GB2182072A - Carbon fibre fabric band and method for its use - Google Patents
Carbon fibre fabric band and method for its use Download PDFInfo
- Publication number
- GB2182072A GB2182072A GB08625263A GB8625263A GB2182072A GB 2182072 A GB2182072 A GB 2182072A GB 08625263 A GB08625263 A GB 08625263A GB 8625263 A GB8625263 A GB 8625263A GB 2182072 A GB2182072 A GB 2182072A
- Authority
- GB
- United Kingdom
- Prior art keywords
- band
- flow
- carbon fibre
- production
- threads
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
- 239000004744 fabric Substances 0.000 title claims abstract description 46
- 239000000835 fiber Substances 0.000 title claims abstract description 36
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 title claims abstract description 30
- 229910052799 carbon Inorganic materials 0.000 title claims abstract description 29
- 238000000034 method Methods 0.000 title claims description 17
- 238000004519 manufacturing process Methods 0.000 claims abstract description 16
- 239000011241 protective layer Substances 0.000 claims abstract description 4
- 238000004804 winding Methods 0.000 claims description 9
- 239000011159 matrix material Substances 0.000 claims description 8
- 239000011248 coating agent Substances 0.000 claims description 6
- 238000000576 coating method Methods 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 6
- 239000002184 metal Substances 0.000 claims description 6
- 230000001154 acute effect Effects 0.000 claims description 3
- 230000015572 biosynthetic process Effects 0.000 claims 1
- 239000002131 composite material Substances 0.000 claims 1
- 239000010425 asbestos Substances 0.000 description 4
- 239000010410 layer Substances 0.000 description 4
- 239000005011 phenolic resin Substances 0.000 description 4
- 229910052895 riebeckite Inorganic materials 0.000 description 4
- KXGFMDJXCMQABM-UHFFFAOYSA-N 2-methoxy-6-methylphenol Chemical compound [CH]OC1=CC=CC([CH])=C1O KXGFMDJXCMQABM-UHFFFAOYSA-N 0.000 description 3
- 238000002679 ablation Methods 0.000 description 3
- 230000006378 damage Effects 0.000 description 3
- 229920001568 phenolic resin Polymers 0.000 description 3
- 230000035882 stress Effects 0.000 description 3
- 229920002430 Fibre-reinforced plastic Polymers 0.000 description 2
- 230000006866 deterioration Effects 0.000 description 2
- 239000011151 fibre-reinforced plastic Substances 0.000 description 2
- 231100000206 health hazard Toxicity 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 2
- 229920006395 saturated elastomer Polymers 0.000 description 2
- 239000004449 solid propellant Substances 0.000 description 2
- 150000001721 carbon Chemical class 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000011152 fibreglass Substances 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Classifications
-
- D—TEXTILES; PAPER
- D03—WEAVING
- D03D—WOVEN FABRICS; METHODS OF WEAVING; LOOMS
- D03D5/00—Selvedges
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0081—Fuselage structures substantially made from particular materials from metallic materials
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Textile Engineering (AREA)
- Woven Fabrics (AREA)
- Moulding By Coating Moulds (AREA)
- Laminated Bodies (AREA)
- Inorganic Fibers (AREA)
Abstract
A carbon fibre fabric band comprises warp and weft threads and is used for the production of protective layers for structural members, or for the production of structural members, subject to a medium having a high temperature and a high flow velocity for example for the production of a nozzle lining for a rocket propulsion unit with a short burning time. The weft threads (3) are in the form of U-shaped individual threads wherein their straight portions (limbs of the "U") are aligned parallel to one another and transversally to the warp threads (2) which take the longitudinal direction (4) of the band. The free ends of the weft threads (3) are all positioned on the same side of the band (5) and the free ends of the weft threads extend from the fabric of the band (5) by a distance at least equal to the width thereof. <IMAGE>
Description
SPECIFICATION
Carbon fibre fabric band and method for use thereof
This invention relates to a carbon fibre fabric band and a method of using same.
