[go: up one dir, main page]

WO2002101221A2 - Procede et appareil de preparation et d'utilisation d'un propergol cryogenique ou d'un systeme explosif - Google Patents

Procede et appareil de preparation et d'utilisation d'un propergol cryogenique ou d'un systeme explosif Download PDF

Info

Publication number
WO2002101221A2
WO2002101221A2 PCT/US2001/043201 US0143201W WO02101221A2 WO 2002101221 A2 WO2002101221 A2 WO 2002101221A2 US 0143201 W US0143201 W US 0143201W WO 02101221 A2 WO02101221 A2 WO 02101221A2
Authority
WO
WIPO (PCT)
Prior art keywords
container
liquid
methane
oxygen
mixture
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.)
Ceased
Application number
PCT/US2001/043201
Other languages
English (en)
Other versions
WO2002101221A3 (fr
Inventor
Thomas M. Flynn
John David Watson
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Cryoco Inc
Original Assignee
Cryoco Inc
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Cryoco Inc filed Critical Cryoco Inc
Priority to AU2001297846A priority Critical patent/AU2001297846A1/en
Publication of WO2002101221A2 publication Critical patent/WO2002101221A2/fr
Anticipated expiration legal-status Critical
Publication of WO2002101221A3 publication Critical patent/WO2002101221A3/fr
Ceased legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/425—Propellants
    • 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
    • C06B47/06—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 a component being a liquefied normally gaseous material supplying oxygen
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants

