CN111453004B - Spar-containing support frame preform - Google Patents
Spar-containing support frame preform Download PDFInfo
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- CN111453004B CN111453004B CN201910051518.0A CN201910051518A CN111453004B CN 111453004 B CN111453004 B CN 111453004B CN 201910051518 A CN201910051518 A CN 201910051518A CN 111453004 B CN111453004 B CN 111453004B
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- spar
- inner ring
- ring
- outer ring
- support frame
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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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Abstract
The invention provides a support frame preform containing a spar, which comprises an inner ring, a plurality of spars and an outer ring, wherein the inner ring, the spars 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 contacted with the inner ring, one end of each spar is attached to the inner ring, the other end of each spar penetrates through the outer side of the outer ring to be attached and connected, and continuous fibers penetrate through the contact parts of the spars, the inner ring and the outer ring in the thickness direction. The content of continuous fibers among adjacent components is increased through the prefabricated body formed by the integrally arranged inner ring, outer ring and spar, so that the integrity and stability of the product are greatly improved, and the prefabricated body is more suitable for a 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 support frame preform containing a spar.
Background
This section is intended to provide a background or context for the implementation of the embodiments of the invention that are set forth 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 a space camera is an important problem in the structural design of a space science instrument, and the optical performance of the space camera is largely determined by the stability of the camera structure under the external load and the environmental influence, so that the supporting structure and the optical element of the camera need to be correspondingly adjusted in material application and structural form to meet the conditions of the space camera for reducing the structural weight and the emission cost.
If a support integrated reflecting mirror, it sets up through integrated into one piece for overall structure can be more stable, and has avoided the trouble of alone preparation, but because metal itself density is higher, thereby lead to prefabricated frame overall structure weight big, and coefficient of thermal expansion is high, can't satisfy the high requirement that space environment is light in weight high strength, cold and hot stable.
And another light coaxial three-reflector space optical remote sensor structure comprises a fiber outer light shield component, a silicon carbide secondary mirror component, a carbon fiber secondary mirror light shield component and the like. The composite material is used for preparing all the components, and the fiber composite material has the advantages of ensuring that the whole structural member can meet the requirements of dimensional stability and structural stability in a severe space environment. However, since the parts are manufactured separately, the parts are required to be connected by a mechanical connection or an adhesive bonding method, so that the overall process is complicated, the production cost is increased, and the continuity of the fibers 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 spar-containing support frame preform, which has the characteristics of capability of ensuring the improvement of the performance of the whole structure of the preform, low production cost and short production period.
The technical scheme provided by the invention is as follows:
the utility model provides a contain spar supporting frame prefabrication body, includes by fibre and its fabric composite forming's inner ring, a plurality of spar and outer loop, the outer loop sets up the outside of inner ring and both are contactless each other, spar one end laminating inner ring, the other end runs through to the outside laminating of outer loop and connects, just spar and inner ring, outer loop contact part thickness direction run through have continuous fiber.
Preferably, the spar comprises a conforming portion circumferentially disposed on the inner ring, the conforming portion being fixedly connected to the inner ring by continuous fibres passing therethrough to form a whole.
Preferably, the spar comprises a stack of layers of fibrous fabric, each layer having one end in contact with the inner ring and the other end extending outwardly in a tangential direction of 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 of a plurality of layers of fiber fabrics in the wing plate, which extend along the tangential direction of the inner ring.
Preferably, the extending part penetrates through the outer ring to form a penetrating seam, and the extending part penetrates through the outer ring and is distributed on two sides of the penetrating seam in a crossed and symmetrical mode.
Preferably, the number of the spars is plural, the circumferential array of the spars is arranged outside the inner ring, and the adjacent two fitting parts are provided with overlapping parts.
Preferably, the attaching portions are arranged on the outer side of the inner ring in a circumferential array at one end of the spar, the ratio of the distance between the two adjacent attaching portion ends to the circumference of the inner ring is one half of the number of the spar, and the attaching portions of the spar and the inner ring are equal in thickness after being attached.
