EP2620422B1 - Nouveaux monergols ioniques à base de N2O pour la propulsion spatiale - Google Patents

Nouveaux monergols ioniques à base de N2O pour la propulsion spatiale Download PDF

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EP2620422B1
EP2620422B1 EP13152595.8A EP13152595A EP2620422B1 EP 2620422 B1 EP2620422 B1 EP 2620422B1 EP 13152595 A EP13152595 A EP 13152595A EP 2620422 B1 EP2620422 B1 EP 2620422B1
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triazolium
nitrate
dicyanamide
fuel
ammonium
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EP2620422A1 (fr
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Nicolas Pelletier
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Centre National dEtudes Spatiales CNES
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    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B43/00—Compositions characterised by explosive or thermic constituents not provided for in groups C06B25/00 - C06B41/00
    • 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

Definitions

  • the chemical propulsion of the satellites is generally ensured by the decomposition or the combustion of propellants thus producing gases with very high temperature and very high pressure.
  • the propellants may be monergols or bergols.
  • hydrazine and its methylated derivatives pose significant risks in terms of manufacturing, handling and operations because of their sensitivity to impurities and, to a lesser extent, to temperature and their extreme toxicity. . These constraints generate cumbersome operating procedures and high implementation costs.
  • hydrazine is currently on the list of compounds listed by REACh (European Chemical Regulation), because of its dangerousness (carcinogenic substance, mutagenic or toxic, persistent, biaccumulable or toxic). In fact, a potential progressive ban on hydrazine and its derivatives is to be expected and its substitution may be necessary in the near future.
  • the patent application WO0050363 discloses a formulation based on the dinitramide anion (N (NO 2 ) 2 - ) associated with an energetic cation - preferably ammonium (NH 4 + ), hydrazinium (N 2 H 5 + ) or hydroxylammonium (OHNH 3 + ), ammonium being preferred - the salt formed being dissolved in an aqueous reducing solution or not.
  • the liquid reductant can thus serve as a solvent or be in equilibrium with a water fraction so as to form a liquid ionic energy solution.
  • the reducing agent may in particular be chosen from alcohols, amines, aldehydes or ketones, a large polarity being sought in order to promote the solubility of the energetic salt.
  • Patent applications WO01 / 51433 and WO2009 / 062183 teach as liquid monolols mixtures of nitrous oxide (N 2 O) as an oxidant and hydrocarbon fuel, such as propane (C 3 H 8 ) or ethane (C 2 H) 6 ), ethylene (C 2 H 4 ), acetylene (C 2 H 2 ).
  • the choice of nitrous oxide as oxidant is motivated by its very good oxidizing power and by its volatile nature offering the possibility of a self-pressurization of the tank.
  • the binary N 2 O / hydrocarbon formed mixture has a high saturation vapor pressure (38 bar at 10 ° C for the monergol NOFB34) and very sensitive to the temperature (48 bar at 20 ° C for the same monergol), which, on the one hand, requires qualified equipment for a higher operating pressure than those currently encountered and, on the other hand, makes its thermal control continuously delicate.
  • the energy density of these mixtures remains to be improved in particular because of their density sometimes less than 700 kg.m -3 .
  • the subject of the present invention is therefore a monergol based on nitrous oxide which does not have the disadvantages stated above, and in particular instability.
  • the problem related to the sensitivity of the mixture has been solved by generating a monergol in which the fuel is, in its isolated form, an energetic salt. Its dissolution in the nitrous oxide generates an ionic liquid phase. Due to its reduced saturated vapor pressure, the fuel is fixed in the liquid phase, so that the vapor phase coexisting with the liquid contains only nitrous oxide.
  • the density of monergols thus formed is high thanks to the contribution of salt, thus guaranteeing a high energy density.
  • the salts used have enthalpies of formation and structures such that their association with nitrous oxide provides theoretical Isp between 300s and 350s depending on the candidates.
  • Nitrous oxide N 2 O molar mass 44.013 kg mol -1
  • N 2 O molar mass 44.013 kg mol -1
  • Its saturation vapor pressure (the pressure at which the gas phase is in equilibrium with its liquid phase) varies in the range [0 +20] ° C between 31.3 bar and 50.6 bar. Over the same interval, the density of its liquid phase increases from 907.4 kg.m -3 to 786.6 kg.m -3 , while that of its gas phase increases from 84.9 kg.m -3 to 158.1 kg.m -3 .
