CN111453004A - Prefabricated body containing wing beam supporting frame - Google Patents
Prefabricated body containing wing beam supporting frame Download PDFInfo
- Publication number
- CN111453004A CN111453004A CN201910051518.0A CN201910051518A CN111453004A CN 111453004 A CN111453004 A CN 111453004A CN 201910051518 A CN201910051518 A CN 201910051518A CN 111453004 A CN111453004 A CN 111453004A
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- Prior art keywords
- inner ring
- spar
- outer ring
- wing
- ring
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- 239000000835 fiber Substances 0.000 claims abstract description 84
- 239000004744 fabric Substances 0.000 claims abstract description 34
- 239000010410 layer Substances 0.000 claims description 36
- 239000002131 composite material Substances 0.000 claims description 19
- 230000000149 penetrating effect Effects 0.000 claims description 13
- 238000009958 sewing Methods 0.000 claims description 7
- 239000002344 surface layer Substances 0.000 claims description 6
- 238000010030 laminating Methods 0.000 claims 5
- 238000013329 compounding Methods 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 10
- 239000012783 reinforcing fiber Substances 0.000 description 5
- 238000007493 shaping process Methods 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000003287 optical effect Effects 0.000 description 3
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- 239000004917 carbon fiber Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
- 238000004026 adhesive bonding Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 1
- 229910010271 silicon carbide Inorganic materials 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention provides a prefabricated body containing a wing beam supporting frame, which comprises an inner ring, a plurality of wing beams and an outer ring, wherein the inner ring is formed by compounding fibers and fabrics of the fibers, the outer ring is arranged on the outer side of the inner ring and is not contacted with the inner ring, one end of each wing beam is attached to the inner ring, the other end of each wing beam penetrates through the outer side of the outer ring to be attached and connected, and continuous fibers penetrate through the contact parts of the wing beams, the inner ring and the outer ring in the thickness direction. The prefabricated body formed by the integrally arranged inner ring, the integrally arranged outer ring and the integrally arranged wing beam increases the content of continuous fibers between adjacent components, so that the integrity and the stability of the product are greatly improved, and the prefabricated body is more suitable for the space environment. The inner surface of the outer ring base of the prefabricated body is flat, and the use requirement of the structure is met.
Description
Technical Field
The invention relates to the technical field of three-dimensional preform design, in particular to a preform with a spar support frame.
Background
This section is intended to provide a background or context to the implementation of the embodiments of the invention that is recited in the claims and the detailed description. The description herein is not admitted to be prior art by inclusion in this section.
The structural stability of the space camera is an important problem in the structural design of space science instruments, and the optical performance of the space camera is determined to a great extent by the stability of the camera structure under the influence of external loads and environments, so that the supporting structure and the optical elements of the camera need to be adjusted correspondingly in material application and structural form to meet the conditions of reducing the structural weight and limiting the emission cost of the space camera.
If a support integration speculum, it sets up through integrated into one piece for overall structure can be more stable, and has avoided the trouble of independent preparation, but because metal density itself is higher, thereby it is big to lead to prefabricated frame overall structure weight, and coefficient of thermal expansion is high, can't satisfy the high requirement of space environment light weight high strength, cold and hot stability.
And another light coaxial three-reflection space optical remote sensor structure comprises a fiber outer lens hood assembly, a silicon carbide secondary mirror assembly, a carbon fiber secondary mirror lens hood assembly and the like. The composite material is used for preparing each part, and the fiber composite material has the advantages of ensuring that the integral structural part can meet the requirements of dimensional stability and structural stability in a space harsh environment. However, since the parts are manufactured separately, the parts need to be connected by mechanical connection or adhesive bonding, so that the overall process is complicated, the production cost is increased, and the continuity of the fiber is easily damaged in the mechanical processing process, thereby reducing the overall performance and stability. There is therefore a need for a structure which is produced from a composite material and which can be integrally formed.
Disclosure of Invention
The invention aims to provide a prefabricated body with a wing beam supporting frame, which has the characteristics of capability of ensuring that the performance of the integral structure of the prefabricated body is improved, low production cost and short production period.
