EP3766859B1 - Hypergolic dual fuel system for rocket engines - Google Patents
Hypergolic dual fuel system for rocket engines Download PDFInfo
- Publication number
- EP3766859B1 EP3766859B1 EP20183064.3A EP20183064A EP3766859B1 EP 3766859 B1 EP3766859 B1 EP 3766859B1 EP 20183064 A EP20183064 A EP 20183064A EP 3766859 B1 EP3766859 B1 EP 3766859B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- hypergolic
- component system
- fuel
- group
- methylimidazolium
- 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.)
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- 239000000446 fuel Substances 0.000 title claims description 52
- 230000009977 dual effect Effects 0.000 title 1
- MHAJPDPJQMAIIY-UHFFFAOYSA-N Hydrogen peroxide Chemical compound OO MHAJPDPJQMAIIY-UHFFFAOYSA-N 0.000 claims description 28
- 239000007800 oxidant agent Substances 0.000 claims description 24
- 239000000654 additive Substances 0.000 claims description 20
- 239000002608 ionic liquid Substances 0.000 claims description 13
- 150000001768 cations Chemical class 0.000 claims description 11
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 10
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 10
- -1 imidazolium ions Chemical class 0.000 claims description 9
- IQQRAVYLUAZUGX-UHFFFAOYSA-N 1-butyl-3-methylimidazolium Chemical compound CCCCN1C=C[N+](C)=C1 IQQRAVYLUAZUGX-UHFFFAOYSA-N 0.000 claims description 8
- WWVMHGUBIOZASN-UHFFFAOYSA-N 1-methyl-3-prop-2-enylimidazol-1-ium Chemical compound CN1C=C[N+](CC=C)=C1 WWVMHGUBIOZASN-UHFFFAOYSA-N 0.000 claims description 7
- 239000001257 hydrogen Substances 0.000 claims description 7
- 229910052739 hydrogen Inorganic materials 0.000 claims description 7
- NJMWOUFKYKNWDW-UHFFFAOYSA-N 1-ethyl-3-methylimidazolium Chemical compound CCN1C=C[N+](C)=C1 NJMWOUFKYKNWDW-UHFFFAOYSA-N 0.000 claims description 6
- 125000000391 vinyl group Chemical group [H]C([*])=C([H])[H] 0.000 claims description 6
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 5
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 5
- ZMZDMBWJUHKJPS-UHFFFAOYSA-M Thiocyanate anion Chemical compound [S-]C#N ZMZDMBWJUHKJPS-UHFFFAOYSA-M 0.000 claims description 5
- 230000003197 catalytic effect Effects 0.000 claims description 5
- 229910017052 cobalt Inorganic materials 0.000 claims description 5
- 239000010941 cobalt Substances 0.000 claims description 5
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims description 5
- 229910052802 copper Inorganic materials 0.000 claims description 5
- 239000010949 copper Substances 0.000 claims description 5
- 229910052742 iron Inorganic materials 0.000 claims description 5
- 229910052759 nickel Inorganic materials 0.000 claims description 5
- 150000003567 thiocyanates Chemical class 0.000 claims description 5
- 125000003903 2-propenyl group Chemical group [H]C([*])([H])C([H])=C([H])[H] 0.000 claims description 4
- 150000001450 anions Chemical class 0.000 claims description 4
- 125000000484 butyl group Chemical group [H]C([*])([H])C([H])([H])C([H])([H])C([H])([H])[H] 0.000 claims description 4
- 125000001495 ethyl group Chemical group [H]C([H])([H])C([H])([H])* 0.000 claims description 4
- 125000002496 methyl group Chemical group [H]C([H])([H])* 0.000 claims description 4
- 239000003381 stabilizer Substances 0.000 claims description 4
- RVEJOWGVUQQIIZ-UHFFFAOYSA-N 1-hexyl-3-methylimidazolium Chemical compound CCCCCCN1C=C[N+](C)=C1 RVEJOWGVUQQIIZ-UHFFFAOYSA-N 0.000 claims description 3
- 230000000996 additive effect Effects 0.000 claims description 3
- 150000002431 hydrogen Chemical group 0.000 claims description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 3
- XFXPMWWXUTWYJX-UHFFFAOYSA-N Cyanide Chemical compound N#[C-] XFXPMWWXUTWYJX-UHFFFAOYSA-N 0.000 claims description 2
- 229910002651 NO3 Inorganic materials 0.000 claims description 2
- NHNBFGGVMKEFGY-UHFFFAOYSA-N Nitrate Chemical compound [O-][N+]([O-])=O NHNBFGGVMKEFGY-UHFFFAOYSA-N 0.000 claims description 2
- 150000001540 azides Chemical class 0.000 claims description 2
- 150000004820 halides Chemical class 0.000 claims description 2
- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 claims description 2
- 229910021645 metal ion Inorganic materials 0.000 claims description 2
- GRVDJDISBSALJP-UHFFFAOYSA-N methyloxidanyl Chemical group [O]C GRVDJDISBSALJP-UHFFFAOYSA-N 0.000 claims description 2
- 125000001436 propyl group Chemical group [H]C([*])([H])C([H])([H])C([H])([H])[H] 0.000 claims description 2
- 229910052723 transition metal Inorganic materials 0.000 claims description 2
- 229910001428 transition metal ion Inorganic materials 0.000 claims description 2
- 150000003624 transition metals Chemical class 0.000 claims description 2
- RAXXELZNTBOGNW-UHFFFAOYSA-O Imidazolium Chemical compound C1=C[NH+]=CN1 RAXXELZNTBOGNW-UHFFFAOYSA-O 0.000 claims 1
- 125000004435 hydrogen atom Chemical group [H]* 0.000 claims 1
- 239000003380 propellant Substances 0.000 claims 1
- 238000004904 shortening Methods 0.000 claims 1
- OAKJQQAXSVQMHS-UHFFFAOYSA-N Hydrazine Chemical compound NN OAKJQQAXSVQMHS-UHFFFAOYSA-N 0.000 description 8
- WFPZPJSADLPSON-UHFFFAOYSA-N dinitrogen tetraoxide Chemical compound [O-][N+](=O)[N+]([O-])=O WFPZPJSADLPSON-UHFFFAOYSA-N 0.000 description 6
