EP1046626A1 - Rocket propellant - Google Patents
Rocket propellant Download PDFInfo
- Publication number
- EP1046626A1 EP1046626A1 EP00108297A EP00108297A EP1046626A1 EP 1046626 A1 EP1046626 A1 EP 1046626A1 EP 00108297 A EP00108297 A EP 00108297A EP 00108297 A EP00108297 A EP 00108297A EP 1046626 A1 EP1046626 A1 EP 1046626A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- insulation layer
- rocket propellant
- fuel
- weight
- binder
- 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
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B45/00—Compositions or products which are defined by structure or arrangement of component of product
- C06B45/12—Compositions or products which are defined by structure or arrangement of component of product having contiguous layers or zones
Definitions
- the invention relates to a rocket propellant reduced smoke combustion, especially for forehead burners, with a fuel based on ammonium perchlorate with a binder made from isocyanate-bound, hydroxy-terminated Polybutadiene and one surrounding the fuel inhibiting insulation layer. Furthermore, the invention to a method for producing such a rocket propellant directed.
- the inhibiting isolation When a rocket propellant that burns over 20, 40 or 60 s, the inhibiting isolation must be next good adhesion and compatibility with the fuel too perform a thermal protection function that the combustion chamber wall just like the inhibited non-burning Fuel surface before premature pyrolysis and ignition protects. With smoke-reduced composite fuels, that contain little or no particles in the exhaust gas the insulation must not release any particles. Likewise, at the high temperatures of the Do not generate soot clouds in the exhaust gas jet and only burn insignificantly, otherwise with small diameters the specific momentum of the fuel and thus reduces the power of the engine become. The sum of these properties is e.g.
- the invention has for its object a rocket propellant to create a simpler and cheaper one Production with an improved connection of the Allows fuel to the insulation. Furthermore, a Process for producing such a rocket propellant be proposed.
- this task is per se well-known smoke-reduced, polyurethane-bound composite fuel based on ammonium perchlorate and isocyanate-bound hydroxy-terminated polybutadiene solved in that for the inhibition of the fuel surface insulation is used that a Polyurethane binder and a filler combination of 2-8 % By weight, preferably 3-5% by weight silicon carbide, 18-16 % By weight, preferably 24-50% by weight of silica in the form of amorphous quartz powder and 2-20% by weight solid temperature-resistant Fibers with a length of 1-20mm are embedded in it contains.
- the insulation according to the invention usually also has a good one without mechanical or chemical pretreatment Liability to the fuel. It shows at high and low Temperature equally good elasticity and is about the composition of the polyurethane binder by the Share of di- or triisocyanate or added crosslinking Triplets adjustable in their mechanical properties.
- this isolation is advantageously based on hydroxy-terminated polybutadiene bonded with isophorone diisocyanate (IPDI) or dimeryl diisocyanate (DMDI) or with other diisocyanates.
- IPDI isophorone diisocyanate
- DMDI dimeryl diisocyanate
- Another polyester polyol or polyether polyol, which is bound with di-, tri or polymeric isocyanate, can also be used as the base material for the insulation.
- ultrafine silicon dioxide, ultrafine titanium dioxide and zirconium dioxide can also be added as further fillers. These fillers are used in a grain size in the range of 20-50 nm for silicon dioxide and 50-1000 nm for TiO 2 and ZrO 2 . They cause the ceramic layer formed during pyrolysis to solidify, thereby reducing its swelling and ablation without influencing the heat transfer.
- Essential for the cohesion of the pyrolyzed layers is a proportion of 1-20% solid fibers in length from 1-20 mm in the form of high temperature resistant plastic fibers made of polyester, polyamide, polyimide or Polybenzimidazole fibers as well as on carbon fibers, glass or Silicate or ceramic fibers can be constructed.
- the fibers can be mixed before into the prepolymeric insulation mixture with water desized or organic solvent and if necessary with be provided with an adhesion-promoting layer. This can be used for glass, silicate or ceramic fibers made of functional Silanes, advantageous for plastic or carbon fibers made of polyisocyanate and short-chain polyester polyol consist.
