US20120124897A1 - Propellant Compositions and Methods of Making and Using the Same - Google Patents

Propellant Compositions and Methods of Making and Using the Same Download PDF

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US20120124897A1
US20120124897A1 US13/295,268 US201113295268A US2012124897A1 US 20120124897 A1 US20120124897 A1 US 20120124897A1 US 201113295268 A US201113295268 A US 201113295268A US 2012124897 A1 US2012124897 A1 US 2012124897A1
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propellant
astm
hydrocarbon fluids
measured
proto
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Kevin Kelly
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Total Marketing Services SA
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Fina Technology Inc
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Priority claimed from US12/949,980 external-priority patent/US8574322B2/en
Application filed by Fina Technology Inc filed Critical Fina Technology Inc
Priority to US13/295,268 priority Critical patent/US20120124897A1/en
Assigned to FINA TECHNOLOGY, INC. reassignment FINA TECHNOLOGY, INC. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: KELLY, KEVIN P.
Priority to PCT/US2011/061181 priority patent/WO2012068369A1/en
Priority to ES11840828T priority patent/ES2822133T3/es
Priority to EP11840828.5A priority patent/EP2640953B1/en
Priority to KR1020137012626A priority patent/KR101831218B1/ko
Priority to CN201180055335.8A priority patent/CN103282635B/zh
Priority to JP2013540012A priority patent/JP5914511B2/ja
Priority to TW100142309A priority patent/TW201235331A/zh
Publication of US20120124897A1 publication Critical patent/US20120124897A1/en
Assigned to TOTAL RAFFINAGE MARKETING reassignment TOTAL RAFFINAGE MARKETING ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: FINA TECHNOLOGY, INC.
Priority to IL226174A priority patent/IL226174A0/en
Abandoned legal-status Critical Current

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    • 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
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid 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
    • 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
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/28—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants having two or more propellant charges with the propulsion gases exhausting through a common nozzle

Definitions

  • the present disclosure generally relates to propellant formulations. Specifically, the present disclosure relates to the combination of hydrocarbon streams to manufacture rocket propellant having specific characteristics.
  • rocket propellant in combination with liquid oxygen, is used as the propellant system in a large percentage of launch vehicles and rockets.
  • supply is limited, resulting in little opportunity to optimize fuel formulations.
  • limited supply results in little to no redundancy in supply in the event of supply shortages/failures.
  • a method of manufacturing a rocket propellant including combining at least two hydrocarbon fluids is disclosed.
  • FIG. 1 illustrates a traditionally manufactured RP-1 propellant distillation curve.
  • FIG. 2 illustrates distillation curves for blend stocks.
  • FIG. 3 illustrates distillation curve data of formulated propellants.
  • FIG. 4 illustrates density data for formulated propellants.
  • FIG. 5 illustrates distillation curve data of blend stocks.
  • FIG. 6 illustrates distillation curves of formulated propellants.
  • FIG. 7 illustrates density data for formulated propellants.
  • FIG. 8 illustrates weight savings of formulated propellants.
  • FIG. 9 illustrates hydrogen content for formulated propellants.
  • FIG. 10 illustrates the net heat of combustion for formulated propellants.
  • FIG. 11 illustrates distillation curve data of formulated propellants.
  • FIG. 12 illustrates distillation curves for formulated propellants and traditionally manufactured RP-1 propellant.
  • Embodiments of the present invention relate to formulated propellants.
  • a large percentage of those vehicles are launch vehicles and rockets, while additional vehicles include hypersonic space planes, such as those powered by ramjets or scramjets, for example.
  • Ramjets are generally jet engines that utilize a jet's forward motion to compress incoming air, which generally cannot produce thrust at zero airspeed and thus cannot move a jet aircraft from a standstill.
  • a scramjet is a variant of the ramjet in which the combustion process takes place in supersonic airflow.
  • Rockets generate thrust by expelling mass behind them at high speed. Chemical rockets react propellant and oxidizer, such as liquid oxygen, in a combustion chamber creating a stream of high velocity gas to produce thrust.
