skin area, wherein the rest 38 layers of epoxy resin-based carbon fiber unidirectional tapes are respectively laid in the upper end frame area, the lower end frame area and the skin area in a missing layer mode, the upper end frame transition area and the lower end frame transition area are correspondingly formed, and the laying sequence of the 52 layers of epoxy resin-based carbon fiber unidirectional tapes is [ +/-45/0/90/0/90/0/(+/-45/0/90/0)3/(±45/0/90)]S。
In some embodiments, the circumferential reinforcing rib area is wound and filled with epoxy resin-based carbon fiber unidirectional tapes, and the winding and filling sequence of each layer of epoxy resin-based carbon fiber unidirectional tapes is [0 ].
In some embodiments, a plurality of air duct outlets are formed through the composite material light shell in the circumferential direction.
In a second aspect, the present invention provides an aircraft comprising the composite shell of any embodiment of the first aspect.
The beneficial effects of the utility model reside in that: the provided composite material shell main structure is integrally formed, so that the weight of a product can be reduced by more than 30%; meanwhile, the strength and the rigidity of the shell are ensured by performing the composite material stringer and co-curing and assembling the composite material stringer and the shell. Meanwhile, the integrally formed structure effectively reduces the fasteners and assembly required by stringer assembly, so that the processing time period is shortened, and the processing cost is reduced.
With regard to the advantageous effects of the present invention in other embodiments, it will be described in detail in the following specific examples.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for the embodiments or the prior art descriptions will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
Fig. 1 is a perspective view of a composite shell according to an embodiment of the present invention;
fig. 2 is a schematic cross-sectional view of the composite shell shown in fig. 1 according to the present invention;
fig. 3 is a schematic cross-sectional view of the composite shell of fig. 1 from the upper frame region to the skin region according to the present invention;
FIG. 4 is a perspective view of the composite stringer of the present invention in the composite shell of FIG. 1;
fig. 5 is a schematic cross-sectional view of composite stringers in the composite shell of fig. 1 according to the present invention.
Wherein the reference numerals in the figures are as follows:
01-a composite optical shell;
11-a skin region;
111-a first layer;
112-a second layer;
12-upper end box area;
13-lower end box area;
14-upper end frame transition region;
15-lower end frame transition region;
16-a circumferential reinforcing rib area;
17-air pipe outlet;
02-composite stringer;
21-a flange;
22-web.
Detailed Description
In order to make the technical problem, technical solution and advantageous effects to be solved by the present invention more clearly understood, the following description is given in conjunction with the accompanying drawings and embodiments to illustrate the present invention in further detail. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the invention.
It will be understood that when an element is referred to as being "secured to" or "disposed on" another element, it can be directly or indirectly secured to the other element. When an element is referred to as being "connected to" another element, it can be directly or indirectly connected to the other element. The terms "upper", "lower", "left", "right", "front", "rear", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positions based on the orientations or positions shown in the drawings, and are for convenience of description only and not to be construed as limiting the technical solution. The terms "first", "second" and "first" are used merely for descriptive purposes and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features. The meaning of "plurality" is two or more unless specifically limited otherwise.
Referring to fig. 1-5, for the composite material casing provided by the embodiment of the present invention, compared with the casing on the cabin structure of the existing aircraft, the composite material casing is made of composite material, so that the structural integrity is ensured, and the structural weight can be effectively reduced.
As shown in fig. 1, the composite shell includes a composite light shell 01 and a number of composite stringers 02. Namely, the embodiment of the utility model provides a combined material casing is covering stringer structure.
It should be noted that the features of the skin, the stringer, the upper end frame and the lower end frame are named after technical features of the shell of the cabin structure prepared by the conventional process in the field, and in this embodiment, since all the technical features are obtained by integrally forming the composite material, in order to facilitate a person skilled in the art to more clearly understand the technical solution of the present invention, the composite material shell is also divided into regions according to the position structure of the conventional technical features, so as to facilitate description and understanding of the technical solution.