  • Nitrous oxide is therefore a highly volatile compound.
  • N 2 O can exist in diphasic form (thermodynamic liquid / gas equilibrium) or monophasic beyond its critical point. Under normal temperature and pressure conditions, nitrous oxide is in liquid / gas equilibrium.
  • the nitrous oxide is in liquid form. It can be partially in the form of gas.
  • N 2 O in liquid form is particularly advantageous in that it solubilizes the fuel and thus act as a solvent.
  • the nitrous oxide is then in solution with the liquid phase of fuel.
  • the liquid phase of N 2 O is then mixed with the fuel.
  • the oxidizing and combustible species are in the same phase.
  • Pressurizing gas is a neutral gas - that is, not intended to participate in the chemical reaction - used in reservoirs to pressurize the monergols and allow them to flow back into the fluidic lines in the direction of flow. thrusters. The system associated with this mode of operation is then called “positive expulsion".
  • Helium (He) and dinitrogen (N 2 ) are the most common pressurizing gases.
  • the use of an additional gas induces certain disadvantages such as the loss of effective volume in the reservoir and the presence of traces of gas in the monergol by absorption.
  • the fuel is an ionic compound introduced into the liquid phase of the monergol.
  • An ionic solution is a liquid containing ions among the solvent.
  • the salt is generally polar, is solid under standard temperature conditions, and is soluble in N 2 O.
  • the salt is generally present as a pure liquid at room temperature (RTIL: Room Temperature Lonic Liquid), has a melting temperature below -20 ° C, and forms a binary mixture with N 2 O.
  • RTIL Room Temperature Lonic Liquid
  • the salt, solid in the standard state is dissolved in a solvent to form an ionic solution itself in admixture with N 2 O present in liquid form.
  • the solvent is advantageously an energy solvent, such as methanol, for example.
  • the liquid phase contains this part of N 2 O in solution.
  • the fuel in liquid form makes it possible to guarantee an advanced stability of the monergol in the face of thermomechanical stimuli, in particular of detonation (shocks, adiabatic compression, etc.) and electrostatic stimuli.
  • the fuel is such that it is compatible with N 2 O and of reduced volatility by its ionic nature.
  • the fuel can be considered as non-volatile.
  • the fuel must be an N 2 O reducing species but may optionally include certain oxidizing groups.
  • the fuel is selected from the salts of the energetic compounds.
  • Energetic compounds are molecules or combinations of molecules with high energy density and high material density. This results in a standard enthalpy of positive and high formation, which may reach several thousand kJ.kg -1 - typically 2000 to 3000 kJ.kg -1 - and a high density, generally greater than 1000 kg.m -3. . This is called HEDM (High Energy Density Materials). Some HEDMs demonstrate outstanding performance but have limitations of use because of their instability (uncontrolled release of energy) and are classified in the category of explosive materials. This is particularly the case of derivatives of pentazole. In addition, an additional feature specific to space propulsion concerns the molar mass of the products resulting from the combustion of these energetic compounds. The latter must be as low as possible - generally less than 30 gmol -1 - in order to guarantee a flame temperature to molar mass ratio. T ad M high, pledge of high specific impulse.
  • the fuel also called “reducing agent”
  • the fuel is any combination of a linear or heterocyclic cation and a linear or heterocyclic anion meeting the criteria presented above.
  • the anion and / or the cation generally comprise one or more nitrogenous and / or unsaturated energetic groups such as amino, azido, cyano, propargyl, tripropargyl and guanidyl.
  • the fuel is usually a nitrogen derivative, in the form of salt.
  • the anion and / or the cation of said salt may contain one or more nitrogen atoms.
  • Said cation may be chosen from nitrogen derivatives such as aliphatic, cyclic or aromatic, quaternary amines.
  • said cation may be chosen from ammonium, imidazolium, triazolium and tetrazolium ions and their derivatives.
  • ion derivatives refers to compounds having a nitrogen atom in the form of said ion.
  • the analogues -inium and -idinium of the above unsaturated heterocyclic compounds refer to the corresponding partially saturated (-inium) and saturated (-idinium) analogues resulting from a partial or complete partial hydrogenation, such as, for example, pyrrolinium as an analogue. partially unsaturated and pyrrolidinium as a saturated analogue of pyrrolium.
