JPH0664101A - Heat-insulative material for rocket motor - Google Patents
Heat-insulative material for rocket motorInfo
- Publication number
- JPH0664101A JPH0664101A JP3151590A JP15159091A JPH0664101A JP H0664101 A JPH0664101 A JP H0664101A JP 3151590 A JP3151590 A JP 3151590A JP 15159091 A JP15159091 A JP 15159091A JP H0664101 A JPH0664101 A JP H0664101A
- Authority
- JP
- Japan
- Prior art keywords
- fiber cloth
- heat
- cloth
- insulating material
- elongation
- 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
- 239000004744 fabric Substances 0.000 claims abstract description 51
- 239000011810 insulating material Substances 0.000 claims abstract description 36
- 229920001971 elastomer Polymers 0.000 claims abstract description 33
- 239000005060 rubber Substances 0.000 claims abstract description 32
- 239000000835 fiber Substances 0.000 claims abstract description 31
- 150000001875 compounds Chemical class 0.000 claims abstract description 9
- 239000004693 Polybenzimidazole Substances 0.000 claims abstract description 8
- 239000005011 phenolic resin Substances 0.000 claims abstract description 8
- 229920006376 polybenzimidazole fiber Polymers 0.000 claims abstract description 8
- 229920006231 aramid fiber Polymers 0.000 claims abstract description 7
- 238000010438 heat treatment Methods 0.000 claims abstract description 7
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 5
- 239000004917 carbon fiber Substances 0.000 claims abstract description 5
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract 2
- 238000000034 method Methods 0.000 abstract description 12
- 239000002131 composite material Substances 0.000 abstract description 9
- 239000003795 chemical substances by application Substances 0.000 abstract description 7
- 239000000853 adhesive Substances 0.000 abstract description 5
- 230000001070 adhesive effect Effects 0.000 abstract description 5
- 238000013329 compounding Methods 0.000 abstract description 3
- 238000004073 vulcanization Methods 0.000 abstract description 3
- 239000000203 mixture Substances 0.000 abstract description 2
- 239000012744 reinforcing agent Substances 0.000 abstract description 2
- 238000013007 heat curing Methods 0.000 abstract 1
- 239000003380 propellant Substances 0.000 description 19
- 238000002485 combustion reaction Methods 0.000 description 16
- 239000000567 combustion gas Substances 0.000 description 9
- 238000012937 correction Methods 0.000 description 8
- 230000000052 comparative effect Effects 0.000 description 7
- 239000007787 solid Substances 0.000 description 7
- 238000012360 testing method Methods 0.000 description 4
- 239000002759 woven fabric Substances 0.000 description 4
- 229920000181 Ethylene propylene rubber Polymers 0.000 description 3
- 238000011160 research Methods 0.000 description 3
- 238000009941 weaving Methods 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
- GDDNTTHUKVNJRA-UHFFFAOYSA-N 3-bromo-3,3-difluoroprop-1-ene Chemical compound FC(F)(Br)C=C GDDNTTHUKVNJRA-UHFFFAOYSA-N 0.000 description 2
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- 239000005062 Polybutadiene Substances 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 238000005452 bending Methods 0.000 description 2
- 239000011230 binding agent Substances 0.000 description 2
- 229920005549 butyl rubber Polymers 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 238000009940 knitting Methods 0.000 description 2
- 239000007800 oxidant agent Substances 0.000 description 2
- 230000001590 oxidative effect Effects 0.000 description 2
- 229920001568 phenolic resin Polymers 0.000 description 2
- 239000004033 plastic Substances 0.000 description 2
- 229920003023 plastic Polymers 0.000 description 2
- 229920002857 polybutadiene Polymers 0.000 description 2
- 229920001195 polyisoprene Polymers 0.000 description 2
- 239000004449 solid propellant Substances 0.000 description 2
- CYRMSUTZVYGINF-UHFFFAOYSA-N trichlorofluoromethane Chemical compound FC(Cl)(Cl)Cl CYRMSUTZVYGINF-UHFFFAOYSA-N 0.000 description 2
- 230000002159 abnormal effect Effects 0.000 description 1
- 230000032683 aging Effects 0.000 description 1
- WNROFYMDJYEPJX-UHFFFAOYSA-K aluminium hydroxide Chemical compound [OH-].[OH-].[OH-].[Al+3] WNROFYMDJYEPJX-UHFFFAOYSA-K 0.000 description 1
- 239000004760 aramid Substances 0.000 description 1
- 229920003235 aromatic polyamide Polymers 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 229910052736 halogen Inorganic materials 0.000 description 1
- 150000002367 halogens Chemical class 0.000 description 1
- 239000012210 heat-resistant fiber Substances 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 229920003049 isoprene rubber Polymers 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229920002480 polybenzimidazole Polymers 0.000 description 1
- 239000000779 smoke Substances 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 239000004636 vulcanized rubber Substances 0.000 description 1
Landscapes
- Laminated Bodies (AREA)
- Inorganic Fibers (AREA)
- Thermal Insulation (AREA)
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明は耐熱性及び難燃性に優
れ、かつ断熱性に富んだ高性能のロケットモーター用断
熱材に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a high-performance heat insulating material for rocket motors, which has excellent heat resistance and flame retardancy and is highly heat insulating.