  • oxidizer such as liquid oxygen
  • Specific impulse of a rocket propellant is a parameter that relates the thrust generated to the mass flow rate of propellant into the combustion chamber.
  • the ratio is proportional to the square root of the chamber temperature and inversely proportional to the square root of the chamber content molecular weight.
  • Specific impulse increases with increasing chamber temperature (which results in higher chamber pressures) and decreasing molecular weight of combustion products (which achieve higher exhaust velocities than heavier products).
  • Specific impulse is essentially a momentum term. Increasing the mass of fuel burned in a given amount of time or the velocity of the exhaust gases will generally have a beneficial effect on specific impulse. Higher specific impulses are desirable since greater thrusts are generated for a given weight of fuel combusted. The result is that a greater payload can be lifted into orbit or a higher orbit can be achieved than would otherwise be possible.
  • RP-1 propellant Many of the current users of propellant use a propellant that meets the “RP-1” specification (hereinafter referred to as an “RP-1 propellant”). Other users that are more sensitive to sulfur content require the use of a propellant that meets the RP-2 specification. Certain relevant chemical and physical property specifications for RP-1 and RP-2 propellants are shown in Table 1 below.
  • RP-1 propellants are highly refined kerosene similar to jet fuel. Kerosene is generally obtained from the fractional distillation of petroleum between 140° C. and 250° C., resulting in a mixture of molecules with carbon chains lengths between 10 and 25 carbon atoms.
  • RP-1 propellants may have an average molecular weight of about 175, a density of about 0.82 g/ml and a boiling point range of from 350° F. (176° C.) to 525° F. (273° C.).
  • the propellants of the present invention are formulated by blending one or more hydrocarbon fluids to form formulated propellants.
  • hydrocarbon fluids is used in a generic sense to describe a wide range of materials used in an equally wide range of applications.
  • the hydrocarbon fluids generally utilized for the formulated propellants described herein may be produced by a number of processes.
  • hydrocarbon fluids can be produced from severe hydrotreating, deep hydrotreatment or hydrocracking to remove sulfur and other heteroatoms or polymerization or oligomerization process, such processes being followed by distillation to separate them into narrow boiling ranges.
  • isoparaffins derived from oligomerization may constitute hydrocarbon fluids.
  • hydrocarbon fluids are described in U.S. Pat. No. 7,311,814 and U.S. Pat. No. 7,056,869, which are incorporated by reference herein.
  • hydrocarbon fluids tend to have a narrow boiling point range, e.g., less than 500° F. (260° C.), or 300° F. (148° C.) or 100° F. (37° C.), for example.
  • narrow cuts provide a more narrow flash point range and provide for tighter viscosity, improved viscosity stability and defined evaporation specifications, as shown by the distillation curve, for example.
  • the hydrocarbon fluids may be produced by hydrocracking a vacuum gas oil distillate followed by fractionating and/or hydrogenating the hydrocracked vacuum gas oil.
  • Such fluids may have an ASTM D86 boiling point range of from 212° F. (100° C.) to 752° F. (400° C.), wherein the individual hydrocarbon fluids may have the narrower boiling ranges described herein.
  • the fluids may further have a naphthenic content of at least 40 wt. %, or 60 wt. % or 70 wt. %, for example.
  • the fluids may further have an aromatics content of less than 2 wt. %, or 1.5 wt. % or 1.0 wt. %, for example.
  • the fluids may further have an aniline point below 212° F. (100° C.), or 205° F. (96° C.) or 200° F. (93° C.), for example.
  • the hydrocarbon fluids have low sulfur concentrations e.g., less than 30 ppm, or less than 15 ppm or less than 3 ppm, aromatics contents that are below 1.0 vol. %, or 0.5 vol. % or 0.01 vol. %, for example, relatively high net heats of combustion, and narrow distillation ranges.
  • the hydrocarbon fluid may be further characterized as predominantly paraffinic, isoparaffinic, or naphthenic (e.g., greater than 40 wt. %, or 50 wt. % or 60 wt. % or 80%). While such characterization may be helpful in blending to achieve very low densities and/or high net heats of combustion, such characterization is not a necessary condition for formulation of propellants.
