GB2191115A - Ablative material - Google Patents
Ablative material Download PDFInfo
- Publication number
- GB2191115A GB2191115A GB08138011A GB8138011A GB2191115A GB 2191115 A GB2191115 A GB 2191115A GB 08138011 A GB08138011 A GB 08138011A GB 8138011 A GB8138011 A GB 8138011A GB 2191115 A GB2191115 A GB 2191115A
- Authority
- GB
- United Kingdom
- Prior art keywords
- ablative material
- loops
- fabric
- ablative
- casing
- 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.)
- Granted
Links
Classifications
-
- 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
- B64G1/52—Protection, safety or emergency devices; Survival aids
- B64G1/58—Thermal protection, e.g. heat shields
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
- F02K9/346—Liners, e.g. inhibitors
Landscapes
- Engineering & Computer Science (AREA)
- Critical Care (AREA)
- Health & Medical Sciences (AREA)
- Physics & Mathematics (AREA)
- Emergency Medicine (AREA)
- General Health & Medical Sciences (AREA)
- Thermal Sciences (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Woven Fabrics (AREA)
Abstract
An ablative material protective liner for the casing of a solid propellant rocket motor includes (a) a layer of reinforcing fabric having projecting therefrom anchor means associated with the fabric layer and (b) a polymeric matrix, the fabric layer and anchor means being embedded within the matrix. Preferably the anchor means projects perpendicularly from the surface of the fabric and points towards the casing, and takes the form of tufts or loops of thread which may be arranged in rows, spaced between about 7.5 mm and about 15.5 mm apart. The polymer matrix is preferably an elastomer and the fabric is preferably woven from threads which neither melt nor soften at the temperatures to which the ablative material is expected to be exposed, e.g. comprise phenolic based fibres, aramid fibres or carbon fibres.
Description
SPECIFICATION
Ablative material
The present invention relates to ablative materials.
Ablation is a process whereby at high tempera tures thermal energy is expended by the sacrificial loss of material from a protective shield, applied to a primary structure for which protection from high temperature environments is sought. The materials which comprise such shields are commonly known as ablative materials and typically consist offibre reinforced composites or composites reinforced with particulate matter. The principle of ablation is typically exploited in certain aerospace applications where it is essential to provide thermal protection for primary structures such as, for example, space reentry vehicles and solid propellent rocket motors.
The rates at which an ablative material is eroded and atwhich heat diffuses through it during the pro- cess of ablation, the duration of exposure to the en vironmentwhich causes the process to occur and the thermal conductivity ofthe material, determine the minimum thickness of material required to provide effectivethermal protection to the primary structure to which it is applied. It is therefore desirable to employ an ablative material which has both a low rate of erosion and a low density in orderthatthe amount of ablative material required and in consequence overall weight is kept to a minimum.
According to a first aspect ofthe present invention an ablative material comprises (a) a layer of woven reinforcing fabric having a first surface and a second surface, the second surface having projecting therefrom anchor means associated with the fabric layer, and (b) a polymeric matrix, the fabric layer and the anchor means being embedded within the matrix.
Preferably the anchor means projects substantially perpendicularlyfrom the second surface ofthe fabric.
Preferably the reinforcing fabric comprises a loosely woven plain weave fabric with a weft to warp ratio of 1:1 and about 9-11 threads per inch (about 3-5 threads percm).
The anchor means may be any suitable arrangement of short discontinuous or continuous threads which stand proud of the fabric surface for example, tufts or loops, and these may be incorporated into the woven fabric either during the weaving process or added to the fabric after weaving in separate operations, by any conventional means employed in the textilesorcarpet-making arts. It is preferred that the anchor means takes the form of loops of thread. The extent to which the loops project beyond the surface of the fabric is determined by the required thickness of the ablative material and it is therefore desirable that the size ofthe loops approximately corresponds to the thickness of the ablative material. Preferably the loops are incorporated in the fabric during the process of weaving and it is preferred that they are provided in alternative warp threads.The loops may be located at random in the fabric or they may be arranged in specific patterns but it is preferred that they are arranged in rows, across the weft. The spacing between the rows may be any desired interval.
