JP5074686B2 - Propellant for low temperature gas generator - Google Patents
Propellant for low temperature gas generator Download PDFInfo
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- JP5074686B2 JP5074686B2 JP2005332610A JP2005332610A JP5074686B2 JP 5074686 B2 JP5074686 B2 JP 5074686B2 JP 2005332610 A JP2005332610 A JP 2005332610A JP 2005332610 A JP2005332610 A JP 2005332610A JP 5074686 B2 JP5074686 B2 JP 5074686B2
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- 239000003380 propellant Substances 0.000 title claims description 26
- 238000002485 combustion reaction Methods 0.000 claims description 44
- 239000002826 coolant Substances 0.000 claims description 21
- 239000005062 Polybutadiene Substances 0.000 claims description 15
- 238000002156 mixing Methods 0.000 claims description 15
- 229920002857 polybutadiene Polymers 0.000 claims description 15
- 229920000642 polymer Polymers 0.000 claims description 14
- 239000004449 solid propellant Substances 0.000 claims description 14
- GDDNTTHUKVNJRA-UHFFFAOYSA-N 3-bromo-3,3-difluoroprop-1-ene Chemical compound FC(F)(Br)C=C GDDNTTHUKVNJRA-UHFFFAOYSA-N 0.000 claims description 11
- UQSXHKLRYXJYBZ-UHFFFAOYSA-N Iron oxide Chemical group [Fe]=O UQSXHKLRYXJYBZ-UHFFFAOYSA-N 0.000 claims description 8
- YCOWFDCCOFCZPM-UHFFFAOYSA-N n,n'-dihydroxyoxamide Chemical group ONC(=O)C(=O)NO YCOWFDCCOFCZPM-UHFFFAOYSA-N 0.000 claims description 4
- 229920002587 poly(1,3-butadiene) polymer Polymers 0.000 claims 1
- 239000007789 gas Substances 0.000 description 17
- 239000011230 binding agent Substances 0.000 description 16
- 239000003795 chemical substances by application Substances 0.000 description 5
- 239000007800 oxidant agent Substances 0.000 description 5
- 238000001723 curing Methods 0.000 description 4
- 239000002131 composite material Substances 0.000 description 3
- 230000007423 decrease Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 230000001590 oxidative effect Effects 0.000 description 3
- 235000015842 Hesperis Nutrition 0.000 description 2
- 229920002121 Hydroxyl-terminated polybutadiene Polymers 0.000 description 2
- 235000012633 Iberis amara Nutrition 0.000 description 2
- YIKSCQDJHCMVMK-UHFFFAOYSA-N Oxamide Chemical compound NC(=O)C(N)=O YIKSCQDJHCMVMK-UHFFFAOYSA-N 0.000 description 2
- 239000000654 additive Substances 0.000 description 2
- 239000000567 combustion gas Substances 0.000 description 2
- 238000013329 compounding Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- XEEYBQQBJWHFJM-UHFFFAOYSA-N iron Substances [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- PQXKHYXIUOZZFA-UHFFFAOYSA-M lithium fluoride Chemical compound [Li+].[F-] PQXKHYXIUOZZFA-UHFFFAOYSA-M 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- JSOGDEOQBIUNTR-UHFFFAOYSA-N 2-(azidomethyl)oxirane Chemical compound [N-]=[N+]=NCC1CO1 JSOGDEOQBIUNTR-UHFFFAOYSA-N 0.000 description 1
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 1
- OYBMVMAXKOGYDC-UHFFFAOYSA-N CTPB Chemical compound CCCCCCCCCCCCCCCC1=CC=CC(OCC)=C1C(=O)NC1=CC=C(Cl)C(C(F)(F)F)=C1 OYBMVMAXKOGYDC-UHFFFAOYSA-N 0.000 description 1
- 239000004215 Carbon black (E152) Substances 0.000 description 1
- 239000005057 Hexamethylene diisocyanate Substances 0.000 description 1
- 239000005058 Isophorone diisocyanate Substances 0.000 description 1
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 1
- 239000000020 Nitrocellulose Substances 0.000 description 1