Definitions

  • the present invention relates generally to a method and means for remotely forming a combustible liquid in a container using non-explosive components.
  • the invention is applicable to the rocket propulsion, excavation, and munitions industries.
  • LOX liquid oxygen
  • LNG liquid methane
  • LOX and LNG can be mixed together to form a cryogenic combustible liquid sometimes referred to as MOX (an acronym derived from methane-oxygen).
  • MOX an acronym derived from methane-oxygen
  • LOX and LNG form a fully miscible and homogeneous fluid over the full range of mixtures from pure LOX to pure LNG.
  • the stoichiometric mixture, CH 4 + 2O 2 is in the liquid phase between about 63 degrees Kelvin, below which methane starts to freeze out, and 92 degrees Kelvin, above which oxygen begins to boil off.
  • MOX will detonate at a range of mixtures around the stoichiometric ratio and will deflagrate for mixtures that are very fuel rich or oxygen rich.
  • Fuel rich mixtures those mixtures which have more methane than the stoichiometric ratio, are typically of interest in the rocket propulsion industry while both detonating and deflagrating mixtures or oxygen rich, those mixtures which have more oxygen that called for in the stoichiometric ratio, are of interest for the rock blasting, excavation, and explosive manufacturing industries.
  • Flynn describes a method for making and storing a cryogenic monopropellant based on the LOX/LNG or MOX system in U.S. Patent Number 5,804,760. Flynn's invention is a significant improvement over the prior art but it is still a method of preparing a LOX/LNG mixture that is too complicated and not practical for use in field applications such as, for example, small rocket experiments or commercial blasting operations.
  • British Patent Number 855,200; and U.S. Patent Numbers 2,939,778; 4,074,629; and 5,804,760 are incorporated by reference in their entireties herein.
  • MOX is subject to initiation, for example, by mechanical shock or electrical spark. This means that MOX must be classified as an explosive material and is therefore subject to many costly regulations for transportation and storage.
  • MOX is also known to have an elevated sensitivity to mechanical import for mixtures in the approximate range of 0.20 to 0.27 mole fraction of LNG.
  • MOX has the potential for unintentional initiation when it is being pumped or otherwise transported through a conveyance system of piping and valves such as might be used in rocket propulsion system or a system for charging blast holes.
  • MOX mixtures can be very sensitive to mechanical or electrical spark initiation when there is a gaseous mixture of oxygen and methane formed above the liquid phase. This phenomenon can occur when the mixture is near or at its boiling point, i.e., when a valve in a fill-line is not properly pre-chilled thereby allowing a small amount of MOX vapor to form. Opening or closing a valve under such conditions can cause the vapor to flash-burn which can then cause the MOX to combust or, if the mixture is near stoichiometric proportions, to detonate.
  • MOX is known to have an extremely small critical diameter and thus a detonation, once initiated, can propagate through the parts of the system even if only connected by small amounts of MOX. Because of the extremely small critical diameter of detonable MOX mixtures, a practical detonation arrester device has never been successfully developed.
  • MOX is required for its intended application, it is formed from a remote and safe location in the container required by the application. MOX is generally not required to pass through valves or other devices that could cause premature initiation by, for example, mechanical shock or electrical spark, except under remote control. For example, MOX would be formed in a fuel tank of a rocket in orbit or in a cartridge in a blast hole.
  • LOX and/or LNG can be transported to the field site in their liquid phase.
  • the oxygen and/or the methane required to form LOX or LNG can be transported to the field site in the gaseous phase.
  • either or both the oxygen and methane are normally liquefied at the field site by using liquid nitrogen ("LN2") to cool the gas to its liquid phase.
  • LN2 liquid nitrogen
  • the liquid nitrogen could also be used to pre-chill all piping, valves and other components required to transfer LOX and LNG to the remote container and to pre-chill the container itself, if necessary.
  • the means to utilize LN2 to form either LOX or LNG from their respective gaseous phases are described, for example, in U.S. Patent Number 5,804,760.
  • various embodiments of the present invention also includes methods to remotely and safely control (1) the composition of the MOX mixtures, (2) the holding time for stable MOX mixtures and (3) the non-explosive termination of the MOX mixture.
  • the present invention further includes means for remotely and safely forming a controllable mixture of MOX in a container at the final location of its desired application.
  • Figure 1 shows a schematic of a prior art apparatus for using liquid nitrogen to liquify gaseous oxygen or gaseous methane
  • Figure 2 shows a phase diagram illustrating possible mixture paths for forming an oxygen rich detonable composition of MOX;
  • Figure 3 shows a phase diagram illustrating possible mixture paths for forming a fuel rich deflagrating composition of MOX
  • Figure 4 shows a schematic of a field site layout for remotely mixing MOX from non-explosive components
  • Figure 5 shows a schematic side view of a possible container for the remote mixing ofMOX
  • Figure 6 shows a schematic diagram for a simple system for remotely forming MOX in a container
  • Figure 7 shows a schematic diagram for a system for remotely forming MOX in a container which allows for purging using gaseous nitrogen and pre-chilling using LN2;
  • Figure 8 shows a schematic diagram for a system for remotely forming MOX in a container which allows for purging and pre-chilling using LOX and LNG; and
  • Figure 9 shows a schematic side view of a possible container for the remote mixing of MOX which has a means for aborting the mixture.
  • the gaseous oxygen and/or gaseous methane may be cooled to their liquid phase by means of an apparatus such as that shown in Figure 1 and stored in separate cryogenic dewars.
  • the embodiment of Figure 1 would form LOX or LNG from their gaseous phases by using liquid nitrogen. It is also possible to form LNG by using LOX to liquify gaseous methane. Even though the LOX is totally separate from the methane, there exists a possibility that, for example, a defective or worn component in the system can lead to a breach in the wall of separation thus allowing oxygen and methane to come in contact even in minute amounts, with the potential to form an explosive mixture. It is for this reason that the use of LN2 to form LNG from gaseous methane is most preferred. LN2 is an inert substance and even if a breach, as described above, occurred, no explosive mixture would be formed.