- GQPLMRYTRLFLPF-UHFFFAOYSA-N Nitrous Oxide Chemical compound [O-][N+]#N GQPLMRYTRLFLPF-UHFFFAOYSA-N 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 4
- 150000001875 compounds Chemical class 0.000 description 4
- 229910002056 binary alloy Inorganic materials 0.000 description 3
- 239000007789 gas Substances 0.000 description 3
- 125000000623 heterocyclic group Chemical group 0.000 description 3
- ZMZDMBWJUHKJPS-UHFFFAOYSA-N hydrogen thiocyanate Natural products SC#N ZMZDMBWJUHKJPS-UHFFFAOYSA-N 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 3
- SIXHYMZEOJSYQH-UHFFFAOYSA-M 1-butyl-3-methylimidazol-3-ium;thiocyanate Chemical compound [S-]C#N.CCCCN1C=C[N+](C)=C1 SIXHYMZEOJSYQH-UHFFFAOYSA-M 0.000 description 2
- VPNMTSAIINVZTK-UHFFFAOYSA-N 1-ethenyl-3-methylimidazol-3-ium Chemical compound C[N+]=1C=CN(C=C)C=1 VPNMTSAIINVZTK-UHFFFAOYSA-N 0.000 description 2
- VASPYXGQVWPGAB-UHFFFAOYSA-M 1-ethyl-3-methylimidazol-3-ium;thiocyanate Chemical compound [S-]C#N.CCN1C=C[N+](C)=C1 VASPYXGQVWPGAB-UHFFFAOYSA-M 0.000 description 2
- MCTWTZJPVLRJOU-UHFFFAOYSA-O 1-methylimidazole Chemical compound CN1C=C[NH+]=C1 MCTWTZJPVLRJOU-UHFFFAOYSA-O 0.000 description 2
- 239000007864 aqueous solution Substances 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- BQVVSSAWECGTRN-UHFFFAOYSA-L copper;dithiocyanate Chemical compound [Cu+2].[S-]C#N.[S-]C#N BQVVSSAWECGTRN-UHFFFAOYSA-L 0.000 description 2
- 238000000354 decomposition reaction Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 125000004433 nitrogen atom Chemical group N* 0.000 description 2
- 239000001272 nitrous oxide Substances 0.000 description 2
- 239000000047 product Substances 0.000 description 2
- VWDWKYIASSYTQR-UHFFFAOYSA-N sodium nitrate Chemical compound [Na+].[O-][N+]([O-])=O VWDWKYIASSYTQR-UHFFFAOYSA-N 0.000 description 2
- DIIIISSCIXVANO-UHFFFAOYSA-N 1,2-Dimethylhydrazine Chemical compound CNNC DIIIISSCIXVANO-UHFFFAOYSA-N 0.000 description 1
- QGJKCEGNUAZATI-UHFFFAOYSA-N 1h-imidazol-1-ium;thiocyanate Chemical class [S-]C#N.C1=C[NH+]=CN1 QGJKCEGNUAZATI-UHFFFAOYSA-N 0.000 description 1
- GRYLNZFGIOXLOG-UHFFFAOYSA-N Nitric acid Chemical compound O[N+]([O-])=O GRYLNZFGIOXLOG-UHFFFAOYSA-N 0.000 description 1
- 125000000217 alkyl group Chemical group 0.000 description 1
- 230000000711 cancerogenic effect Effects 0.000 description 1
- 125000004432 carbon atom Chemical group C* 0.000 description 1
- 231100000315 carcinogenic Toxicity 0.000 description 1
- 239000003054 catalyst Substances 0.000 description 1
- 239000003638 chemical reducing agent Substances 0.000 description 1
- 230000001934 delay Effects 0.000 description 1
- HTHDWDSBYOUAFF-UHFFFAOYSA-N dipotassium;dioxido(oxo)tin;trihydrate Chemical compound O.O.O.[K+].[K+].[O-][Sn]([O-])=O HTHDWDSBYOUAFF-UHFFFAOYSA-N 0.000 description 1
- SFXJSNATBHJIDS-UHFFFAOYSA-N disodium;dioxido(oxo)tin;trihydrate Chemical compound O.O.O.[Na+].[Na+].[O-][Sn]([O-])=O SFXJSNATBHJIDS-UHFFFAOYSA-N 0.000 description 1
- 238000003912 environmental pollution Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000008014 freezing Effects 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- 231100000086 high toxicity Toxicity 0.000 description 1
- 231100001231 less toxic Toxicity 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- HDZGCSFEDULWCS-UHFFFAOYSA-N monomethylhydrazine Chemical compound CNN HDZGCSFEDULWCS-UHFFFAOYSA-N 0.000 description 1
- 150000002978 peroxides Chemical class 0.000 description 1
- 230000000704 physical effect Effects 0.000 description 1
- 239000002244 precipitate Substances 0.000 description 1
- 230000009257 reactivity Effects 0.000 description 1
- 230000000241 respiratory effect Effects 0.000 description 1
- 150000003839 salts Chemical class 0.000 description 1
- 235000010344 sodium nitrate Nutrition 0.000 description 1
- 239000004317 sodium nitrate Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 125000001424 substituent group Chemical group 0.000 description 1
- 231100000331 toxic Toxicity 0.000 description 1
- 230000002588 toxic effect Effects 0.000 description 1
- 231100000419 toxicity Toxicity 0.000 description 1
- 230000001988 toxicity Effects 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06D—MEANS FOR GENERATING SMOKE OR MIST; GAS-ATTACK COMPOSITIONS; GENERATION OF GAS FOR BLASTING OR PROPULSION (CHEMICAL PART)
- C06D5/00—Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets
- C06D5/08—Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets by reaction of two or more liquids
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B47/00—Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosives; Suspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B47/00—Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosives; Suspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase
- C06B47/02—Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosives; Suspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase the components comprising a binary propellant
Definitions
- the present invention relates to a hypergolic two-fuel system for rocket engines according to claim 1, comprising a fuel and an oxidizer, which are provided separately from one another and which can be brought into reaction in a rocket engine by being brought into contact with one another.