【０００２】[0002]
【従来の技術】一般に固体ロケットは図３に示すように
推進薬10、断熱材11、推進薬燃焼室12、推進薬10に点火
する点火装置13及びノズル14から成っている。即ち推進
薬10の燃焼火炎が直接に耐圧容器の燃焼室12の内壁に触
れないように壁面に断熱材11を貼付し、また燃焼推力曲
線が所要の値になるように耐炎性を有する断熱材（レス
トリクター）で推進薬の一部表面を覆っている。これら
の断熱材には次の性能が要求されている。即ち１）燃焼
抑制力及び耐熱性に優れていること、２）推進薬との接
着性に優れていること、３）貯蔵安定性に優れているこ
と、４）耐老化性に優れていること、５）機械的強度が
大であること、６）比重が小さいこと、７）断熱性に優
れていること、８）価格が低廉であること、９）気密性
に優れていること、等である。現在使用されている断熱
材は、火薬である推進薬と類似の化学構造を有するゴム
又はプラスチックス等よりなっており、接着性、気密性
には優れているが、燃焼抑制力において満足できるもの
はない。それ故ロケットモーターに於いて断熱材の肉厚
は相当程度厚くすることが必要であり、その結果、断熱
材の占めるスペースが大きくなり、ロケットモーター内
の10％以上を越える欠点があった。又、この断熱材が燃
焼する際に大量の酸素を必要とするため、不完全燃焼に
よる多量の黒煙を発生し、ロケット打ち上げ観測の邪魔
になり、公害問題を引き起こす等の不具合もあった。こ
れらの欠点を改善するためにゴム又はプラスチックスを
ベースとした断熱材の耐熱性を向上させるためにアスベ
スト、燐又はハロゲン系の防炎剤及び水酸化アルミニウ
ムの如き吸熱剤を配合している。又、このように配合さ
れた耐熱性ゴム配合物層の中間に耐熱性の優れた繊維布
を配置し、複合化したものを断熱材に使用する場合もあ
る。ここに用いる繊維布としては防炎性に優れ、高温で
も溶融したり、収縮したりせず、原形のまま炭化できる
フェノール樹脂、アラミド、ポリベンズイミダゾール等
の繊維布等が用いられている。2. Description of the Related Art Generally, a solid rocket comprises a propellant 10, a heat insulating material 11, a propellant combustion chamber 12, an ignition device 13 for igniting the propellant 10 and a nozzle 14 as shown in FIG. That is, the heat insulating material 11 is attached to the wall surface so that the combustion flame of the propellant 10 does not directly touch the inner wall of the combustion chamber 12 of the pressure vessel, and the heat insulating material has flame resistance so that the combustion thrust curve has a required value. (Restrictor) partially covers the surface of the propellant. The following performances are required for these heat insulating materials. That is, 1) excellent in burn suppressing power and heat resistance, 2) excellent in adhesion to propellant, 3) excellent in storage stability, and 4) excellent in aging resistance. 5) high mechanical strength, 6) low specific gravity, 7) excellent heat insulation, 8) low price, 9) excellent airtightness, etc. is there. The heat insulating material currently used is made of rubber or plastics, which has a chemical structure similar to that of propellant, which is explosive, and has excellent adhesiveness and airtightness, but it is satisfactory in combustion suppressing power. There is no. Therefore, in the rocket motor, it is necessary to increase the thickness of the heat insulating material to a considerable extent, and as a result, the space occupied by the heat insulating material becomes large, and there is a drawback of exceeding 10% or more in the rocket motor. Further, since a large amount of oxygen is required when the heat insulating material burns, a large amount of black smoke is generated due to incomplete combustion, which interferes with rocket launch observations and causes pollution problems. In order to improve these drawbacks, asbestos-, phosphorus- or halogen-based flameproofing agents and endothermic agents such as aluminum hydroxide are blended in order to improve the heat resistance of heat insulating materials based on rubber or plastics. In some cases, the heat-resistant rubber compound layer thus blended may be used as a heat insulating material by arranging a highly heat-resistant fiber cloth in the middle. As the fiber cloth used here, a fiber cloth of phenol resin, aramid, polybenzimidazole, etc., which is excellent in flameproof property, does not melt or shrink even at high temperature, and can be carbonized in its original form, and the like are used.