  • the hydrocarbon fluids can be derived from any suitable starting material that can result in materials that meet the final use requirements. It is to be noted that starting materials need not fall into final product boiling range, as in the gas oil case stated above.
  • starting materials for production of hydrocarbon fluids can be gas oils or other high molecular weight material (that are further hydrocracked to lower molecular weight materials or deep hydrotreated to decrease sulfur content, materials that are normally classified as distillates, such as kerosene, straight run diesel, ultralow sulfur diesel, coker diesel (with sufficient hydroprocessing), or light cycle oil from FCC units, for example.
  • Starting materials can be kerosene or gas oils from Gas to Liquid process or from biomass conversion processes.
  • biodiesel and biojet are used as starting materials. Typically, biodiesel and biojet are hydroprocessed to remove oxygen.
  • triglycerides that, after processing yield a carbon chain in the C12 to C18 range, are used as starting materials.
  • Biodiesel and biojet may be plant or animal sourced.
  • the starting materials may be olefins to produce the hydrocarbon fluids, olefins being polymerized or oligomerized.
  • the starting materials may include propene, butene or combinations thereof, for example. Olefins may be produced from traditional sources such as a naphtha cracker.
  • olefins are produced from dehydration of low carbon number alcohols.
  • Low carbon number alcohols may be produced through various biomass fermentation processes.
  • hydrocarbon fluids can include gas oil, kerosene, straight run diesel, ultralow sulfur diesel, coker diesel, light cycle oil, hydrodewaxed gasoil or kerosene cuts, ethylene, propene, butene or combinations thereof.
  • the hydrocarbon fluids are generally components selected from C 9 -C 18 or narrower distillation cuts.
  • distillation cuts characterizing hydrocarbon fluids that may be blended to form the formulated propellant include SPIRDANE® (e.g., D-40 having a density of about 0.790 g/mL, a boiling range of 356° F.-419° F. (180-215° C.), flash point of 107.6° F. (42° C.) and D-60 having a density of about 0.770 g/mL, a boiling range of 311° F.-392° F. (155-200° C.), flash point of 145° F.
  • SPIRDANE® e.g., D-40 having a density of about 0.790 g/mL, a boiling range of 356° F.-419° F. (180-215° C.), flash point of 107.6° F. (42° C.) and D-60 having a density of about 0.770 g/mL, a boiling range of 311
  • KETRUL® e.g., D-70 having a density of about 0.817 g/mL, a boiling range of 381° F.-462° F. (193-238° C.), flash point of 160° F. (71° C.) and D-80 having a density of about 0.817 g/mL, a boiling range of 397° F.-465° F. (202-240° C.), flash point of 170.6° F. (77° C.)), HYDROSEAL® (e.g., G 232 H) and ISANE IP® fluids, commercially available from TOTAL FLUIDES, S.A., ISOPARTM fluids, commercially available from ExxonMobil Chemical Corp. and IP2835, commercially available from Idemitsu Corp.
  • HYDROSEAL® e.g., G 232 H
  • ISANE IP® fluids commercially available from TOTAL FLUIDES, S.A., ISOPARTM fluids, commercially available from ExxonMobil Chemical
  • the formulated propellants include two or more hydrocarbon fluids.
  • the formulated propellant includes two hydrocarbon fluids.
  • the formulated propellant includes three hydrocarbon fluids.
  • the formulated propellant includes four hydrocarbon fluids. Individual hydrocarbon fluids are chosen for formulation into propellants depending on how each contributes to the final properties of a rocket fuel blend.
  • the formulated propellant is formulated to exhibit a particular distillation curve or aspects of a particular distillation curve.
  • the formulated propellant may be designed to have a front end within the fuel evaporated limits designated in Table 1 and an endpoint at or below the temperature of the endpoint specified in Table 1.