The technical scheme provided by the invention is as follows:
a prefabricated body containing a wing beam supporting frame comprises an inner ring, a plurality of wing beams and an outer ring which are formed by fibers and fabrics in a composite mode, wherein the outer ring is arranged on the outer side of the inner ring, the inner ring and the outer ring are not in contact with each other, one end of each wing beam is attached to the inner ring, the other end of each wing beam penetrates through the outer side of the outer ring to be attached and connected, and continuous fibers penetrate through the thickness direction of the contact portion of the wing beams, the inner ring and the outer ring.
Preferably, the spar comprises a fitting portion arranged around the inner ring, the fitting portion being fixedly connected to the inner ring by continuous fibres running through it to form a single piece.
Preferably, the spar comprises a plurality of layers of fibre fabric stacked one on top of the other, each layer of fibre fabric having one end in contact with the inner ring and the other end extending outwardly in a direction tangential to the inner ring to form a wing.
Preferably, the wing plate is provided with an extension part which penetrates through the outer ring and is mutually attached to the outer side of the circumference of the outer ring, and the extension part is continuous fibers which extend from a plurality of layers of fiber fabrics in the wing plate along the tangential direction of the inner ring.
Preferably, the extension part penetrates through the outer ring to form a through seam, and the extension part penetrates through the outer ring and then is distributed on two sides of the through seam in a crossed and symmetrical mode.
Preferably, the spar is provided with a plurality of spars, the circumferential array of spars is arranged on the outer side of the inner ring, and two adjacent attaching portions are provided with overlapping portions.
Preferably, the attaching portions are far away from one end of the wing beam and are circumferentially arranged outside the inner ring, the ratio of the distance between the end portions of the two adjacent attaching portions to the circumference of the inner ring is one-fourth of the number of the wing beams, and the attaching portions of the wing beams are attached to the inner ring to form equal thickness.
Preferably, the connection corner regions of the contact parts of the spar and the inner ring and the outer ring are respectively provided with a reinforcing fiber felt.
Preferably, the inner surface layer and the outer surface layer of the preform are respectively provided with a fiber composite profiling layer, and the fiber composite profiling layer is fixed with the preform through penetrating continuous fibers.
Preferably, the inner ring comprises a plurality of layers of fiber fabrics, and at least two layers of fiber fabrics extend along the radial direction, are attached and connected in a sewing mode to form an inner rib which equally divides the circumference of the inner ring.
Compared with the prior art, the supporting frame prefabricated body containing the wing beam comprises an inner ring, a plurality of wing beams and an outer ring, wherein the inner ring, the wing beams and the outer ring are formed by compounding fibers and fabrics of the fibers, the outer ring is arranged on the outer side of the inner ring and is not in contact with the inner ring, one end of each wing beam is attached to the inner ring, the other end of each wing beam penetrates through the outer side of the outer ring to be attached and connected, and continuous fibers penetrate through the contact parts of the wing beams, the inner ring and the outer ring in the thickness. The prefabricated body formed by the integrally arranged inner ring, the integrally arranged outer ring and the integrally arranged wing beam increases the content of continuous fibers between adjacent components, so that the integrity and the stability of the product are greatly improved, and the prefabricated body is more suitable for the space environment. The inner surface of the outer ring base of the prefabricated body is flat, and the use requirement of the structure is met.
And the content of continuous fibers between adjacent components is increased through the reinforced fiber felt which is added in the connecting corner area, so that the integrity and the stability of the product are greatly improved.
The connection between the wing beam and the inner ring and the connection between the wing beam and the outer ring are tighter through the joint part sewed and fixed with the inner ring on the wing beam and the extension part penetrating through the outer ring; and through the fiber composite profiling layer on the outer side, the surface of the prefabricated body can be smooth, and the use requirement of the structure is met.
Drawings
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
Fig. 1 is an overall schematic view of a support frame preform including a spar according to example 1 of the present invention.
Fig. 2 is an overall schematic view of the spread of the spars in embodiment 1 of the present invention.
Fig. 3 is an enlarged schematic view of a portion a in fig. 1.
Fig. 4 is an enlarged schematic view of a portion B in fig. 1.
FIG. 5 is a schematic view of the entire structure of embodiment 2.
Description of reference numerals:
the following detailed description further illustrates embodiments of the invention in conjunction with the above-described figures.
Detailed Description
So that the manner in which the above recited objects, features and advantages of embodiments of the present invention can be understood in detail, a more particular description of the invention, briefly summarized above, may be had by reference to the embodiments thereof which are illustrated in the appended drawings. In addition, the features of the embodiments of the present application may be combined with each other without conflict.