【０００３】[0003]
【発明が解決しようとする課題】併しながら近年、ロケ
ットモーターが高性能化、高速化されるに従い、断面積
が小さく、細長い構造のものが設計されるようになった
が、このようなロケットモーターが急旋回を行うとロケ
ットは湾曲し、更に長軸の屈曲振動を起こす。これらの
屈曲や振動に伴い、ロケットモーター内の断熱材に伸び
及び収縮の力が働き20％以上の伸びに耐えることが要求
される。しかるに断熱材に使用される耐熱性ゴム加硫物
自体は 150％以上の伸びを有するが、前記の如き従来使
用されている繊維布の破断伸びは５〜20％迄であり、従
ってこの繊維布と上記ゴムとのサンドイッチ構造のゴム
シートの破断時伸びは20％より小さいから、高性能ロケ
ットモーターには使用できなかった。又、複雑な形状や
細長い構造の場合は伸びの大きな布でなければ成型が困
難であった。At the same time, as rocket motors have become more sophisticated and faster in recent years, those having a narrow cross-sectional area and an elongated structure have been designed. When the motor makes a sharp turn, the rocket bends, causing further bending vibration of the long axis. Due to these bending and vibration, the heat insulating material in the rocket motor is required to withstand the elongation of 20% or more due to the force of expansion and contraction. However, the heat-resistant rubber vulcanizate itself used for the heat insulating material has an elongation of 150% or more, but the breaking elongation of the conventionally used fiber cloth as described above is up to 5 to 20%. Since the elongation at break of the rubber sheet having a sandwich structure with the above rubber was less than 20%, it could not be used for a high performance rocket motor. Further, in the case of a complicated shape or an elongated structure, it is difficult to mold unless the cloth has a large elongation.
【０００４】[0004]
【課題を解決するための手段】本発明者等は、繊維布を
サンドイッチした構造のゴムシートの伸びを決定するの
は用いる繊維布の伸びの大きさであることに注目して、
伸びの大きな布を開発すべく研究の結果、伸張率50％以
上を有する炭化し易い繊維布を得て、本発明に到ったも
のである。即ち、本発明は耐熱性ゴム配合物層の中間に
伸張率50％以上を有する高温加熱により炭素繊維化し易
い繊維布を配置し、複合させてなることを特徴とするロ
ケットモーター用断熱材に係るものである。The inventors of the present invention have noticed that it is the elongation of the fiber cloth used that determines the elongation of the rubber sheet having a structure in which the fiber cloth is sandwiched.
As a result of research to develop a cloth having a large elongation, the present invention has been accomplished by obtaining a fiber cloth which has an elongation rate of 50% or more and is easily carbonized. That is, the present invention relates to a heat insulating material for a rocket motor, characterized in that a fiber cloth which has an elongation of 50% or more and is easily converted into carbon fibers by heating at high temperature is arranged in the middle of the heat resistant rubber compound layer, and is made into a composite. It is a thing.