  • ammonium derivatives that may be mentioned are substituted ammonium compounds, such as ethylenediammonium, ethanolammonium, propylammonium, monopropargylammonium, tripropargylammonium, tetraethylammonium, N-tributyl-N-methylammonium, N-trimethylammonium, N-butylammonium, N-trimethyl-N-hexylammonium, N-trimethyl-N-propylammonium.
  • substituted ammonium compounds such as ethylenediammonium, ethanolammonium, propylammonium, monopropargylammonium, tripropargylammonium, tetraethylammonium, N-tributyl-N-methylammonium, N-trimethylammonium, N-butylammonium, N-trimethyl-N-hexylammonium, N-trimethyl-N-propylammonium.
  • pyrrolium derivatives that may be mentioned are substituted pyrroliums, in particular with an alkyl group, such as N-methylpyrrolium.
  • imidazolium derivatives mention may be made of substituted imidazoliums, in particular with one or more alkyl groups, and / or hydroxyalkyls, such as 1-butyl-2,3-dimethylamidazolium or 1-butyl-3-methylimidazolium, 1,3-dimethylimidazolium, 1-ethanol-3-methylimidazolium, 1-ethyl-3-methylimidazolium, 1-hexyl-3-methylimidazolium, methylimidazolium, 1-octyl-3-methylimidazolium, 1-propyl-2 3-dimethylimidazolium, 1-propyl-2,3-dimethylimidazolium.
  • 1-butyl-2,3-dimethylamidazolium or 1-butyl-3-methylimidazolium 1,3-dimethylimidazolium, 1-ethanol-3-methylimidazolium, 1-ethyl-3-methylimidazolium, 1-hexyl
  • pyrrolidinium derivatives By way of pyrrolidinium derivatives, mention may be made of substituted pyrrolidiniums, in particular with one or more alkyl groups, such as 1-butyl-1-methylpyrrolidinium, 1-ethyl-1-methylpyrrolidinium and N-propyl-N-methylpyrrolidinium. .
  • piperidinium derivatives mention may be made of piperidinium substituted with one or more alkyl groups, such as 1-methyl-1-propylpiperidinium.
  • triazolium derivatives there may be mentioned 1-methyl-1,2,4-triazolium, 3-azido-1,2,4-triazolium, 1-methyl-3-azido-1,2,4 -triazolium, 4-amino-1,2,4-triazolium.
  • tetrazolium As derivatives of tetrazolium, there may be mentioned 1-amino-4,5-dimethyltetrazolium, 2-amino-4,5-dimethyltetrazolium, 1,5-diamino-4-methyltetrazolium.
  • alkyl group saturated hydrocarbon radicals, straight or branched chain, of 1 to 20 carbon atoms, preferably 1 to 5 carbon atoms. Mention may in particular be made, when they are linear, the methyl, ethyl, propyl, butyl, pentyl, hexyl, octyl, nonyl, decyl, dodecyl, hexadecyl and octadecyl radicals.
  • alkyl radicals When they are branched or substituted by one or more alkyl radicals, mention may be made especially of the isopropyl, tert-butyl, 2-ethylhexyl, 2-methylbutyl, 2-methylpentyl, 1-methylpentyl and 3-methylheptyl radicals.
  • the counterion is especially chosen from azide, nitrate, dinitramide, dicyanamide, imidazolate and tetrazolate ions and their derivatives.
  • the salts according to the invention can be obtained by application or adaptation of known methods, in particular according to the methods described by Keskin et al., J. of Supercritical Fluids 43 (2007) 150-180 , in particular by coupling of its constituents, by metathesis or by acid-base reaction.
  • the desired salt can be prepared from the compound in neutral form by salification, for example by addition of the acid containing the desired anion; or from another ionic compound by ion exchange, for example on a column, or by transsalification in the presence of an acid containing the desired anion, or by metathesis.
  • nitrate, dinitramide and azide salts can be advantageously prepared by metathesis in the presence of the silver salts of nitrate, dinitramide and azide from the corresponding halides.