A problem frequently arising in aeronautics and space travel is that the surfaces of bodies are subjected to high temperatures and high speed of flow simultaneously. Examples are propulsion units of all kinds as well as space vehicles re-entering the Earth's atmosphere. If the high temperature and rapid flow continue over a long period or occur often the surface in question will have been designed and protected in such a way as to ensure that deterioration will progress very slowly. Nozzles for rocket propulsion units with a long burning time, for example, are generally liquid-cooled and made of materials, usually metal, having a high melting point. If the aforementioned stresses are of only short duration, as in the case of rocket nozzles with a short burning time, a higher degree of heat and mechanical damage through ablation and erosion may be accepted.In such cases use can be made of fibre-reinforced plastics, both by reason of a favourable strength-to weight ratio and due to the simple and economical production processes involved. One combination of materials customary until recently was phenol resin with asbestos fibre, but asbestos is no longer to be used owing to the health hazard. A useful substitues with the required mechanical and thermal properties is carbon fibre.If, for example, a nozzle body is made from carbon fibre fabric and phenolic resin by a method in which the materials are placed on a negative mould as is usual, and with other components in such a way that the layers of fabric are parallel to the surface of the negative mould (flow contour), then the damage from heat and the mechanical stresses in operation may be expected to cause whole layers of fabric to become delaminated or blister which rapidly leads to the destruction of the nozzle.
DEP 1203646 describes a layered, fibre-reinforced plastic wall for projectile, rocket propulsion units and the like, which enables deterioration such as that mentioned to be largely avoided. In this method a resin-saturated strip of fibre glass fabric is wound helically onto a negative mould in such a way that the cross sections of the strip overlap with a roofing tile configuration and take up an angle of about 20 in relation to the direction of flow, while the flow contour is formed by those edges of the fabric strips which are orientated downstream.This reliably prevents the blistering of whole layers of fabric but certain threads of the fabric which are positioned transversally to the flow can still become detached from those edges of the strips of fabric which form the flow contour, as a result of which ablation or wear will steadily continue, even though at a slower rate.
This invention seeks to provide a fabric which will form the flow contour wherein ablation or wear steadily continues but at a slower rate.
In this invention a fabric band is provided and a method for use thereof, wherein a structural member will last for a far longer time.
According to this invention there is provided a carbon fibre fabric band for the production of protective layers for structural members or for the production of structural members subjected to a medium with a high temperature and with a high flow velocity, the band comprising warp and weft threads wherein the weft threads are in the form of U-shaped individual threads with the straight portions (limbs of the "U") aligned parallel to one another and transversally to the warp threads, the warp threads extending longitudinally of the band, the free ends of the weft threads being all positioned on the same side of the band and extending from the fabric of the band by a distance at least equal to the width thereof.
This invention also provides a process for the production of structural members wholly or partly comprising the carbon fibre fabric band as above described and a matrix, in which process the carbon fibre fabric band is placed in a position substantially transverse to the direction of flow, such that the successive cross sections of the band overlap in roof tile fashion at an acute angle in the direction of flow and towards the contour of the flow, the free projecting ends of the weft in the cross section of the bands being directed downsteam and together with the matrix form the flow contour, overlying the relevant warp threads positioned downstream.
The process of this invention is suitable not only for the winding of rotationally symmetrical components but also for the production of components of laminar shape by positioning a number os separate strips of fabric band in succession to one another. For example segments may be produced, for adjustable nozzles, flow guide profiles or heat shielding tiles.
This invention is explained hereinafter in greater detail by reference to examples shown in the accompanying drawings.
In the drawings: Figure 1 shows a plan view of a portion of a carbon fibre fabric band in accordnce with the invention,
Figure 2 shows a longitudinal section through the upper half of a rotationally sym
metrical hollow body with a negative mould (core), and
Figure 3 shows a longitudinal section through the nozzle zone of a solid-fuei rocket propulsion unit.
As shown in Fig. 1, the weft threads 3 of the carbon fibre fabric band 1 are woven transversally, as U-shaped individual threads, into the warp threads 2 which extend in the longitudinal direction 4 of the band. It goes without saying that according to the type of weave, (linen, twill, etc.) the weft threads 3 at the insersection point with the warp threads 2 follow a fixed pattern either above or below the said warp threads. Owing to the free ends of the weft threads 3, which project to a considerable distance, the width 5 of the band fabric is considerably smaller than the total width of the carbon fibre band 1. In fabric bands according to the existing prior art, on the other hand, a continuous weft thread is usually woven in meander-shaped configuration with the warp threads, the width of the fabric then corresponding to the width of the band.