【０００５】本発明者等の研究によれば、従来ロケット
モーター用断熱材に使用されたフェノール樹脂繊維布、
アラミド繊維布、ポリベンズイミダゾール繊維布の如き
高温加熱により炭素繊維化し易い繊維布の原糸はすべて
破断時伸びは約３％、大きいもので20％と小さいことが
判明した。そこで、本発明では布の破断時伸びを大きく
するため原糸の織り方を改良し、メリヤス編布又はニッ
ト編布とすることにより、破断時の伸びを50％以上にす
ることが可能であることを見出した。これに対して、平
織と朱子織では織布の破断時伸びは20％が限度であっ
た。本発明に於て、耐熱性ゴム配合物層の中間に配置さ
れる高温加熱により炭素繊維化し易い繊維布としてはフ
ェノール樹脂繊維布、アラミド繊維布、ポリベンツイミ
ダゾール繊維布等が使用し得る。本発明に使用される耐
熱性ゴム配合物としては、従来使用されている耐熱性ゴ
ムを使用し得るが、好ましいものとしてはエチレンプロ
ピレンゴム、ポリイソプレンゴム、及びブチルゴム等が
挙げられる。According to the research conducted by the present inventors, a phenolic resin fiber cloth conventionally used as a heat insulating material for rocket motors,
It has been found that the raw yarns of fiber cloths such as aramid fiber cloths and polybenzimidazole fiber cloths, which are easily carbonized by heating at high temperature, have elongations at break of about 3% and large ones of 20%. Therefore, in the present invention, it is possible to improve the elongation at break by 50% or more by improving the weaving method of the raw yarn in order to increase the elongation at break of the cloth and forming the knitted or knitted knit fabric. I found that. On the other hand, in plain weave and satin weave, the elongation at break of the woven fabric was limited to 20%. In the present invention, a phenol resin fiber cloth, an aramid fiber cloth, a polybenzimidazole fiber cloth, or the like may be used as the fiber cloth arranged in the middle of the heat-resistant rubber compound layer and easily converted into carbon fibers by high temperature heating. As the heat-resistant rubber compound used in the present invention, conventionally used heat-resistant rubbers can be used, but preferable examples include ethylene propylene rubber, polyisoprene rubber, butyl rubber and the like.
【０００６】[0006]
【実施例】以下実施例により本発明を詳細に説明する
が、本発明は実施例のみに限定されるものではない。耐
熱性ゴムとしてエチレンプロピレンゴム及びイソプレン
ゴムを用い、これらのゴム配合物を表１に示す繊維布の
両面に貼付して実施例及び比較例の断熱材を作製した。The present invention will be described in detail below with reference to examples, but the present invention is not limited to the examples. Ethylene propylene rubber and isoprene rubber were used as the heat resistant rubber, and these rubber compounds were attached to both sides of the fiber cloth shown in Table 1 to prepare heat insulating materials of Examples and Comparative Examples.
【０００７】[0007]
【表１】 [Table 1]
【０００８】使用した耐熱ゴムは常法に従って加硫剤、
加硫助剤、補強剤等の配合剤を混入し、その混合物を接
着処理を施した繊維布の両面に貼り合わせ、熱加硫を行
って繊維布入りゴムシート複合体を作製し、供試体とし
た。使用したポリベンズイミダゾール繊維の編布及び織
布の破断時伸びを表２に示した。The heat-resistant rubber used is a vulcanizing agent according to a conventional method,
Compounding agents such as vulcanization aids and reinforcing agents are mixed, the mixture is pasted on both sides of the adhesive-treated fiber cloth, and thermal vulcanization is performed to produce a rubber sheet composite containing fiber cloth, And Table 2 shows the elongation at break of the knitted and woven fabrics of the polybenzimidazole fibers used.
【０００９】[0009]
【表２】 [Table 2]
【００１０】本発明によるメリヤス編布入りゴムシート
複合体及び比較例として平織布入りゴムシート複合体加
硫物の破断時の伸びを表３に示す。Table 3 shows the elongation at break of the vulcanized rubber sheet composite with knitted fabric according to the present invention and the rubber sheet composite with plain woven fabric as a comparative example.