- the fibers ensure the cohesion of the formed Slag and for the formation of a solid ceramized Layer.
- the insulation can be made into a corresponding slurry as a prepolymer slurry by die-casting or vacuum pull-up Form associated with the fuel.
- the insulation combines with the fuel for a fixed ready-to-install propellant block.
- the insulation can also be in the prepolymeric state in the combustion chamber or a non-stick coated Tube of the same inner diameter and ejected be cured.
- the propellant is then poured in of the fuel slurries in the finished, if necessary through mechanical roughening or chemical bonding agents pre-treated insulation jacket with subsequent hardening Made at 60-65 ° C.
- the fuel can be in the smoke-reduced version in addition to ammonium perchlorate (AP) in proportions of 50-90 %
- AP ammonium perchlorate
- nitramines such as hexogen or octogen
- ferric oxide or ferrocene derivatives as Combustion catalysts in proportions of 0 to 15% by weight
- the binder is advantageously composed of 8-20% by weight hydroxy-terminated polybutadiene with isophorone diisocyanate (IPDI) or dimeryl diisocyanate (DMDI) in equivalents Proportions was bound, as well as 2-8% by weight plasticizer, 0.1-0.5% by weight of antioxidant, optionally 0.1-0.3% by weight of processing aids, 50-500ppm curing catalyst, preferably triphenyl bismuth and 0.1-1% coupling agent for AP, preferably based on cyanoethylated polyamines or cyanoethylated polyamino alcohols.
- IPDI isophorone diisocyanate
- DMDI dimeryl diisocyanate
- HTPB Hydroxy-terminated polybutadiene
- IPDI Isophorone diisocyanate
- Antioxidant 0.20%
- Plasticizer diisooctyl adipate
- Adhesion promoter triphenyl bismuth
- Silicon carbide 4.53% SiO 2 powder quartz 33.79% TiO 2 super fine 1.90% Carbon fiber 3.65%
- the practical impulse of the fuel is about 93% the theoretical value, the weight loss of the insulation when burned up about 2%.
Landscapes
- Chemical & Material Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Organic Chemistry (AREA)
- Compositions Of Macromolecular Compounds (AREA)
- Medicinal Preparation (AREA)
- Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)
- Polyurethanes Or Polyureas (AREA)
Abstract
Description
Die Erfindung betrifft einen Raketentreibsatz mit rauchreduziertem Abbrand, insbesondere für Stirnbrenner, mit einem Treibstoff auf der Basis von Ammoniumperchlorat mit einem Binder aus isocyanatgebundenen, hydroxyterminierten Polybutadien und einer den Treibstoff umgebenden inhibierenden Isolationsschicht. Ferner ist die Erfindung auf ein Verfahren zur Herstellung eines solchen Raketentreibsatzes gerichtet.The invention relates to a rocket propellant reduced smoke combustion, especially for forehead burners, with a fuel based on ammonium perchlorate with a binder made from isocyanate-bound, hydroxy-terminated Polybutadiene and one surrounding the fuel inhibiting insulation layer. Furthermore, the invention to a method for producing such a rocket propellant directed.