- SNIOPGDIGTZGOP-UHFFFAOYSA-N Nitroglycerin Chemical compound [O-][N+](=O)OCC(O[N+]([O-])=O)CO[N+]([O-])=O SNIOPGDIGTZGOP-UHFFFAOYSA-N 0.000 description 1
- 239000000006 Nitroglycerin Substances 0.000 description 1
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 239000007767 bonding agent Substances 0.000 description 1
- 150000004649 carbonic acid derivatives Chemical class 0.000 description 1
- 125000003178 carboxy group Chemical group [H]OC(*)=O 0.000 description 1
- 239000003054 catalyst Substances 0.000 description 1
- 239000003431 cross linking reagent Substances 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 229910001873 dinitrogen Inorganic materials 0.000 description 1
- 229920001971 elastomer Polymers 0.000 description 1
- 150000004673 fluoride salts Chemical class 0.000 description 1
- 229960003711 glyceryl trinitrate Drugs 0.000 description 1
- 238000013007 heat curing Methods 0.000 description 1
- RRAMGCGOFNQTLD-UHFFFAOYSA-N hexamethylene diisocyanate Chemical compound O=C=NCCCCCCN=C=O RRAMGCGOFNQTLD-UHFFFAOYSA-N 0.000 description 1
- 229930195733 hydrocarbon Natural products 0.000 description 1
- 150000002430 hydrocarbons Chemical class 0.000 description 1
- 125000002887 hydroxy group Chemical group [H]O* 0.000 description 1
- 239000004615 ingredient Substances 0.000 description 1
- NIMLQBUJDJZYEJ-UHFFFAOYSA-N isophorone diisocyanate Chemical compound CC1(C)CC(N=C=O)CC(C)(CN=C=O)C1 NIMLQBUJDJZYEJ-UHFFFAOYSA-N 0.000 description 1
- 229910052749 magnesium Inorganic materials 0.000 description 1
- 239000011777 magnesium Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 150000002736 metal compounds Chemical class 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000003607 modifier Substances 0.000 description 1
- 229920001220 nitrocellulos Polymers 0.000 description 1
- 239000004014 plasticizer Substances 0.000 description 1
- 229920000728 polyester Polymers 0.000 description 1
- 229920005596 polymer binder Polymers 0.000 description 1
- 229920002635 polyurethane Polymers 0.000 description 1
- 239000004814 polyurethane Substances 0.000 description 1
- 229920000915 polyvinyl chloride Polymers 0.000 description 1
- 239000004800 polyvinyl chloride Substances 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 239000005060 rubber Substances 0.000 description 1
- 239000003381 stabilizer Substances 0.000 description 1
- 229910052726 zirconium Inorganic materials 0.000 description 1
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Description
本発明は、ガスジェネレータ用推進薬に関し、特に、低い燃焼温度においても安定した燃焼を維持することができるガスジェネレータ用固体推進薬に関する。 The present invention relates to a propellant for a gas generator, and more particularly to a solid propellant for a gas generator that can maintain stable combustion even at a low combustion temperature.
固体推進薬は、構造が単純で部品点数が少なく、取扱いが比較的容易であること、推進薬を装填したまま長期保存が可能であること、及び、大きな初期加速度の推力が得られること等の特長を有しており、例えば、中規模人工衛星打上げ用ロケット或いは気象観測用ロケットなどに広く用いられている。固体推進薬としては、酸化剤と燃料成分（バインダー）を混合して得られるコンポジット系固体推進薬と、ニトログリセリン及びニトロセルロースを主成分とするダブルベース系固体推進薬とに大別される。 The solid propellant has a simple structure with a small number of parts, is relatively easy to handle, can be stored for a long time with the propellant loaded, and has a large initial acceleration thrust. For example, it is widely used in rockets for launching medium-scale artificial satellites or rockets for weather observation. Solid propellants are roughly classified into composite solid propellants obtained by mixing an oxidant and a fuel component (binder) and double base solid propellants mainly composed of nitroglycerin and nitrocellulose.