  • the components to remotely form MOX are now all stored and available at the field site for use in the final application.
  • the container is positioned in its final location which is the location where MOX is to be mixed and initiated.
  • the means of initiation of MOX may be installed in the container (for example, if used in a cartridge for blasting) or the means of initiation may be elsewhere (for example, if used in a fuel tank that feeds MOX to a rocket motor).
  • the means of conveying gaseous nitrogen, liquid nitrogen (“LN2”), LOX and LNG to the container, if necessary, are also installed.
  • the means of conveying or transferring the various components to the container are comprised of various fill lines, valves and flow regulators. Any instrumentation desired for monitoring the process are also installed. At this point the system is in place for the final step - to remotely form and utilize an explosive mixture of MOX.
  • Figures 2 and 3 show the path of the composition of the mixture in the container on a gas-liquid-solid phase diagram for MOX. Two possible paths are shown as examples.
  • Figure 2 depicts a loading path that might be used for charging blast holes with a detonable composition of MOX.
  • Figure 3 depicts a loading path that might be used for charging a rocket motor with a fuel rich deflagrating composition of MOX. It will be noted by one of skill in the art that the loading paths will vary, dependent on the intended use and desired mixture composition of the MOX mixture.
  • gaseous nitrogen may be flowed through the charging system and, if desired, the container in order to purge any air in the charging system and, if desired, the container. Such a purge will remove any risk of premature or inadvertent detonation.
  • LN2 may be flowed through the charging system and, if desired, the container to chill the components of the charging system and, if desired, the container in order to minimize the temperature rise of the LOX and LNG when they are conveyed from their respective long term storage dewars to the container. Referring to either Figure 2 or 3, first, the desired amount of LNG is introduced into the container at a temperature just above its freezing point, approximately 90 degrees Kelvin (mole fraction of methane equal to 1).
  • LOX is added to the LNG in the container at a temperature that is low enough to maintain the MOX mixture as a liquid near its local freezing point, approximately 63 degrees Kelvin, when the mixture composition is within the range required by its application.
  • a portion of the liquid methane may temporarily freeze out as shown, for example, by one of the possible paths in the phase diagrams of Figures 2 and 3.
  • the composition will have more methane in the composition than that required by the stoichiometric ratio.
  • an oxygen rich composition is desired, the composition will have more oxygen in the composition than that required by the stoichiometric ratio.
  • the mixture could be 2CH 4 + 2O 2 .
  • the mixture is ready to be initiated for its desired final application. It is observed that loading the LNG first means that the MOX mixture never reaches the range of enhanced impact sensitivity (between the approximate range of about 0.20 to 0.27 mole fraction of LNG per mole fraction of LOX) except if a very oxygen rich final mixture were desired.
  • thermocouples, flow meters and weighing devices can be used to monitor the progress of the mixing the LOX and LNG in the container and follow the path of the mixture on a MOX phase diagram such as shown in Figures 2 and 3.
  • the MOX conditions in the container can be determined by reference to prior, off-site testing and measurement of the flow of components to a container via a conveyance system identical to the container and conveyance system to be used in the final application.
  • the mixture can be held for a desired length of time, dictated by the quality of the insulation of the container.
  • the measured temperature can not be used alone to determine mixture composition.
  • a temperature sensor or sensors immersed in the liquid phase can be used to uniquely determine mixture composition.
  • a means of determining the onset of boiling so that simple temperature sensors would be able to monitor mixture composition. This could be accomplished by any number of means, including but not limited to, acoustic sensors which would measure the sounds associated with the boiling of the MOX mixture, pressure sensors which would measure the relative pressure throughout the addition of the liquid oxygen, visual sensors which would visually detect the color of the liquid and the relative miscibility of the liquids, or any combination of these.
  • a feedback loop utilizing a processor is contemplated wherein the sensors would provide feedback to the processor, which could consult preset reference numerals and change the control conditions (such as temperature, mole fraction or ratio or resident time) automatically or which could prompt an operator for additional input before changing the control conditions.
  • the processor could consult preset reference numerals and change the control conditions (such as temperature, mole fraction or ratio or resident time) automatically or which could prompt an operator for additional input before changing the control conditions.
  • the desired MOX mixture can be initiated or otherwise utilized at any time that the mixture composition remains in the range acceptable to the application.
  • the container is provided with a means of venting vapors formed in the event that the MOX mixture approaches its local boiling temperature.
  • the temperature of the mixture can be raised by any of a number of means such that the mixture boils controUably and the resultant vapors are vented, for example to the atmosphere, until no liquid phase remains.
  • the oxygen would, as explained above, preferentially boil away first and, as the remaining liquid is heated, the methane will return to its gaseous state.
  • molecular oxygen, in a gaseous state, and methane, in a gaseous state are relatively harmless gases that can be vented to the atmosphere.
  • a metal object at approximately atmospheric temperature can be introduced slowly into the mixture to absorb heat energy and cause the temperature of the mixture to rise rapidly but controUably until all the liquid is boiled off and the resultant vapors vented.