Preferably, the joint angles of the spar and the contact parts of the inner ring and the outer ring are respectively provided with a reinforced 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 and the preform are fixed through continuous fibers penetrating through the fiber composite profiling layer.
Preferably, the inner ring comprises a plurality of layers of fiber fabrics, and at least two layers of fiber fabrics are adhered along the radial direction, and are connected in a sewing way to form an inner rib which equally divides the circumference of the inner ring.
Compared with the prior art, the spar-containing support frame preform comprises an inner ring, a plurality of spars and an outer ring, wherein the inner ring, the spars 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 contacted with the inner ring, one end of each spar is attached to the inner ring, the other end of each spar penetrates through the outer side of the outer ring to be attached and connected, and continuous fibers penetrate through the contact parts of the spars, the inner ring and the outer ring in the thickness direction. The content of continuous fibers among adjacent components is increased through the prefabricated body formed by the integrally arranged inner ring, outer ring and spar, so that the integrity and stability of the product are greatly improved, and the prefabricated body is more suitable for a 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 by the reinforced fiber felt added in the connecting corner area, so that the integrity and stability of the product are greatly improved.
The spar is tightly connected with the inner ring and the outer ring respectively through the joint part which is sewn and fixed with the inner ring on the spar and the extension part which penetrates through the outer ring; and the surface of the preform can be leveled by the outer fiber composite profiling layer, so that the use requirement of the structure is met.
Drawings
The invention will be described in further detail with reference to the drawings and the detailed description.
FIG. 1 is a schematic view of a spar-containing support frame preform according to example 1 of the present invention.
Fig. 2 is an overall schematic of the deployment of the spar in example 1 of the present invention.
Fig. 3 is an enlarged schematic view of the portion a in fig. 1.
Fig. 4 is an enlarged schematic view of a portion B in fig. 1.
Fig. 5 is a schematic overall structure of embodiment 2.
Reference numerals illustrate:
the following detailed description will further illustrate embodiments of the invention in conjunction with the above-described drawings.
Detailed Description
In order that the above-recited objects, features and advantages of embodiments of the present application can be more clearly understood, a more particular description of the application will be rendered by reference to the appended drawings and appended detailed description. The features of the embodiments of the present application may be combined with each other without collision.
In the following description, numerous specific details are set forth in order to provide a thorough understanding of embodiments of the invention, and the described embodiments are merely some, rather than all, of the embodiments of the invention. All other embodiments, based on the embodiments of the invention, which are obtained by a person of ordinary skill in the art without making any inventive effort, are within the scope of the embodiments of the 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 invention belong. The terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention.
The utility model provides a contain spar braced frame prefabrication body, as shown in fig. 1, includes inner ring 1, a plurality of spar 2 and outer loop 3, and here, outer loop 3 locates the outside of inner ring 1 and each other does not contact between the two and set up, and spar 2 one end laminating inner ring 1, and its other end runs through to the outside of outer loop 3 and laminating with it and be connected, and spar 2 and inner ring 1, outer loop 3 contact part thickness direction run through have continuous fiber. In this way, the integral structure of the preform can be more stable through the integral arrangement of the components; and through each component of being made by fibre combined material, can reduce the damage that causes the fibre in the mechanical connection process for the wholeness and the stability of prefabrication body can promote by a wide margin, satisfy the high requirement of space environment light in weight high strength and cold and hot stable.
In some embodiments, as shown in fig. 1, the inner ring 1 is a preform center support structure that is a circular ring formed by stacking multiple layers of fiber fabric; when the inner ring 1 is large in size, the inner ring 1 is easy to deform during the supporting process of the inner ring 1, 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 are adhered along the radial direction in an extending way and are connected in a sewing way to form an inner rib 6 which equally divides the circumference of the inner ring 1. The inner ring 1 is supported by 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 joint portion 21, a wing plate 23 and an extension portion 22, wherein the joint portion 21 may be arranged around the outer circumference of the inner ring 1, and the joint portion 21 is fixedly connected with the inner ring 1 by continuous fibers passing through. The spar 2 and the inner ring 1 are integrally connected through the fitting part 21, and stable connection between the spar 2 and the fitting part 21 is ensured through the fitting part 21.