当該コンポジット系固体推進薬は、飛翔体の進路変更や姿勢制御を行うサイドスラスタ（例えば、特許文献1及び特許文献2など）、或いは、加圧ポンプのタービン及びアクチュエータ等の動力源に用いられるガスジェネレータにおける推進薬として有用であることが知られている。しかし、これらのガスジェネレータに用られる場合には、飛翔体及び装置の耐熱温度等の観点から推進薬を低温で燃焼させつつも、所望の用途に応じた十分な推力又は高圧ガスを提供することが求められる。 The composite solid propellant is a gas used for a power source such as a side thruster (for example, Patent Document 1 and Patent Document 2) for changing the course of the flying object and controlling its attitude, or a turbine and an actuator of a pressure pump. It is known to be useful as a propellant in generators. However, when used in these gas generators, provide sufficient thrust or high-pressure gas according to the desired application while burning the propellant at a low temperature from the viewpoint of the heat resistance temperature of the flying object and the device. Is required.
この点につき、従来は、ガスジェネレータ用固体推進薬の燃焼温度を下げるため、冷却剤を添加すると共に、バインダー配合比を上げて調整していた。しかしながら、このような配合条件では、バインダーが完全に燃焼できないことによりピッチ状の残さが生じる。その結果、これらが燃焼ガス中に混入して制御機器におけるタービン、バルブ、フィルター等に悪影響を与え、低燃焼温度において安定した燃焼を維持できないという問題点があった。
本発明は、こうした実情に鑑みてなされたものであり、燃焼ガス中における残さの混入を抑制し、低燃焼温度においても安定な燃焼を維持することができるガスジェネレータ用固体推進薬を提供することを課題とするものである。 The present invention has been made in view of such circumstances, and provides a solid propellant for a gas generator that can suppress the mixing of residues in combustion gas and can maintain stable combustion even at a low combustion temperature. Is an issue.
本発明者等は、ガスジェネレータ用の固体推進薬において、その燃焼温度を下げるために冷却剤を添加し、バインダー含有量を増大させた場合であっても、通常は燃焼速度速向上のための触媒として使用されている燃焼促進剤を添加することによって、低燃焼温度において生じるピッチ状残さを抑制できるという知見を見出し、本発明を完成するに至った。 In the solid propellant for gas generators, the present inventors usually add a coolant to lower the combustion temperature and increase the binder content. The inventors have found that the addition of a combustion accelerator used as a catalyst can suppress a pitch-like residue generated at a low combustion temperature, thereby completing the present invention.
すなわち、本発明は、少なくともポリブタジエン系ポリマーと、過塩素酸アンモニウムと、冷却剤とを含む固体推進薬であって、当該推進薬が燃焼促進剤をさらに含み、及び当該ポリブタジエン系ポリマーの配合比が、ポリブタジエン系ポリマーと過塩素酸アンモニウムと冷却剤の総和１００部に対して１８乃至３０重量部であることを特徴とする低温ガスジェネレータ用推進薬に関する。 That is, the present invention is a solid propellant including at least a polybutadiene polymer, ammonium perchlorate, and a coolant, the propellant further including a combustion accelerator, and the blending ratio of the polybutadiene polymer is Further, the present invention relates to a propellant for a low-temperature gas generator, characterized in that the amount is 18 to 30 parts by weight with respect to 100 parts by total of a polybutadiene-based polymer, ammonium perchlorate and a coolant.
本発明によれば、冷却剤を含む固体推進薬に、さらに燃焼促進剤を含むことにより、低い燃焼温度においてもピッチ状残さの発生を抑制して安定した燃焼を維持することができる。また前記冷却剤としてオキサロジヒドロキサム酸を用い、前記燃焼促進剤として鉄酸化物を用いた場合に、前記の効果がより大きくなる。また冷却剤と燃焼促進剤の配合比が特定割合のときに前記の効果がさらに大きくなる。 According to the present invention, by including a combustion accelerator in the solid propellant containing the coolant, it is possible to suppress the occurrence of pitch residue and maintain stable combustion even at a low combustion temperature. In addition, when oxalodihydroxamic acid is used as the coolant and iron oxide is used as the combustion accelerator, the above-described effect becomes greater. In addition, the above effect is further increased when the mixing ratio of the coolant and the combustion accelerator is a specific ratio.