  • a metal object at an atmospheric temperature of 50 degrees Celsius is at approximately 323 degrees Kelvin, or approximately 250 degrees higher than the temperature of the liquid. Such an insertion will cause the temperature of the mixture to rise rapidly, given the temperature differential between the metal object and the temperature of the mixture.
  • the apparatuses necessary for the present invention can include but are not limited to:
  • FIG. 4 An example of a simple embodiment of a field system for applying the method of the present invention is shown in Figure 4.
  • the protective structure is capable of protecting personnel, component materials and other valuable property from an accidental or intentional explosion of a MOX mixture that is prepared in the remote container.
  • All of the components described above are non-explosive materials and are not subject to explosive materials transportation, storage or handling regulations.
  • the container used in the final application is placed at a safe distance from the protective structure.
  • the fill lines, electrical, signal, pre-chill, purge and other control lines that connect the control area to the remote application area are installed.
  • FIG. 5 An example of a container for remote mixing of MOX is shown in Figure 5.
  • the container includes but is not limited to fill ports for the LOX and LNG and a vent for releasing vapors that form above the MOX in the event the MOX begins to boil as a result of standing for a long period of time or as a result of intentionally heating the MOX to non-explosively eliminate the explosive MOX mixture.
  • the vent should be located at or near the top of the container or such that the vent is higher than the level of the MOX mixture. It is preferred to locate the fill lines at the top of the container to enhance mixing of the LOX with the LNG.
  • the LNG is loaded into the container first.
  • the heavier LOX density II 3 4 kg/m'
  • FIG. 6 An example of a schematic for a simple system for mixing MOX remotely is shown in Figure 6.
  • the system shown assumes that both LOX and LNG have been created previously and both are readily available from storage dewars. It is assumed that all cryogenic storage dewars include pressure relief valves as part of their structure, which are not shown in Figure 6.
  • a dewar containing LNG is connected to its fill line through a simple shut-off valve mounted on or near its dewar.
  • the dewar is self-pressurizing for gas-pressure transfer of the liquid contents through the fill line and into the container.
  • a second dewar containing LOX is also connected to its fill line through a simple shut-off valve mounted on or near on its dewar and is also self-pressurizing for gas-pressure transfer of the liquid contents through the fill line and into the container.
  • An electrical spark discharge unit is shown as an example of a simple MOX initiation system. This system represents a very simple embodiment of the present invention that could be used, for example, to carry out uncomplicated blasting operations when the general MOX mixture characteristics are known from prior experience and measurement.
  • FIG. 7 An example of a schematic of a more complex system for mixing MOX remotely is shown in Figure 7.
  • the system shown assumes that both LOX and LNG have been created previously and both are readily available from storage dewars.
  • This system additionally depicts examples of how additional apparatuses can be connected to add air purge and component pre-chill functions for the remote MOX mixing operations.
  • This system also shows a means to isolate the LOX dewar from any LOX back-but event that might be caused, for example, by hot debris created when the MOX is initiated.
  • the system always includes pressure relief valves between any two flow regulating valves because of the possibility of trapped liquid between the two flow regulating valves.
  • This system uses transfer dewars for both the LOX and LNG to provide a possible means for accurate determination of the mass and/or volume of LOX and LNG transferred to the container.
  • Check valves are included to prevent any LOX from accidentally mixing with LNG during purge or pre-chill operations.
  • cryogenic storage and transfer dewars include pressure relief valves as part of their structure, which are not shown in Figure 7.
  • the general sequence of operations of this system is: • Nitrogen gas is flushed sequentially or simultaneously through the LOX, LNG and LN2 lines, the transfer dewars and the container to remove most of the air in the system. LN2 is flushed sequentially or simultaneously through the LOX and LNG lines the transfer dewars and the container to pre-chill these components to minimize temperature change when the LOX and LNG are conveyed to the container.
  • the lines can be chilled to a range of temperatures from around the freezing point of methane which is 63 degrees Kelvin to around the boiling point of oxygen which is approximately 93 degrees Kelvin. It is believed that an appropriate range of temperatures could be a range of temperatures from about 48 degrees Kelvin to approximately 100 degrees Kelvin.
  • the LNG transfer dewar is charged with the desired amount of LNG from its storage dewar.
  • the LOX transfer dewar is charged with the desired amount of LOX from its storage dewar.
  • LOX transfer dewar conveyed to the container where it is mixed to form the desired MOX mixture.
  • the initiation system is armed and the MOX is initiated when desired.
  • This system represents a practical embodiment of the present invention that could be used, for example, to carry out rocket launching experiments or controlled blasting operations when a relatively accurate knowledge of the MOX mixture composition and temperature just prior to initiation are required.
  • FIG 8 The system shown schematically in Figure 8 is an example of a simplification of the system shown in Figure 7.
  • the gaseous nitrogen and LN2 are eliminated and LOX and LNG are used to purge and pre-chill their respective lines.
  • This system may be preferred when LOX and LNG are plentiful.
  • Figure 1 illustrates a simple method for forming LNG from gaseous methane as disclosed in U.S. Patent Number 5,804,760.
  • Gaseous methane is contained in a commercially available or otherwise suitable bottle 1 which has a flow regulator 2 and a shut-off valve 3.
  • a vessel 4 is filled with LN2 5.
  • the methane flow path is via line 6, through a refrigeration coil 7 and into a LNG storage dewar 8.
  • the methane from bottle 1 is allowed to flow through line 6 as a gas and into the portion of line 6 and coil 7 which are immersed in LN2 5 contained in the vessel 4.
  • the LN2 5 can be maintained at or just below its boiling temperature of 77 K. Methane liquefies at 112 K and freezes at 89K. Therefore the flow rate of methane through refrigeration coil 7 must be regulated to allow the methane to liquify but not to freeze and therefore block the portion of line 6 and coil 7 which are immersed in LN2 5. This process is discussed in further detail in U.S. Patent Number 5,804,760 which is incorporated by reference into the present invention.