In the following description, numerous specific details are set forth to provide a thorough understanding of embodiments of the invention, and the described embodiments are merely a subset of embodiments of the invention, rather than a complete embodiment. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments of the present invention without any creative effort belong to the protection scope of the embodiments of the present invention.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which embodiments of the present invention belong. The terminology used herein in the description of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the embodiments of the invention.
A prefabricated body containing a spar support frame comprises an inner ring 1, a plurality of spars 2 and an outer ring 3, wherein the outer ring 3 is arranged on the outer side of the inner ring 1 and is not in contact with the inner ring 1, one end of each spar 2 is attached to the inner ring 1, the other end of each spar 2 penetrates through the outer side of the outer ring 3 and is attached to the outer ring, and continuous fibers penetrate through the contact parts of the spars 2, the inner ring 1 and the outer ring 3 in the thickness direction. Therefore, the integral structure of the prefabricated body can be more stable through the integral arrangement of all the components; and through each component by fibre combined material makes, can reduce the damage that the mechanical connection in-process caused to the fibre for the wholeness and the stability of preform can promote by a wide margin, satisfy the high requirement of space environment light weight high strength and cold and hot stability.
In some embodiments, as shown in fig. 1, the inner ring 1 is a preform central support structure, which is a circular ring formed by stacking a plurality of layers of fiber fabrics; the inner ring 1 is used as a supporting structure, when the size of the inner ring 1 is large, the inner ring 1 is easy to deform in the supporting process, so that, as shown in fig. 1, the inner ring 1 comprises a plurality of layers of fiber fabrics, and at least two layers of fiber fabrics extend along the radial direction to be attached and are connected in a sewing mode to form an inner rib 6 which is used for equally dividing the circumference of the inner ring 1. The periphery of the inner ring 1 is supported through the inner ribs 6, so that deformation of the inner ring 1 in the supporting process is avoided.
In some embodiments, as shown in fig. 2, the spar 2 comprises a fitting 21, a wing 23 and an extension 22, wherein the fitting 21 may be arranged around the outer circumference of the inner ring 1, the fitting 21 being fixedly connected with the inner ring 1 by continuous fibres running through. The wing spar 2 and the inner ring 1 are integrally connected through the attaching portion 21, and stable connection between the wing spar 2 and the attaching portion 21 is guaranteed through the attaching portion 21.
In some embodiments, a plurality of spars 2 are provided, the spars 2 being arranged in a circumferential array around the circumference of the inner ring 1, with an overlap between two adjacent doublers 21. Through the setting of a plurality of spars 2 for be connected inseparabler between outer ring 3 and the inner ring 1, and simultaneously, through the setting of a plurality of spars 2, can provide the support by the multiple spot in inner ring 1 periphery, avoided the deformation of inner ring 1 and outer ring 3 in the use.
In some embodiments, the attaching portions 21 are arranged outside the inner ring 1 in a circumferential array away from one end of the spar 2, the ratio of the distance between the ends of two adjacent attaching portions 21 to the circumference of the inner ring 1 is one-third of the distance between the ends of two adjacent attaching portions 21 to the circumference of the inner ring 1 if the spars 2 are three, and the attaching portions 21 of the spars 2 and the inner ring 1 are equal in thickness after being attached. Thus, the equal thickness formed by the attaching part 21 and the inner ring 1 after attaching can keep the consistent thickness in the circumferential direction of the inner ring 1 in the using process, thereby ensuring the balanced and stable support of the inner ring 1.
In some embodiments, the spar 2 comprises a plurality of stacked layers of continuous fiber fabric, as shown in fig. 2, the stacked layers of fiber fabric on the spar 2 extend outward along the tangent direction of the inner ring 1 to form a wing plate 23, wherein the plurality of layers of fiber fabric forming the wing plate 23 surround the outer periphery of the inner ring 1 near one end of the inner ring 1 to form a fitting portion 21, or the fitting portion 21 on the spar 2 comprises a plurality of layers of fiber fabric stacked with the plurality of layers of fiber fabric forming the wing plate 23, and the overlapped portion between the layers of fiber fabric on the fitting portion 21 and the layers of fiber fabric on the wing plate 23 is fixed on the outer periphery of the inner ring 1 through continuous fibers. The wing plates 23 are arranged to facilitate the connection of the space between the inner ring 1 and the outer ring 3, and the wing plates 23 extend along the tangential direction of the inner ring 1, so that the mutual stress between the inner ring 1 and the wing plates 23 in the supporting process is reduced, and the deformation of the connection part of the wing plates 23 and the inner ring 1 in the using process can be effectively avoided.
