EP0141163A1 - Treibladungszusammensetzung - Google Patents

Treibladungszusammensetzung Download PDF

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Publication number
EP0141163A1
EP0141163A1 EP84110646A EP84110646A EP0141163A1 EP 0141163 A1 EP0141163 A1 EP 0141163A1 EP 84110646 A EP84110646 A EP 84110646A EP 84110646 A EP84110646 A EP 84110646A EP 0141163 A1 EP0141163 A1 EP 0141163A1
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Prior art keywords
lead
percent
set forth
combination
weight
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English (en)
French (fr)
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EP0141163B1 (de
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Frank A. Marion
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Universal Propulsion Co Inc
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Universal Propulsion Co Inc
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Priority claimed from US06/530,956 external-priority patent/US4619722A/en
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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
    • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B33/00—Compositions containing particulate metal, alloy, boron, silicon, selenium or tellurium with at least one oxygen supplying material which is either a metal oxide or a salt, organic or inorganic, capable of yielding a metal oxide
    • C06B33/12—Compositions containing particulate metal, alloy, boron, silicon, selenium or tellurium with at least one oxygen supplying material which is either a metal oxide or a salt, organic or inorganic, capable of yielding a metal oxide the material being two or more oxygen-yielding compounds

Definitions

  • This invention relates to materials for prowinding an efficient propulsion of vehicles such as rockets.
  • the invention further relates to materials having a high density and stable properties at ambient temperatures and providing considerable energy at elevated temperatures for producing an efficient propulsion of vehicles such as rockets.
  • the invention is particularly concerned with propellants which combust to provide end products which are not deleterious to the propulsion chamber.
  • the amount of propulsion energy capable of being stored in a limited volume of propulsion material is of prime importance.
  • the volume of propulsion material required to store a particular amount of energy can be accordingly reduced.
  • the rocket to be reduced in size and in weight, thereby causing the drag imposed on the rocket during the flight of the rocket through a fluid such as air or water to be correspondingly reduced.
  • the drag imposed on the rocket is reduced, the amount of energy required to propel the rocket through a particular distance is reduced so that the amount of propulsion material required becomes correspondingly reduced.
  • This in turn allows a further reduction in the size of the vehicle, with a corresponding reduction in drag.
  • a rocket required to push a heavy payload or move through a dense or viscous medium may have an increased efficiency if its propulsion material can be stored in a relatively small volume and can be provided with a high energy level.
  • the propulsion energy of a material is commonly measured in pound-seconds of force per pound of propellant (lb.sec./lb.). For example, if a propellant has a "specific impulse" of two hundred (200) lb.sec./lb., it can produce in a rocket motor two hundred (200) pounds of thrust (or force), per pound of weight of the propellant, for a duration of one (1) second. It can also produce any combination of thrust and time which, when multiplied, equals two hundred (200) lb.sec.per pound of propellant.
  • the density of the propulsion material tends to be reduced since magnesium, titanium and beryllium are relatively light. This has tended to be disadvantageous since the amount of energy obtained in combustion per cubic inch of volume becomes reduced. In other words, even though such metals as beryllium, titanium and magnesium have a high energy, the available energy per cubic inch of the propulsion material has not tended to be increased in view of the decreased density of the material.
  • United States Patent No. 3,945,20.2 issued to me and Hugh J. McSpadden discloses a propellant which overcomes the disadvantages described above.
  • the propulsion materials disclosed and claimed in patent 3,945,202 have a high density and provide a high value of specific impulse. They can be safely and easily formulated and are stable 'at ambient and elevated temperatures. They are not toxic in their formulation, storage or use. Furthermore, density-impulses as high as approximately twenty-four (24) lb.sec. per pound of formulation have been obtained from the propulsion materials disclosed and claimed in this patent.
  • the propulsion materials disclosed and claimed in patent 3,945,202 include a binder, an oxidizer..and a fuel additive.
  • the binder preferably constitutes a hydrocarbon; the oxidizer preferably constitutes an inorganic lead oxidizer; and the fuel additive preferably constitutes particles of a metal such as aluminum.
  • the propellants combust in the combustion chamber to produce end products, one of which may be vaporized lead.