【００１１】[0011]
【表３】 [Table 3]
【００１２】表３より、本発明によるゴムシート複合体
は、従来品である比較例に比して６〜16倍の破断時伸び
を示し、ゴムマトリックスの伸びの良さが生かされてい
るのが特徴的であることが判る。次に厚さ1.1mm 、巾25
mm、長さ200mm の軟鉄板に厚さ３mmの本発明によるゴム
シート複合体と、比較例のゴムシート複合体をそれぞれ
接着剤で貼付け、直径10cmの鉄管に両端を持って押し付
け試料に伸びを与えると、比較例のゴムシート複合体は
中央部で破断し、試料が伸び歪に耐えないことを示し
た。一方、本発明による試料は破断せず異常がなかっ
た。更に本発明の断熱材の耐熱性及び燃焼抑制力につい
て、公知の固体ロケットモーター燃焼試験によって評価
を行った。From Table 3, the rubber sheet composite according to the present invention exhibits elongation at break which is 6 to 16 times as much as that of the conventional comparative example, and the good elongation of the rubber matrix is utilized. It turns out to be characteristic. Next, thickness 1.1mm, width 25
3 mm thick rubber sheet composite according to the present invention and a comparative rubber sheet composite are attached to a soft iron plate having a length of 200 mm and a length of 200 mm with an adhesive, respectively. When applied, the rubber sheet composites of the Comparative Example broke at the center, indicating that the sample did not withstand elongation strain. On the other hand, the sample according to the present invention did not break and was not abnormal. Further, the heat resistance and the combustion suppressing power of the heat insulating material of the present invention were evaluated by a known solid rocket motor combustion test.
【００１３】試験に用いた固体ロケットモーターの概略
図を図１に示す。図１に於いて１はロケットモーター本
体を、２は燃焼室を、３はノズルスロートを、４はノズ
ル先細部を示し、このノズル先細部４の内表面に試料断
熱材５を接着剤で貼付けてある。６は燃焼室圧力を検出
する圧力ピックアップを、７は推進薬８を着火させる点
火器を示す。推進薬８は過塩素アンモニウムを酸化剤と
し、発熱剤としてアルミニウム粉末を用い、燃料兼結合
剤として末端水酸基ポリブタジエンを用いた混成系固体
推進薬である。点火電力信号を脚線９から供給すると点
火器７が発火し、推進薬８の表面が着火する。推進薬８
から発生した約3000℃の燃焼ガスはノズル先細部４で流
速を早めながらノズルスロート３で音速に達し、外部に
噴出する。試料の断熱材５はノズル先細部４の表面に貼
付されているので、先細部になるに従い燃焼ガス表面流
速は0.03〜0.13マッハと速くなる。各燃焼ガス流速に対
する試料断熱材の焼損速度を図２に示す。縦軸に焼損速
度(mm/s)を、横軸に試料表面の燃焼ガス流速をマッハ数
で示す。A schematic view of the solid rocket motor used in the test is shown in FIG. In FIG. 1, 1 is a rocket motor main body, 2 is a combustion chamber, 3 is a nozzle throat, 4 is a nozzle tip detail, and a sample heat insulating material 5 is attached to the inner surface of the nozzle tip detail 4 with an adhesive. There is. Reference numeral 6 is a pressure pickup for detecting the combustion chamber pressure, and 7 is an igniter for igniting the propellant 8. The propellant 8 is a hybrid solid propellant which uses ammonium perchlorate as an oxidant, aluminum powder as a heat generating agent, and polyhydroxyl terminal terminal polybutadiene as a fuel / binder. When the ignition power signal is supplied from the leg wire 9, the igniter 7 is ignited and the surface of the propellant 8 is ignited. Propellant 8
The combustion gas of about 3000 ° C. generated from the nozzle reaches the speed of sound at the nozzle throat 3 while increasing the flow velocity at the nozzle tip portion 4 and is ejected to the outside. Since the heat insulating material 5 of the sample is attached to the surface of the nozzle tip portion 4, the combustion gas surface flow velocity increases to 0.03 to 0.13 Mach as the tip portion becomes finer. FIG. 2 shows the burning rate of the sample heat insulating material with respect to each combustion gas flow velocity. The vertical axis shows the burning rate (mm / s), and the horizontal axis shows the combustion gas flow velocity on the sample surface in Mach number.
【００１４】実施例１と比較例１の両者の試料は同じ焼
損速度を示している。実施例２と比較例２の両者も同じ
燃損速度を示しており、繊維布の織り方、編み方による
焼損速度の差はない。実施例１，２の焼損速度の差は用
いたゴムの耐熱性の差によるものである。又、ロケット
モーター外壁の温度上昇は僅かであり、優れた断熱性を
示し、繊維布の織り方、編み方による差はなかった。The samples of both Example 1 and Comparative Example 1 show the same burning rate. Both Example 2 and Comparative Example 2 exhibit the same burnout speed, and there is no difference in burnout speed depending on the weave and knitting methods of the fiber cloth. The difference in burning rate between Examples 1 and 2 is due to the difference in heat resistance of the rubbers used. In addition, the temperature rise of the outer wall of the rocket motor was slight, and it showed excellent heat insulation, and there was no difference due to the weaving or knitting method of the fiber cloth.
