JPS63191629A - Heat-insulating structure - Google Patents
Heat-insulating structureInfo
- Publication number
- JPS63191629A JPS63191629A JP62023582A JP2358287A JPS63191629A JP S63191629 A JPS63191629 A JP S63191629A JP 62023582 A JP62023582 A JP 62023582A JP 2358287 A JP2358287 A JP 2358287A JP S63191629 A JPS63191629 A JP S63191629A
- Authority
- JP
- Japan
- Prior art keywords
- insulating structure
- heat
- heat insulating
- rocket motor
- structural material
- 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.)
- Pending
Links
- 239000000463 material Substances 0.000 claims description 15
- 239000012784 inorganic fiber Substances 0.000 claims description 9
- 229920001971 elastomer Polymers 0.000 claims description 5
- 239000000835 fiber Substances 0.000 claims description 5
- 239000011347 resin Substances 0.000 claims description 5
- 229920005989 resin Polymers 0.000 claims description 5
- 239000000806 elastomer Substances 0.000 claims description 4
- 229920001187 thermosetting polymer Polymers 0.000 claims description 4
- 238000009413 insulation Methods 0.000 claims description 3
- 229910000831 Steel Inorganic materials 0.000 description 4
- 239000000567 combustion gas Substances 0.000 description 4
- 229920002379 silicone rubber Polymers 0.000 description 4
- 239000010959 steel Substances 0.000 description 4
- 239000000853 adhesive Substances 0.000 description 3
- 230000001070 adhesive effect Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 239000005011 phenolic resin Substances 0.000 description 3
- 239000003380 propellant Substances 0.000 description 3
- 239000002344 surface layer Substances 0.000 description 3
- KXGFMDJXCMQABM-UHFFFAOYSA-N 2-methoxy-6-methylphenol Chemical compound [CH]OC1=CC=CC([CH])=C1O KXGFMDJXCMQABM-UHFFFAOYSA-N 0.000 description 2
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 2
- 229910000323 aluminium silicate Inorganic materials 0.000 description 2
- 239000011230 binding agent Substances 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- HNPSIPDUKPIQMN-UHFFFAOYSA-N dioxosilane;oxo(oxoalumanyloxy)alumane Chemical compound O=[Si]=O.O=[Al]O[Al]=O HNPSIPDUKPIQMN-UHFFFAOYSA-N 0.000 description 2
- 239000010410 layer Substances 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 229920001568 phenolic resin Polymers 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 229920002943 EPDM rubber Polymers 0.000 description 1
- 229920000459 Nitrile rubber Polymers 0.000 description 1
- 238000002679 ablation Methods 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 1
- 239000010425 asbestos Substances 0.000 description 1
- 238000003490 calendering Methods 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000003763 carbonization Methods 0.000 description 1
- 239000003054 catalyst Substances 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000003822 epoxy resin Substances 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000007849 furan resin Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000011810 insulating material Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
- 229920001721 polyimide Polymers 0.000 description 1
- 239000009719 polyimide resin Substances 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 229910052895 riebeckite Inorganic materials 0.000 description 1
- 239000000377 silicon dioxide Substances 0.000 description 1
- 239000004945 silicone rubber Substances 0.000 description 1
- 238000004073 vulcanization Methods 0.000 description 1
Abstract
(57)【要約】本公報は電子出願前の出願データであるた
め要約のデータは記録されません。(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明は断熱構造体に関し、特にロケットモータチャツ
バに有利に適用される同構造体に関する。DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a heat insulating structure, and particularly to the same structure advantageously applied to a rocket motor chatuba.
〔従来の技術」
従来、ロケットモータチャツバは、推進薬燃焼ガスに暴
露されることから、内面に断熱構造が必須で、これまで
に実用化されたものとしては、下記のようなものかある
。[Conventional technology] Conventionally, rocket motor chatubas are exposed to propellant combustion gas, so it is essential to have an insulating structure on the inside, and the ones that have been put into practical use so far include the following: .
（１）第２図に示すように、ニトリルゴム、エチレン侮
プロピレノ・ジエン−モノマーゴム（ＺＰＤＭゴム）、
シリコーンゴム等のエラストマ１にアスベスト繊維２等
を混線、カレンダ加工によって分散しシート状とし友も
の３を加硫しｔ後接着剤で、ま几は該シート状のもの５
を加硫前接着剤を塗布しｔ構造物に貼りつけて同時に加
硫して構造物４に接Ｎ５した断熱構造物
（２）第３図に示すように、フェノール樹脂６と耐熱無
機繊維織布７からなるａ層成形品８を構造材４に接着剤
によシ接９５した断熱構造物
（５）第４図に示すように、エポキシ樹脂９、セラミッ
ク粉末１０及び耐熱無機繊維１１を適量配合しスラリ状
とじ几もの１２全ロケツトモ一タチヤンバ七回転させな
がら構造材４に一定卑さに接着硬化５させた断熱講造材
（４） 第５図に示すように、シリコーンエラストマ
ー１３にスチール製のリボン１４金入れ該リボン１４を
構造材４に溶接によシ接着５し九断熱構造材（米国ラム
ロケットモータで開発中〕
〔発明か解決しようとする問題点〕
従来の断熱構造のうち、前記（す、（２）、（３）のも
のは断熱構造中の無機繊維のほとんどが面方向に配向し
ている几め、表層部の炭化層の強度が低くなり、高温ガ
ス流によって飛散するため浸食か大きくなる。(1) As shown in Figure 2, nitrile rubber, ethylene-propylene diene monomer rubber (ZPDM rubber),
Asbestos fibers 2, etc. are mixed into an elastomer 1 such as silicone rubber, dispersed by calendering, made into a sheet, vulcanized the friend 3, and then glued with an adhesive.