Beim Abbrand eines Raketentreibsatzes, der über 20, 40 oder 60 s abläuft, muß die inhibierende Isolation neben guter Haftung und Verträglichkeit zum Treibstoff auch eine thermische Schutzfunktion erfüllen, die die Brennkammerwand ebenso wie die inhibierte nichtbrennende Treibstoffoberfläche vor vorzeitiger Pyrolyse und Anzündung schützt. Bei rauchreduzierten Composittreibstoffen, die im Abgas keine oder nur wenig Partikel enthalten dürfen, darf auch die Isolation keine Partikel freisetzen. Ebenso darf sie bei den hohen Temperaturen des Treibstoffabbrands keine Rußwolken im Abgasstrahl erzeugen und nur unwesentlich mitverbrennen, da sonst bei kleinen Durchmessern der spezifische Impuls des Treibstoffs und damit die Leistung des Triebwerks reduziert werden. Die Summe dieser Eigenschaften wird z.B. bei Unterwasserantrieben, die beim Abbrand keine heißen Partikel ausschleudern dürfen, und bei Marschtriebwerken von aktiv über Laser oder Radar gelenkten Flugkörpern gefordert. Für diesen Zweck werden bisher stets schwierig herzustellende und teure Isolierungen auf Silikonharzbasis mit silikatischen Füllstoffen verwendet, die in aufwendigen Verfahren aufgerauht und chemisch vorbehandelt werden müssen, um die für die Anbindung des Treibstoffs an die Isolationsschicht notwendige Haftung zu erreichen.When a rocket propellant that burns over 20, 40 or 60 s, the inhibiting isolation must be next good adhesion and compatibility with the fuel too perform a thermal protection function that the combustion chamber wall just like the inhibited non-burning Fuel surface before premature pyrolysis and ignition protects. With smoke-reduced composite fuels, that contain little or no particles in the exhaust gas the insulation must not release any particles. Likewise, at the high temperatures of the Do not generate soot clouds in the exhaust gas jet and only burn insignificantly, otherwise with small diameters the specific momentum of the fuel and thus reduces the power of the engine become. The sum of these properties is e.g. at Underwater drives that are not called hot when they burn up Permitted to eject particles, and with march engines of missiles actively guided by laser or radar required. So far, this has always been difficult Manufactured and expensive insulation based on silicone resin with silicate fillers used in complex processes roughened and chemically pretreated need to be in order to bind the fuel necessary liability to the insulation layer to reach.
Der Erfindung liegt die Aufgabe zugrunde, einen Raketentreibsatz zu schaffen, der eine einfachere und kostengünstigere Herstellung bei einer verbesserten Anbindung des Treibstoffs an die Isolation erlaubt. Ferner soll ein Verfahren zur Herstellung eines solchen Raketentreibsatzes vorgeschlagen werden.The invention has for its object a rocket propellant to create a simpler and cheaper one Production with an improved connection of the Allows fuel to the insulation. Furthermore, a Process for producing such a rocket propellant be proposed.
Erfindungsgemäß wird diese Aufgabe bei einem an sich bekannten rauchreduzierten, polyurethangebundenen Composittreibstoff auf der Basis von Amnmoniumperchlorat und isocyanatgebundenem hydroxyterminiertem Polybutadien dadurch gelöst, daß für die Inhibierung der Treibstoffoberfläche eine Isolation verwendet wird, die einen Polyurethanbinder und eine Füllstoffkombination aus 2-8 Gew.%, vorzugsweise 3-5 Gew.% Siliciumcarbid, 18-16 Gew.%, vorzugsweise 24-50 Gew.% Siliciumdioxid in Gestalt von amorphen Quarzpulver und 2-20 Gew.% feste temperaturbeständige Fasern mit einer Länge von 1-20mm darin eingebettet enthält.According to the invention, this task is per se well-known smoke-reduced, polyurethane-bound composite fuel based on ammonium perchlorate and isocyanate-bound hydroxy-terminated polybutadiene solved in that for the inhibition of the fuel surface insulation is used that a Polyurethane binder and a filler combination of 2-8 % By weight, preferably 3-5% by weight silicon carbide, 18-16 % By weight, preferably 24-50% by weight of silica in the form of amorphous quartz powder and 2-20% by weight solid temperature-resistant Fibers with a length of 1-20mm are embedded in it contains.