Suitably, the rows of loops are located at intervals of
between about 0.3 inches (7.5 mm) and about 0.6 inches (15.5 mm).
Preferably, the fabric comprises threads which are sufficientlyflexibleto permittheformation of loops without cracking or breaking either during the formation of the loops or subsequently. In addition it is preferred thatthe fabric comprises threads which neither soften nor melt at the temperatures to which the ablative material is expected to be exposed. Ex amples ofsuitablethreads include phenolic based fibres, aramid fibres, and carbon fibres. Certain other fibres, for example cellulosic fibres and poly acrylonitrilefibres may also be suitable. it is believed that such fibres produce carbonaceous fibrous residues under non-oxidising ablative conditions, which are sufficiently strong to continue to provide a reinforcing effect in the matrix.It is preferred that they comprise phenolic based fibres. Advantageously both weft and warp threads comprisethe same fibres, although hybrid fabrics in which weft and warp threads comprise different fibres may also be suitable. Preferably the fabric is provided with a selvedge, as it is woven, which may be discarded afterthefabric has been incorporated into the matrix.
The polymeric matrix may be selected from any of the materials used in the art for protective ablative shields. It is preferred that the polymer matrix is an elastomerand preferably is based upon aterpolymer of ethylene, propylene and a non-conjugated diene, for example cyclopentadiene.
Ablative materials according to the first aspect of the present invention may be used as protective shields for primary structures for which protection from high temperature environments is necessary in orderto permit the primary structure to fulfil itsfunction, for example, protective liners for solid propellent rocket motors.
Solid propel lent rocket motors burn at high tem peratures, sufficientto cause damageto orfailure of the rocket motorcasing by burning through it. Itis therefore necessary to line the internal surface ofthe motor casing with some form ofthermal insulation which is commonly an ablativematerial.Thelinerof ablative material separates the propellent charge from the motor casing. As the motor is fired the propellent burns rapidly at a high temperature which chars the liner and by sacrificial loss of the liner mat erial, iethe process of ablation,the liner protectsthe motor casing from thermal damage.
According to a second aspect of the present invention a rocket motor comprises (a) a casing, (b) a protective liner comprising an ablative material according to the first aspect which is applied to internal surfaces ofthe casing and (c) a solid propellent charge, the layer of reinforcing fabric of the ablative material being orientated to lie essentially parallel to the casing, the first surface of the fabric being located adjacent to the propellent and the surface con tainingtheanchormeans being directed towardsthe adjacent part of the casing. Prefera,bly the surface containing the anchor means is essentially parallel to the adjacent part of the casing so that the anchor means point towards that part of the casing.
Conventional reinforced protective liners are effectively reinforced randomly or in two dimensions only, ie parallel with the rocket motor casing. The purpose of the reinforcement is to slow down the rate of erosion ofthe liner. However as the char advances towards the casing it eventually travels beyond the reinforcement and having doneso,the reinforcement ceases to be effective and the liner tends to delaminate and spall causing pieces of char containing reinforcementto break away from the liner. Therefore conventional reinforced protective liners may incorporate several layers of reinforcement in orderthatthe liner does not erode too rapidly.This inevitably leads to thicker liners than are desirablewith a consequent undesirable increase in weighs These undesirable features of conventional motor casing liners are overcome in an embodiment ofthe present invention bythe incorporation of loops in the reinforcing fabric which hold the reinforcing fabric layer in place. As the chartravels through the liner towards the motor casing the tendency of the charto break away from the uncharred material is considerably reduced by virtue ofthe loops which effectively anchor the char in place. Because the reinforcing fab ric layer is held in place by the loops it is possible to usethinnerand consequently lighter liners than conventional rocket motor casing liners.
An embodiment of the present invention will now be described byway of example with reference to the accompanying drawings in which:
Figure lisa schematic representation of a section of a reinforcing fabric, and
Figure2 is a cross-section through part of a rocket motor incorporating a liner which includesthefabric as shown in Figure 1.