In some embodiments, in order to achieve the interconnection between the spar 2 and the outer ring 3, as shown in fig. 2, the wing plate 23 is provided with an extension portion 22, the extension portion 22 is formed by extending an end of the wing plate 23 away from the inner ring 1, the extension portion 22 is a plurality of continuous fibers extending in a tangential direction of the inner ring 1 from a fiber fabric layer in the wing plate 23, and the extension portion 22 penetrates through the outer ring 3 and is attached to the outer side of the circumference of the outer ring 3; in some embodiments, extensions 22 occupy 1/2-1/4 of the radially continuous fibers in panel 23. Through the limitation of the proportion of the extension parts 22 in the warp fibers, not only can the stable fixation between the outer ring 3 and the spar 2 be ensured, but also the accumulation of the extension parts 22 caused by the overhigh ratio of the extension parts 22 is effectively avoided, and the stable connection of the fixed structure is facilitated.
In some embodiments, in order to ensure the penetration of the extension 22, as shown in fig. 3, the extension 22 forms a penetrating slit through the outer ring 3, and the extensions 22 are stacked crosswise on both sides of the penetrating slit after penetrating through the outer ring 3. The extending part 22 penetrates through the outer ring 3, so that the spar 2 and the outer ring 3 are integrally arranged, and the stability of the connecting structure between the outer ring 3 and the extending part 22 is ensured.
According to the invention, the integral performance of the prefabricated body is improved through the prefabricated body consisting of the integrally arranged inner ring 1, the integrally arranged outer ring 3 and the integrally arranged wing beam 2, and the inner ring 1, the integrally arranged outer ring 3 and the integrally arranged wing beam 2 are all made of fiber composite materials, so that the prefabricated body can meet the high requirements of light weight, high strength and cold and hot stability of a space environment in the using process, and the content of continuous fibers between adjacent components is increased through the reinforced fiber felt 4 additionally arranged in the connecting corner area, so that the integrity and the stability of a product are greatly improved.
To better illustrate the spar-containing support frame preform provided by the present invention, some examples of the present invention are given below.
Example 1:
a prefabricated body containing a spar support frame comprises an inner ring 1, a plurality of spars 2 and an outer ring 3 which are integrally formed, wherein the spars 2 are positioned between the inner ring 1 and the outer ring 3, and the number of the spars 2 is three; in the embodiment, the inner ring 1, the spar 2 and the outer ring 3 are all made of fiber composite materials, and the inner ring 1 is formed by laying fiber cloth layer by layer in a profiling staggered manner and sewing.
In the embodiment, as shown in fig. 5, inner ribs 6 are arranged on the inner side of the inner ring 1, the inner ribs 6 are arranged along the radius of the inner ring 1, and the inner ribs are arranged on the inner side of the inner ring 1 in a circumferential array; in this embodiment, the inner ribs 6 are formed by sewing a plurality of sets of fiber cloth two by two, and after sewing a plurality of sets of fiber cloth two by two, the remaining fiber cloth is wrapped around the inner ring 1 respectively to two sides in a staggered manner and sewn to form the inner ring 1 with the inner ribs 6.
In the present embodiment, in order to ensure the integral arrangement between the spar 2 and the inner ring 1, as shown in fig. 1 and 2, the spar 2 includes an attaching portion 21 attached to the inner ring 1, where the attaching portion 21 is fixedly connected to the inner ring 1 through a continuous fiber penetrating therethrough to form a whole, and two adjacent attaching portions 21 are stacked.
In this embodiment, the attaching portion 21 includes a plurality of layers of stacked fiber fabrics, and one end of each layer of fiber fabric is disposed in contact with the inner ring 1; in the embodiment, as shown in fig. 1, the attaching portions 21 are arranged outside the inner ring 1 in a circumferential array at an end away from the spar 2, and a ratio of a distance between two adjacent attaching portions 21 to a circumference of the inner ring 1 is one third.