Die erfindungsgemäße Isolation besitzt in der Regel auch ohne mechanische oder chemische Vorbehandlung eine gute Haftung zum Treibstoff. Sie zeigt bei hoher und tiefer Temperatur gleichermaßen gute Elastizität und ist über die Zusammensetzung des Polyurethanbinders durch den Anteil an Di- oder Triisocyanat oder beigefügten vernetzenden Triolen in ihren mechanischen Eigenschaften einstellbar.The insulation according to the invention usually also has a good one without mechanical or chemical pretreatment Liability to the fuel. It shows at high and low Temperature equally good elasticity and is about the composition of the polyurethane binder by the Share of di- or triisocyanate or added crosslinking Triplets adjustable in their mechanical properties.
Beim Treibstoffabbrand bewirkt die endotherm ablaufende Reaktion von SiC und SiO2 zusammen mit dem Anteil an Kohlenstoff-, Kunststoff- oder Keramikfasern die Ausbildung einer zusammenhängenden keramisierten Schlacke, die im Brennkammerraum verbleibt und weder Partikel noch Rußwolken im Abgas erzeugt. Die endotherm verlaufende Reaktion der Füllstoffe bewirkt ebenso wie die langsame Pyrolyse des Bindermaterials eine effektive Wärmeschutzwirkung gegenüber dem Brennkammergehäuse und nicht aktiviertem Treibsatzteil. Da zudem nur sehr wenig von dieser Isolationsschicht verbrennt -nach 20 s. Brenndauer treten nur etwa 2% Gewichtsverlust auf- wird der spezifische Impuls des Treibstoffs und damit die Leistung des Triebwerks nicht beeinträchtigt.When fuel is burned off, the endothermic reaction of SiC and SiO 2 together with the proportion of carbon, plastic or ceramic fibers leads to the formation of a coherent, ceramized slag which remains in the combustion chamber and does not produce any particles or soot clouds in the exhaust gas. The endothermic reaction of the fillers, like the slow pyrolysis of the binder material, has an effective thermal protection effect against the combustion chamber housing and the inactivated propellant part. Since only very little of this insulation layer burns - after 20 s. Burning time occurs only about 2% weight loss - the specific impulse of the fuel and thus the performance of the engine is not affected.
Erfindungsgemäß ist diese Isolation vorteilhaft auf der Basis von mit Isophorondiisocyanat (IPDI) oder Dimeryldiisocyanat (DMDI) oder mit anderen Diisocyanaten gebundenem hydroxyterminiertem Polybutadien aufgebaut. Ebenso kann aber auch ein anderes Polyesterpolyol oder Polyetherpolyol, das mit Di-, Tri oder polymerem Isocyanat gebunden wird, als Grundmaterial für die Isolation eingesetzt werden. Als weitere Füllstoffe können erfindungsgemäß auch ultrafeines Siliciumdioxid, ultrafeines Titandioxid und Zirkoniumdioxid zugesetzt werden. Diese Füllstoffe werden in einer Korngröße im Bereich von 20-50 nm für Siliciumdioxid sowie 50-1000 nm für TiO2 und ZrO2 verwendet. Sie bewirken eine Verfestigung der bei der Pyrolyse gebildeten Keramikschicht und vermindern dadurch deren Aufquellung und Ablation, ohne den Wärmedurchgang zu beeinflussen.According to the invention, this isolation is advantageously based on hydroxy-terminated polybutadiene bonded with isophorone diisocyanate (IPDI) or dimeryl diisocyanate (DMDI) or with other diisocyanates. Another polyester polyol or polyether polyol, which is bound with di-, tri or polymeric isocyanate, can also be used as the base material for the insulation. According to the invention, ultrafine silicon dioxide, ultrafine titanium dioxide and zirconium dioxide can also be added as further fillers. These fillers are used in a grain size in the range of 20-50 nm for silicon dioxide and 50-1000 nm for TiO 2 and ZrO 2 . They cause the ceramic layer formed during pyrolysis to solidify, thereby reducing its swelling and ablation without influencing the heat transfer.