In Figure 1 a reinforcing fabric 1 comprises a series of regularly alternating warp threads 2 and 3 which are interwoven with a series ofweftthreads Sin a plain weave pattern with a weftto warp ratio of 1:1.
The warp threads 3 are provided with loops 4 at re gularlyspaced intervals along their length.Thewarp threads 2 are unlooped. The fabric 1 is provided with a selvedge 6.
In Figure 2, a rocket motor has a casing 9 a propellent charge 11 and a liner7 located between the casing 9 and the propeilent charge 1 1.The liner 7 comprises an elastomeric matrix 8 in which is embedded
reinforcing fabric 1 which is a fabric as shown in
Figure 1. The fabric 1 is orientated so that the surface containing the loops 4faces towards the casing 9.
The unlooped surface ofthe fabric 1 labelled 10in Figure 2 is located adjacentto the propellent 11 and
parallel to the adjacent part ofthe casing 9.
An example of a liner as shown in Figure 2 incor
porating fabric as shown in Figure 1 was made as follows: Areinforcingfabricwaswoven in a plain weave with a weftto warp ratio of 1:1 and with about 9 to 11 threads per inch (3 to 5 threads per cm) incorporating
loops in the warp at intervals of 1.3 cm by a con ventional weaving process using Kynol (trade name) threads. The woven fabric was placed in a mould and
biaxially stretched to ensurethatthe loops remained
upright. Asolution of Royalene 501 (trade name), a suitable curing system and various ablative additives of the type commonly used in the art, dissolved in toluene solvent, was coated onto the fabric. The solvent was allowed to evaporate before the process was repeated. After tern coats of the solution had been applied and all the solvent had been allowed to evaporate the resulting composite sheet was cold pressed to a thickness of about 2 mm.
On a subsequentfiring testthe liner was foundto erode by 0.4 mm, which compares favourably with 1.3 mm of erosion typicaliy experienced with conventional liners. The liner had a specific gravity of about 1.1 compared to a range of 1.4to 1.8 in conventional liners.
Claims (21)
1. An ablative material including (a) a layer of woven reinforcing fabric having a first surface and a second surface, the second surface having projecting therefrom anchor means associated with the fabric layer and (b) a polymeric matrix,thefabric layer and the anchor means being embedded within the matrix.
2. An ablative material as claimed in claim 1 and wherein the anchor means extends into the polymeric matrix and projects essentially perpendicularly from the second surface of the fabric.
3. An ablative material as claimed in claim 1 or claim 2 and wherein the anchor means is in the form of short discontinuous or continuous threads which stand proud ofthe second surface of the fabric, the extent bywhich they projectfromthesurfaceapp- roximately corresponding to the required thickness of the ablative material.
4. An ablative material as claimed in any one pm ceding claim and wherein the reinforcing fabric is a loosely woven plain weave with a weft to warp ratio of :1 and about 3-5 threads percm.
5. An ablative material as claimed in any one preceding claim and wherein the anchor means has been incorporated in the fabric during the weaving process used for making the fabric.
6. An ablative material as claimed in any one preceding claim and wherein the anchor means is in the form oftufts or loops ofthreads.
7. An ablative material as claimed in claim 6 and wherein the anchor means is in the form of the loops of threads which are provided in the warp.
8. An ablative material as claimed in claim 7 and wherein the loops are provided in alternate warp threads.
9. An ablative material as claimed in claim 7 or claim 8 and wherein the loops are arranged at random or in a specific pattern in the fabric.
10. An ablative material as claimed in claim 7 or claim 8 and wherein the loops are arranged in rows across the weft.
11. An ablative material as claimed in claim 10 and wherein the spacing between each row of loops is between about 7.5 mm and about 15.5 mm.
12. An ablative material as clalmed in claim 11 and wherein the spacing between each row of loops is about 13 mm.
13. An ablative material as claimed in anyone preceding claim and wherein the fabric is provided with a selvedge, which may be discarded afterthe fabric has been incorporated in the polymer matrix.
14. An ablative material as claimed in any one preceding claim and wherein the fabric comprises threads which are sufficiently flexible to allow the formation of loops without cracking or breaking either during formation of the loops or subsequently.