Specifically, as shown in fig. 1 to 3, the composite light shell 01 includes: the composite carbon fiber composite material comprises a skin area 11, an upper end frame area 12 and a lower end frame area 13 which are positioned at two ends of the skin area 11, an upper end frame transition area 14 which is formed by the transition and extension of the upper end frame area 12 to the skin area 11, a lower end frame transition area 15 which is formed by the transition and extension of the lower end frame area 13 to the skin area 11, and hoop reinforcing rib areas 16 which are circumferentially arranged on the inner side surfaces of the upper end frame area 12 and the lower end frame area 13 respectively, wherein the skin area 11, the upper end frame area 12, the lower end frame area 13, the upper end frame transition area 14, the lower end frame transition area 15 and the hoop reinforcing rib areas 16 are epoxy resin-based carbon fiber unidirectional belt integrally laid and solidified and formed.
The epoxy resin-based carbon fiber unidirectional tape (also referred to as unidirectional tape for short) in the composite material shell can be specifically T700S/603B epoxy resin-based carbon fiber unidirectional tape with the thickness of 0.15 mm.
Furthermore, in fig. 3, only half of the symmetrical structures are shown, since the upper end frame region 12, the upper end frame transition region 14 and the lower end frame region 13, the lower end frame transition region 15 on both sides of the skin 11 are symmetrical identical structures with respect to the skin. Therefore, the lay-up positional relationship and the layer structure of the unidirectional tape in the composite material case will be described below with the skin region 11, the upper end frame transition region 14, the upper end frame region 12, and the bead regions shown in fig. 3.
Specifically, in the composite light shell 01, as shown in fig. 3, the skin region 11 includes a first layer 111 and a second layer 112, the epoxy resin-based carbon fiber unidirectional tape in the first layer 111 continuously passes through the upper end frame transition region 14 to the upper end frame region 12 along the outer side of the composite light shell 01, and the epoxy resin-based carbon fiber unidirectional tape in the second layer 112 continuously passes through the upper end frame transition region 14 along the inner side of the composite light shell 01, and joins after bypassing the annular reinforcing rib region 16.
Similarly, the configurations of the lower end frame transition region 15, the lower end frame region 13, and the bead regions thereon have the same configurations as described above. Namely, the skin region 11 includes a first layer 111 and a second layer 112, the epoxy resin-based carbon fiber unidirectional tape in the first layer 111 continuously passes through the lower end frame transition region 15 to the position of the lower end frame region 13 along the outer side of the composite light shell 01, and the epoxy resin-based carbon fiber unidirectional tape in the second layer 112 continuously passes through the lower end frame transition region 15 along the inner side of the composite light shell 01, and joins after bypassing the circumferential reinforcing rib region 16.
In more detail, in the skin region 11, the skin region 11 at least includes 14 layers of epoxy resin-based carbon fiber unidirectional tapes, wherein the first layer 111 includes 7 layers of epoxy resin-based carbon fiber unidirectional tapes, the second layer 112 includes 7 layers of epoxy resin-based carbon fiber unidirectional tapes, the laying sequence of the epoxy resin-based carbon fiber unidirectional tapes in the first layer 111 and the second layer 112 is symmetrical, and the laying sequence of the epoxy resin-based carbon fiber unidirectional tapes in the first layer 111 and the second layer 112 may be [ ± 45/0/90/0/90/0 [ -45/0/90/0/90/0 [)] S。
Note that the unidirectional tape is laid in the order of [ + -45/0/90/0/90/0 [ + -. ]] SWherein, the unidirectional tapes with +45 degrees, -45 degrees, 0 degrees, 90 degrees, 0 degrees, 7 layers of different laying angles relative to the same absolute coordinate system are sequentially shown, wherein, S represents the following value]The laying sequence in the' is symmetrical to lay. Wherein, how all the composite material laying angles in the material shell are laid based on the same absolute coordinate system. Since the above-mentioned representation of the unidirectional tape laying sequence is prior art, it is not described herein in detail.