Wesentlich für den Zusammenhalt der pyrolisierten Schichten ist ein Anteil von 1-20% festen Fasern in der Länge von 1-20 mm, die in Form hochtemperaturbeständiger Kunststoffasern aus Polyester, Polyamid-, Polyimid- oder Polybenzimidazolfasern sowie auf Kohlefasern, Glas- oder Silikat- oder Keramikfasern aufgebaut sein können. Dabei besitzen Kohlefasern oder aluminiumoxidhaltige Keramikfasern wegen ihrer Hochtemperaturbeständigkeit Vorteile gegenüber den anderen. Die Fasern können vor der Einmischung in die prepolymere Isolationsmischung mit Wasser oder organischem Lösemittel entschlichtet und ggf. mit einer haftvermittelnden Schicht versehen werden. Diese kann bei Glas-, Silikat- oder Keramikfasern aus funktionellen Silanen, bei Kunststoff- oder Kohlefasern vorteilhaft aus Polyisocyanat und kurzkettigem Polyesterpolyol bestehen.Essential for the cohesion of the pyrolyzed layers is a proportion of 1-20% solid fibers in length from 1-20 mm in the form of high temperature resistant plastic fibers made of polyester, polyamide, polyimide or Polybenzimidazole fibers as well as on carbon fibers, glass or Silicate or ceramic fibers can be constructed. Here have carbon fibers or ceramic fibers containing aluminum oxide advantages because of their high temperature resistance towards the others. The fibers can be mixed before into the prepolymeric insulation mixture with water desized or organic solvent and if necessary with be provided with an adhesion-promoting layer. This can be used for glass, silicate or ceramic fibers made of functional Silanes, advantageous for plastic or carbon fibers made of polyisocyanate and short-chain polyester polyol consist.
Bei der Pyrolyse der Isolation während des Treibstoffabbrandes sorgen die Fasern für den Zusammenhalt der gebildeten Schlacke und für die Ausbildung einer festen keramisierten Schicht.During the pyrolysis of the insulation during the burning of fuel the fibers ensure the cohesion of the formed Slag and for the formation of a solid ceramized Layer.
Die Isolation kann als prepolymerer Slurry durch Druckguß- oder im Vakuumaufziehverfahren in eine entsprechende Form mit dem Treibstoff verbunden werden. Bei der anschließenden Aushärtung, die vorteilhaft bei 60-65°C stattfindet, verbindet sich die Isolation mit dem Treibstoff zum festen montagebereiten Treibsatzblock.The insulation can be made into a corresponding slurry as a prepolymer slurry by die-casting or vacuum pull-up Form associated with the fuel. In the subsequent Curing, which is advantageous at 60-65 ° C takes place, the insulation combines with the fuel for a fixed ready-to-install propellant block.
Alternativ kann auch die Isolation im prepolymeren Zustand in der Brennkammer oder einem antihaftbeschichteten Rohr gleichen Innendurchmessers ausgeschleudert und ausgehärtet werden. Der Treibsatz wird dann durch Eingießen des Treibstoffslurries in den fertigen, ggf. durch mechanisches Aufrauhen oder über chemische Haftvermittler vorbehandelten Isolationsmantel mit anschließender Aushärtung bei 60-65°C hergestellt.Alternatively, the insulation can also be in the prepolymeric state in the combustion chamber or a non-stick coated Tube of the same inner diameter and ejected be cured. The propellant is then poured in of the fuel slurries in the finished, if necessary through mechanical roughening or chemical bonding agents pre-treated insulation jacket with subsequent hardening Made at 60-65 ° C.
Der Treibstoff kann in der rauchreduzierten Ausführung neben Ammoniumperchlorat (AP) in Anteilen von 50-90 Gew.%, Nitramine, wie Hexogen oder Oktogen, in Anteilen von 0-30 Gew.%, Eisen-III-oxid oder Ferrocenderivate als Abbrandkatalysatoren in Anteilen von 0 bis 15 Gew.% enthalten.The fuel can be in the smoke-reduced version in addition to ammonium perchlorate (AP) in proportions of 50-90 % By weight, nitramines, such as hexogen or octogen, in proportions from 0-30% by weight, ferric oxide or ferrocene derivatives as Combustion catalysts in proportions of 0 to 15% by weight contain.