本明細書において、“燃焼促進剤”という語は、当該技術分野において、一般に、燃焼速度の向上のために添加される金属化合物を意味する。当該燃焼促進剤は、好ましくは鉄酸化物であり、例えば、三酸化二鉄（Ｆｅ２Ｏ３）、四三酸化鉄（Ｆｅ３Ｏ４）である（ただし、これらに限定されるものではない）。本発明の低温ガスジェネレータ用推進薬に用いられる燃焼促進剤の配合比は、ポリブタジエン系ポリマーと過塩素酸アンモニウムと冷却剤の総和１００部に対して０．１乃至１重量部、好ましくは０．３乃至１重量部であり、特に、０．３重量部が好ましい。 As used herein, the term “combustion promoter” generally refers to a metal compound added in the art to improve the combustion rate. The combustion accelerator is preferably an iron oxide, for example, ferric trioxide (Fe 2 O 3 ) or triiron tetroxide (Fe 3 O 4 ) (however, it is not limited thereto). ). The blending ratio of the combustion accelerator used in the propellant for the low-temperature gas generator of the present invention is 0.1 to 1 part by weight, preferably 0. 0 parts by weight based on 100 parts of the total of the polybutadiene polymer, ammonium perchlorate and the coolant. It is 3 to 1 part by weight, and 0.3 part by weight is particularly preferable.
本発明の低温ガスジェネレータ用推進薬において用いられる冷却剤は、当該技術分野において通常用いられる冷却剤を使用することができ、好ましくはオキサロジヒドロキサム酸である。当該用いられる冷却剤の配合比は、ポリブタジエン系ポリマーと過塩素酸アンモニウムと冷却剤の総和１００部に対して７５重量部以下、好ましくは３０乃至７０重量部である。なお、冷却剤と燃焼促進剤の配合比は、本明細書に記載される配合比の任意の組合せで用いることができる。 As the coolant used in the propellant for a low temperature gas generator of the present invention, a coolant usually used in the art can be used, and preferably oxalodihydroxamic acid. The blending ratio of the coolant used is 75 parts by weight or less, preferably 30 to 70 parts by weight with respect to 100 parts of the total of the polybutadiene polymer, ammonium perchlorate, and the coolant. The mixing ratio of the coolant and the combustion accelerator can be used in any combination of the mixing ratios described in this specification.
本発明の低温ガスジェネレータ用推進薬において用いられるバインダー成分（燃料成分）は、任意の炭化水素高分子又はゴム質材料の中から適宜選択して用いることができ、それらには、例えば、ポリブタジエン系ポリマー、ポリエステル、ポリウレタン、ポリ塩化ビニル、グリシジルアジ化ポリマー等が含まれる。本発明において用いられるバインダー成分は、好ましくはポリブタジエン系ポリマーであり、特に、末端水酸基ポリブタジエン（ＨＴＰＢ）又は末端カルボキシル基ポリブタジエン（ＣＴＰＢ）が好ましい。当該バインダー成分の配合比は、ポリブタジエン系ポリマーと過塩素酸アンモニウムと冷却剤の総和１００部に対して１８乃至３０重量部、好ましくは２０乃至３０重量部である。 The binder component (fuel component) used in the propellant for the low temperature gas generator of the present invention can be appropriately selected from any hydrocarbon polymer or rubber material, and includes, for example, polybutadiene Polymers, polyesters, polyurethanes, polyvinyl chloride, glycidyl azide polymers and the like are included. The binder component used in the present invention is preferably a polybutadiene-based polymer, and particularly preferably terminal hydroxyl group polybutadiene (HTPB) or terminal carboxyl group polybutadiene (CTPB). The blending ratio of the binder component is 18 to 30 parts by weight, preferably 20 to 30 parts by weight, based on 100 parts of the total of the polybutadiene-based polymer, ammonium perchlorate and the coolant.
本発明の低温ガスジェネレータ用推進薬において用いられる酸化剤成分は、好ましくは過塩素酸アンモニウムである。当該酸化剤成分の配合比は、当該技術分野における当業者であれば適宜選択することができるものであるが、ポリブタジエン系ポリマーと過塩素酸アンモニウムと冷却剤の総和１００部に対して１０乃至４８重量部が好ましい。 The oxidant component used in the propellant for the low temperature gas generator of the present invention is preferably ammonium perchlorate. The compounding ratio of the oxidant component can be appropriately selected by those skilled in the art, but it is 10 to 48 with respect to 100 parts of the total of the polybutadiene-based polymer, ammonium perchlorate, and the coolant. Part by weight is preferred.