  • the monergols according to the invention are such that the ratio N 2 O / fuel (by mass), known as the mixing ratio and often noted O / F or OF (for Oxidizer / Fuel ratio) is generally between 0, 1 and 10, preferably between 1 and 6.
  • the specific impulse represents the duration during which the engine provides a thrust equal to the weight of the consumed propellant. It is thus an indicator of the "sobriety" and therefore of the energy performance of an ergol.
  • C *, g 0 , ⁇ , P e and P c respectively represent the characteristic velocity of the gases ejected by the nozzle, the gravity at the altitude considered, the average isentropic coefficient of the ejected gases, the ejection pressure and the pressure in the room.
  • R, T ad and M are respectively the universal constant of the ideal gases, the adiabatic temperature within the chamber (so-called "flame" if presence of combustion) and the average molar mass of the ejected gases.
  • the present invention also relates to the process for preparing the monergol according to the invention.
  • said process comprises the step of mixing the fuel and N 2 O.
  • This mixture can be carried out at room temperature, but in the case where a solid salt in the standard state is used, the maximum solubility should be considered at room temperature.
  • the minimum storage temperature of the monergol orbit to overcome any risk of saturation and recrystallization in flight. It is therefore necessary, during the synthesis of the monergol, to respect this threshold.
  • the minimum operating temperature of the monolgy in orbit is typically 0 ° C.
  • the monolif according to the invention can be stored taking care not to exceed the maximum permissible storage temperature so as not to exceed a certain saturation vapor pressure level, the MEOP (Maximum Expected Operating Pressure, maximum pressure expected in operation) being between 10 and 50 bar, typically between 20 and 40 bar.
  • the maximum storage temperature is generally between 0 ° and 50 ° C.
  • the monoling stone must have sufficient stability to be stored in orbit for a period of several years - typically 5 years, but possibly up to 15 years. The stability must be reflected in particular by the absence of phase separation (demixing, settling, etc.).
  • the present invention also relates to a method of spatial propulsion using the monergol according to the invention.
  • Spatial propulsion is the propulsion of spacecraft such as launchers and satellites.
  • the monergol according to the invention is suitable for combustion operation.
  • Combustion makes it possible to dispense with a catalytic bed and consequently with a complex propellant structure.
  • the life of the propellant may be extended insofar as the catalyst currently constitutes the limiting element due to phenomena such as catalyst deactivation by erosion, oxidation, sintering, etc.
  • the method according to the invention therefore comprises the combustion of the monergol according to the invention.
  • the combustion is generally carried out by controlled ignition. This can be done according to the usual technologies, in particular by means of a high energy candle.
  • the spark plug is generally positioned in the injection head, at the arrival of the monergol in the combustion chamber, the gases burned and evacuated by a nozzle placed at the opposite end of the combustion chamber.
  • the method according to the invention may also comprise the means for pressurizing the monergol in the tank.
  • the present propellant systems known as "catalytic monergols" with hydrazine operate for pressures in the tank of the order of 20 bar at the beginning of life (initial pressure) and 5 bar at the end of life. This pressure decreases during the draining of the monergol due to the relaxation of the pressurizing gas in the volume released by the propellant.
  • Some systems provide for tank pressure regulation to keep it constant over a certain part of the satellite's mission (performance optimization). This is the case on a telecommunication platform, but this introduces a complex and expensive equipment.
  • the pressurization can be advantageously carried out by the N 2 O solution itself because of its volatile nature, so that the use of an additional inert gas is no longer necessary. This results in a gain on the filling rate of the reservoir as well as on the apparent density of the liquid-gas torque.
  • the pressurizing means can be ensured only by filling the monergol in the tank.
  • the return to equilibrium between the liquid and vapor phases by vaporization of a liquid N 2 O fraction is accompanied by a slight drop in temperature (endothermic phenomenon), so that a slight decrease in pressure will be observed.
  • This phenomenon can be counterbalanced by the exercise of a reheating of the tank via a thermal control (thermistors).
  • This phenomenon of self-pressurization "represents a major advantage since, similarly to pressure regulators on biliquid engines, it allows the thrusters to operate near their optimum performance.
  • the tank then operates in a conventional "blow down" manner similar to an inert gas pressurization.
  • the method according to the invention may also include the previous step of loading the monolgy into the tank of the spacecraft.