15. An ablative material as claimed in any one preceding claim and wherein the th reads neither soften nor melt at the temperatures to which the ablative material is expected to be exposed.
16. An ablative material as claimed in claim 15 and wherein the threads comprise phenolic based fibres.
17. An ablative material as claimed in claim 15 and wherein the threads comprise aramid fibres or carbon fibres.
18. An ablative material as claimed in any one preceding claim and wherein the weft and warp threads comprise the same type of fibre.
19. An ablative material as claimed in claim 1 and wherein the polymer matrix is an elastomer.
20. An ablative material as claimed in claim 19 and wherein the polymer matrix is based on a terpolymer of ethylene, propylene and anon- conjugated diene.
21. A rocket motor as claimed in claim 18 or 19 and having a construction substantially as here it before described with reference to Figure 2.
21. An ablative material as claimed in claim 20 and wherein the non-conjugated diene is cyclopentadiene.
22. An ablative material as claimed in any one preceding claim and wherein the ablative material is used as a protective shield for a primary structure for which protection from high temperature environments is necessary in order to perm it the primary structure to fulfil its function.
23. A rocket motor including (a) a casing, (b) a protective liner comprising an ablative material as claimed in any one of claims 1 to 21 applied to internal surfaces ofthe casing and (c) a solid propellent charge, the layer of reinforcing fabric ofthe ablative material being orientated to lie essentially parallel to the casing, the first surface of the fabric being loc ated adjacentto the propellent and the surface con- taining the anchor means being directed towards the adjacent part of the casing.
24. A rocket motor as claimed in claim 23 and wherein the surface containing the anchor means is essentially parallel to the adjacent part of the casing sothatthe anchor means point towards that part of the casing.
25. An ablative material as claimed in any one of claims 1 to 21 and substantially as hereinbefore describedwith referenceto Figure 1.
26. A rocket motor as claimed in claim 23 or 24 and having a construction substantially as herein before described with reference to Figure 2.
Amendments to the claims have been filed, and have the following effect: (a) Claims 1-26 above have been deleted ortextually amended.
(b) New ortextually amended claims have been filed asfollows:
1. An ablative material having a first surface and
a second surface including a layer of woven reinforc
ing fabric embedded in a polymeric matrix, the layer
of reinforcing fabric having a first surface and a second surface,thesecond surface having project
ing essentially perpendicularlytherefrom loops of thread associated with the fabric, the first surface of the fabric layer being adjacent to the first surface of the ablative material and the loops projecting towards the second surface of the ablative material, the extent by which the loops project from the second surface ofthefabric being such that the looped part of each loop is adjacent to the second surface ofthe ablative material, the loops being arranged in the fabricsoasto anchorthefabric in the polymeric matrix, particularly during ablation occuring in the ablative material from the first surface of the material towards the second surface of the material, thereby reducing spalling ofthe material.
2. An ablative material as claimed in claim 1 and wherein the reinforcing fabric is a loosely woven plain weave with a weft to warp ratio of 1:1 and about 3-5 threads percm.
3. An ablative material as claimed in claim 1 or claim 2 and wherein the loops are provided in alternate warp threads.
4. An ablative material as claimed in claim 3 and wherein the loops are arranged at random inthefabric.
5. An ablative material as claimed in claim 3 and wherein the loops are arranged in rows across the weft.
6. An ablative material as claimed in claim Sand wherein the spacing between each row of loops is between about 7.5 mm and about 15.5 mm.
7. An ablative material as claimed in claim 6 and wherein the spacing between each row of loops is about 13 mm.
8. An ablative material as claimed in any one preceding claim and wherein the fabric is provided with a selvedge, which may be discarded after the fabric has been embedded in the polymeric matrix.
9. An ablative material as claimed in anyone preceding claim andwhereinthefabriccomprises threads which are sufficiently flexible to allow the formation of loops without cracking or breaking either during formation of the loops orsubsequently.
10. An ablative material as claimed in any one preceding claim and wherein the threads neither soften nor melt atthetemperaturesto which theab- ative material is expected to be exposed.