また、本発明の低温ガスジェネレータ用推進薬には、その他の添加剤として、燃焼速度調整剤、助燃剤、硬化剤、架橋剤、結合剤（ボンディングエージェント）、可塑剤、安定化剤等を必要に応じて任意に用いることができる。ここで、そのような燃焼速度調整剤の非限定的な例には、オキサミド、フッ化リチウム、２ａ族金属元素の炭酸塩及びフッ化物などが含まれ得る。助燃剤の非限定的な例には、アルミニウム、マグネシウム、ジルコニウム等の金属粉末が含まれ得る。バインダーの硬化剤は、当該技術分野において通常用いられる硬化剤であることができ、例えば、イソホロンジイソシアネート、ヘキサメチレンジイソシアネート等である。 In addition, the propellant for the low temperature gas generator of the present invention requires other additives such as a combustion rate adjusting agent, a combustion aid, a curing agent, a crosslinking agent, a binder (bonding agent), a plasticizer, and a stabilizer. It can be arbitrarily used depending on the case. Here, non-limiting examples of such burning rate modifiers may include oxamide, lithium fluoride, group 2a metal element carbonates and fluorides, and the like. Non-limiting examples of the combustion aid can include metal powders such as aluminum, magnesium, zirconium, and the like. The curing agent for the binder may be a curing agent that is usually used in the art, and examples thereof include isophorone diisocyanate and hexamethylene diisocyanate.
本発明は、ガスジェネレータ用推進薬に上記燃焼促進剤を添加することによって、低燃焼温度においても、バインダー成分の不十分な燃焼によるピッチ状残さの発生を抑制し安定な燃焼を実現できるという効果を有する。当該効果発現のメカニズムは明らかではないが、従来のようなバインダー成分及び冷却剤が多い組成の推進薬を用いる場合には、断熱火炎温度が低下し推進薬へのヒートインプットが減少することにより、結果として、燃焼温度の低下と引換えにバインダー成分の不十分な燃焼によるピッチ状残さが生じてしまうのに対し、本発明の推進薬の場合には、本明細書に記載の鉄酸化物等の燃焼促進剤を推進薬中に添加することによって酸化剤（過塩素酸アンモニウム等）の分解開始温度が低下し、当該推進薬全体の燃焼性の向上がもたらされるものと推察される。 According to the present invention, by adding the above combustion accelerator to the propellant for a gas generator, it is possible to achieve stable combustion by suppressing generation of pitch residue due to insufficient combustion of the binder component even at a low combustion temperature. Have Although the mechanism of the manifestation of the effect is not clear, when using a propellant having a composition with a large amount of binder component and coolant as in the past, the adiabatic flame temperature decreases and the heat input to the propellant decreases, As a result, a pitch-like residue due to insufficient combustion of the binder component occurs in exchange for a decrease in the combustion temperature, whereas in the case of the propellant of the present invention, the iron oxide or the like described in this specification By adding the combustion accelerator into the propellant, it is presumed that the decomposition start temperature of the oxidizing agent (such as ammonium perchlorate) is lowered, and the combustibility of the entire propellant is improved.
本発明の推進薬は、当該技術分野において通常のコンポジット系固体推進薬に用いられている製造方法を用いて製造することができる。例えば、バインダー成分に硬化剤等のその他の添加剤を必要量加え混合する。次いで、燃焼促進剤及び酸化剤を添加し更に混合する。その後、加温硬化を行う。 The propellant of the present invention can be produced by using a production method used for a normal composite solid propellant in the art. For example, a necessary amount of other additives such as a curing agent is added to the binder component and mixed. Next, a combustion accelerator and an oxidizing agent are added and further mixed. Thereafter, heat curing is performed.
以下の実施例により、本発明を更に説明する。 The following examples further illustrate the invention.
本発明におけるガスジェネレータ用固体推進薬の典型的な配合比は以下のとおりである。 The typical compounding ratio of the solid propellant for gas generator in the present invention is as follows.