  • a plurality of hydrocarbon fluids may be blended to create a formulated propellant that meets the RP-1 specifications for “fuel evaporated” and “end point.”
  • the formulated propellant may be formulated from a broad spectrum of hydrocarbon fluids that in and of themselves do not meet the desired specification. Further, known jet fuel formulations may be incorporated with the hydrocarbon fluid. By utilizing such combinations, a broader tailored property distribution is achievable.
  • a specific, non-limiting formulated propellant may be formed of a first hydrocarbon fluid having an end point higher than the desired specification while a second hydrocarbon fluid may have an end point below that of the desired specification to achieve a blend that has an end point that falls within the desired specification. Further, by selecting the individual hydrocarbon fluids, it may be possible to replicate a desired distillation curve within an acceptable margin.
  • a single hydrocarbon fluid may be used as a propellant, such as one that falls within or overlaps the distillation range for a particular propellant specification, such as RP-1
  • the combination of two or more fluids results in greater flexibility in how closely it is possible to match the entirety of the desired distillation curve. For instance, when matching two points within the specification for RP-1 propellant distillation curves, for example the 10% and final point, it may not be necessary to match the entire RP-1 propellant curve to be within the specification.
  • a formulated propellant that more closely matches the desired distillation curve, thereby improving performance or standardizing performance, for instance.
  • hydrocarbon fluids may be blended to achieve numerous other characteristics.
  • hydrocarbon fluids may be blended to achieve formulated propellants with certain cold flow properties such as pour point, cloud point, freeze point and viscosity.
  • hydrocarbon fluids may be blended to achieve certain propellant performance characteristics, such as density, hydrogen content, and net heat of combustion.
  • hydrocarbon fluids that have a flash point below the RP-1 propellant specification of 140° F. (60° C.) may be used in the formulation, but only in amounts that do not reduce the flash point of the final blend below the specification.
  • fluids with freeze points above the ⁇ 60° F. ( ⁇ 51° C.) maximum specification, such as those with a minor amount of aromatics, may be included in the blend as long as the final freeze point is below the RP-1 propellant specification value.
  • hydrocarbon fluids from which aromatics have been reduced/removed yields another benefit to the propellant.
  • the reduced amount of aromatics in the hydrocarbon fluid components leads to a higher net heat of combustion for the hydrocarbon fluids components used as blend stock.
  • the combination of these high net heat of combustion hydrocarbon fluids results in a product that exceeds the 18,500 BTU/pound minimum specification of RP-1 propellant.
  • the net heat of combustion is from 18,500 BTU/pound to 19,000 BTU per pound as measured by ASTM D-240.
  • the net heat of combustion is between 18,700 BTU/pound to 18,900 BTU/pound as measured by ASTM D-240.
  • the use of hydrocarbon fluids from which aromatics have been removed or reduced may also increase hydrocarbon content of the formulated propellant.
  • isoparaffinic blend stocks may help to raise the net heat of combustion when included in the blend, as such blend stocks' net heat of combustion is greater than aromatics or naphthenics that are characterized by the same carbon number.
  • Normal paraffin blend stock may also raise the net heat of combustion.
  • Different blend stocks may have different rates of combustion.
  • designers of rocket engines prefer a particular range or rate of combustion in order to make sure the flame front propagates through the rocket engine at a desired rate.
  • a rate of combustion that is too fast may result in combustion completion before the desired point in the engine.
  • a rate of combustion that is too slow may result in the opposite problem.
  • normal parrafins have a very high rate of combustion.
  • Isoparrafins typically have a lesser rate of combustion.
  • the isoparrafin/paraffin ratio of the blend stocks are controlled to achieve an optimized rate of combustion for the formulated propellant.
  • Density is an important parameter of the propellant as it determines the weight of the fuel that must be lifted by the vehicle.
  • hydrocarbon fluids may be chosen to alter the density of the final blend.
  • naphthenic based fluids will tend to raise the final density while isoparaffinic fluids tend to reduce the density of the final product.
  • Materials that contain a significant amount of naphthenes and are at the high end of the distillation curve relative to a propellant specification such as RP-1, such as HYDROSEALS®, can be used to increase the density of the blended product.