11. An ablative material as claimed in claim 10 and wherein the threads comprise phenolic based fibres.
12. An ablative material as claimed in claim 10 and wherein the threads comprise aramidfibres or carbon fibres.
13. An ablative material as claimed in any one preceding claim and wherein the weft and warp threads comprise the same type offibre.
14. An ablative material as claimed in claim 1 and wherein the polymer matrix is an elastomer.
15. An ablative material as claimed in claim 14 and wherein the polymer matrix is based on ater polymer of ethylene, propylene and anon- conjugated diene.
16. An ablative material as claimed in claim 15 and wherein the non-conjugated diene is cyclopentadiene.
17. An ablative material as claimed in any one preceding claim and wherein the ablative material is used as a protective shield for a primarystructurefor which protection from high temperature environments is necessary in order to permitthe primary structure to fulfil its function.
18. A rocket motor including (a) a casing, (b) a protective liner comprising an ablative material as claimed in anyone of claims 1 to 16 applied to internal surfaces ofthe casing and (c) a solid propellent charge, the layer of reinforcing fabric of the ablative material being orientated to lie essentially parallel to the casing, the first surface ofthefabric being located adjacentto the propellent and the surface containing the anchor means being directed towards the adjacent part of the casing.
19. A rocket motor as claimed in claim 18 and wherein the surface containing the loops is essentially parallel to the adjacent part of the casing so that the loops point towards that part of the casing.
20. An ablative material as claimed in any one of claims 1 to 16 and substantially as hereinbefore described with reference to Figure 1.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB8040563 | 1980-12-18 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB2191115A true GB2191115A (en) | 1987-12-09 |
| GB2191115B GB2191115B (en) | 1988-05-11 |
Family
ID=10518070
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB08138011A Expired GB2191115B (en) | 1980-12-18 | 1981-12-18 | Ablative material |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2191115B (en) |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0398787A1 (en) * | 1989-05-16 | 1990-11-22 | AEROSPATIALE Société Nationale Industrielle | Tufted thermal protection layer and production method therefor |
| FR2652036A1 (en) * | 1989-09-19 | 1991-03-22 | Aerospatiale | THERMAL PROTECTIVE COATING, A PROCESS AND AN INSTALLATION FOR ITS MANUFACTURE. |
| EP0441704A1 (en) * | 1990-02-09 | 1991-08-14 | AEROSPATIALE Société Nationale Industrielle | Rigid and pressure permeable thermal protection device |
| US5232534A (en) * | 1989-09-19 | 1993-08-03 | Aerospatiale Soiete Nationale Industrielle | Thermal protection coating, and method and installation for manufacturing it |
| US5236529A (en) * | 1989-05-16 | 1993-08-17 | Aerospatiale Societe Nationale Industrielle | Fringed thermal protection device and method of manufacturing it |
| EP0600652A1 (en) * | 1992-12-01 | 1994-06-08 | Avco Corporation | Reinforcement system for mastic intumescent fire protection coatings |
| EP0600651A1 (en) * | 1992-12-01 | 1994-06-08 | Avco Corporation | Reinforcement system for mastic intumescent fire protection coatings |
| EP0733547A2 (en) * | 1995-03-22 | 1996-09-25 | Nissan Motor Co., Ltd. | Ablator compositions |
| EP0769363A1 (en) * | 1995-10-20 | 1997-04-23 | AEROSPATIALE SOCIETE NATIONALE INDUSTRIELLE, Société Anonyme | Thermal protection article made of low density reinforced material and process for its manufacture |
| US5836715A (en) * | 1995-11-19 | 1998-11-17 | Clark-Schwebel, Inc. | Structural reinforcement member and method of utilizing the same to reinforce a product |