- rocket propulsion systems are required not only to reach earth orbit, but also for attitude control and for maneuvering the spacecraft within orbit.
- the orbital drives used for this are based, like all rocket engines, on the recoil principle, whereby three types of orbital drives can be distinguished depending on the fuel used:
- the fuel is a pressurized gas that is expanded by opening a valve and ejected through a nozzle.
- Cold gas engines are therefore based on a purely physical effect and are very simply constructed, but only deliver a comparatively small amount of drive energy.
- the specific impulse of these engines is typically in the range of 70 to 80 s.
- Chemical rocket engines based on single-fuel systems use a chemical compound as fuel that is capable of an exothermic decay reaction.
- the gaseous decomposition products of this decomposition reaction which is normally initiated by a catalyst, are expelled through a nozzle and generate the thrust.
- the specific impulse of such engines is typically in the range of 170 to 250 s.
- the disadvantage is that a heating system is usually required to liquefy the fuels suitable as a single-fuel system or to prevent them from freezing.
- the two-fuel systems relevant for orbital engines are basically hypergol, i.e. the chemical reaction between the fuel and the oxidizer takes place spontaneously when they are brought into contact, without the need for an external ignition source.
- hypergol i.e. the chemical reaction between the fuel and the oxidizer takes place spontaneously when they are brought into contact, without the need for an external ignition source.
- some fuels or oxidizers it may be necessary to add reactive or catalytic additives to enable hypergolic ignition.
- the hypergolic binary systems known from the prior art include hydrazine and / or their derivatives (e.g. monomethylhydrazine and asymmetrical dimethylhydrazine) as fuel, and dinitrogen tetroxide as oxidizer, possibly as a mixture with other nitrogen oxides.
- hydrazine and / or their derivatives e.g. monomethylhydrazine and asymmetrical dimethylhydrazine
- dinitrogen tetroxide as oxidizer, possibly as a mixture with other nitrogen oxides.
- a major disadvantage of these systems is the high toxicity of hydrazine and its derivatives. These are carcinogenic compounds that must be handled with strict safety measures. This causes high costs in production, storage, transport and refueling. Dinitrogen tetroxide is also classified as toxic.
- Sun ET AL, Combustion and flame, vol. 205, pages 441-445 discloses a hypergolic binary system comprising the ionic liquid [AMIM] [SCN] (1-allyl-3-methyl imidazolium thiocyanate) as fuel and fuming nitric acid as oxidizer.
- AMIM ionic liquid
- SCN 1-allyl-3-methyl imidazolium thiocyanate
- the present invention is therefore based on the object of providing a fuel system for rocket engines, in particular for orbital drives, with which the above-mentioned disadvantages can be completely or partially overcome.
- the fuels used in the two-fuel system according to the invention have a significantly lower toxicity compared to hydrazine and its derivatives, so that the potential environmental pollution can also be considerably reduced.
- a decisive advantage, however, results primarily from the fact that the fuels are ionic liquids that have practically no vapor pressure under ambient conditions. This enables problem-free, open handling of these fuels, which simplifies the entire handling compared to hydrazine and reduces the associated costs.
- the fuels used according to the invention ignite in combination with water peroxide as an oxidizer even without the addition of further additives hypergol, whereby an ignition delay of less than 50 ms can be achieved in the so-called drop test.
- this hypergolic behavior in particular is favored by the thiocyanate anion, which acts as a reducing agent on the hydrogen peroxide.
- the cations of the ionic liquids used as fuel are selected according to the invention from five-membered heterocycles with two to four nitrogen atoms, which can be extensively substituted. Particularly preferred are the heterocycles with only two nitrogen atoms, i.e. the imidazolium ions according to the general formula I. A number of substituted imidazolium thiocyanates are commercially available.
- R 2 can also be hydrogen, while R 1 must be an alkyl or alkenyl radical.
- R 1 and R 2 are each independently selected from a methyl group, an ethyl group, a propyl group, a butyl group, a vinyl group and an allyl group.
- the substituents X 1 , X 2 and X 3 on the carbon atoms of the heterocycle in the general formulas I to IV are preferably each hydrogen.
- At least the compounds EMIM thiocyanate and BMIM thiocyanate are currently commercially available.
- the oxidizer of the two-component system according to the invention comprises hydrogen peroxide, advantageously in the form of an aqueous solution. It is preferred here if the oxidizer has a hydrogen peroxide concentration of 70% by weight or more, preferably 98% by weight or more. The highest possible concentration is preferred insofar as this increases both the storage stability and the reactivity of the hydrogen peroxide with the fuel.
- the oxidizer advantageously contains only water, and optionally one or more stabilizers.
- stabilizers can be dispensed with.
- Preferred stabilizers approved for use in rocket fuels are selected from sodium nitrate, potassium stannate trihydrate and sodium stannate trihydrate.
- the two-component systems according to the invention offer the essential advantage that they show a hypergolic ignition behavior when the fuel is brought into contact with the oxidizer even without the addition of further additives.
- the fuel within the scope of the invention comprises one or more additives in order to further shorten the ignition delay when it is brought into contact.
- additives are optionally present in the fuel in a proportion of up to 30% by weight, more preferably up to 10% by weight.
- the additives used according to the invention are preferably catalytic additives which accelerate the reaction of the fuel with the oxidizer.
- the additives are preferably selected from thiocyanates of transition metals, in particular from thiocyanates of manganese, iron, cobalt, nickel and copper.
- the fuel can also comprise a further ionic liquid with a proportion of up to 50% by weight, preferably up to 20% by weight, which contains metal ions.
- a further ionic liquid with a proportion of up to 50% by weight, preferably up to 20% by weight, which contains metal ions.