【００１５】[0015]
【発明の効果】本発明による固体ロケットモーター用断
熱材は、従来の耐熱性ゴムと繊維布を複合させた断熱材
と比較して、耐炎性、耐熱性、断熱性は同等であるが、
破断時伸びの機械的性質が著しく優れており、細長く、
柔軟な高性能ロケットモーターに使用することが可能と
なり、かつロケットモーターの作製に際し、加工性、成
型性を大幅に改善した効果は大である。The heat insulating material for a solid rocket motor according to the present invention has the same flame resistance, heat resistance and heat insulating property as compared with the conventional heat insulating material in which heat resistant rubber and fiber cloth are combined.
Mechanical properties of elongation at break are remarkably excellent, long and thin,
It is possible to use it for flexible high-performance rocket motors, and the effect of greatly improving the workability and moldability when manufacturing rocket motors is great.
【図１】試験に用いた固体ロケットモーターの概略図で
ある。FIG. 1 is a schematic view of a solid rocket motor used in a test.
【図２】各燃焼ガス流速に対する試料断熱材の焼損速度
の関係を示す図である。FIG. 2 is a diagram showing a relationship of burning rate of a sample heat insulating material with respect to each combustion gas flow velocity.
【図３】従来の固体ロケットの概略図であるFIG. 3 is a schematic view of a conventional solid rocket.
【符号の説明】 １ ロケットモーター本体 ２ 燃焼室 ３ ノズルスロート ４ ノズル先端部 ５ 試料断熱材 ６ 圧力ピックアップ ７ 点火器 ８ 推進薬 ９ 脚線 10 推進薬 11 断熱材 12 推進薬燃焼室 13 点火装置 14 ノズル[Explanation of symbols] 1 rocket motor body 2 combustion chamber 3 nozzle throat 4 nozzle tip 5 sample heat insulating material 6 pressure pickup 7 igniter 8 propellant 9 leg 10 propellant 11 heat insulating material 12 propellant combustion chamber 13 ignition device 14 nozzle
─────────────────────────────────────────────────────
─────────────────────────────────────────────────── ───
【手続補正書】[Procedure amendment]
【提出日】平成３年９月４日[Submission date] September 4, 1991
【手続補正１】[Procedure Amendment 1]
【補正対象書類名】明細書[Document name to be amended] Statement
【補正対象項目名】０００５[Name of item to be corrected] 0005
【補正方法】変更[Correction method] Change
【補正内容】[Correction content]
【０００５】本発明者等の研究によれば、従来ロケット
モーター用断熱材に使用されたフェノール樹脂繊維布、
アラミド繊維布、ポリベンズイミダゾール繊維布の如き
高温加熱により炭素繊維化し易い繊維布の原糸はすべて
破断時伸びは約３％、大きいもので20％と小さいことが
判明した。そこで、本発明では布の破断時伸びを大きく
するため原糸の織り方を改良し、メリヤス編布又はニッ
ト編布とすることにより、破断時の伸びを50％以上にす
ることが可能であることを見出した。これに対して、平
織と朱子織では織布の破断時伸びは20％が限度であっ
た。本発明に於て、耐熱性ゴム配合物層の中間に配置さ
れる高温加熱により炭素繊維化し易い繊維布としてはフ
ェノール樹脂繊維布、アラミド繊維布、ポリベンズイミ
ダゾール繊維布等が使用し得る。本発明に使用される耐
熱性ゴム配合物としては、従来使用されている耐熱性ゴ
ムを使用し得るが、好ましいものとしてはエチレンプロ
ピレンゴム、ポリイソプレンゴム、及びブチルゴム等が
挙げられる。According to the research conducted by the present inventors, a phenolic resin fiber cloth conventionally used as a heat insulating material for rocket motors,
It has been found that the raw yarns of fiber cloths such as aramid fiber cloths and polybenzimidazole fiber cloths, which are easily carbonized by heating at high temperature, have elongations at break of about 3% and large ones of 20%. Therefore, in the present invention, it is possible to improve the elongation at break by 50% or more by improving the weaving method of the raw yarn in order to increase the elongation at break of the cloth and forming the knitted or knitted knit fabric. I found that. On the other hand, in plain weave and satin weave, the elongation at break of the woven fabric was limited to 20%. In the present invention, a phenol resin fiber cloth, an aramid fiber cloth, a polybenzimidazole fiber cloth, or the like may be used as the fiber cloth disposed in the middle of the heat resistant rubber compound layer and easily converted into carbon fibers by high temperature heating. As the heat-resistant rubber compound used in the present invention, conventionally used heat-resistant rubbers can be used, but preferable examples include ethylene propylene rubber, polyisoprene rubber, butyl rubber and the like.