| US5985405A (en) * | 1996-01-30 | 1999-11-16 | Textron Systems Corporation | Three dimensionally reinforced ablative/insulative composite |
| US6174483B1 (en) | 1997-05-07 | 2001-01-16 | Hexcel Cs Corporation | Laminate configuration for reinforcing glulam beams |
| US6231946B1 (en) | 1999-01-15 | 2001-05-15 | Gordon L. Brown, Jr. | Structural reinforcement for use in a shoe sole |
| FR2811018A1 (en) * | 2000-06-30 | 2002-01-04 | Alliant Techsystems Inc | Rocket motor assembly insulation or thermal protection ablation material is made from impregnated resin matrix with carbonizing reinforcement |
| GB2571915A (en) * | 2018-02-19 | 2019-09-18 | Gregory Smith Anthony | Use of metal foam or lattice structures to support solid propellant |
| DE102020112101A1 (en) | 2020-05-05 | 2021-11-11 | Technische Universität Dresden, Körperschaft des öffentlichen Rechts | Composite component, component, and method for producing a composite component |
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| GB787260A (en) * | 1955-01-10 | 1957-12-04 | White & Co Ltd Samuel | Method of manufacturing structures from thermo-setting plastic materials combined with fibrous materials |
| GB990730A (en) * | 1960-10-06 | 1965-04-28 | Dunlop Rubber Co | Improvements in mechanical belting |
| GB1104092A (en) * | 1963-06-19 | 1968-02-21 | Mini Of Technology | Composite synthetic resin materials |
| GB1419924A (en) * | 1973-04-16 | 1975-12-31 | Bortolaso R | Panel comprising two parallel layers and a sandwiched core therebetween |
-
1981
- 1981-12-18 GB GB08138011A patent/GB2191115B/en not_active Expired
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB275320A (en) * | 1926-05-03 | 1927-08-03 | Frederick William Thomas | Improvements in roofing materials |
| GB787260A (en) * | 1955-01-10 | 1957-12-04 | White & Co Ltd Samuel | Method of manufacturing structures from thermo-setting plastic materials combined with fibrous materials |
| GB990730A (en) * | 1960-10-06 | 1965-04-28 | Dunlop Rubber Co | Improvements in mechanical belting |
| GB1104092A (en) * | 1963-06-19 | 1968-02-21 | Mini Of Technology | Composite synthetic resin materials |
| GB1419924A (en) * | 1973-04-16 | 1975-12-31 | Bortolaso R | Panel comprising two parallel layers and a sandwiched core therebetween |
Cited By (33)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2647187A1 (en) * | 1989-05-16 | 1990-11-23 | Aerospatiale | FRAME STRUCTURE THERMAL PROTECTION DEVICE AND METHOD FOR MANUFACTURING THE SAME |
| EP0398787A1 (en) * | 1989-05-16 | 1990-11-22 | AEROSPATIALE Société Nationale Industrielle | Tufted thermal protection layer and production method therefor |
| US5236529A (en) * | 1989-05-16 | 1993-08-17 | Aerospatiale Societe Nationale Industrielle | Fringed thermal protection device and method of manufacturing it |
| US5178922A (en) * | 1989-05-16 | 1993-01-12 | Societe Nationale Industrielle Et Aerospatiale | Fringed thermal protection device |
| US5173350A (en) * | 1989-09-18 | 1992-12-22 | Aerospatiale Societe Nationale Industrielle | Thermal protection coating comprising a fiber reinforced main layer and an insulative sublayer |
| US5232534A (en) * | 1989-09-19 | 1993-08-03 | Aerospatiale Soiete Nationale Industrielle | Thermal protection coating, and method and installation for manufacturing it |
| FR2652036A1 (en) * | 1989-09-19 | 1991-03-22 | Aerospatiale | THERMAL PROTECTIVE COATING, A PROCESS AND AN INSTALLATION FOR ITS MANUFACTURE. |
| EP0419338A1 (en) * | 1989-09-19 | 1991-03-27 | AEROSPATIALE Société Nationale Industrielle | Thermal protection skin, a method and a production installation |
| EP0441704A1 (en) * | 1990-02-09 | 1991-08-14 | AEROSPATIALE Société Nationale Industrielle | Rigid and pressure permeable thermal protection device |