Der Binder setzt sich vorteilhaft zusammen aus 8-20 Gew.% hydroxyterminiertem Polybutadien, das mit Isophorondiisocyanat (IPDI) oder Dimeryldiisocyanat (DMDI) in äquvalenten Anteilen gebunden wurde, sowie 2-8 Gew.% Weichmacher, 0,1-0,5 Gew.% Antioxidanz, wahlweise 0,1-0,3 Gew.% Verarbeitungshilfsstoffe, 50-500ppm Härtungskatalysator, vorzugsweise Triphenylwismut und 0,1-1% Haftvermittler für AP, vorzugsweise auf der Basis cyanethylierter Polyamine oder cyanethylierter Polyaminoalkohole.The binder is advantageously composed of 8-20% by weight hydroxy-terminated polybutadiene with isophorone diisocyanate (IPDI) or dimeryl diisocyanate (DMDI) in equivalents Proportions was bound, as well as 2-8% by weight plasticizer, 0.1-0.5% by weight of antioxidant, optionally 0.1-0.3% by weight of processing aids, 50-500ppm curing catalyst, preferably triphenyl bismuth and 0.1-1% coupling agent for AP, preferably based on cyanoethylated polyamines or cyanoethylated polyamino alcohols.
Als inhibierende Isolation (ISO 1) dient eine Mischung
von:
Treibstoff und Isolation bilden ein gut funktionierendes System, das beim Abbrand eines Treibsatzes von 165 mm Durchmesser und 5 mm inhibierender Isolationsschicht über 20 s. keine Partikel und keinen schwarzen Rauch erzeugt. Der praktische Impuls des Treibstoffs beträgt etwa 93% des theoretischen Wertes, der Gewichtsverlust der Isolation beim Abbrand etwa 2%.Fuel and insulation form a well-functioning one System that burns a propellant charge of 165 mm Diameter and 5 mm inhibiting insulation layer over 20 s. no particles and no black smoke. The practical impulse of the fuel is about 93% the theoretical value, the weight loss of the insulation when burned up about 2%.
Die Ummantelung des Treibsatzes mit inhibierender Isolation
erfolgt vorteilhaft durch nachträgliches Umgießen
des ausgehärteten Treibstoffblocks.
Claims (21)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19917672 | 1999-04-19 | ||
DE19917672A DE19917672A1 (en) | 1999-04-19 | 1999-04-19 | Rocket propellant |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1046626A1 true EP1046626A1 (en) | 2000-10-25 |
EP1046626B1 EP1046626B1 (en) | 2004-08-18 |
Family
ID=7905106
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00108297A Expired - Lifetime EP1046626B1 (en) | 1999-04-19 | 2000-04-14 | Rocket propellant |
Country Status (3)
Country | Link |
---|---|
EP (1) | EP1046626B1 (en) |
AT (1) | ATE273943T1 (en) |
DE (2) | DE19917672A1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20100255317A1 (en) * | 2007-11-01 | 2010-10-07 | Kuraray Co., Ltd. | Polyurethane composition |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102005030437B4 (en) | 2005-06-30 | 2007-09-13 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Drive device based on gel-type fuel and method for fuel delivery |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE3643824A1 (en) * | 1986-12-20 | 1988-06-30 | Bayern Chemie Gmbh Flugchemie | Liner layer for lining rocket combustion chambers |
EP0555008A2 (en) * | 1992-01-29 | 1993-08-11 | Thiokol Corporation | Low smoke rocket motor liner compositions |
FR2727402A1 (en) * | 1978-12-29 | 1996-05-31 | Poudres & Explosifs Ste Nale | Propulsion acceleration charge |