  • Figure 2 is a gas-liquid-solid phase diagram for MOX.
  • the ordinate 11 of the diagram is the MOX mixture temperature in kelvins (K).
  • the abscissa 12 of the diagram is the mole fraction of methane.
  • the dotted line 13 represents the stoichiometric mixture, CH 4 + 2O 2 .
  • the range arrow 14 represents the range of methane mole fractions over which MOX can detonate and its products of combustion have an approximately constant work potential or heaving power.
  • the range arrow 15 represents the range of methane mole fractions over which MOX has an enhanced impact sensitivity.
  • the boiling point of MOX for various mole fractions of methane is shown by solid line 16 while the freezing point of MOX for various mole fractions of methane is shown by solid line 17.
  • a possible loading path that might be used for charging blast holes with a detonable composition of MOX is illustrated by the dotted line 18.
  • the desired amount of LNG is loaded into the MOX container at a point above its freezing temperature of 89 K as shown by point 19.
  • LOX is added at a temperature lower than 89K such that the mixture follows path 18.
  • the mixture temperature may be low enough for some methane to freeze out as would be the case during the portion 20 of the loading path 18 which shows a mixture temperature less than the freezing point. In general, it is desirable to maintain the mixture temperature always just above the freezing point curve 17.
  • the mixture is represented by point 21, which is shown here, for example, as slightly oxygen rich.
  • the mixture may be initiated for its intended use or it may be allowed to sit in the container. If it sits in the container, the mixture temperature will begin to rise with little change in mixture along portion 22 of the path 18. As the mixture nears the boiling point, more oxygen will begin to boil off than methane and the mixture will begin to increase in methane mole fraction along portion 23 of the path 18. Once the methane mole fraction exceeds the limit of the desired application indicated by range arrow 14, it may be desirable to abort the application or add more LOX. It is noted that the example path illustrated never takes the mixture into the region 15 of enhanced impact sensitivity.
  • Figure 3 is a the same gas-liquid-solid phase diagram for MOX as shown in Figure 2.
  • the ordinate 31 of the diagram is the MOX mixture temperature in kelvins (K).
  • the abscissa 32 of the diagram is the mole fraction of methane.
  • the dotted line 33 represents the stoichiometric mixture, CH 4 + 2O 2 .
  • the range arrow 34 represents the range of methane mole fractions over which MOX can detonate and its products of combustion have an approximately constant work potential or heaving power.
  • the range arrow 35 represents the range of methane mole fractions over which MOX has an enhanced impact sensitivity.
  • the boiling point of MOX for various mole fractions of methane is shown by solid line 36 while the freezing point of MOX for various mole fractions of methane is shown by solid line 37.
  • a possible loading path that might be used for forming a fuel rich deflagrating composition of MOX is illustrated by the dotted line 38.
  • the desired amount of LNG is loaded into the MOX container at a point above its freezing temperature of 89 K as shown by point 39.
  • LOX is added at a temperature lower than 89K such that the mixture follows path 38.
  • the mixture temperature may be low enough for some methane to freeze out as would be the case during the portion 40 of the loading path 38 which shows a mixture temperature less than the freezing point.
  • the mixture is represented by point 41.
  • the mixture may be initiated for its intended use or it may be allowed to sit in the container. If it sits in the container, the mixture temperature will begin to rise with little change in mixture along portion 42 of the path 38. As the mixture nears the boiling point, more oxygen will begin to boil off than methane and the mixture will begin to increase in methane mole fraction along portion 43 of the path 38. Once the methane mole fraction exceeds the limit of the desired mixture indicated by point 44, it maybe desirable to abort the application or add more LOX. It is noted that the example path illustrated never takes the mixture into the region 35 of enhanced impact sensitivity or the region of detonable mixtures 34.
  • FIG 4 shows a schematic of a possible field site layout for remotely mixing MOX from non- explosive components.
  • the site is divided into a safe side 51 and a test side 52, separated by a blast and debris barrier 53.
  • LOX, LNG and, if used, LN2 may be stored in this work and storage area 54.
  • LNG may be prepared from gaseous methane in area 54 as well.
  • a container 55 for the final application is shown positioned at a safe distance from the barrier 53.
  • the container 55 which includes a vent 64.
  • a LOX dewar 56 and an LNG dewar 57 are shown on the safe side 51 of the barrier 53.
  • the LOX dewar 56 is connected to the container 55 by a conveyance means 58 which maybe an insulated tubing for example.
  • the LNG dewar 57 is connected to the container 55 by a conveyance means 59 which may also be an insulated tubing for example.
  • a firing box 60 is located on the safe side 51 and connected to the container 55 by a firing line 61 which may be, for example a pair of electrical wires.
  • An example of a MOX initiation device 62 is shown inside the container 55 and connected to the firing line 61.
  • FIG. 5 A schematic side view of a possible container for the remote mixing of MOX is illustrated in Figure 5.
  • the cartridge 71 consists of a bottom section which may have walls formed from one of any number of thermally insulating materials.
  • the container is shown with a top section 72 which also contains provision for a LOX fill line 73, an LNG fill line 74, an LN2 purge and pre-chill line 75 and a vent 76.
  • a MOX initiator device 77 is also shown entering the container 71 through the top section 72.
  • the MOX mixture is formed within the container volume 78.
  • the container may also be made as a single structure with fill holes, vent holes and other holes drilled through the structure wall.
  • FIG. 6 shows a schematic diagram for a near minimal number of components that could form a simple system for remotely forming MOX in a container. It is assumed that all cryogenic storage dewars include pressure relief valves as part of their structure, which are not shown.