More specifically, referring to fig. 3, after entering the upper end frame transition region 14 or the lower end frame transition region 15, the first layer 111 and the second layer 112 of the skin region 11 are respectively formed on the outer side surface and the inner side surface of the composite shell. In order to enhance the strength of the reinforcing rib region, the epoxy resin-based carbon fiber unidirectional tape in the second layer 112 continuously passes through the lower end frame transition region along the inner side of the composite material light shell 01 and joins after bypassing the annular reinforcing rib region 16, and the specific structure may include:
7 layers of epoxy resin based carbon fiber one-way belts in the second layer 112 are following the inboard of combined material light shell 01 place is in succession through upper end frame transition district and lower extreme frame transition district to the regional 16 positions of hoop strengthening rib separately lay, wherein 2 layers of epoxy resin based carbon fiber one-way belts on surface are walked around and are joined at the hoop strengthening rib inboard with 5 layers of epoxy resin based carbon fiber one-way belts in addition after the regional 16 of hoop strengthening rib, 5 layers of epoxy resin based carbon fiber one-way belts in bottom of second side lay promptly under the regional 16 of hoop strengthening rib, 2 layers of epoxy resin based carbon fiber one-way belts in addition walk around behind the regional 16 of hoop strengthening rib with bottom 5 layers of epoxy resin based carbon fiber one-way belts join and lay the shaping.
In addition, the upper end frame region 12 and the lower end frame region 13 each include 52 layers of epoxy resin-based carbon fiber unidirectional tapes, wherein the 52 layers of epoxy resin-based carbon fiber unidirectional tapes include 14 layers of epoxy resin-based carbon fiber unidirectional tapes of the first layer 111 and the second layer 112 of the skin region 11, the remaining 38 layers of epoxy resin-based carbon fiber unidirectional tapes are laid in layers from the upper end frame region 12, the lower end frame region 13 to the skin region 11, and the upper end frame transition region 14 and the lower end frame transition region 15 are correspondingly formed, wherein the laying sequence of the 52 layers of epoxy resin-based carbon fiber unidirectional tapes is [ ± 45/0/90/0/90/0/(± 45/0/90/0)3/(±45/0/90)]S. Wherein "3" indicates that the ply structure in parentheses is overlapped 3 times.
The circumferential reinforcing rib area 16 is wound and filled with epoxy resin-based carbon fiber unidirectional tapes, and the winding and filling sequence of each layer of epoxy resin-based carbon fiber unidirectional tapes is [0 ].
For example, in a specific implementation, the thickness of the skin region 11 may be 2.1mm, and the thickness of the upper end frame region 12 and the lower end frame region 13 may be 7.8 mm.
Specifically, as shown in fig. 4 to 5, in the composite material housing, the composite material beams 02 are co-cured and molded along the axial direction of the composite material optical shell 01 and connected to the inner wall of the composite material optical shell 01, and the composite material beams 02 are arranged at intervals.
The composite stringer 02 is a T-shaped stringer, the T-shaped stringer comprises a flange plate 21 and a web plate 22, the web plate 22 is attached to the inner wall of the composite light shell 01, and the flange plate 21 is perpendicular to the web plate 22. In the embodiment, the T-shaped stringer can be respectively co-cured and connected to the circumferential reinforcing rib area 16 by using the structure of the circumferential reinforcing rib area 16, so as to improve the strength of the composite material shell.
More specifically, as shown in fig. 5, in the T-shaped stringer: the above-mentionedThe flange plate 21 at least comprises 10 layers of epoxy resin-based carbon fiber unidirectional tapes, and the layering sequence of the 10 layers of epoxy resin-based carbon fiber unidirectional tapes is [ +/-45/0/90/0]S. Furthermore, the web 22 comprises at least 16 layers of epoxy resin-based carbon fiber unidirectional tape, and the ply sequence of the 16 layers of epoxy resin-based carbon fiber unidirectional tape is [ + -45/0/90/0/+ -45/0 [)]S。
Illustratively, in particular implementations, the rim plate 21 may be 1.5mm thick and the web plate 22 may be 2.4mm thick.