US5762746A (en) * | 1989-08-16 | 1998-06-09 | Thiokol Corporation | Method of internally insulating a propellant combustion chamber |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1200184B (en) * | 1963-11-16 | 1965-09-02 | Nitrochemie G M B H | Process for the production of solid propellants provided with an insulating layer |
DE2004472C1 (en) * | 1970-01-31 | 1979-11-29 | Wasagchemie Gmbh, 8000 Muenchen | Process for applying insulating layers to solid propellants |
US3764420A (en) * | 1971-01-06 | 1973-10-09 | Us Army | Suppression of combustion instability by means of pbi fibers |
BE791854A (en) * | 1971-11-25 | 1973-05-24 | Poudres & Explosifs Ste Nale | SOLID PROPERGOL BLOCKS COMBUSTION INHIBITORS |
CA1056984A (en) * | 1976-01-16 | 1979-06-19 | Her Majesty The Queen In Right Of Canada As Represented By The Minister Of National Defence Of Her Majesty's Canadian Government | Curable binding systems |
JPH08231291A (en) * | 1994-12-27 | 1996-09-10 | Daicel Chem Ind Ltd | Gas generating agent composition |
DE19516528C1 (en) * | 1995-05-05 | 1996-12-12 | Fraunhofer Ges Forschung | Solid composite fuel and process for its manufacture |
-
1999
- 1999-04-19 DE DE19917672A patent/DE19917672A1/en not_active Withdrawn
-
2000
- 2000-04-14 EP EP00108297A patent/EP1046626B1/en not_active Expired - Lifetime
- 2000-04-14 AT AT00108297T patent/ATE273943T1/en not_active IP Right Cessation
- 2000-04-14 DE DE50007431T patent/DE50007431D1/en not_active Expired - Fee Related
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2727402A1 (en) * | 1978-12-29 | 1996-05-31 | Poudres & Explosifs Ste Nale | Propulsion acceleration charge |
DE3643824A1 (en) * | 1986-12-20 | 1988-06-30 | Bayern Chemie Gmbh Flugchemie | Liner layer for lining rocket combustion chambers |
US5762746A (en) * | 1989-08-16 | 1998-06-09 | Thiokol Corporation | Method of internally insulating a propellant combustion chamber |
EP0555008A2 (en) * | 1992-01-29 | 1993-08-11 | Thiokol Corporation | Low smoke rocket motor liner compositions |
Non-Patent Citations (6)
Title |
---|
CHEMICAL ABSTRACTS, vol. 108, no. 4, 25 January 1988, Columbus, Ohio, US; abstract no. 24138a, M. PROEBSTER: "Smokeless combustible insulation for double-basepropellants" page 134; XP002142650 * |
CHEMICAL ABSTRACTS, vol. 122, no. 14, 3 April 1995, Columbus, Ohio, US; abstract no. 164861v, D.C. GUPTA ET AL.: "HTPB-based polyurethanes for inhibition of composite propellants." page 267; XP000665923 * |
CHEMICAL ABSTRACTS, vol. 123, no. 26, 25 December 1995, Columbus, Ohio, US; abstract no. 344937d, S.B. HASKA ET AL.: "Adhesion properties of liner to propellant and metal in HTPB based systems." page 290; XP000663353 * |
Int. Annu. Conf. ICT 1995, 26th(Pyrotechnics), 49/1-49/12 * |
Int. Jahrestag.- Fraunhofer-Inst. Treib- Explosivst. 1987, 18th(Technol. Energ. Mater.), 40/1-40/14 * |
J. APPL. POLYM. SCI., vol. 55, no. 8, 1995, pages 1151 - 1155 * |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20100255317A1 (en) * | 2007-11-01 | 2010-10-07 | Kuraray Co., Ltd. | Polyurethane composition |
Also Published As
Publication number | Publication date |
---|---|
DE19917672A1 (en) | 2000-10-26 |
EP1046626B1 (en) | 2004-08-18 |
DE50007431D1 (en) | 2004-09-23 |
ATE273943T1 (en) | 2004-09-15 |
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