  • the system is comprised of a LOX dewar 81 connected to a conveyance means 82 which may be an insulated tubing for example, which is used to transfer LOX to a container 83.
  • the flow of LOX is controlled by a shut-off valve 84.
  • An LNG dewar 85 is also connected to a conveyance means 86 which maybe an insulated tubing for example, which is used to transfer LNG to the container 83.
  • the flow of LNG is controlled by a shut-off valve 87.
  • the container 83 has a vent 88 to relieve any pressure buildup from boiling LNG or MOX mixtures.
  • the system also includes a firing box 89 connected to the container 83 by a firing line 90 which may be, for example, a pair of electrical wires.
  • a MOX initiation device 91 is shown inside the container 83 and connected to the firing line 90.
  • valves 84 and 87 are closed.
  • the LNG valve 87 is opened to allow some LNG to flow down line 86 and into the container 83 in order to purge the line 86 of air and to pre-chill valve 87, line 86 and the container 83.
  • Valve 87 is closed and the LNG in the line 86 and the container 83 is then allowed to boil away.
  • the LOX valve 84 is opened to allow some LOX to flow down line 82 and into the container 83 in order to purge the line 82 of air and to pre-chill valve 84, line 82 and, if necessary, the container 83. Now valve 84 is closed and the LOX in the line 82 and the container 83 is then allowed to boil away. Now the system is ready to be charged with the desired MOX mixture.
  • the LNG valve 87 is again opened to allow the required amount of LNG to flow down line 86 and into the container 83. Valve 87 is closed.
  • the LOX valve 84 is opened to allow the desired amount of LOX to flow down line 82 and into the container 83 in order to form the desired mixture of MOX 92. Valves 84 and 87 are closed. Now the MOX 92 in the container 83 is ready to be initiated.
  • the MOX 92 is initiated by activating the firing box 89 and initiating the MOX 92 with the initiation device 91.
  • FIG. 7 shows a schematic diagram for a preferred embodiment of a system for remotely forming MOX in a container which allows for purging using gaseous nitrogen and pre-chilling using LN2.
  • the system is comprised of a LOX dewar 201 and its shut-off valve 202; an LNG dewar 203 and its shut-off valve 204; an LN2 dewar 205 and its shut-off valve 206.
  • a bottle of nitrogen gas 207 with its flow regulator 208 and shut-off valve 209 is connected into the LN2 line.
  • cryogenic storage and transfer dewars include pressure relief valves as part of their structure, which are not shown.
  • shut-off valves 214, 216, 217, 219 and 220 which are used to control the purging, pre-chilling, venting and loading operations.
  • pressure relief valves 221, 223 and 224 which are positioned between any two adjacent shut-off valves so that trapped cryogenic fluids can -boil and automatically vent prior to over-pressuring the line.
  • check valves 225 and 226 to isolate the flow of either LOX into the LNG lines, or LNG into the LOX lines. These check valves prevent any explosive mixture from being formed in the system other than in the container 250.
  • the system also includes a firing box 230 connected to the container 250 by a firing line 231 which may be, for example a pair of electrical wires.
  • a MOX initiation device 232 is shown inside the container 250 and connected to the firing line 231.
  • the container 250 also has a vent line 235 to allow the vapors above the cryogenic fluids 251 in the container 250 to continuously vent to the atmosphere.
  • Pre-Chilling Transfer Dewars with LN2 - Open valves 206, 214, 216 and 211 to pre-chill the LOX lines to LOX transfer dewar 210 and the LOX lines to the container 250. Close valves 216 and 211. Open valves 219 and 213 to pre-chill the LNG lines to LNG transfer dewar 212 and the LNG lines to the container 250. Close valves 219, 213, 214 and 206 so that all valves are closed again to complete the line, valve and transfer dewar pre-chilling operations. The order of pre-chilling the lines, valves and transfer dewars is not important.
  • the LOX and LNG lines may be formed from coaxial tubing such that the LOX or
  • LN2 used to pre-chill the LOX and LNG lines is flowed down the outer portion of the coaxial tubing.
  • FIG 8 shows a schematic diagram for another embodiment of a system for remotely forming MOX in a container which allows for purging and pre-chilling using LOX and LNG.
  • the system is comprised of a LOX dewar 501 and its shut-off valve 502 and an LNG dewar 511 and its shut-off valve 512.
  • all cryogenic storage and transfer dewars include pressure relief valves as part of their structure, which are not shown.
  • shut-off valves 504, 505, 514 and 515 which are used to control the purging, pre-chilling, venting and loading operations.
  • pressure relief valves 503 and 513 which are positioned between any two adjacent shut-off valves so that trapped cryogenic fluids can boil and automatically vent prior to over-pressuring the line.
  • the system also includes a firing box 530 connected to the container 520 by a firing line 531 which maybe, for example a pair of electrical wires.
  • a MOX initiation device 532 is shown inside the container 520 and connected to the firing line 531.
  • the container 520 also has a vent line 522 to allow the vapors above the cryogenic fluids 521 in the container 520 to continuously vent to the atmosphere.
  • FIG 9 shows a schematic side view of a possible container for the remote mixing of MOX which has a means for aborting the mixture.
  • the cartridge 121 consists of a bottom section which may have walls formed from one of any number of thermally insulating materials.
  • the container is shown with a top section 122 which also contains provision for a LOX fill line 123, an LNG fill line 124, a vent 125, and a means of aborting the mixture 126.
  • a MOX initiator device 127 is also shown entering the container 121 through the top section 122.
  • the MOX mixture is formed within the container volume 128.
  • the means for aborting the mixture 126 is comprised of a metallic portion 129 normally not exposed to the inside volume 128 of the container 121, and a thermally insulating portion 130 normally exposed to the inside volume 128 of the container 121.
  • the means for aborting the mixture 126 is caused to fall into the mixture so that the mixture is exposed to the surfaces of the metallic portion 129.
  • the metallic portion 129 is at or near ambient atmospheric temperature and has sufficient heat capacity such that it will absorb sufficient heat from the MOX so as to cause the MOX to boil off more rapidly than it would by heat conduction through the container walls 121 and the top 122.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Organic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)