In some embodiments, the number of the spars 2 is plural, the spars 2 are arranged along a circumferential array on the outer circumference of the inner ring 1, and an overlapping portion is provided between two adjacent abutting portions 21. Through the arrangement of a plurality of spars 2 for the connection between outer loop 3 and inner loop 1 is inseparabler, and simultaneously, through the arrangement of a plurality of spars 2, can provide the support at the multiple spot in inner loop 1 periphery, has avoided the deformation of inner loop 1 and outer loop 3 in the use.
In some embodiments, the abutting portions 21 are circumferentially arranged on the outer side of the inner ring 1 away from one end of the spar 2, the ratio of the distance between the two adjacent abutting portions 21 ends to the circumference of the inner ring 1 is one half of the number of the spar 2, if the spar 2 is three, the ratio of the distance between the two adjacent abutting portions 21 ends to the circumference of the inner ring 1 is one third, and the abutting portions 21 of the multiple spars 2 are equal in thickness after being abutted with the inner ring 1. In this way, through the equal thickness formed after laminating between laminating portion 21 and inner ring 1, in the use, the circumference of inner ring 1 can keep thickness unanimous to the support of inner ring 1 has been guaranteed can balanced stability.
In some embodiments, the spar 2 comprises a plurality of stacked layers of continuous fiber fabrics, as shown in fig. 2, the stacked layers of fiber fabrics on the spar 2 are arranged to extend outwards along the tangential direction of the inner ring 1 to form a wing plate 23, wherein the layers of fiber fabrics forming the wing plate 23 are arranged around the periphery of the inner ring 1 near one end of the inner ring 1 to form a joint part 21 or the joint part 21 on the spar 2 comprises a plurality of layers of fiber fabrics mutually stacked with the layers of fiber fabrics forming the wing plate 23, and the overlapped parts between the layers of fiber fabrics on the joint part 21 and the layers of fiber fabrics on the wing plate 23 are respectively fixed on the periphery of the inner ring 1 through continuous fibers. The arrangement of the wing plates 23 facilitates 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 joint 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 one end of the wing plate 23 away from the inner ring 1 outwards, the extension portion 22 is a plurality of continuous fibers in the wing plate 23, wherein the fiber fabric layer extends along the tangential direction of the inner ring 1, and the extension portion 22 penetrates through the outer ring 3 and is mutually attached to the outer side of the circumference of the outer ring 3; in some embodiments, the extension 22 accounts for 1/2 to 1/4 of the radial continuous fibers in the wing plate 23. Through the limitation of the proportion of the extension parts 22 to 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 excessively high ratio of the extension parts 22 can be effectively avoided, and the stable connection of the fixed structure is facilitated.
In some embodiments, in order to ensure penetration of the extension 22, as shown in fig. 3, the extension 22 penetrates the outer ring 3 to form a penetration slit, and the extension 22 penetrates the outer ring 3 to be cross-piled on both sides of the penetration slit. The extension 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 a connecting structure between the outer ring 3 and the extension part 22 is ensured.
According to the invention, the integral performance of the prefabricated body is improved through the prefabricated body formed by the inner ring 1, the outer ring 3 and the spar 2 which are integrally arranged, and the prefabricated body can meet the high requirements of light weight, high strength and stable cold and heat of a space environment in the use process through the inner ring 1, the outer ring 3 and the spar 2 which are all made of fiber composite materials, and the content of continuous fibers between adjacent components is increased through the reinforced fiber felt 4 which is increased in the connecting angle area, so that the integrity and the stability of a product are greatly improved.
In order to better illustrate the spar-containing support frame preform provided by the present invention, some embodiments of the present invention are set forth below.
Example 1:
A prefabricated body with a spar supporting frame, as shown in figure 1, 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 this 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 and sewing fiber cloth layer by layer in a profiling and staggered manner.
In this embodiment, as shown in fig. 5, an inner rib 6 is disposed inside the inner ring 1, the inner rib 6 is disposed along the radius of the inner ring 1 and the circumferential array is disposed inside the inner ring 1; in this embodiment, the inner ribs 6 are formed by sewing a plurality of groups of fiber cloths in pairs, and after sewing a plurality of groups of fiber cloths in pairs, the remaining fiber cloths are respectively wrapped around the inner ring 1 in a staggered manner on both sides and sewn to form the inner ring 1 with the inner ribs 6.