| FR2658265A1 (en) * | 1990-02-09 | 1991-08-16 | Aerospatiale | RIGID THERMAL PROTECTION DEVICE PERMEABLE TO PRESSURE. |
| EP0600652A1 (en) * | 1992-12-01 | 1994-06-08 | Avco Corporation | Reinforcement system for mastic intumescent fire protection coatings |
| EP0600651A1 (en) * | 1992-12-01 | 1994-06-08 | Avco Corporation | Reinforcement system for mastic intumescent fire protection coatings |
| US5433991A (en) * | 1992-12-01 | 1995-07-18 | Avco Corporation | Reinforcement system for mastic intumescent fire protection coatings comprising a hybrid mesh fabric |
| US5580648A (en) * | 1992-12-01 | 1996-12-03 | Avco Corporation | Reinforcement system for mastic intumescent fire protection coatings |
| AU706226B2 (en) * | 1992-12-01 | 1999-06-10 | Akzo Nobel N.V. | Reinforcement system for mastic intumescent fire protection coatings |
| EP0733547A2 (en) * | 1995-03-22 | 1996-09-25 | Nissan Motor Co., Ltd. | Ablator compositions |
| US5905101A (en) * | 1995-03-22 | 1999-05-18 | Nissan Motor Co., Ltd. | Ablator compositions |
| EP0733547A3 (en) * | 1995-03-22 | 1997-05-28 | Nissan Motor | Ablator compositions |
| FR2740068A1 (en) * | 1995-10-20 | 1997-04-25 | Aerospatiale | REINFORCED LOW DENSITY THERMAL PROTECTION MATERIAL AND METHOD OF OBTAINING SAME |
| EP0769363A1 (en) * | 1995-10-20 | 1997-04-23 | AEROSPATIALE SOCIETE NATIONALE INDUSTRIELLE, Société Anonyme | Thermal protection article made of low density reinforced material and process for its manufacture |
| US5882765A (en) * | 1995-10-20 | 1999-03-16 | Aerospatiale Societe Nationale Industrielle | Element made of a reinforced low density heat protective material and method to obtain said element |
| US6454889B1 (en) | 1995-11-19 | 2002-09-24 | Hexcel Cs Corporation | Method of utilizing a structural reinforcement member to reinforce a product |
| US5836715A (en) * | 1995-11-19 | 1998-11-17 | Clark-Schwebel, Inc. | Structural reinforcement member and method of utilizing the same to reinforce a product |
| US6123879A (en) * | 1995-11-19 | 2000-09-26 | Hexcel Cs Corporation | Method of reinforcing a concrete structure |
| US6632309B1 (en) | 1995-11-19 | 2003-10-14 | Hexcel Cs Corporation | Structural reinforcement member and method of utilizing the same to reinforce a product |
| US5985405A (en) * | 1996-01-30 | 1999-11-16 | Textron Systems Corporation | Three dimensionally reinforced ablative/insulative composite |
| US6468625B1 (en) | 1997-05-07 | 2002-10-22 | Hexcel Cs Corporation | Laminate configuration for reinforcing glulam beams |
| US6174483B1 (en) | 1997-05-07 | 2001-01-16 | Hexcel Cs Corporation | Laminate configuration for reinforcing glulam beams |
| US6231946B1 (en) | 1999-01-15 | 2001-05-15 | Gordon L. Brown, Jr. | Structural reinforcement for use in a shoe sole |
| FR2811018A1 (en) * | 2000-06-30 | 2002-01-04 | Alliant Techsystems Inc | Rocket motor assembly insulation or thermal protection ablation material is made from impregnated resin matrix with carbonizing reinforcement |
| GB2571915A (en) * | 2018-02-19 | 2019-09-18 | Gregory Smith Anthony | Use of metal foam or lattice structures to support solid propellant |
| GB2571915B (en) * | 2018-02-19 | 2023-07-19 | Gregory Smith Anthony | Use of metal foam or lattice structures to support solid propellant |
| DE102020112101A1 (en) | 2020-05-05 | 2021-11-11 | Technische Universität Dresden, Körperschaft des öffentlichen Rechts | Composite component, component, and method for producing a composite component |
Also Published As
| Publication number | Publication date |
|---|---|
| GB2191115B (en) | 1988-05-11 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PCNP | Patent ceased through non-payment of renewal fee |
Effective date: 20001218 |