- Such compounds also act as catalytic additives.
- the further ionic liquid preferably comprises a complexed transition metal ion as the anion, preferably a halide, cyanide, nitrate, tetrahydroborate, azide, dicarbide or methyloxy complex of iron, cobalt, nickel or copper.
- a complexed transition metal ion as the anion preferably a halide, cyanide, nitrate, tetrahydroborate, azide, dicarbide or methyloxy complex of iron, cobalt, nickel or copper.
- BMIM tetrachloroferrate anion such as BMIM tetrachloroferrate
- the hypergolic fuel system according to the invention is characterized by a short ignition delay when the fuel is brought into contact with the oxidizer.
- This ignition delay in the drop test is preferably less than 50 ms, more preferably less than 20 ms.
- the present invention also relates to the use of the hypergolic two-fuel system according to the invention as fuel in a rocket engine, in particular in an orbital drive.
- the possible use is not limited to orbital drives, but in principle encompasses all areas of application of rocket engines.
- the respective fuel is placed in an open vessel in an amount of 1 ml.
- a drop of a 96% strength by weight aqueous hydrogen peroxide solution with a volume of 50 ⁇ l as an oxidizer is dropped onto the fuel from a height of 80 mm.
- the ignition delay is determined, which is defined as the time between the first contact of the fuel with the oxidizer and the first appearance of a flame.
- the measured ignition delays are given in the following table. In each case, it is the mean value with standard deviation from the number of experiments given in brackets: Ignition delay without addition + 6% Cu-SCN + 30% BMIM-FeCl 4 BMIM-SCN 45.1 ⁇ 1.7 ms (7) 18.5 ⁇ 0.7 ms (6) 20.5 ⁇ 2.0 ms (5) EMIM-SCN 28.8 ⁇ 2.9 ms (21) 12.0 ⁇ 0.1 ms (5) -
- the ignition delay of the two-component system according to the invention can be further reduced, so that values below 20 ms are preferably achieved.
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- Chemical & Material Sciences (AREA)
- Organic Chemistry (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Liquid Carbonaceous Fuels (AREA)
Description
Die vorliegende Erfindung betrifft ein hypergoles Zweistoffsystem für Raketentriebwerke gemäß Anspruch 1, umfassend einen Brennstoff- und einen Oxidator, die getrennt voneinander bereitgestellt werden und die in einem Raketentriebwerk durch Inkontaktbringen miteinander zur Reaktion gebracht werden können. Bei Raumfahrzeugen werden Raketenantriebe nicht nur zum Erreichen einer Erdumlaufbahn (Orbit) benötigt, sondern auch zur Lagesteuerung und zum Manövrieren des Raumfahrzeuges innerhalb des Orbits. Die hierfür eingsetzten Orbitalantriebe basieren, wie alle Raketentriebwerke, auf dem Rückstoßprinzip, wobei in Abhängigkeit vom verwendeten Treibstoff drei Typen von Orbitaltriebwerken unterschieden werden können:
Bei Kaltgastriebwerken ist der Treibstoff ein unter Druck stehendes Gas, dass durch Öffnen eines Ventils entspannt und über eine Düse ausgestoßen wird. Kaltgastriebwerke basieren somit auf einem reinen physikalischen Effekt und sind sehr einfach aufgebaut, liefern aber nur eine vergleichsweise geringe Antriebsenergie. Der spezifische Impuls dieser Triebwerke liegt typischerweise im Bereich von 70 bis 80 s.The present invention relates to a hypergolic two-fuel system for rocket engines according to claim 1, comprising a fuel and an oxidizer, which are provided separately from one another and which can be brought into reaction in a rocket engine by being brought into contact with one another. In spacecraft, rocket propulsion systems are required not only to reach earth orbit, but also for attitude control and for maneuvering the spacecraft within orbit. The orbital drives used for this are based, like all rocket engines, on the recoil principle, whereby three types of orbital drives can be distinguished depending on the fuel used:
In cold gas engines, the fuel is a pressurized gas that is expanded by opening a valve and ejected through a nozzle. Cold gas engines are therefore based on a purely physical effect and are very simply constructed, but only deliver a comparatively small amount of drive energy. The specific impulse of these engines is typically in the range of 70 to 80 s.
Chemische Raketentriebwerke auf der Basis von Einstoffsystemen nutzen eine chemische Verbindung als Treibstoff, die zu einer exothermen Zerfallsreaktion in der Lage ist. Die gasförmigen Zerfallsprodukte dieser Zerfallsreaktion, die normalerweise durch einen Katalysator eingeleitet wird, werden durch eine Düse ausgestoßen und erzeugen den Schub. Der spezifische Impuls solcher Triebwerke liegt typischerweise im Bereich von 170 bis 250 s. Nachteilig ist, dass in der Regel ein Heizungssystem benötigt wird, um die als Einstoffsystem geeigneten Treibstoffe zu verflüssigen bzw. ein Einfrieren zu verhindern.Chemical rocket engines based on single-fuel systems use a chemical compound as fuel that is capable of an exothermic decay reaction. The gaseous decomposition products of this decomposition reaction, which is normally initiated by a catalyst, are expelled through a nozzle and generate the thrust. The specific impulse of such engines is typically in the range of 170 to 250 s.The disadvantage is that a heating system is usually required to liquefy the fuels suitable as a single-fuel system or to prevent them from freezing.
Die größte Bedeutung bei Orbitalantrieben, insbesondere für größere Raumfahrzeuge, haben hypergole Zweistoffsysteme. Diese umfassen als Treibstoffsystem einen flüssigen Brennstoff und einen flüssigen Oxidator, die exotherm miteinander reagieren und gasförmige Verbrennungsprodukte zur Erzeugung des Schubes freisetzen. Die Energiedichte eines Zweistoffsystems aus Brennstoff und Oxidator ist im Vergleich zu Einstoffsystemen generell höher, so dass ein spezifischer Impuls im Bereich von 270 bis 320 s erreicht werden kann. Zudem ist keine Heizung erforderlich, da die verwendbaren Komponenten über einen weiten Temperaturbereich in flüssiger Form vorliegen.The greatest importance in orbital drives, especially for larger space vehicles, are hypergolic binary systems. As a fuel system, these comprise a liquid fuel and a liquid oxidizer, which react exothermically with one another and release gaseous combustion products to generate the thrust. The energy density of a two-component system consisting of fuel and oxidizer is generally higher compared to single-component systems, so that a specific pulse in the range of 270 to 320 s can be achieved. In addition, no heating is required, since the components that can be used are in liquid form over a wide temperature range.