【手続補正２】[Procedure Amendment 2]
【補正対象書類名】明細書[Document name to be amended] Statement
【補正対象項目名】００１３[Correction target item name] 0013
【補正方法】変更[Correction method] Change
【補正内容】[Correction content]
【００１３】試験に用いた固体ロケットモーターの概略
図を図１に示す。図１に於いて１はロケットモーター本
体を、２は燃焼室を、３はノズルスロートを、４はノズ
ル先細部を示し、このノズル先細部４の内表面に試料断
熱材５を接着剤で貼付けてある。６は燃焼室圧力を検出
する圧力ピックアップを、７は推進薬８を着火させる点
火器を示す。推進薬８は過塩素酸アンモニウムを酸化剤
とし、発熱剤としてアルミニウム粉末を用い、燃料兼結
合剤として末端水酸基ポリブタジエンを用いた混成系固
体推進薬である。点火電力信号を脚線９から供給すると
点火器７が発火し、推進薬８の表面が着火する。推進薬
８から発生した約3000℃の燃焼ガスはノズル先細部４で
流速を早めながらノズルスロート３で音速に達し、外部
に噴出する。試料の断熱材５はノズル先細部４の表面に
貼付されているので、先細部になるに従い燃焼ガス表面
流速は0.03〜0.13マッハと速くなる。各燃焼ガス流速に
対する試料断熱材の焼損速度を図２に示す。縦軸に焼損
速度(mm/s)を、横軸に試料表面の燃焼ガス流速をマッハ
数で示す。A schematic view of the solid rocket motor used in the test is shown in FIG. In FIG. 1, 1 is a rocket motor main body, 2 is a combustion chamber, 3 is a nozzle throat, 4 is a nozzle tip detail, and a sample heat insulating material 5 is attached to the inner surface of the nozzle tip detail 4 with an adhesive. There is. Reference numeral 6 is a pressure pickup for detecting the combustion chamber pressure, and 7 is an igniter for igniting the propellant 8. The propellant 8 is a hybrid solid propellant using ammonium perchlorate as an oxidant, aluminum powder as a heat generating agent, and polyhydroxyl end-capped polybutadiene as a fuel and binder. When the ignition power signal is supplied from the leg wire 9, the igniter 7 is ignited and the surface of the propellant 8 is ignited. The combustion gas of about 3000 ° C. generated from the propellant 8 reaches the speed of sound at the nozzle throat 3 while increasing the flow velocity at the nozzle tip portion 4 and is ejected to the outside. Since the heat insulating material 5 of the sample is attached to the surface of the nozzle tip portion 4, the combustion gas surface flow velocity increases to 0.03 to 0.13 Mach as the tip portion becomes finer. FIG. 2 shows the burning rate of the sample heat insulating material with respect to each combustion gas flow velocity. The vertical axis shows the burning rate (mm / s), and the horizontal axis shows the combustion gas flow velocity on the sample surface in Mach number.