  • the density at 15° C. is between 0.77 and 0.82, between 0.799-0.815, between 0.81 to 0.8135, and between 0.77 to 0.80, as measured by D-1298.
  • the propellant may include a first hydrocarbon fluid having a density greater than 0.8 g/ml and a second hydrocarbon fluid having a density less than 0.8 g/ml, for example.
  • the formulated propellants may have a weight that is about 5%, or 7% or 9% less than the weight of the RP-1 propellant, for example.
  • Hydrogen content of the propellant has a significant effect on the performance of the propellant. Generally, the higher the hydrogen content, the higher the Isp of the propellant. In certain embodiments, in order to keep the exhaust molecular weight low, the rocket engine is run slightly fuel rich to produce CO rather than CO 2 as a combustion product. As the hydrogen content is increased, the amount of oxidizer needed (the mixture ratio) to combust the propellant also may increases because more atoms are present for a given carbon number compound. Specifically, an increase in the fuel hydrogen to carbon ratio results in a stoichiometric oxygen to fuel ratio increase. Thus, more moles of gas are expelled from the exhaust nozzle as combustion products.
  • the hydrogen content of the formulated propellant is controlled by increasing the ratio of hydrogen of carbon atoms of the molecules of the hydrocarbon fluid blend stocks. For instance, reducing rings and branching and increasing the degree of hydrogen saturation of hydrocarbon molecules increases the hydrogen:carbon atom ratio, thereby increasing hydrogen content of the propellant. Removing or reducing aromatics in the hydrocarbon fluid blend stocks may result in a significant increase in hydrogen content.
  • Hydrogen content in certain embodiments of rocket propellant of the present disclosure are from 14.25-15 wt %, from 14-14.8 wt %, less than 15.3 wt %, and between 14.8 and 15 wt % as measured by ASTM D-3343
  • the hydrocarbon fluids used in the blended formulated propellant have very low sulfur concentration. Sulfur adversely affects propellant performance in a number of ways, including reducing the net heat of combustion and increasing fouling. Therefore in some embodiments, the formulated propellants include significantly reduced sulfur contents compared to conventional RP-1 propellants.
  • the formulated propellants may include less than 30 ppm or less than 5 ppm sulfur. In other embodiments, the formulated propellants contain less than 3 ppm sulfur or less than 1 ppm sulfur.
  • the formulated propellants Due to the significant absence of olefins and aromatics from the formulated propellant, the formulated propellants exhibit improved thermal stability over a traditionally manufactured RP-1 propellant.
  • Engines utilized in the vehicles described herein may include cooling coils around an exhaust nozzle through which fuel from tanks flows prior to injection into a combustion chamber. The cooling coils periodically foul, in large part due to aromatics and/or olefins present in the propellant. Accordingly, the formulated propellants provide a fuel that may allow reuse of booster stage rocket motors due to significantly reduced, if not eliminated, cooling coil fouling, for example.
  • RP-1 propellant may be used in both the booster stage and in upper stages. However, it is more common for upper stages to include or entirely use higher energy fuels because of density and performance issues with RP-1.
  • formulated propellants consistent with this disclosure may be used in upper stages, either alone, or in combination with higher energy fuels.
  • the formulated propellant may be combined with powdered metal capable of forming a metal oxide in order to achieve a higher level of specific impulse.
  • a metal is aluminum.
  • the formulated propellants of the present disclosure overcome problems of certain traditional RP-1 propellants' availability/performance by blending existing hydrocarbon fluids to produce a propellant at least equal in properties and cost, if not superior to, traditionally manufactured RP-1 propellants. Further, the formulated propellants of the present disclosure can be tailored to provide properties such as density, hydrogen content, and heat of combustion while exhibiting the ability to maintain a higher level of specific impulse (Isp) than that available with conventionally manufactured RP-1.
  • Isp specific impulse
  • the formulated propellant may contain various additives, such as dyes, antioxidants, metal deactivators, and combinations thereof, for example.