Die für Orbitaltriebwerke relevanten Zweistoffsysteme sind grundsätzlich hypergol, d.h. die chemische Reaktion zwischen dem Brennstoff und dem Oxidator erfolgt beim Inkontaktbringen spontan, ohne dass eine externe Zündquelle notwendig wäre. Allerdings kann bei manchen Brennstoffen oder Oxidatoren ein Zusatz von reaktiven oder katalytischen Additiven notwendig sein, um die hypergole Zündung zu ermöglichen.The two-fuel systems relevant for orbital engines are basically hypergol, i.e. the chemical reaction between the fuel and the oxidizer takes place spontaneously when they are brought into contact, without the need for an external ignition source. However, with some fuels or oxidizers it may be necessary to add reactive or catalytic additives to enable hypergolic ignition.
Die aus dem Stand der Technik bekannten hypergolen Zweistoffsysteme umfassen als Brennstoff Hydrazin und/oder deren Derivate (z.B. Monomethylhydrazin und unsymmetrisches Dimethylhydrazin), sowie als Oxidator Distickstofftetroxid, ggf. als Mischung mit weiteren Stickstoffoxiden. Ein wesentlicher Nachteil dieser Systeme ist die hohe Giftigkeit von Hydrazin und dessen Derivaten. Es handelt sich um karzinogene Verbindungen, bei deren Handhabung strenge Sicherheitsmaßnahmen eingehalten werden müssen. Dies verursacht hohe Kosten bei der Herstellung, Lagerung, Transport und Betankung. Auch Distickstofftretroxid wird als giftig eingestuft.The hypergolic binary systems known from the prior art include hydrazine and / or their derivatives (e.g. monomethylhydrazine and asymmetrical dimethylhydrazine) as fuel, and dinitrogen tetroxide as oxidizer, possibly as a mixture with other nitrogen oxides. A major disadvantage of these systems is the high toxicity of hydrazine and its derivatives. These are carcinogenic compounds that must be handled with strict safety measures. This causes high costs in production, storage, transport and refueling. Dinitrogen tetroxide is also classified as toxic.
Der vorliegenden Erfindung liegt daher die Aufgabe zugrunde, ein Treibstoffsystem für Raketentriebwerke, insbesondere für Orbitalantriebe, zur Verfügung zu stellen, mit dem die oben genannten Nachteile ganz oder teilweise überwunden werden können.The present invention is therefore based on the object of providing a fuel system for rocket engines, in particular for orbital drives, with which the above-mentioned disadvantages can be completely or partially overcome.
Diese Aufgabe wird bei dem hypergolen Zweistoffsystem der eingangs genannten Art erfindungsgemäß dadurch gelöst, dass der Brennstoff eine ionische Flüssigkeit ist, die aus einem Thiocyanat-Anion und einem oder mehreren Kationen gebildet ist,
wobei das oder die Kationen ausgewählt sind aus einem oder mehreren Imidazolium-Ionen mit der allgemeinen Formel I, Triazolium-Ionen mit der allgemeinen Formel II oder III, und/oder Tetrazolium-Ionen mit der allgemeinen Formel IV:
- wobei R2 Wasserstoff oder ein C1- bis C6-Alkylrest oder ein C2- bis C6-Alkenylrest ist, und
- wobei X1, X2 und X3 jeweils unabhängig voneinander Wasserstoff, ein C1- bis C6-Alkylrest oder ein C2- bis C6-Alkenylrest sind; und dass
- der Oxidator Wasserstoffperoxid umfasst.
where the cation or cations are selected from one or more imidazolium ions with the general formula I, triazolium ions with the general formula II or III, and / or tetrazolium ions with the general formula IV:
- where R 2 is hydrogen or a C 1 - to C 6 -alkyl radical or a C 2 - to C 6 -alkenyl radical, and
- where X 1 , X 2 and X 3 are each, independently of one another, hydrogen, a C 1 - to C 6 -alkyl radical or a C 2 - to C 6 -alkenyl radical; and that
- the oxidizer comprises hydrogen peroxide.
Die in dem erfindungsgemäßen Zweistoffsystem verwendeten Brennstoffe weisen im Vergleich zu Hydrazin und dessen Derivaten eine deutlich geringere Toxizität auf, so dass auch die potentielle Umweltbelastung erheblich verringert werden kann. Ein entscheidender Vorteil ergibt sich aber vor allem durch die Tatsache, dass es sich bei den Brennstoffen um ionische Flüssigkeiten handelt, die bei Umgebungsbedingungen praktisch keinen Dampfdruck aufweisen. Somit ist ein problemloser, offener Umgang mit diesen Brennstoffen möglich, was die gesamte Handhabung im Vergleich zu Hydrazin vereinfacht und die damit verbundenen Kosten reduziert.The fuels used in the two-fuel system according to the invention have a significantly lower toxicity compared to hydrazine and its derivatives, so that the potential environmental pollution can also be considerably reduced. A decisive advantage, however, results primarily from the fact that the fuels are ionic liquids that have practically no vapor pressure under ambient conditions. This enables problem-free, open handling of these fuels, which simplifies the entire handling compared to hydrazine and reduces the associated costs.