  • the production of vaporized lead in the combustion chamber is not advantageous. This results from the fact that lead vapor is an effective solvent for steel and for other me.tals. Lead vapor condenses at a temperature of approximately 1751°C, whereas iron melts at a temperature of approximately 1530°C. Since the combustion chamber will tend to be made from a material such as iron, the walls of the combustion chamber tend to become melted as the lead is vaporized during combustion. Furthermore, the heat of fusion of iron is approximately 3.67 kilocalories per mole and the heat of vaporization of lead is approximately 46.34 kilocalories per mole. As a result, for each mole of lead vapor condensate produced, 12.6 moles of iron can be melted.
  • lead vapor acts as a solvent on steel and other metals
  • lead oxide does not have such an effect. This results from the fact that lead oxide condenses at a temperature of approximately 1472°C, which is below the melting temperature of iron. Since lead oxide does not have any adverse effects on the. walls of the combustion chamber, it is desirable that the end products of the combustion of inorganic lead oxidizer salts should be lead oxide rather than lead.
  • This invention provides a propellant which preferably includes a binder having hydrocarbon linkages, an inorganic lead oxidizer salt and a fuel made from a fuel additive such as aluminum.
  • the propellant of this invention combusts to produce as an end product lead oxide rather than lead.
  • the propellant of this invention has a density-impulse which approximates, if not exceeds, the density-impulses of the propellants of patent 3,945,202 while providing significantly reduced temperatures during the combustion of the propellant.
  • the propellant of this invention preferably includes a binder having hydrocarbon linkages and a lead compound oxidizer formed from an inorganic lead oxidizer salt.
  • This oxidizer has dense characteristics and stable properties at ambient temperatures and through a particular range of temperatures above ambient.
  • the propellant also includes in one embodiment, a fuel additive, preferably a metal such as aluminum, having properties of being oxidized by the oxidizer and of reducing the lead.
  • the fuel additive has a percentage by weight relative to the lead compound oxidizer to reduce the lead to the lead oxide.
  • the fuel additive is preferably included in such embodiment of the propellant in the range to approximately twenty precent (20%) by weight and is preferably in a fragmentary form.
  • the binder preferably is included in the range of approximately eight percent (8%) to ten percent (10%) by weight.
  • a second oxidizer such as potassium perchlorate may also be included in the propellant.
  • the oxidizers are preferably included in the propellant in the range of approximately seventy-two percent (72%) to ninety-two percent (92%) by weight.
  • An additional binder such as carbon can also be included in the propellant.
  • a second embodiment of the propellant preferably includes a binder also acting as a reducing agent and a lead compound oxidizer formed from an inorganic lead oxidizer salt.
  • This oxidizer has dense characteristics and stable properties at ambient temperatures and through a range of temperatures above ambient.
  • a second oxidizer made from a metallic salt such as potassium perchlorate may also be included in the propellant. Carbon, preferably in particulate form, may also be included in the mixture.
  • the second embodiment dies not include a fuel additive such as aluminum.
  • the different materials are included in the second embodiment in relative amounts by weight to reduce the lead salt in the oxidizer to lead oxide.
  • the oxidizing materials including the lead compound oxidizer may be included in the propellant in the range of approximately eighty-four percent (84%) to ninety-one percent (91%) by weight, the hydrocarbon in the range of approximately eight percent (8%) to ten percent (10%) by weight and the carbon in the range of approximately zero percent (0%) to eight percent (8%) by weight.
  • the propellant of this invention has certain distinct advantages over the propellants of the prior art. It provides high density-impulses and, when combusted, produces end products which do not have any deleterious effects. This results at least partly from the fact that the propellant produces lead oxide rather than lead when it combusts.
  • the propellant is also advantageous in that it generates relatively low temperatures during combustion. For example, temperatures less than 1000°F can be generated by at least some of the propellants of this invention. The invention accomplishes this by eliminating the fuel such as aluminum from the propellant. This is further advantageous in that it tends to simplify the formulation of the 0
  • the formation of the propulsion chamber can be simplified.
  • the walls of the chamber can be made from a relatively standard material such as steel or copper and the heat insulation in the walls of the chamber can be minimized.
  • FIG. 1 schematically illustrates a chamber, generally shown at 10, for combusting the propellants of this invention.
  • the walls of the chamber 10 may be made from a suitable material such as iron or steel.
  • the components of the propellant combust in a burning area 12 and escape through a throat area 14.
  • the propellant is isolated ; from the atmosphere so that the combustion occurs entirely from the components in the propellant.