In this embodiment, in order to ensure the integrated arrangement between the spar 2 and the inner ring 1, as shown in fig. 1 and 2, the spar 2 includes a joint portion 21 that is mutually jointed with the inner ring 1, where the joint portion 21 is fixedly connected with the inner ring 1 through continuous fibers that penetrate therethrough to form a whole, and two adjacent joint portions 21 are laminated.
In this embodiment, the attaching portion 21 includes a plurality of stacked layers of fiber fabrics, one end of each layer of fiber fabric being disposed in contact with the inner ring 1; in this embodiment, as shown in fig. 1, the abutting portions 21 are circumferentially arranged on the outer side of the inner ring 1 at the end far from the spar 2, and the ratio of the distance between the ends of two adjacent abutting portions 21 to the 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, in order to fix the spar 2 and the outer ring 3 to each other, as shown in fig. 3, an extension portion 22 penetrating the outer ring 3 is disposed at an end portion of the wing plate 23 near 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 out on an outer side of a circumference of the outer ring 3 and is adhered to the outer ring 3.
As shown in fig. 3, the extending portions 22 penetrate through the outer ring 3 to form a penetrating seam, and the extending portions 22 are symmetrically distributed on two sides of the penetrating seam after penetrating through the outer ring 3. In this embodiment, the extension 22 through the outer ring 3 is 1/2 of the total amount of warp fibers on the 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 arranged on the spar 2 at the connection angles with the inner ring 1 and the outer ring 3, and the reinforcing fiber mats 4 are placed in the connection angles by filling and are respectively connected with the spar 2, the inner ring 1 and the outer ring 3 by stitching. In this way, the content of continuous fibers between adjacent components is effectively increased by the arrangement of the reinforcing fiber mat 4 arranged in the connecting corner area, and the integrity and stability of the whole preform are further improved in the use process.
In this embodiment, as shown in fig. 4, the fiber composite profiling layer 5 further comprises an outer fiber composite profiling layer 5, the fiber composite profiling layer 5 is arranged on the inner surface layer and the outer surface layer of the preform to protect the surfaces of the preform, and the fiber composite profiling layer 5 and the preform are fixed through continuous fibers penetrating through the fiber composite profiling layer.
In this embodiment, the fiber composite material and the fiber cloth used to form the inner ring 1, the spar 2, the outer ring 3 and the fiber composite profiling layer 5 are carbon fiber cloth, and the surface density thereof is 150g/m 2.
Example 2:
This embodiment is substantially the same as embodiment 1, except that the number of the spars 2 is four as shown in fig. 5, and the support structure can be more stabilized by increasing the number of the spars 2. Here, the distance between the adjacent two abutment portions 21 away from the end of the spar 2 is one quarter of the outer diameter of the inner ring 1. In this way, the bonding 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 realized by the arrangement of the bonding portions 21, and stable fixation between the inner ring 1 and the bonding portions 21 is ensured.
In summary, in the invention, the prefabricated body composed of the inner ring 1, the outer ring 3 and the spar 2 which are integrally arranged improves the overall performance of the prefabricated body, and the prefabricated body is made of fiber composite materials through the inner ring 1, the outer ring 3 and the spar 2, so that in the use process, the prefabricated body can meet the high requirements of light weight, high strength and cold and heat stability of a space environment, and the content of continuous fibers between adjacent components is increased through the reinforced fiber mat 4 which is increased in a connecting angle area, so that the integrity and stability of a product are greatly improved.
The foregoing embodiments are merely for illustrating the technical solution of the embodiment of the present invention, but not for limiting the same, although the embodiment of the present invention has been described in detail with reference to the foregoing preferred embodiments, it will be understood by those skilled in the art that modifications and equivalent substitutions may be made to the technical solution of the embodiment of the present invention without departing from the spirit and scope of the technical solution of the embodiment of the present invention.