In this embodiment, as shown in fig. 1, the spar 2 further includes a wing plate 23 extending along a tangential direction of the inner ring 1, and in order to achieve mutual fixation between the spar 2 and the outer ring 3, as shown in fig. 3, an extension portion 22 penetrating the outer ring 3 is provided at an end portion of the wing plate 23 close to the outer ring 3, where the extension portion 22 is a continuous fiber extending from an inside of the wing plate 23, and the extension portion 22 is laid on and attached to an outer side of a circumference of the outer ring 3.
And as shown in fig. 3, the extension portion 22 penetrates the outer ring 3 to form a penetrating seam, and the extension portion 22 penetrates the outer ring 3 and then is symmetrically distributed on two sides of the penetrating seam. In this embodiment, extensions 22 through outer ring 3 account for 1/2 of the total amount of warp fibers on spar 2.
In this embodiment, in order to further ensure the stability of the connection between the spar 2 and the inner ring 1 and the outer ring 3, as shown in fig. 4, reinforcing fiber mats 4 are respectively disposed on the spar 2 at the connection corner regions with the inner ring 1 and the outer ring 3, and the reinforcing fiber mats 4 are placed in the connection corner regions by filling and are respectively connected with the spar 2, the inner ring 1 and the outer ring 3 by sewing. Like this, through the setting of the reinforcing fiber felt 4 that is located the connection angle district setting for the content of continuous fiber has obtained increasing effectively between adjacent component, in the use, has further promoted the holistic wholeness of preform and stability.
In this embodiment, as shown in fig. 4, the composite fiber shaping layer 5 further includes an outer fiber shaping layer, the composite fiber shaping layer 5 is disposed on an inner surface layer and an outer surface layer of the preform to protect the surface of the preform, and the composite fiber shaping layer 5 and the preform are fixed by continuous fibers penetrating through the continuous fibers.
In this embodiment, the fiber composite material and the fiber cloth used for forming the inner ring 1, the spar 2, the outer ring 3 and the fiber composite conformal layer 5 are carbon fiber cloth, and the surface density thereof is 150g/m2。
Example 2:
this embodiment is substantially the same as embodiment 1 except that, as shown in fig. 5, the number of spars 2 is four, and the support structure can be made more stable by increasing the number of spars 2. Here, the distance between two adjacent abutting portions 21 away from the end of the spar 2 is one fourth of the outer diameter of the inner ring 1. Thus, the attaching portions 21 can be uniformly distributed on the outer side of the inner ring 1, stable fixation between the spar 2 and the inner ring 1 is achieved through the attaching portions 21, and stable fixation between the inner ring 1 and the attaching portions 21 is guaranteed.
In conclusion, according to the invention, the integral performance of the prefabricated body is improved by the integrally arranged prefabricated body consisting of the inner ring 1, the outer ring 3 and the wing beam 2, and the inner ring 1, the outer ring 3 and the wing beam 2 are all made of fiber composite materials, so that the prefabricated body can meet the high requirements of light weight, high strength and cold and hot stability of a space environment in the using process, and the content of continuous fibers between adjacent components is increased by the reinforcing fiber felt 4 added in the connecting corner area, so that the integrity and the stability of a product are greatly improved.
Although the embodiments of the present invention have been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that various changes may be made and equivalents may be substituted without departing from the spirit and scope of the embodiments of the present invention.
Claims (10)
1. The utility model provides a contain spar braced frame prefabricated body which characterized in that: the composite fiber beam comprises an inner ring, a plurality of wing beams and an outer ring, wherein the inner ring is formed by fibers and fabrics of the fibers in a composite mode, the outer ring is arranged on the outer side of the inner ring, the inner ring and the outer ring are not in contact with each other, one end of each wing beam is attached to the inner ring, the other end of each wing beam penetrates through the outer side of the outer ring to be attached and connected, and continuous fibers penetrate through the thickness direction of the contact portion of the wing.
2. The spar-containing support frame preform of claim 1, wherein: the spar comprises a joint part arranged on the inner ring in a surrounding mode, and the joint part is fixedly connected with the inner ring through continuous fibers so as to form a whole.
3. The spar-containing support frame preform of claim 2, wherein: the wing beam comprises a plurality of layers of fiber fabrics which are stacked, one end of each layer of fiber fabric is in contact with the inner ring, and the other end of each layer of fiber fabric extends outwards along the tangential direction of the inner ring to form a wing plate.