From Fig. 2 it can be seen why the special structure of a carbon fibre fabric band 1 improves the durability of the structural member concerned. For the production of a rotationally symmetrically hollow body 12 a core 8 is encased helically with the carbon fibre fabric band 1, starting from the upstream inlet zone
10 and proceeding via the main zero 9 as far as the downstream outlet zone 11, as viewed in the direction of flow 6. The outside of the core 8, forming the flow contour 7, is coated with a parting agent, while the carbon fibre fabric band 1 is saturated before or during the application with the matrix (e.g. phenolic resin) not shown in the drawing. The inlet zone 10 serves to enable the parallel position of the cros sections of the band in relation to the flow contour in the first windings to be replaced by the desired oblique roof tile configuration in the main zone 9.The outlet zone 11 serves as a support for the projecting weft threads 3 of the last windings of the carbon fibre fabric band 1 which are not required. In the main zone 9 it may be clearly seen that the flow contour 7, apart from the matrix, is formed exclusively by the weft threads 3 positioned at an acute angle in relation to it. The weft threads 3 cover the warp threads 2 and protect them from thermal stresses and also from mechanical stresses caused by the flow.
In operation it is true that matrix bends in the zone of the surface (flow contour 7), but the
residues form, together with the weft threads
3 secured in the outer layers of the structural
member, a reliable protective layer for the material immediately adjacent thereto on the outside. To this protection a further contribution
is made by the fact that the weft threads 3 are favourably arranged approximately in the direction of flow 6. In order to increase the
strength of the structural member still further
it is possible, in the main zone 9, to apply a
high-strength wound structure 13 with the
carbon fibre base (fabric, rovings or the like) to the windings of the common fibre fabric
band 1.After the hollow body 12 has hardened and the core 8 has been removed the projecting fabric band windings of the inlet and outlet zone 10 and 11, which windings do not form part of the structural member itself, are removed from the main zone 9. For the sake of simplicity Fig. 2 only shows the structure of a circularly cylindrical hollow body, the length of the main zone 9 being considerably reduced in the diagram. This structural method, however, is particularly suitable for the production of the complete nozzle body of a Laval nozzle, in which case the core 8 has to be sub-divided transversally to the axis and in the zone of the neck of the nozzle (narrowest cross section), so that it can be removed from the structural member when the latter has hardened.
It should also be pointed out that according to the thermal and mechanical requirements arising in the zone of the warp threads 2 additional fibre reinforcement (rovings etc.) can be worked in between the windings of the carbon fibre fabric band 1. All that is required is to make sure that these fibre reinforcements, like the warp threads 2 themselves, are completely covered by the weft threads 3.
Fig. 3 shows a further possible use for the carbon fibre fabric band 1, which is the coating of the metal supporting structure 16 of the nozzle 15 of a solid-fuel rocket propulsion unit 14 of a known type of construction. With propulsion units in accordance with the existing prior art the metal supporting structure is connected in the zone of the nozzle neck, with a thick-walled graphite ring, while in the convergent and divergent part a coating of phenolic resin and asbestos fibre is applied.
According to Fig. 3 the coating 17 of the metal supporting structure 16 in the convergent and divergent part of the nozzle 15 consists of windings of the carbon fibre fabric band 1 in a roof tile configuration, comparable to that shown in Fig. 2. The application to the metal supporting structure 16, however, is effected helically against the direction of flow and the matrix connecting the fabric band is undetachably connected with the supporting structure (positive mould). The remaining structural characteristics of the solid fuel rocket propulsion unit 14, such as the graphite ring 18 and the arrangement of the propellant 19 have been retained unaltered, so that in relation to Fig. 3 the invention primarily resides in the replacement of the asbestos by a material less of a health hazard. As already previously mentioned there are numerous further possible applications for the fabric band according to the invention and it may be used for heat shielding tiles, segments of adjustable nozzles, flow guide profiles and the like. The structure of the components are nevertheless in all cases based on the same roof tile configuration in which the cross sections of the fabric band are staggered and on the connection between the weft threads and the flow.