Ähnliche Vorteile ergeben sich gemäß der Erfindung auch durch das als Oxidator eingesetzte Wasserstoffperoxid. Dieses ist nicht nur wesentlich weniger toxisch als Distickstofftetroxid, sondern hat auch einen wesentlich geringeren Dampfdruck (Distickstofftetroxid siedet bereits bei 21 °C). Während ein offener Umgang mit Distickstofftetroxid nur unter Atemschutz möglich ist, kann Wasserstoffperoxid, sowohl in reiner Form als auch in wässriger Lösung, relativ unproblematisch gehandhabt werden.According to the invention, similar advantages also result from the hydrogen peroxide used as the oxidizer. This is not only significantly less toxic than nitrous oxide, but also has a significantly lower vapor pressure (nitrous oxide already boils at 21 ° C). While dinitrogen tetroxide can only be handled openly with respiratory protection, hydrogen peroxide, both in its pure form and in an aqueous solution, can be handled relatively unproblematically.
Zweistoffsysteme für Raketentriebwerke, die auf Wasserstoffperoxid als Oxidator und ionischen Flüssigkeiten als Brennstoff basieren, wurden bereits beschrieben, beispielsweise in der
Überraschenderweise zünden die erfindungsgemäß eingesetzten Brennstoffe in Kombination mit Wasserperoxid als Oxidator bereits ohne den Zusatz weiterer Additive hypergol, wobei im sogenannten Tropftest ein Zündverzug von weniger als 50 ms erreicht werden kann. Ohne an eine bestimmte Theorie gebunden zu sein, wird davon ausgegangen, dass dieses hypergole Verhalten insbesondere durch das Thiocyanat-Anion begünstigt wird, welches als Reduktionsmittel auf das Wasserstoffperoxid wirkt.Surprisingly, the fuels used according to the invention ignite in combination with water peroxide as an oxidizer even without the addition of further additives hypergol, whereby an ignition delay of less than 50 ms can be achieved in the so-called drop test. Without being bound by any particular theory, it is assumed that this hypergolic behavior in particular is favored by the thiocyanate anion, which acts as a reducing agent on the hydrogen peroxide.
Die Kationen der als Brennstoff eingesetzten ionischen Flüssigkeiten sind erfindungsgemäß ausgewählt aus fünfgliedrigen Heterocyclen mit zwei bis vier Stickstoffatomen, die umfangreich substituiert sein können. Besonders bevorzugt sind dabei die Heterocyclen mit nur zwei Stickstoffatomen, d.h. die Imidazolium-Ionen gemäß der allgemeinen Formel I. Eine Reihe von substituierten Imidazolium-Thiocyanaten sind kommerziell erhältlich.The cations of the ionic liquids used as fuel are selected according to the invention from five-membered heterocycles with two to four nitrogen atoms, which can be extensively substituted. Particularly preferred are the heterocycles with only two nitrogen atoms, i.e. the imidazolium ions according to the general formula I. A number of substituted imidazolium thiocyanates are commercially available.
In den allgemeinen Formeln I bis IV kann R2 auch Wasserstoff sein, während R1 ein Alkyl- oder Alkenylrest sein muss. Vorzugsweise sind R1 und R2 jeweils unabhängig voneinander ausgewählt aus einer Methylgruppe, einer Ethylgruppe, einer Propylgruppe, einer Butylgruppe, einer Vinylgruppe und einer Allylgruppe.In the general formulas I to IV, R 2 can also be hydrogen, while R 1 must be an alkyl or alkenyl radical. Preferably, R 1 and R 2 are each independently selected from a methyl group, an ethyl group, a propyl group, a butyl group, a vinyl group and an allyl group.
Besonders bevorzugt sind solche Kationen der ionischen Flüssigkeit, bei denen R1 eine Methylgruppe oder eine Vinylgruppe ist, und/oder bei denen R2 eine Ethylgruppe, eine Butylgruppe, eine Vinylgruppe oder eine Allylgruppe ist.Those cations of the ionic liquid in which R 1 is a methyl group or a vinyl group and / or in which R 2 is an ethyl group, a butyl group, a vinyl group or an allyl group are particularly preferred.
Die Substituenten X1, X2 und X3 an den Kohlenstoffatomen des Heterocyclus in den allgemeinen Formeln I bis IV sind vorzugsweise jeweils Wasserstoff.The substituents X 1 , X 2 and X 3 on the carbon atoms of the heterocycle in the general formulas I to IV are preferably each hydrogen.
Besonders bevorzugt im Rahmen der Erfindung sind die Thiocyanat-Salze folgender Kationen als Brennstoff:
- 3-Methylimidazolium (HMIM):
- 1-Ethyl-3-methylimidazolium (EMIM):
- 1-Butyl-3-methylimidazolium (BMIM):
- 1-Allyl-3-methylimidazolium (AMIM):
- 1-Vinyl-3-methylimidazolium (VMIM):
- 1-Allyl-3-vinylimidazolium (AVIM):
- 3-methylimidazolium (HMIM):
- 1-Ethyl-3-methylimidazolium (EMIM):
- 1-Butyl-3-methylimidazolium (BMIM):
- 1-Allyl-3-methylimidazolium (AMIM):
- 1-vinyl-3-methylimidazolium (VMIM):
- 1-Allyl-3-vinylimidazolium (AVIM):
Zumindest die Verbindungen EMIM-Thiocyanat und BMIM-Thiocyanat sind derzeit kommerziell erhältlich.At least the compounds EMIM thiocyanate and BMIM thiocyanate are currently commercially available.
Der Oxidator des erfindungsgemäßen Zweistoffsystems umfasst Wasserstoffperoxid, günstigerweise in Form einer wässrigen Lösung. Dabei ist es bevorzugt, wenn der Oxidator eine Konzentration an Wasserstoffperoxid von 70 Gew.% oder mehr aufweist, bevorzugt von 98 Gew.% oder mehr. Eine möglichst hohe Konzentration ist insofern bevorzugt, als dies sowohl die Lagerstabilität als auch die Reaktivität des Wasserstoffperoxids mit dem Brennstoff erhöht.The oxidizer of the two-component system according to the invention comprises hydrogen peroxide, advantageously in the form of an aqueous solution. It is preferred here if the oxidizer has a hydrogen peroxide concentration of 70% by weight or more, preferably 98% by weight or more. The highest possible concentration is preferred insofar as this increases both the storage stability and the reactivity of the hydrogen peroxide with the fuel.