  • 1-Butyl-3-methyl-imidazolium dicyanamide can be prepared using the methodology described by Asikkala et al (Application of Ionic Liquids and Microactivation in Selected Organic Reactions, Acta Univ Oul. A 502, 2008, p. 134) by transsalification from 1-butyl-3-methyl-imidazolium chloride in the presence of sodium dicyanamide, the chloride being prepared by reaction between 1-chlorobutane and 1-methylimidazole.
  • the dicyanamide of 1-butyl-3-methyl-imidazolium can be prepared by metathesis as described in particular in US8,034,202 from 1-butyl-3-methylimidazolium bromide in the presence of silver dicyanamide.
  • ⁇ Based on triazolium cation: Denomination Atomic composition T FUS T DECOMP ⁇ ⁇ H f ° VS NOT H O [° C] [° C] [Kg / m3] [KJ / kg] 1,2,4-triazolium 4,5-dinitroimidazolate 5 7 5 4 156 165 1730 1022.5 4,5-dinitroimidazolate of 1-methyl-1,2,4-triazolium 6 7 7 4 102 150 1660 831.1 3-azido-1,2,4-triazolium 4,5-dinitro-im idazoate 5 10 4 4 92 158 1700 2214.6 4,5-dinitroimidazolate of 1-methyl-3-azido-1,2,4-tri
  • the above salts can be prepared according to Singh et al Structure Bond 2007, 125: 35-83.
  • Example 1 the first case can be illustrated by the use of the azide of 1- (2-butynyl) -3-methyl-imidazolium, noted [ByMIM] [N 3 - ].
  • This compound can be prepared from bromide of 1- (2-butynyl) -3-methyl-imidazolium on azide exchange resin according to Schneider et al Inorganic Chemistry 2008, 47 (9), 3617-3624 . It can be dissolved by direct dissolution in N 2 O. The following figure gives the structure of [ByMIM] [N 3 - ]:
  • Example 2 the second case can be represented by the liquid-liquid binary mixture between 1-butyl-3-methyl-imidazolium dicyanamide, denoted [BMIM] [N (CN) 2 - ] (marketed by Solvionic), and the N 2 O.
  • BMIM 1-butyl-3-methyl-imidazolium dicyanamide
  • Example 3 the third case can be illustrated by the ternary equilibrium between 1,5-diamino-4-methyl-tetrazolium dinitramide, noted [DAMT] [N (NO 2 ) 2 ] synthesized according to Singh et al Structure Bond 2007, 125: 35-83 ,, pyrrolidine and N 2 O.
  • the structure of [DAMT] [N (NO 2 ) 2 ] is as follows:
  • the specific impulse generated by monergol combustion is closely dependent on the O / F mixture ratio between N 2 O and the fuel (dissolved "crystalline" salt or liquid salt).
  • a curve can then be described by plotting the evolution of the Isp as a function of O / F , any other parameter being kept constant (chamber pressure, initial temperature, expansion ratio ⁇ ).
  • a maximum of Isp can then be identified as well as the corresponding optimal O / F.
  • the monergol must be synthesized respecting this mixing ratio in order to provide the best propulsive performance.
  • the solubility of the salt in N 2 O or in the N 2 O combined solution limits the range of O / F available.
  • the crystalline salts of interest must therefore either have a high solubility at the specified minimum temperature (typically S T min > 100 ⁇ boy Wut . k ⁇ boy Wut NOT 2 ⁇ O - 1 or to disassemble a high mixing ratio Isp optimum (typically 4 O O / F ⁇ 10).
  • the use of energetic solvent makes it possible to enhance the optimal mixing ratio, to reduce the amount of salt required and thus to respect the solubility ceiling.
  • an optimal mixing ratio of 3.4 is found, which makes it possible to lower the mass of salt necessary for 117 ⁇ boy Wut . k ⁇ boy Wut NOT 2 ⁇ O - 1 .
  • this approach alters the maximum Isp (here, about -6s), which shows all the importance of the energy density of the solvent used.
  • the filling of the satellite tank can then be carried out by placing the storage tank and the propulsion module tank in communication and withdrawing the liquid phase.
  • the driving force for the transfer of monoling from the drum to the reservoir is directly ensured by the self-pressurization of the monergol.
  • the use of an additional neutral gas may be considered to expel the monolgy from the storage drum.