Claims (7)
1. A spar-containing support frame preform, characterized by: the outer ring is arranged on the outer side of the inner ring and is not contacted with the inner ring, one end of the spar is jointed with the inner ring, the other end of the spar penetrates through the outer side of the outer ring to be jointed and connected, and continuous fibers penetrate through the contact parts of the spar, the inner ring and the outer ring in the thickness direction;
The spar comprises a fitting part which is arranged on the inner ring in a surrounding manner, and the fitting part is fixedly connected with the inner ring through continuous fibers penetrating through the fitting part to form a whole;
The spar comprises a plurality of layers of stacked fiber fabrics, 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 is outwards extended along the tangential direction of the inner ring to form a wing plate;
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, the extension part is a plurality of bundles of continuous fibers, extending in the tangential direction of the inner ring, of a plurality of layers of fiber fabrics in the wing plate, and the extension part accounts for 1/2-1/4 of the radial continuous fibers in the wing plate.
2. The spar-containing support frame preform of claim 1, wherein: the extending parts penetrate through the outer ring to form penetrating slits, and the extending parts penetrate through the outer ring and are distributed on two sides of the penetrating slits in a crossed and symmetrical mode.
3. The spar-containing support frame preform of claim 1, wherein: the spar is provided with a plurality of spar, the spar circumferential array is arranged on the outer side of the inner ring, and two adjacent fitting parts are provided with overlapping parts.
4. A spar-containing support frame preform according to claim 3, wherein: the laminating portion is far away from spar one end circumference array sets up the inner ring outside, and adjacent two the ratio of distance between the laminating portion tip and inner ring perimeter is the spar number one-half, and a plurality of laminating portions of spar are equal thickness with the inner ring laminating back.
5. The spar-containing support frame preform of claim 1, wherein: and reinforcing fiber mats are respectively arranged at the connection angles of the contact parts of the spar and the inner ring and the outer ring.
6. The spar-containing support frame preform of claim 1, wherein: the inner and outer surface layers of the preform are respectively provided with a fiber composite profiling layer, and the fiber composite profiling layer is fixed with the preform through continuous fibers.
7. The spar-containing support frame preform of claim 1, wherein: the inner ring comprises a plurality of layers of fiber fabrics, at least two layers of fiber fabrics are adhered along the radial direction, and the fiber fabrics are connected in a sewing way to form an inner rib which equally divides the circumference of the inner ring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201910051518.0A CN111453004B (en) | 2019-01-21 | 2019-01-21 | Spar-containing support frame preform |
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| CN201910051518.0A CN111453004B (en) | 2019-01-21 | 2019-01-21 | Spar-containing support frame preform |
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| CN111453004A CN111453004A (en) | 2020-07-28 |
| CN111453004B true CN111453004B (en) | 2024-09-17 |
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Citations (2)
| 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 | The Wing-fuselage section of aircraft |
| CN101767646A (en) * | 2009-01-07 | 2010-07-07 | 通用电气航空系统有限公司 | Composite spars |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102007003277B4 (en) * | 2007-01-23 | 2012-08-02 | Airbus Operations Gmbh | Hull of an aircraft or spacecraft in CFRP metal. Hybrid construction with a metal frame |
| CN102619693B (en) * | 2012-04-05 | 2014-04-16 | 昂海松 | Wind driven generator with bionic wing structure blades |
| CN102814996B (en) * | 2012-08-24 | 2014-11-19 | 中国人民解放军国防科学技术大学 | Preparation method of hybrid composite spar for large wind turbine blades |
| US9145197B2 (en) * | 2012-11-26 | 2015-09-29 | The Boeing Company | Vertically integrated stringers |
| US10199745B2 (en) * | 2015-06-04 | 2019-02-05 | The Boeing Company | Omnidirectional antenna system |
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2019
- 2019-01-21 CN CN201910051518.0A patent/CN111453004B/en active Active
Patent Citations (2)
| 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 | The Wing-fuselage section of aircraft |
| CN101767646A (en) * | 2009-01-07 | 2010-07-07 | 通用电气航空系统有限公司 | Composite spars |
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