  • Figure 2 illustrates the relationship between the pressure of the gases escaping from the burning area 12 into the throat area 14 and the rate at which the propellant is combusted in the burning area 12. As will be seen, the relationship between rate and pressure is essentially linear with changes in pressure. Figure 2 also indicates the relationship between pressure of the gases escaping from the burning area 12 into the throat area 14 and the area ratio. As will be seen, this relationship is also essentially linear with changes in pressure.
  • Figure 3 illustrates the pressure of the gases at progressive instants of.time in the chamber illustrated in Figure 1.
  • t a represents the time between an initial pressure of ten percent (10%) of maximum pressure during the period of pressure build up and ten percent (10%) of maximum pressure during the period of pressure reduction.
  • the propellants of this invention include a binder preferably having hydrogen and carbon linkages.
  • the binder includes a material having a formula such as CH 2 .
  • the binder preferably has properties of being cured at a particular temperature.
  • the binder may also be selected from a group including polysulfides, carboxy-terminated polybutadiene polymers, tetrafluorethylene, polyfluorethylene propylene and acetal homopolymers (which do not cure but remain thermoplastic). These binders are advantageous since they retain good physical properties even in environments at high temperatures.
  • Certain of these binders such as the polysulfides and the carboxy-terminated polybutadiene polymers are castable and can be cured at ambient temperatures and also at oven temperatures with other materials to form the propellant formulations constituting the invention.
  • a number of propulsion materials have been formulated successfully with a mixture of a binder such as polybutadiene with carboxy-terminated linkages and a curing agent such as 1, 2, 4 Tris [2-(1-Aziridinyl)Ethyl] Trimellitate.
  • the polybutadiene has been designated as "Butarez CTL Type II ".
  • Such a binder constitutes a liquid rubber polybutadiene with carboxy-terminated linkages. It has carboxy end-groups on both ends of the polymer chain, as illustrated as follows:
  • the binder has a relatively narrow molecular weight distribution and is not easily crystallized. This allows the cured composition of the polymer to remain rubbery to very low temperatures.
  • a lead compound oxidizer such as an oxidizer formed from an inorganic lead oxidizer salts, is also included in the propellant.
  • the oxidizer preferably constitutes lead nitrate.
  • other lead oxidizers such as lead dioxide or lead iodate or any combination of the lead compounds specified above may also be used.
  • Lead nitrate has approximately 0.041 moles of oxygen per cubic centimeter. It has a specific gravity of approximately 4.53 grams per cubic centimeter. It has a decomposition temperature of approximately 470°C and has a heat of formation of only approximately 107.35 Kilocalories per mole of oxygen. It can be reacted chemically to produce reasonably good enthalpy.
  • a fuel additive is also included in one embodiment of the propellant of this invention.
  • the fuel additive is preferably a metal such as aluminum, which becomes oxidized to aluminum oxide by the oxidizer.
  • the. aluminum is in a fragmented form such as in a particulate form.
  • such metal is commonly added as a powder, it can be added as filaments of fine wire or as sheets or strips of thin foil.
  • the aluminum provides substantial physical reinforcement to the propellant. In these forms, the aluminum can provide composites or laminates of high strength. This is desirable since considerable forces must be withstood by a propellant in various applications such as anti-missile rocket applications.
  • metals than aluminum are also theoretically useful as the fuel additive in some propulsion formulations. These include beryllium, magnesium, lithium and titanium. All of these metals are advantageous since they have high melting temperatures. For example, aluminum has a melting temperature of approximately 1220°F and strontium has a melting temperature of approximately 1202°F. In this way, the propulsion materials can be formulated with reasonable safety when these additives are included. Furthermore, although the melting temperatures of these metals are relatively high, they are still below the melting temperature of steel or iron.
  • втори ⁇ ески ⁇ oxidizers include strontium nitrate, barium nitrate, cesium nitrate, rubidium nitrate, ammonium perchlorate, potassium permanganate, potassium chlorate, potassium periodate, potassium nitrate, urea nitrate and guanidine nitrate.
  • strontium nitrate barium nitrate
  • cesium nitrate rubidium nitrate
  • ammonium perchlorate potassium permanganate
  • potassium chlorate potassium periodate
  • potassium nitrate urea nitrate
  • guanidine nitrate guanidine nitrate.
  • This secondary oxidizer preferably constitutes potassium perchlorate.
  • additives have been used to control the rate of propellant burning or to change the sensitivity of the burning rate to pressure.
  • These additives have included copper manganite, cupric oxide, iron oxide and a liquid iron containing a burning rate catalyst designated by the trademark or tradename "HYCAT 6".