Abstract

Cette invention concerne un procédé et un appareil qui permettent de former à distance un mélange d'oxygène liquide ("LOX") et de gaz naturel liquéfié ("LNG") avec le mélange communément appelé MOX, de sorte que le LOX et le LNG n'entrent jamais en contact l'un avec l'autre qu'une fois placés à l'intérieur du récipient dans lequel le mélange sera utilisé. Le procédé de l'invention interdit le contact entre le LOX et le LNG dans le but d'empêcher une combustion explosive prématurée ou accidentelle pouvant survenir de différentes manières. Le procédé de l'invention prévoit un moyen de désactiver le mélange MOX, même après sa formation. L'invention concerne en outre divers appareils servant à mettre en oeuvre le procédé de l'invention.
PCT/US2001/043201 2000-11-20 2001-11-20 Procede et appareil de preparation et d'utilisation d'un propergol cryogenique ou d'un systeme explosif Ceased WO2002101221A2 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU2001297846A AU2001297846A1 (en) 2000-11-20 2001-11-20 A method and apparatus for the preparation and usage of a cryogenic propellant or explosive system

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US25234900P 2000-11-20 2000-11-20
US60/252,349 2000-11-20

Publications (2)

Publication Number Publication Date
WO2002101221A2 true WO2002101221A2 (fr) 2002-12-19
WO2002101221A3 WO2002101221A3 (fr) 2003-11-20

Family

ID=22955657

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2001/043201 Ceased WO2002101221A2 (fr) 2000-11-20 2001-11-20 Procede et appareil de preparation et d'utilisation d'un propergol cryogenique ou d'un systeme explosif

Country Status (3)

Country Link
US (1) US20030089434A1 (fr)
AU (1) AU2001297846A1 (fr)
WO (1) WO2002101221A2 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7726359B2 (en) * 2006-12-20 2010-06-01 Chevron U.S.A. Inc. Method for transferring a cryogenic fluid
US7726358B2 (en) * 2006-12-20 2010-06-01 Chevron U.S.A. Inc. Method for loading LNG on a floating vessel
EP3123864A1 (fr) 2008-12-08 2017-02-01 Gilead Connecticut, Inc. Inhibiteurs de syk d'imidazopyrazine
EP3552607A3 (fr) 2008-12-08 2020-01-15 Gilead Connecticut, Inc. Inhibiteurs de syk d'imidazopyrazine
JP2022521413A (ja) 2019-02-22 2022-04-07 クロノス バイオ インコーポレイテッド Ｓｙｋ阻害剤としての縮合ピラジンの固体形態
US12049855B1 (en) 2023-05-27 2024-07-30 Victoria Arel Lucas Method and apparatus for reducing consequences of a bulkhead failure for a liquid methane and liquid oxygen rocket