A heat insulating structure (2), which was applied with pre-vulcanization adhesive and attached to the structure, and simultaneously vulcanized and connected to the structure 4 (2) As shown in Fig. 3, phenolic resin 6 and heat-resistant inorganic fiber woven A heat insulating structure (5) in which an A-layer molded product 8 made of cloth 7 is bonded 95 to a structural material 4 with an adhesive (5) As shown in FIG. Insulating material (4) made of slurry-like binding material 12, which is bonded to structural material 4 and hardened to a certain degree while rotating the entire rocket seven times. As shown in Figure 5, silicone elastomer 13 is made of steel Ribbon 14 gold insert The ribbon 14 is welded to the structural material 4 and bonded 5 and 9. Insulating structural material (currently being developed by Ramrocket Motor in the United States) [Problems to be solved by the invention] Of the conventional heat insulating structures, In the case of (2) and (3) above, most of the inorganic fibers in the insulation structure are oriented in the plane direction, and the strength of the carbonized layer on the surface layer is low, causing it to be scattered by the high-temperature gas flow. This will cause erosion and increase.
また前記（４）のものは、スチールリボンで炭化したシ
リコーンエラストマの飛散防止か可能であるか、スチー
ルの融点から使用温度制限かあシ、かつ飛散防止効果を
上げるにはスチールリボン密度を高めることが必要で、
加工性にも難点がある。In addition, regarding the item (4) above, is it possible to prevent the carbonized silicone elastomer from scattering with a steel ribbon?Is it possible to limit the usage temperature due to the melting point of steel?And to increase the scattering prevention effect, it is necessary to increase the density of the steel ribbon. is necessary,
There are also difficulties in processability.
本発明は上記従来断熱構造体の有する工具合金解消しう
る同構造体を提供しようとするものである。The present invention aims to provide a structure capable of eliminating the tool alloys of the conventional heat insulating structure.
本発明は、構造材に、高度のニードル加工によって面に
直角方向に多数の繊維が配向した耐熱無機繊維に熱硬化
性樹脂及び／又はエラストマを含浸させ友材料を接着さ
せてなることを特徴とする断熱構造体である。The present invention is characterized in that the structural material is made of heat-resistant inorganic fibers in which a large number of fibers are oriented in a direction perpendicular to the surface by advanced needle processing, impregnated with a thermosetting resin and/or elastomer, and bonded with a supporting material. It is a heat insulating structure.
すなわち、本発明は断熱効果の大きなアブレーション（
ａｂｌａｔｉｏｎ ：融除）材料で高温ガス流による炭
化層の飛散防止の友め、面に直角方図に耐熱無機繊維を
配回させるよう、中間素材として高密度にニードル加工
し九耐熱無機繊維よりなるフェルト材に、熱硬化性樹脂
又はエラストマ會含浸したものを準備して、構造材、例
えばロケットモータチャツバの内面に内張すしたもので
ある。In other words, the present invention provides ablation (
This material is made of nine heat-resistant inorganic fibers that are needle-processed to a high density as an intermediate material so that the heat-resistant inorganic fibers are arranged at right angles to the surface. A felt material impregnated with a thermosetting resin or an elastomer is prepared and lined on the inner surface of a structural material, such as a rocket motor chatter.
ニードル加工で表面直角方向に配回させた耐熱無機繊維
によって、ロケットモータ推進系の燃焼ガスの暴露によ
って、表層部が炭化しても飛散を起さないため炭化浸食
が極めて小さくなる。Heat-resistant inorganic fibers arranged perpendicular to the surface by needle processing do not cause scattering even if the surface layer is carbonized by exposure to the combustion gas of the rocket motor propulsion system, so carbonization corrosion is extremely small.
以下、本発明断熱構造体の一実施例を第１図によって説
明する。第１図の（〜はロケットモータチャンバの全体
図、（Ｂ）はそのム−ム断面図管示す。Hereinafter, one embodiment of the heat insulating structure of the present invention will be described with reference to FIG. In FIG. 1, (-) is an overall view of the rocket motor chamber, and (B) is a cross-sectional view of the rocket motor chamber.
第１図に示す如く、ロケットモータチャンバ１の構造材
２にフェノール樹脂糸グライマ３を塗布した後、断熱構
造体４としてニードル加ニジ友アルミノシリケート稙維
製フェルト５に７エノール樹脂６を官浸しＢステージ状
としたプリプレグを真空又はオート７レープ成形によっ
て、硬化・接着させたものである。As shown in FIG. 1, after coating the structural material 2 of the rocket motor chamber 1 with phenolic resin thread glitter 3, a felt 5 made of needle-cured aluminosilicate fiber is impregnated with 7-enol resin 6 as a heat insulating structure 4. B-stage prepreg is cured and bonded by vacuum or auto-7 rape molding.