4. The spar-containing support frame preform of claim 3, wherein: the wing plate is provided with an extension part which penetrates through the outer ring and is mutually attached to the outer side of the circumference of the outer ring, and the extension part is a plurality of bundles of continuous fibers extending from a plurality of layers of fiber fabrics in the wing plate along the tangential direction of the inner ring.
5. The spar-containing support frame preform of claim 4, wherein: the extension parts penetrate through the outer ring to form penetrating seams, and the extension parts penetrate through the outer ring and then are distributed on two sides of the penetrating seams in a crossed and symmetrical mode.
6. The spar-containing support frame preform of claim 2, wherein: the wing beam is provided with a plurality of, and wing beam circumference array sets up the inner ring outside, two adjacent laminating portion is equipped with the overlap portion.
7. The spar-containing support frame preform of claim 6, wherein: the laminating portion is kept away from spar one end circumference array sets up the inner ring outside, and adjacent two the distance between the laminating portion tip is one-tenth of the spar number with the ratio of inner ring girth, and is a plurality of the laminating portion of spar is equal thickness with the inner ring laminating back.
8. The spar-containing support frame preform of claim 1, wherein: and the connection angle regions of the contact parts of the wing beam and the inner ring and the outer ring are respectively provided with a reinforced fiber felt.
9. The spar-containing support frame preform of claim 1, wherein: the inner surface layer and the outer surface layer of the prefabricated body are respectively provided with a fiber composite profiling layer, and the fiber composite profiling layer is fixed with the prefabricated body through penetrating continuous fibers.
10. The spar-containing support frame preform of claim 1, wherein: the inner ring comprises a plurality of layers of fiber fabrics, and at least two layers of fiber fabrics extend along the radial direction to be attached and are connected in a sewing mode to form inner ribs which equally divide the circumference of the inner ring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910051518.0A CN111453004B (en) | 2019-01-21 | 2019-01-21 | Spar-containing support frame preform |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910051518.0A CN111453004B (en) | 2019-01-21 | 2019-01-21 | Spar-containing support frame preform |
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| CN111453004A true CN111453004A (en) | 2020-07-28 |
| CN111453004B CN111453004B (en) | 2024-09-17 |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101668679A (en) * | 2007-04-26 | 2010-03-10 | 空中客车营运有限公司 | Aircraft wing-fuselage section |
| US20100090061A1 (en) * | 2007-01-23 | 2010-04-15 | Airbus Deutschland Gmbh | Fuselage of an aircraft or spacecraft of crp/metal hybrid construction with a metal framework |
| CN101767646A (en) * | 2009-01-07 | 2010-07-07 | 通用电气航空系统有限公司 | Composite spars |
| CN102619693A (en) * | 2012-04-05 | 2012-08-01 | 昂海松 | Wind driven generator with bionic wing structure blades |
| CN102814996A (en) * | 2012-08-24 | 2012-12-12 | 中国人民解放军国防科学技术大学 | Preparing method of hybrid composite wing spar of large-scale wind power blade |
| US20140145031A1 (en) * | 2012-11-26 | 2014-05-29 | The Boeing Company | Vertically Integrated Stringers |
| US20170302006A1 (en) * | 2015-06-04 | 2017-10-19 | The Boeing Company | Omnidirectional Antenna System |
-
2019
- 2019-01-21 CN CN201910051518.0A patent/CN111453004B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100090061A1 (en) * | 2007-01-23 | 2010-04-15 | Airbus Deutschland Gmbh | Fuselage of an aircraft or spacecraft of crp/metal hybrid construction with a metal framework |
| CN101668679A (en) * | 2007-04-26 | 2010-03-10 | 空中客车营运有限公司 | Aircraft wing-fuselage section |
| CN101767646A (en) * | 2009-01-07 | 2010-07-07 | 通用电气航空系统有限公司 | Composite spars |
| CN102619693A (en) * | 2012-04-05 | 2012-08-01 | 昂海松 | Wind driven generator with bionic wing structure blades |
| CN102814996A (en) * | 2012-08-24 | 2012-12-12 | 中国人民解放军国防科学技术大学 | Preparing method of hybrid composite wing spar of large-scale wind power blade |
| US20140145031A1 (en) * | 2012-11-26 | 2014-05-29 | The Boeing Company | Vertically Integrated Stringers |
| US20170302006A1 (en) * | 2015-06-04 | 2017-10-19 | The Boeing Company | Omnidirectional Antenna System |
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| CN111453004B (en) | 2024-09-17 |
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