成分 重量部
ポリブタジエン系ポリマー ２４
過塩素酸アンモニウム １６
オキサロジヒドロキサム酸 ６０
三酸化二鉄 ０．３
オキサミド ５
上記ポリブタジエン系ポリマー（バインダー成分:HTPB）及び三酸化二鉄（燃焼促進剤成分）の配合比を表1に示すように変えた種々の推進薬を製造した（それ以外の成分は一定である）。
Ingredients by weight Polybutadiene polymer 24
Ammonium perchlorate 16
Oxalodihydroxamic acid 60
Ferric trioxide 0.3
Oxamide 5
Various propellants were produced by changing the blend ratio of the above polybutadiene polymer (binder component: HTPB) and ferric trioxide (combustion accelerator component) as shown in Table 1 (other components are constant) .
表１に示す各種推進薬について、以下の方法によりストランド試験を行い、試験後に生じる残さを調べた。
上記推進薬の一部を７ｘ７ｘ７０ｍｍの形状に切りだして、試験用試料を作成した。当該試料一端よりヒューズ線を通し、これを圧力容器内にセットし密閉した。窒素ガスを用いて所定圧に加圧したのち、当該試料に着火し、完全に燃焼した後に生じる残さの量を観測した。用いた燃焼圧力は、約７ＭＰａである。なお、当該ストランド試験についての他の条件は、当該技術分野において周知であり、当業者が実験設備等に応じて適宜決定できるものである。得られた結果を表１に示す。
The various propellants shown in Table 1 were subjected to a strand test by the following method, and the residues generated after the test were examined.
A part of the propellant was cut into a 7 × 7 × 70 mm shape to prepare a test sample. A fuse wire was passed from one end of the sample, which was set in a pressure vessel and sealed. After pressurizing to a predetermined pressure using nitrogen gas, the sample was ignited and the amount of residue generated after complete combustion was observed. The combustion pressure used is about 7 MPa . The other conditions for the strand test are well known in the technical field and can be appropriately determined by those skilled in the art according to the experimental equipment and the like. The obtained results are shown in Table 1.
また、当該試験結果の明確化のために、典型例として、試料１及び３について試料燃焼後の残さの発生状態を撮影した写真のハーフトーンコピーを図１及び２に示す。燃焼促進剤を添加していない試料１では、試料を固定する針の周辺にバインダーの残さである黒い塊が生じているのに対し（図１）、燃焼促進剤を含有する試料３については、そのような残さは全く見られない（図２）。 In addition, in order to clarify the test results, as a typical example, halftone copies of photographs of the samples 1 and 3 taken after the sample combustion are shown in FIGS. In the sample 1 to which the combustion accelerator is not added, a black lump which is a residue of the binder is generated around the needle for fixing the sample (FIG. 1), whereas for the sample 3 containing the combustion accelerator, No such residue is seen (Figure 2).
これらの結果は、本発明のガスジェネレータ用推進薬においては、バインダー成分及び冷却剤を高い配合比で含む場合であっても、当該バインダー成分の不十分な燃焼によるピッチ状残さの発生を抑制できることを明示するものである。 These results show that in the propellant for gas generator of the present invention, even when the binder component and the coolant are included at a high blending ratio, it is possible to suppress the occurrence of pitch residue due to insufficient combustion of the binder component. Is specified.
Claims (2)
ポリブタジエン系ポリマーと過塩素酸アンモニウムと冷却剤の総和１００部に対して
ポリブタジエン系ポリマーの配合比が、２４乃至３０重量部であり
冷却剤の配合比が、７５重量部以下であり、
燃焼促進剤の配合比が、０．１乃至１重量部である
ことを特徴とする低温ガスジェネレータ用推進薬。
A solid propellant including at least a polybutadiene-based polymer, ammonium perchlorate, and a coolant, the propellant further including a combustion accelerator ;
On the sum 100 parts of Po Li butadiene polymer and ammonium perchlorate as the coolant
The blending ratio of the polybutadiene polymer is 24 to 30 parts by weight
The mixing ratio of the coolant is 75 parts by weight or less,
A propellant for a low-temperature gas generator , wherein the blending ratio of the combustion accelerator is 0.1 to 1 part by weight .
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