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1551650A (en) * 1921-08-26 1925-09-01 Universal Oil Prod Co Explosive and process of making same
US2886424A (en) * 1954-08-04 1959-05-12 Jr Andrew Hyslop Explosive compositions and method of preparing them
US2939778A (en) * 1956-06-21 1960-06-07 Air Prod Inc Liquid explosive
US3081157A (en) * 1958-09-19 1963-03-12 Little Inc A Liquid composition comprising liquid free oxygen and method of reducing the sensitivity of same
US3709748A (en) * 1970-05-26 1973-01-09 Us Air Force Ionic interhalogen oxidizing agent and method
US4074629A (en) * 1975-06-25 1978-02-21 Colgate Stirling A Blasting agent and method
US5705771A (en) * 1990-10-29 1998-01-06 Flynn; Thomas M. Cryogenic propellants and method for producing cryogenic propellants
US5804760A (en) * 1997-06-23 1998-09-08 Cryoco, Inc. Method for making and storing cryogenic monopropellant
US6101808A (en) * 1998-05-29 2000-08-15 Orbital Technologies Corporation Cryogenic solid hybrid rocket engine and method of propelling a rocket
US6212876B1 (en) * 1999-05-14 2001-04-10 Roger Everett Gregory Simplified high-efficiency propulsion system

Also Published As

Publication number Publication date
AU2001297846A1 (en) 2002-12-23
US20030089434A1 (en) 2003-05-15
WO2002101221A3 (fr) 2003-11-20

Similar Documents

Publication Publication Date Title
US6101808A (en) Cryogenic solid hybrid rocket engine and method of propelling a rocket
US4074629A (en) Blasting agent and method
US20030089434A1 (en) Method and apparatus for the preparation and usage of a cryogenic propellant or explosive system
Breon et al. Robotic refueling mission-3—an overview
US5804760A (en) Method for making and storing cryogenic monopropellant
US7926403B1 (en) Transient, high rate, closed system cryogenic injection
Whitmore et al. N2O/O2 blends safe and volumetrically efficient oxidizers for small spacecraft hybrid propulsion
US5862670A (en) Cyrogenic upper stage for reusable launch vehicle
US2759418A (en) Frozen nitrogen tetroxide-hydrocarbon explosives
McDevitt et al. Initiation step of boiling liquid expanding vapour explosions
Cassutt et al. A study of the hazards in the storage and handling of liquid hydrogen
Stoddard Experimental Investigation of N2O/O2 Mixtures as Volumetrically Efficient Oxidizers for Small Spacecraft Hybrid Propulsion Systems
Whitmore et al. Analyzing and reducing ignition latency of a nytrox/ABS hybrid propulsion system
Velthuysen et al. Safety aspects of nitrous oxide use in hybrid rocket motor design and testing
Negrette et al. The Combustion Response of Liquid Methane and Oxygen Mixtures to Pyrotechnic Ignition
Whitmore et al. Medical Grade N2O/O2 Mixtures as Inexpensive and Volumetrically Efficient Oxidizers for Small Spacecraft Hybrid Propulsion Systems
RU2222749C2 (ru) Емкость для хранения газа
Ribovich et al. Detonation studies with nitric oxide, nitrous oxide, nitrogen tetroxide, carbon monoxide, and ethylene
EP3360856B1 (fr) Procédé de dégazage d'agents propulseurs hypergoliques
Abdelraouf et al. Thrust termination of solid rocket motor
Yagihashi et al. Experimental Study of Temperature and Phase Transition of Liquid Oxygen at Ignition in Impinging Injector of Gas Generator
RU2832113C1 (ru) Вытеснительная система заправки ракеты космического назначения жидким метаном
Rose et al. Integrated refrigeration and storage of LNG for compositional stability
RU2238422C2 (ru) Двигательная установка первой ступени ракеты-носителя воздушно-космической системы
JP2024163418A (ja) 低温液化ガス爆発試験用耐圧容器、及び低温液化ガス爆発試験装置

Legal Events

Date Code Title Description
AK Designated states

Kind code of ref document: A2

Designated state(s): AE AG AL AM AT AU AZ BA BB BG BR BY BZ CA CH CN CR CU CZ DE DK DM DZ EC EE ES FI GB GD GE GH GM HR HU ID IL IN IS JP KE KG KP KR KZ LC LK LR LS LT LU LV MA MD MG MK MN MW MX MZ NO NZ PL PT RO RU SD SE SG SI SK SL TJ TM TR TT TZ UA UG US UZ VN YU ZA ZW

AL Designated countries for regional patents

Kind code of ref document: A2

Designated state(s): GH GM KE LS MW MZ SD SL SZ TZ UG ZM ZW AM AZ BY KG KZ MD RU TJ TM AT BE CH CY DE DK ES FI FR GB GR IE IT LU MC NL PT SE TR BF BJ CF CG CI CM GA GN GQ GW ML MR NE SN TD TG

121 Ep: the epo has been informed by wipo that ep was designated in this application
REG Reference to national code

Ref country code: DE

Ref legal event code: 8642

DFPE Request for preliminary examination filed prior to expiration of 19th month from priority date (pct application filed before 20040101)
122 Ep: pct application non-entry in european phase
NENP Non-entry into the national phase

Ref country code: JP

WWW Wipo information: withdrawn in national office

Country of ref document: JP