  • a sample of traditionally manufactured RP-1 propellant and samples of various formulated propellants were analyzed by D-86, density, aniline point, cloud point, sulfur content, and aromatics content by FIA.
  • the distillation curve and density were used to calculate hydrogen content by ASTM D-3343.
  • the distillation curve, density, aniline point, sulfur content, and aromatics content were used to calculate the net heat of combustion by ASTM D-4529.
  • a sample of traditionally manufactured RP-1 propellant was obtained and analyzed, with results illustrated in the data below.
  • the density was measured at 15° C., as required by ASTM D-4529, which is an estimation of the net heat of combustion.
  • Subsequent density measurements made on formulated propellants were done on the same basis. The latter was used to calculate the net heat of combustion.
  • the traditionally manufactured RP-1 propellant would also be characterized by the presence of naphthenic rings. Its hydrogen content of 14.3% was consistent with a single naphthenic ring per molecule.
  • the traditionally manufactured RP-1 propellant distillation curve is shown in FIG. 1 . The lines were inserted to show the distillation curve specifications for RP-1 propellant. The 10% point must be reached between 365° F. (185° C.) and 410° F. (210° C.) and the end point must be below 525° F. (273° C.) for RP-1 specifications.
  • traditionally manufactured RP-1 propellant is a narrow cut consisting of carbon number compounds ranging from C 12 to C 18 . The gradual increase in temperature with percent distilled is indicative of a complex mixture of multiple carbon number compounds.
  • the materials analyzed for use in the formulated propellants were SPIRDANE® D-40, SPIRDANE® D-60, KETRUL® D-70, KETRUL® D-80, HYDROSEAL® G 232 H, ISANE IP® 175, and ISANE IP® 185.
  • the distillation curves for these components are shown in FIG. 2 . Data is shown relative to the distillation curve for the traditionally manufactured RP-1 propellant. None of the individual components was a close enough match to the traditionally manufactured RP-1 propellant to be used “as is,” i.e. without formulation.
  • the components were either higher boiling, as was the G 232H, lower boiling, like the D-60, or characterized by a narrower boiling range, like the D-80.
  • this combination of attributes for the blend components allows flexibility in blending as the front, middle, and back end of the distillation curve for the propellant can be tailored to match the RP-1 specification.
  • various characteristics of the propellant relating to the distillation curve or other properties can be optimized through the appropriate selection of components for blending.
  • ISANE IP® materials were close to that of the traditionally manufactured RP-1 propellant.
  • ISANE IP® materials were characterized by a lower density than that of the traditionally manufactured RP-1 propellant.
  • the net heats of combustion and hydrogen content for those components, including ISANE IP® materials, were comparable to the traditionally manufactured RP-1 propellant.
  • Cloud point data for all formulations was below the freeze specification of ⁇ 60° F. ( ⁇ 51° C.) indicating that all have an acceptable freeze point.
  • the sulfur content of the traditionally manufactured RP-1 propellant was measured at 1 ppm by wavelength dispersive x-ray fluorescence, as noted earlier.
  • Prototype formulations were at the limit of detection for that method with measurements at 0.5-0.6 ppm. These values are very close to the 0.1 ppm max limit for an RP-2 formulation.
  • the density measurements were very close to that of the traditionally manufactured RP-1 propellant, albeit slightly higher, but still within the RP-1 specification. This was consistent with the density of the blend stocks that were slightly above that of the traditionally manufactured RP-1 propellant. The density measurements are compared in FIG. 4 .
  • ISANE IP® 175 and 185 are characterized by densities significantly lower than the traditionally manufactured RP-1 propellant, but have flash points that are at or above that of the RP-1 specification. The density of each of these was below 0.77 g/ml, a significant reduction relative to other blend components and the traditionally manufactured RP-1 propellant. Additionally, the hydrogen content was measured between 15.1 and 15.2. This is in agreement with the theoretical value for a fully saturated sample with no naphthenic rings in the C 12 to C 18 range and as reflected by typical values reported on the certificate of analysis for these materials.