Claims (8)
1. A carbon fibre fabric band for the production of protective layers for structural members or for the production of structural members subjected to a medium with a high temperature and with a high flow velocity, the band comprising warp and weft threads wherein the weft threads are in the form of Ushaped individual threads with the straight portions (limbs of the "U") aligned parallel to one another and transversally to the warp threads, the warp threads extending longitudinally of the band, the free ends of the weft threads being all positioned on the same side of the band and extending from the fabric of the band by a distance at least equal to the width thereof.
2. Process for the production of structural members wholly or partly comprising the carbon fibre fabric band according to Claim 1 and a matrix, in which process the carbon fibre fabric band is placed in a position substantially transverse to the direction of flow, such that the successive cross sections of the band overlap in roof tile fashion at an acute angle in the direction of flow and towards the contour of the flow, the free projecting ends of the weft in the cross section of the bands being directed downstream and together with the matrix form the flow contour, overlying the relevant warp threads positioned downstream.
3. Process in accordance with Claim 2, wherein for production on a negative mould a subsequent coating operation is effected with a composite fibre material, preferably one of high mechanical strength.
4. Process in accordance with Claim 2 or 3, for production on a core of a mainly rotationally symmetrical hollow body with a flow contour situated on the inside, such as for the production of the nozzle body of a rocket propulsion unit, in which process the core is provided with a main zone for the formation of the flow contour of the hollow body and, as a prolongation of the flow contour, with an inlet zone and an outlet zone the length of the two said zones in the direction of flow being approximately equal in each case to the total width of the carbon fibre fabric band including the projecting weft threads, the core being helically encased, from the inlet zone to the outlet zone and in the direction of flow with the carbon fibre fabric band, the main zone having a further coating carried out with a high-strength helical structure with a carbon fibre base and in which after the removal of the core the fibre band windings in the inlet and outlet zone extending beyond the main zone are removed.
5. Process in accordance with Claim 2 for coating a positive mould, such as the metal supporting structure of a nozzle of a rocket propulsion unit, wherein the carbon fibre fabric band is applied to the positive mould helically and progressively against the direction of flow.
6. A carbon fibre fabric band substantially as described herein and exemplified in the drawings.
7. Structural members when constructed from a carbon fibre band as described herein and exemplified in the drawings.
8. Process for producing structural members as described herein and exemplified with reference to the drawings.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19853537844 DE3537844A1 (en) | 1985-10-24 | 1985-10-24 | CARBON FIBER TAPE AND METHOD FOR ITS PROCESSING |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB8625263D0 GB8625263D0 (en) | 1986-11-26 |
| GB2182072A true GB2182072A (en) | 1987-05-07 |
Family
ID=6284355
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB08625263A Withdrawn GB2182072A (en) | 1985-10-24 | 1986-10-22 | Carbon fibre fabric band and method for its use |
Country Status (4)
| Country | Link |
|---|---|
| JP (1) | JPS62117844A (en) |
| DE (1) | DE3537844A1 (en) |
| FR (1) | FR2591618A1 (en) |
| GB (1) | GB2182072A (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10245741B4 (en) * | 2002-10-01 | 2005-10-06 | Bayern-Chemie Gesellschaft Für Flugchemische Antriebe Mbh | Discharge nozzle for a solid rocket |
-
1985
- 1985-10-24 DE DE19853537844 patent/DE3537844A1/en not_active Withdrawn
-
1986
- 1986-10-22 GB GB08625263A patent/GB2182072A/en not_active Withdrawn
- 1986-10-23 FR FR8614746A patent/FR2591618A1/en not_active Withdrawn
- 1986-10-24 JP JP61252122A patent/JPS62117844A/en active Pending
Also Published As
| Publication number | Publication date |
|---|---|
| FR2591618A1 (en) | 1987-06-19 |
| GB8625263D0 (en) | 1986-11-26 |
| JPS62117844A (en) | 1987-05-29 |
| DE3537844A1 (en) | 1987-04-30 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |