EP3766859B1 - Hypergoles zweistoffsystem für raketentriebwerke - Google Patents
Hypergoles zweistoffsystem für raketentriebwerke 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.)
- Active
Links
- 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.
Landscapes
- Chemical & Material Sciences (AREA)
- Organic Chemistry (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Liquid Carbonaceous Fuels (AREA)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PL20183064T PL3766859T3 (pl) | 2019-07-19 | 2020-06-30 | Hipergoliczny układ dwuskładnikowy do rakietowych zespołów napędowych |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102019119598.5A DE102019119598B4 (de) | 2019-07-19 | 2019-07-19 | Hypergoles Zweistoffsystem für Raketentriebwerke |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP3766859A1 EP3766859A1 (de) | 2021-01-20 |
| EP3766859B1 true EP3766859B1 (de) | 2021-09-29 |
Family
ID=71409131
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP20183064.3A Active EP3766859B1 (de) | 2019-07-19 | 2020-06-30 | Hypergoles zweistoffsystem für raketentriebwerke |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US11897826B2 (pt) |
| EP (1) | EP3766859B1 (pt) |
| DE (1) | DE102019119598B4 (pt) |
| ES (1) | ES2895390T3 (pt) |
| PL (1) | PL3766859T3 (pt) |
| PT (1) | PT3766859T (pt) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102021118007A1 (de) | 2021-07-13 | 2023-01-19 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Hypergoles Zweistoffsystem für Hybridraketentriebwerke |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8034202B1 (en) * | 2007-10-04 | 2011-10-11 | The United States Of America As Represented By The Secretary Of The Air Force | Hypergolic fuels |
| US9090519B1 (en) * | 2010-06-17 | 2015-07-28 | The United States Of America As Represented By The Secretary Of The Airforce | Green hypergolic fuels |
| US8758531B1 (en) | 2011-03-15 | 2014-06-24 | The United States Of America As Represented By The Secretary Of The Air Force | Catalytic hypergolic bipropellants |
-
2019
- 2019-07-19 DE DE102019119598.5A patent/DE102019119598B4/de not_active Expired - Fee Related
-
2020
- 2020-06-30 EP EP20183064.3A patent/EP3766859B1/de active Active
- 2020-06-30 PL PL20183064T patent/PL3766859T3/pl unknown
- 2020-06-30 PT PT201830643T patent/PT3766859T/pt unknown
- 2020-06-30 ES ES20183064T patent/ES2895390T3/es active Active
- 2020-07-02 US US16/946,729 patent/US11897826B2/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| PL3766859T3 (pl) | 2022-02-14 |
| DE102019119598A1 (de) | 2021-01-21 |
| ES2895390T3 (es) | 2022-02-21 |
| DE102019119598B4 (de) | 2021-10-07 |
| EP3766859A1 (de) | 2021-01-20 |
| US20210017097A1 (en) | 2021-01-21 |
| US20210355046A9 (en) | 2021-11-18 |
| US11897826B2 (en) | 2024-02-13 |
| PT3766859T (pt) | 2021-10-28 |
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