  • the distillation curve data for traditionally manufactured RP-1 propellant is shown in FIG. 5 in comparison with certain hydrocarbon fluids.
  • the new materials are very narrow cuts with end points below 400° F. (204° C.). This necessitates the use of a middle and heavy cut in order to create an RP-1 propellant formulation. Additionally, the front end of the distillation curve was very clean indicating that few very light, low flash point compounds were present making these ideal blend components for the light portion of the formulation.
  • the prototype blends formulated with the new components were designated proto-9 through proto-12. The composition of these blends is shown in Table 4.
  • the distillation curves corresponding to the new formulations are shown in FIG. 6 .
  • Proto-9 matched the traditionally manufactured RP-1 propellant distillation curve closely.
  • Proto-11 was designed to be a low density propellant, as shown by the rather high concentration of ISANE IP®175 in its formulation.
  • Proto-10 and Proto-12 were formulated to contain a greater proportion of middle boiling compounds and examine the difference between the contributions of D-70 versus D-80 to the distillation curve. As shown, the difference was minimal for the quantities used.
  • the immediate effect of the presence of replacing the lower boiling components with isoparaffins can be seen on the density measurement in FIG. 7 .
  • the step change in density is apparent.
  • the low-density blend proto-11 was measured at 0.7744 g/ml.
  • the weight saved through use of the low-density prototypes is shown in FIG. 8 .
  • the upper stage weight savings for proto-9, the distillation curve copy of the traditionally manufactured RP-1 propellant, is nearly 7% of the orbital payload. This savings is about 9% for the low-density proto-11. This is a huge increase in payload.
  • the hydrogen content for the prototypes is shown in FIG. 9 .
  • Replacing some of the compounds that are naphthenic in nature with the fully saturated isoparaffins resulted in a net increase in hydrogen content to nearly 14.9 for the traditionally manufactured RP-1 propellant copy proto-9 and to 15 for the low-density formulation, proto-11. This was a significant increase relative to the traditionally manufactured RP-1 propellant sample.
  • the net heat of combustion for the prototypes is shown in FIG. 10 .
  • Proto-20 was formulated.
  • Proto-20 like proto-6 and proto-9 was designed to match within reasonable limits the distillation curve associated with traditionally produced RP-1 propellant.
  • FIG. 11 illustrates the distillation curves for all four formulations.
  • proto-20 was also designed to provide an intermediate density, hydrogen content, and net heat of combustion between proto-6 and proto-9.
  • Proto-20 has a density at 15° C. of 0.8001, a hydrogen content of 14.51 wt %, and a net heat of combustion of 18,736 BTU/lb.

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US13/295,268 2010-11-19 2011-11-14 Propellant Compositions and Methods of Making and Using the Same Abandoned US20120124897A1 (en)

Priority Applications (9)

Application Number Priority Date Filing Date Title
US13/295,268 US20120124897A1 (en) 2010-11-19 2011-11-14 Propellant Compositions and Methods of Making and Using the Same
JP2013540012A JP5914511B2 (ja) 2010-11-19 2011-11-17 推進薬組成物、その作製方法、およびその使用方法
CN201180055335.8A CN103282635B (zh) 2010-11-19 2011-11-17 一种制造火箭推进剂的方法
EP11840828.5A EP2640953B1 (en) 2010-11-19 2011-11-17 Method of manufacturing a rocket propellant
ES11840828T ES2822133T3 (es) 2010-11-19 2011-11-17 Método de fabricación de un propulsor de cohete
PCT/US2011/061181 WO2012068369A1 (en) 2010-11-19 2011-11-17 Propellant compositions and methods of making and using the same
KR1020137012626A KR101831218B1 (ko) 2010-11-19 2011-11-17 추진제 조성물 및 그의 제조 방법 및 이용 방법
TW100142309A TW201235331A (en) 2010-11-19 2011-11-18 Propellant compositions and methods of making and using the same
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KR20140042765A (ko) 2014-04-07
CN103282635A (zh) 2013-09-04

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