In addition, as shown in fig. 1-2, a plurality of air duct outlets 17 are formed through the composite material light shell 01 in the circumferential direction. The air duct outlet 17 serves as an outlet for the track correction flame when the composite shell is assembled for use.
To sum up, the utility model discloses compare in prior art, its outstanding contribution lies in: the composite material shell main structure is integrally formed, so that the weight of a product can be reduced by more than 30%; meanwhile, the strength and the rigidity of the shell are ensured by performing and co-curing assembly of the composite material stringer 02 and the shell. Meanwhile, the integrally formed structure effectively reduces the fasteners and assembly required by stringer assembly, so that the processing time period is shortened, and the processing cost is reduced.
The above description is only exemplary of the present invention and should not be taken as limiting the scope of the present invention, as any modifications, equivalents, improvements and the like made within the spirit and principles of the present invention are intended to be included within the scope of the present invention.
Claims (10)
1. A composite shell, comprising: the composite material light shell and a plurality of composite material stringers, its characterized in that:
the composite light shell comprises: the composite structure comprises a skin area, an upper end frame area and a lower end frame area which are positioned at two ends of the skin area, an upper end frame transition area which is in transition extension from the upper end frame area to the skin area, a lower end frame transition area which is in transition extension from the lower end frame area to the skin area, and annular reinforcing rib areas which are circumferentially arranged along the inner side surfaces of the upper end frame area and the lower end frame area respectively, wherein the skin area, the upper end frame area, the lower end frame area, the upper end frame transition area, the lower end frame transition area and the annular reinforcing rib areas are epoxy resin-based carbon fiber unidirectional belts which are integrally paved with a curing molding structure;
the composite material stringers are connected to the inner wall of the composite material light shell in a co-curing molding mode along the axial direction of the composite material light shell, and the composite material stringers are arranged at intervals.
2. The composite shell of claim 1, wherein:
the composite stringer is a T-shaped stringer, the T-shaped stringer comprises a flange plate and a web plate, the web plate is attached to the inner wall of the composite light shell, and the flange plate is perpendicular to the web plate.
3. The composite shell of claim 2, wherein:
the flange plate at least comprises 10 layers of epoxy resin-based carbon fiber unidirectional tapes, and the layering sequence of the 10 layers of epoxy resin-based carbon fiber unidirectional tapes is [ +/-45/0/90/0 [)]S；
The web plate at least comprises 16 layers of epoxy resin-based carbon fiber unidirectional tapes, and the layering sequence of the 16 layers of epoxy resin-based carbon fiber unidirectional tapes is [ +/-45/0/90/0/+/-45/0]S。
4. The composite shell of claim 1, wherein:
in the composite material light shell, the skin area comprises a first layer and a second layer, the epoxy resin-based carbon fiber unidirectional tape in the first layer continuously passes through an upper end frame transition area to an upper end frame area along the outer side of the composite material light shell, and the epoxy resin-based carbon fiber unidirectional tape in the second layer continuously passes through a lower end frame transition area along the inner side of the composite material light shell and joins after bypassing the annular reinforcing rib area.
5. The composite shell of claim 4, wherein:
the skin area at least comprises 14 layers of epoxy resin-based carbon fiber unidirectional tapes;
the first layer comprises 7 layers of epoxy resin-based carbon fiber unidirectional tapes, the second layer comprises 7 layers of epoxy resin-based carbon fiber unidirectional tapes, the epoxy resin-based carbon fiber unidirectional tapes in the first layer and the second layer are of symmetrical structures, and the paving sequence of the epoxy resin-based carbon fiber unidirectional tapes in the first layer and the second layer is [ +/-45/0/90/0/90/0 ] s.