【手続補正３】[Procedure 3]
【補正対象書類名】明細書[Document name to be amended] Statement
【補正対象項目名】符号の説明[Correction target item name] Explanation of code
【補正方法】変更[Correction method] Change
【補正内容】[Correction content]
【符号の説明】 １ ロケットモーター本体 ２ 燃焼室 ３ ノズルスロート ４ ノズル先細部 ５ 試料断熱材 ６ 圧力ピックアップ ７ 点火器 ８ 推進薬 ９ 脚線 10 推進薬 11 断熱材 12 推進薬燃焼室 13 点火装置 14 ノズル[Explanation of symbols] 1 rocket motor body 2 combustion chamber 3 nozzle throat 4 nozzle tip 5 sample heat insulating material 6 pressure pickup 7 igniter 8 propellant 9 leg 10 propellant 11 heat insulating material 12 propellant combustion chamber 13 ignition device 14 nozzle
───────────────────────────────────────────────────── フロントページの続き (72)発明者 横山 章 東京都品川区大井５−21−１ (72)発明者 上月 功 兵庫県姫路市野里慶雲寺前町661−３ (72)発明者 西井 茂樹 兵庫県姫路市網干区新在家940 (72)発明者 船山 秀夫 埼玉県狭山市入間川１丁目15番40号 入間 川ゴム株式会社内 ─────────────────────────────────────────────────── ─── Continuation of the front page (72) Inventor Akira Yokoyama 5-21-1 Oi, Shinagawa-ku, Tokyo (72) Inventor Isao Kotsuki 661-3 Nori Keiunjimae-cho, Himeji City, Hyogo Prefecture (72) Inventor Nishii Shigeki 940, new inhabitant, Aboshi-ku, Himeji-shi, Hyogo Prefecture (72) Inventor Hideo Funayama 1-15-40 Irumagawa, Sayama-shi, Saitama Irumagawa Rubber Co., Ltd.
Claims (3)
以上を有する高温加熱により炭素繊維化し易い繊維布を
配置し、複合させてなることを特徴とするロケットモー
ター用断熱材。1. An elongation of 50% in the middle of the heat resistant rubber compound layer.
A heat insulating material for a rocket motor, characterized in that a fiber cloth which is easily transformed into carbon fiber by heating at a high temperature as described above is arranged and combined.
ール樹脂繊維布、アラミド繊維布、又はポリベンズイミ
ダゾール繊維布である請求項１記載のロケットモーター
用断熱材。2. The heat insulating material for a rocket motor according to claim 1, wherein the fiber cloth is a phenol resin fiber cloth, an aramid fiber cloth, or a polybenzimidazole fiber cloth having an elongation of 50% or more.
ある請求項１又は２記載のロケットモーター用断熱材。3. The heat insulating material for a rocket motor according to claim 1, wherein the fiber cloth is a knitted knitted cloth or a knitted knitted cloth.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP15159091A JP3144429B2 (en) | 1991-06-24 | 1991-06-24 | Insulation for rocket motor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP15159091A JP3144429B2 (en) | 1991-06-24 | 1991-06-24 | Insulation for rocket motor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH0664101A true JPH0664101A (en) | 1994-03-08 |
| JP3144429B2 JP3144429B2 (en) | 2001-03-12 |
Family
ID=15521844
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP15159091A Expired - Lifetime JP3144429B2 (en) | 1991-06-24 | 1991-06-24 | Insulation for rocket motor |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3144429B2 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006095733A (en) * | 2004-09-28 | 2006-04-13 | Ihi Aerospace Co Ltd | Multilayered sheet material for insulation |
| CN108839400A (en) * | 2018-06-28 | 2018-11-20 | 湖北三江航天江北机械工程有限公司 | Intermediate course formula is insulated layer material and preparation method thereof |
| CN114571744A (en) * | 2022-04-21 | 2022-06-03 | 内蒙古工业大学 | Fiber preform reinforced resin rubber ternary composite material and preparation method and application thereof |
-
1991
- 1991-06-24 JP JP15159091A patent/JP3144429B2/en not_active Expired - Lifetime
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006095733A (en) * | 2004-09-28 | 2006-04-13 | Ihi Aerospace Co Ltd | Multilayered sheet material for insulation |
| CN108839400A (en) * | 2018-06-28 | 2018-11-20 | 湖北三江航天江北机械工程有限公司 | Intermediate course formula is insulated layer material and preparation method thereof |
| CN114571744A (en) * | 2022-04-21 | 2022-06-03 | 内蒙古工业大学 | Fiber preform reinforced resin rubber ternary composite material and preparation method and application thereof |
| CN114571744B (en) * | 2022-04-21 | 2024-04-26 | 内蒙古工业大学 | Fiber preform reinforced resin rubber ternary composite material and preparation method and application thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| JP3144429B2 (en) | 2001-03-12 |
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