Günstigerweise enthält der Oxidator neben Wasserstoffperoxid nur Wasser, und optional einen oder mehrere Stabilisatoren. Bei annähernd reinem Wasserstoffperoxid kann auf Stabilisatoren verzichtet werden. Bevorzugte Stabilisatoren, die zur Verwendung in Raketentreibstoffen zugelassen sind, sind ausgewählt aus Natriumnitrat, Kaliumstannat-Trihydrat und Natriumstannat-Trihydrat.In addition to hydrogen peroxide, the oxidizer advantageously contains only water, and optionally one or more stabilizers. With almost pure hydrogen peroxide, stabilizers can be dispensed with. Preferred stabilizers approved for use in rocket fuels are selected from sodium nitrate, potassium stannate trihydrate and sodium stannate trihydrate.
Wie bereits erwähnt, bieten die erfindungsgemäßen Zweistoffsysteme den wesentlichen Vorteil, dass sie auch ohne den Zusatz weiterer Additive ein hypergoles Zündverhalten beim Inkontaktbringen des Brennstoffs mit dem Oxidator zeigen. Dies schließt allerdings nicht die Möglichkeit aus, dass der Brennstoff im Rahmen der Erfindung ein oder mehrere Additive umfasst, um den Zündverzug beim Inkontaktbringen weiter zu verkürzen. Solche Additive sind gegebenenfalls mit einem Anteil von bis zu 30 Gew.% in dem Brennstoff enthalten, weiter bevorzugt bis zu 10 Gew.%.As already mentioned, the two-component systems according to the invention offer the essential advantage that they show a hypergolic ignition behavior when the fuel is brought into contact with the oxidizer even without the addition of further additives. However, this does not rule out the possibility that the fuel within the scope of the invention comprises one or more additives in order to further shorten the ignition delay when it is brought into contact. Such additives are optionally present in the fuel in a proportion of up to 30% by weight, more preferably up to 10% by weight.
Die erfindungsgemäß eingesetzten Additive sind vorzugsweise katalytische Additive, die die Reaktion des Brennstoffs mit dem Oxidator beschleunigen. Bevorzugt sind die Additive ausgewählt aus Thiocyanaten von Übergangsmetallen, insbesondere aus Thiocyanaten von Mangan, Eisen, Cobalt, Nickel und Kupfer.The additives used according to the invention are preferably catalytic additives which accelerate the reaction of the fuel with the oxidizer. The additives are preferably selected from thiocyanates of transition metals, in particular from thiocyanates of manganese, iron, cobalt, nickel and copper.
Alternativ oder zusätzlich kann der Brennstoff auch eine weitere ionische Flüssigkeit mit einem Anteil von bis zu 50 Gew.%, bevorzugt bis zu 20 Gew.%, umfassen, welche Metallionen enthält. Derartige Verbindungen wirken ebenfalls als katalytische Additive.As an alternative or in addition, the fuel can also comprise a further ionic liquid with a proportion of up to 50% by weight, preferably up to 20% by weight, which contains metal ions. Such compounds also act as catalytic additives.
Die weitere ionische Flüssigkeit umfasst als Anion bevorzugt ein komplexiertes Übergangsmetallion, bevorzugt einen Halogenid-, Cyanid-, Nitrat-, Tetrahydroborat-, Azid-, Dicarbid- oder Methyloxy-Komplex von Eisen, Cobalt, Nickel oder Kupfer.The further ionic liquid preferably comprises a complexed transition metal ion as the anion, preferably a halide, cyanide, nitrate, tetrahydroborate, azide, dicarbide or methyloxy complex of iron, cobalt, nickel or copper.
Besonders günstig ist der Zusatz einer weiteren ionischen Flüssigkeit, die ein Tetrachloroferrat-Anion umfasst, wie z.B. BMIM-Tetrachloroferrat.It is particularly advantageous to add another ionic liquid that includes a tetrachloroferrate anion, such as BMIM tetrachloroferrate.
Das erfindungsgemäße hypergole Treibstoffsystem zeichnet sich durch einen kurzen Zündverzug beim Inkontaktbringen des Brennstoffs mit dem Oxidator aus. Bevorzugt beträgt dieser Zündverzug im Tropftest weniger als 50 ms, weiter bevorzugt weniger als 20 ms.The hypergolic fuel system according to the invention is characterized by a short ignition delay when the fuel is brought into contact with the oxidizer. This ignition delay in the drop test is preferably less than 50 ms, more preferably less than 20 ms.
Die vorliegende Erfindung betrifft ferner die Verwendung des erfindungsgemäßen hypergolen Zweistoffsystems als Treibstoff in einem Raketentriebwerk, insbesondere in einem Orbitalantrieb. Die mögliche Verwendung ist jedoch nicht auf Orbitalantriebe beschränkt, sondern umfasst prinzipiell alle Einsatzbereiche von Raketentriebwerken.The present invention also relates to the use of the hypergolic two-fuel system according to the invention as fuel in a rocket engine, in particular in an orbital drive. However, the possible use is not limited to orbital drives, but in principle encompasses all areas of application of rocket engines.
Die nachfolgenden Beispiele dienen der näheren Erläuterung der Erfindung, ohne diese in irgendeiner Weise zu beschränken.The following examples serve to explain the invention in more detail without restricting it in any way.