6. The composite material housing of claim 5, wherein the epoxy resin-based carbon fiber unidirectional tape in the second layer continuously passes through a lower end frame transition region along the inner side of the composite material light shell and joins after bypassing the circumferential reinforcing rib region, and specifically comprises:
7 layers of epoxy resin-based carbon fiber one-way belts in the second layer are separated from the annular reinforcing rib area through the lower end frame transition area continuously along the inner side of the composite material light shell, wherein 2 layers of epoxy resin-based carbon fiber one-way belts bypass the annular reinforcing rib area and then are converged with the other 5 layers of epoxy resin-based carbon fiber one-way belts on the inner side of the annular reinforcing rib.
7. The composite shell of any of claims 4-6, wherein:
the upper end frame area and the lower end frame area respectively comprise 52 layers of epoxy resin-based carbon fiber unidirectional tapes, each 52 layers of epoxy resin-based carbon fiber unidirectional tapes comprise 14 layers of epoxy resin-based carbon fiber unidirectional tapes of the first layer and the second layer of the skin area, wherein the remaining 38 layers of epoxy resin-based carbon fiber unidirectional tapes are arranged in the upper end frame area and the lower end frame area to the skin area respectively to be subjected to layer losing and laying, the upper end frame transition area and the lower end frame transition area are correspondingly formed, and the laying sequence of the 52 layers of epoxy resin-based carbon fiber unidirectional tapes is [ +/-45/0/90/0/90/0/(+/-45/0/90/0)3/(±45/0/90)]S。
8. The composite material shell as claimed in claim 7, wherein the circumferential reinforcing rib area is wound and filled with epoxy resin-based carbon fiber unidirectional tapes, and the winding and filling sequence of each layer of epoxy resin-based carbon fiber unidirectional tapes is [0 ].
9. The composite housing of claim 1 wherein a plurality of duct outlets are formed through the composite lightshell circumferentially.
10. An aircraft, characterized in that it comprises a composite shell according to any one of claims 1 to 9.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114001599A (en) * | 2021-11-16 | 2022-02-01 | 天津爱思达新材料科技有限公司 | Cabin section internal reinforcing rib structure |
| CN114046694A (en) * | 2021-11-03 | 2022-02-15 | 天津爱思达航天科技有限公司 | Composite material shell connecting frame reinforcing structure |
| CN114659415A (en) * | 2022-03-01 | 2022-06-24 | 航天科工火箭技术有限公司 | Lightweight cabin section structure of carrier |
| CN116518795A (en) * | 2023-07-03 | 2023-08-01 | 江苏亨睿航空工业有限公司 | Carbon fiber composite satellite supporting cabin and preparation method thereof |
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2020
- 2020-10-27 CN CN202022407622.XU patent/CN212290307U/en active Active
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114046694A (en) * | 2021-11-03 | 2022-02-15 | 天津爱思达航天科技有限公司 | Composite material shell connecting frame reinforcing structure |
| CN114001599A (en) * | 2021-11-16 | 2022-02-01 | 天津爱思达新材料科技有限公司 | Cabin section internal reinforcing rib structure |
| CN114659415A (en) * | 2022-03-01 | 2022-06-24 | 航天科工火箭技术有限公司 | Lightweight cabin section structure of carrier |
| CN114659415B (en) * | 2022-03-01 | 2024-02-09 | 航天科工火箭技术有限公司 | Light cabin section structure of carrier |
| CN116518795A (en) * | 2023-07-03 | 2023-08-01 | 江苏亨睿航空工业有限公司 | Carbon fiber composite satellite supporting cabin and preparation method thereof |
| CN116518795B (en) * | 2023-07-03 | 2023-09-15 | 江苏亨睿航空工业有限公司 | Carbon fiber composite satellite supporting cabin and preparation method thereof |
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