  • the monol ⁇ N 2 O + ionic fuel ⁇ stored in the pressurized tank is injected into the propellant via a usual fluid line including in particular a flow control valve called "motor valve".
  • the monergol is withdrawn at the reservoir by its liquid phase insofar as only this phase comprises both the oxidant and the fuel.
  • a bleeding technique well adapted to the present invention is the capillary network system (also known as the surface tension tank), well known to those skilled in the art.
  • the expulsion of the monergol through the fluidic line supplying the thrusters is ensured by the pressure generated by the N 2 O gas in equilibrium with the liquid solution. Only the liquid phase is then expelled.
  • the value of the mass flow rate of the monergol injected into the propellant (s) is dictated by the total pressure drop in the fluid lines of the reservoir to the engine (s), in particular by the singular pressure drop of the injector (dictated by its design). As long as the monergol has not crossed the injection head, it remains in liquid phase as long as it exists in this state in the tank.
  • the monergol When the monergol goes through the injector located at the engine head (called “front end”), the latter undergoes a relaxation. It then enters the upstream part of the combustion chamber and is caused to undergo a phase change.
  • the cause of the phase change differs according to the state of the combustion chamber, more precisely its pressure and temperature level. If it is an ignition, it can be assumed that the monergol enters a "fresh" environment and empty or near vacuum (so-called rarefied medium) to the extent that the room communicates with the vacuum space via the nozzle.
  • the monolol will volatilize rapidly since its saturation vapor pressure will be significantly higher than the residual pressure within the combustion chamber. This phenomenon will be exacerbated if the monolayer or the walls of the thruster are at a higher temperature.
  • the ignition phase consists in synchronizing the triggering of the spark plug with the arrival of the flow of the monergol in order to generate a "soft" ignition (contrary to the "hard start” involving a peak of transient pressure and violent damage to the system) .
  • the assurance of a quality ignition can also be achieved by the realization of a train of triggers of the candle (bursts of electric arcs) with relatively constant frequency (period of the order of a few tens of milliseconds to hundreds of milliseconds).
  • the arcing stream can also be fired in a slight phase advance over the injection to act as a local preheat.
  • the optimization of the ignition thus relies on the conjunction of a geometric design and an optimized sequence of trips.
  • the combustion is maintained after ignition as long as the monergol flow is maintained (open motor valve) and therefore does not require additional spark plugs.
  • the energy released by the combustion of the monergol is sufficient to maintain the reaction of the fresh species injected.
  • Combustion consists of a reaction between the main oxidant, namely N 2 O, and the ionic fuel optionally comprising oxidizing groups (eg nitramides).
  • the reaction produces hot gases at high pressure.
  • the combustion chamber is dimensioned such that the thermodynamic equilibrium is reached before ejection of the flue gas so as to achieve maximum efficiency.
  • the gases are ejected through a nozzle provided with a convergent, sonic and divergent neck to initiate and accelerate the flow to generate an optimal thrust force.

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  • Chemical & Material Sciences (AREA)
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  • Chemical Kinetics & Catalysis (AREA)
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  • Combustion & Propulsion (AREA)
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  • Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)
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  • Nitrogen Condensed Heterocyclic Rings (AREA)
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JP6240940B2 (ja) * 2014-02-06 2017-12-06 株式会社Adeka エポキシ樹脂組成物
CN106370301A (zh) * 2016-08-24 2017-02-01 中国科学院合肥物质科学研究院 用于星载大气环境探测仪的防潮防污染导流吹氮保护系统
CN108981162A (zh) * 2018-06-06 2018-12-11 朱焕旺 一种熔盐循环运行工艺
CN111925262B (zh) * 2020-08-19 2021-08-27 中国工程物理研究院化工材料研究所 基于金属氯化物的多组分低共融液体的制备方法
DE102020122337A1 (de) * 2020-08-26 2022-03-03 LabOrbital GmbH Heißgaserzeugungsvorrichtung mit monergolem ionischen Treibstoff und Niederspannungsanzündung

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JP2013155105A (ja) 2013-08-15
FR2986229A1 (fr) 2013-08-02
US20130305685A1 (en) 2013-11-21
EP2620422A1 (fr) 2013-07-31
JP6154142B2 (ja) 2017-06-28

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