断熱構造体４０庫さはフェルトの密度、厚さ、ニードル
加工密度、硬化時の圧力に依存するが、一般に１〜１０
５ｍ庫のものが推進薬燃焼ガスの熱特性と暴露時間に対
応し九厚さで用いられる。The strength of the insulation structure 40 depends on the density and thickness of the felt, the needle processing density, and the pressure at the time of curing, but is generally 1 to 10.
The 5m chamber is used in nine thicknesses depending on the thermal characteristics and exposure time of the propellant combustion gas.
耐熱無機繊維は、アルミノシリケート以外にカーボン、
シリカ、アルミナ、アルミノボロシリケート等、ニード
ル加工できるものであれば適用可能でｉｂシ、マトリッ
クス（バインダ）としてはフェノール樹脂以外に、フラ
ンｍ脂、エポキシ樹脂、ポリイミド樹脂等の熱硬化性樹
脂や’ｙリコーンエラストマー等フェス状で繊維間に含
なでき、加熱、加圧又は触媒添加により硬化するもので
あれば通用可能である。In addition to aluminosilicate, heat-resistant inorganic fibers include carbon,
Silica, alumina, aluminoborosilicate, etc., which can be processed by needles, can be used.In addition to phenol resin, the matrix (binder) can be thermosetting resins such as furan resin, epoxy resin, polyimide resin, etc. Any material, such as silicone elastomer, which is in the form of a face and can be contained between fibers and can be cured by heating, pressure, or addition of a catalyst, can be used.
〔発明の効果」
本発明による断熱構造体、特にロケットモータチャンバ
内部断熱構造体は推進薬燃焼ガスに暴露され表層か炭化
しても、高密度にニードル加ニレ′ｆｃ＃熱無機繊維が
面に■角万同に配回しているｔめ飛散を防止できる優れ
７′ｃ耐食性をもち、かつ、チャンバ内面への内張υが
、マトリックス（バインダ）金言浸し友ものを真空底形
又はオート７レープ底形等によって容易に達成できるの
で製作も容易である。[Effects of the Invention] Even if the heat insulating structure according to the present invention, especially the rocket motor chamber internal heat insulating structure, is exposed to propellant combustion gas and the surface layer is carbonized, the needle-burned elm'fc# thermal inorganic fibers remain on the surface at a high density. ■ It has excellent 7'c corrosion resistance that can prevent scattering, and the lining υ on the inner surface of the chamber allows the matrix (binder) to be immersed in a vacuum bottom type or auto 7 rape. Since this can be easily achieved by changing the bottom shape, etc., it is easy to manufacture.
第１図は本発明断熱構造体の一実施例會祝明するための
図で、（勾はロケットモータチャンバ全体図、（Ｂ）は
そのＡ−Ａ断面を示す。
第２図〜第５図は従来の断熱構造体の構成を説明する几
めの図である。
第１図
第２図
第３図
第４図
第５図Fig. 1 is a diagram for explaining one embodiment of the heat insulating structure of the present invention (the slope shows the overall view of the rocket motor chamber, and (B) shows its A-A cross section. Figs. 2 to 5 are FIG. 1 is a schematic diagram illustrating the configuration of a conventional heat insulating structure.
Claims (1)
多数の繊維が配向した耐熱無機繊維に熱硬化性樹脂及び
／又はエラストマを含浸させた材料を接着させてなるこ
とを特徴とする断熱構造体。A thermal insulation characterized by adhering to a structural material a material made by impregnating a heat-resistant inorganic fiber with a thermosetting resin and/or an elastomer, in which a large number of fibers are oriented perpendicular to the plane through advanced needle processing. Structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP62023582A JPS63191629A (en) | 1987-02-05 | 1987-02-05 | Heat-insulating structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP62023582A JPS63191629A (en) | 1987-02-05 | 1987-02-05 | Heat-insulating structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS63191629A true JPS63191629A (en) | 1988-08-09 |
Family
ID=12114569
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP62023582A Pending JPS63191629A (en) | 1987-02-05 | 1987-02-05 | Heat-insulating structure |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS63191629A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008101678A3 (en) * | 2007-02-21 | 2009-07-16 | Johns Manville Europe Gmbh | New composite materials, method for their manufacture and their use |
| JP2013029100A (en) * | 2011-06-24 | 2013-02-07 | Ihi Aerospace Co Ltd | Pulse rocket motor |
-
1987
- 1987-02-05 JP JP62023582A patent/JPS63191629A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008101678A3 (en) * | 2007-02-21 | 2009-07-16 | Johns Manville Europe Gmbh | New composite materials, method for their manufacture and their use |
| JP2013029100A (en) * | 2011-06-24 | 2013-02-07 | Ihi Aerospace Co Ltd | Pulse rocket motor |
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