Zur Bestimmung des Zündverzugs bei verschiedenen erfindungsgemäßen Zweistoffsystemen wird der jeweilige Brennstoff in einer Menge von 1 ml in einem offenen Gefäß vorgelegt. Ein Tropfen einer 96 Gew.%igen wässrigen Wasserstoffperoxidlösung mit einem Volumen von 50 µl als Oxidator wird aus einer Höhe von 80 mm auf den Brennstoff fallen gelassen. Mit Hilfe einer Kamera wird der Zündverzug bestimmt, der definiert ist als die Zeit zwischen dem ersten Kontakt des Brennstoffs mit dem Oxidator und dem ersten Erscheinen einer Flamme.To determine the ignition delay in various two-component systems according to the invention, the respective fuel is placed in an open vessel in an amount of 1 ml. A drop of a 96% strength by weight aqueous hydrogen peroxide solution with a volume of 50 μl as an oxidizer is dropped onto the fuel from a height of 80 mm. With the help of a camera, the ignition delay is determined, which is defined as the time between the first contact of the fuel with the oxidizer and the first appearance of a flame.
Als Beispiele für verschiedene erfindungsgemäße Zweistoffsysteme wurden im Tropftest folgende Brennstoffe untersucht:
- 1-Butyl-3-methylimidazolium-thiocyanat (BMIM-SCN), sowohl ohne Zusätze als auch mit 6 Gew.% Kupferthiocyanat oder mit 30 Gew.% BMIM-Tetrachloroferrat als Additiv
- 1-Ethyl-3-methylimidazolium-thiocyanat (EMIM-SCN), sowohl ohne Zusätze als auch mit 6 Gew.% Kupferthiocyanat als Additiv
- 1-Butyl-3-methylimidazolium thiocyanate (BMIM-SCN), both without additives and with 6% by weight of copper thiocyanate or with 30% by weight of BMIM tetrachloroferrate as an additive
- 1-Ethyl-3-methylimidazolium thiocyanate (EMIM-SCN), both without additives and with 6% by weight of copper thiocyanate as an additive
Die gemessenen Zündverzüge sind in der folgenden Tabelle angegeben. Es handelt sich jeweils um den Mittelwert mit Standardabweichung aus der in Klammern angegebenen Anzahl an Versuchen:
Die Versuche zeigen, dass sowohl mit BMIM-SCN als auch mit EMIM-SCN als Brennstoff ohne weitere Zusätze ein Zündverzug von deutlich weniger als 50 ms erreicht wird, was in der Praxis ein ausreichend schnelles Zündverhalten für ein hypergoles Zweistoffsystem darstellt.The tests show that both with BMIM-SCN and with EMIM-SCN as fuel, without further additives, an ignition delay of significantly less than 50 ms is achieved, which in practice represents a sufficiently fast ignition behavior for a hypergolic dual-fuel system.
Durch den Zusatz von verschiedenen katalytischen Additiven kann der Zündverzug des erfindungsgemäßen Zweistoffsystems weiter reduziert werden, so dass bevorzugt Werte unterhalb von 20 ms erreicht werden.By adding various catalytic additives, the ignition delay of the two-component system according to the invention can be further reduced, so that values below 20 ms are preferably achieved.
Claims (15)
- A hypergolic two-component system for rocket engines, including a fuel and an oxidising agent that are provided in a manner separated from one another and can be reacted in a rocket engine by bringing them into contact with one another,
characterised in that- the fuel is an ionic liquid comprising a thiocyanate anion and one or more cations,
wherein the cation or cations are selected from one or more imidazolium ions of the general formula I, triazolium ions of the general formula II or III, and/or tetrazolium ions of the general formula IV:
where X1, X2 and X3 are each independently hydrogen, a C1- to C6-alkyl radical or a C2- to C6-alkenyl radical; and in that- the oxidising agent comprises hydrogen peroxide. - The hypergolic two-component system according to claim 1, wherein the cation is an imidazolium ion of the general formula I.
- The hypergolic two-component system according to one of the preceding claims, wherein R1 and R2 are each independently selected from a methyl group, an ethyl group, a propyl group, a butyl group, a vinyl group and an allyl group.
- The hypergolic two-component system according to one of the preceding claims, wherein R1 is a methyl group or a vinyl group.
- The hypergolic two-component system according to one of the preceding claims, wherein R2 is an ethyl group, a butyl group, a vinyl group or an allyl group.
- The hypergolic two-component system according to one of the preceding claims, wherein X1, X2 and X3 are each hydrogen.
- The hypergolic two-component system according to one of the preceding claims, wherein the fuel comprises one or more of the following cations:- 3-methylimidazolium (HMIM),- 1-ethyl-3-methylimidazolium (EMIM),- 1-butyl-3-methylimidazolium (BMIM),- 1-allyl-3-methylimidazolium (AMIM),- 1-vinyl-3-methylimidazolium (VMIM),- 1-allyl-3-vinylimidazolium (AVIM).
- The hypergolic two-component system according to one of the preceding claims, wherein the oxidising agent has a concentration of hydrogen peroxide of 70 weight% or above, preferably 98 weight% or above.
- The hypergolic two-component system according to one of the preceding claims, wherein besides hydrogen peroxide the oxidising agent contains only water and, optionally, one or more stabilisers.
- The hypergolic two-component system according to one of the preceding claims, wherein the fuel comprises one or more additives for the purpose of shortening the ignition delay when it is brought into contact with the oxidising agent, with a proportion of up to 30 weight%, preferably up to 10 weight%.
- The hypergolic two-component system according to claim 10, wherein the additive or additives are catalytic additives that are preferably selected from thiocyanates of transition metals, in particular thiocyanates of manganese, iron, cobalt, nickel and copper.
- The hypergolic two-component system according to one of the preceding claims, wherein the fuel comprises a further ionic liquid in a proportion of up to 50 weight%, preferably up to 20 weight%, wherein the further ionic liquid contains metal ions.
- The hypergolic two-component system according to claim 12, wherein the further ionic liquid comprises as an anion a transition metal ion complex, preferably a halide, cyanide, nitrate, tetrahydroborate, azide, dicarbide or methyloxy complex of iron, cobalt, nickel or copper.
- The hypergolic two-component system according to one of the preceding claims, wherein, when the fuel is brought into contact with the oxidising agent in the dripping test, the system has an ignition delay of less than 50 ms, preferably less than 20 ms.
- Use of a hypergolic two-component system according to one of the preceding claims as a propellant in a rocket engine, in particular in an orbital propulsion device.
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