  • the amount of additive used has varied between zero percent (0%) and five percent (5%) by weight of the propulsion formulation, but in certain formulations the amount of additive has been as high as approximately fifteen percent (15%).
  • chromium oxide manganese dioxide
  • cuprous oxide cuprous oxide
  • n-butyl ferrocene cupric acetylacetonate
  • molybdenal-bis-acetylacetonate titanium acetylacetonate
  • calcium oxalate calcium oxalate and lead oxalate.
  • the propulsion formulation specified above also has other important advantages.
  • the values of specific impulse for the propellants using the oxidizers specified above range from approximately 190 lb. sec/lb. to approximately 260 lb. sec/lb. and are accordingly within the range of previous propellants
  • the high density of the propellants using these oxidizers produces theoretical values of density-impulse from approximately 22 lb. sec./in 3 to approximately 27.6 lb. sec./in 3 . Comparing such values with previously available values of approximately 15 lb. sec./in 3 , this represents an increase of approximately sixty percent (60%) over the density-impulses of previously available propellants.
  • the materials specified above can be varied in relative amounts to overcome the disadvantage specified in the previbus paragraph without losing any of the advantages specified above.
  • the different materials can be included in the relative percentages specified below for one embodiment of the invention to provide a combustion which produces lead oxide, rather than lead, in the combustion gases:
  • the improved formulation of equation (2) also offers other important advantages.
  • the formulation of equation (2) provides an increased enthalpy over the formulation of equation (1) even though the amount of fuel in the formulation of equation (2) is significantly reduced relative to the amount in the formulation of equation (1).
  • the formulation of equation (2) produces ah estimated combustion enthalpy of approximately -988 gram-calories/gram versus approximately -931 gram-calories/gram estimated for the formulation of equation (1).
  • the increased enthalpy for the formulation of equation (2)' results in part from the formation of lead oxide.
  • the propellant of equation (2) produces an increase of approximately three percent (3%) in density-impulse relative to the propellant of equation (1).
  • the propellant of equation (2) maintains burning rates and other performance characteristics comparable to the propellant of equation (1).
  • the propellant of equation (2) can provide a simple replacement for the propellant of equation (1).
  • the elimination of lead vapor from the exhaust products of the propellant of equation (2) offers significant improvements in the design of the combustion chamber. This can be accomplished by reductions in the required insulating weight and volume of the combustion chamber, by reduction in the size of special seals and heat sinks and reduction in the heat transfer of vapor condensates at -temperatures above the melting point of the material of the chamber walls.
  • the propellant of equation (2) provides an aggregate improvement in product performance and reliability relative to the propellant of equation (1).
  • the decreased amount of the fuel such as aluminum causes the estimated enthalpy to be reduced to an estimated value such as approximately -826 gram-calories/gram from an estimated value of approximately -931 gram-calories/gram for the propellant of equation (1).
  • the propellant of equation (3) has an increase of approximately ten percent (10%) in density relative to the propellant of equation (1). This increase is from a value of approximately 0.10 lb/cubic inch to a value of approximately 0.11 lb/cubic- inch. This results in an estimated decrease of approximately only one percent (1%) in the density-impulse of the propellant of equation (3) relative to the propellant of equation (1).
  • the slight reduction in density-impulse in the formulation of equation (3) relative to the formulation of equation (1) is in contrast to the significant reduction in the temperatures of the combustion gases from the propellant of equation (3) relative to the propellant of equation (1).
  • Corresponding reductions occur in the average molecular weight of the exhaust gases. This can in fact increase the specific impulse to produce an over-all improvement in the density-impulse performance of the propellant formulation of equation (3) relative to the propellant formulation of equation (1).
  • the volume displaced by the reduction in the amount of aluminum can be replaced by an equal volume of high density oxidizer or hydrocarbon binder or by a combination of the two (2).
  • Aluminum has a lower density than the high density oxidizer such as lead nitrate (2.70 vs. 4.53). This causes an increased volume of lead nitrate equal to that in the reduction in the amount of aluminum to produce a sixty-eight percent (68%) increase in specific gravity of lead nitrate relative to aluminum. In other words, replacing aluminum with lead nitrate causes the propellant density to be increased.
  • Aluminum reduces the burning rate of the propellant of equations (1), (2) and (3). Therefore, as the amount of aluminum in the propellant is reduced, the burning of the propellant is accelerated. This allows some of the potassium perchlorate to be removed from the propellant to maintain a particular burning rate.
  • the potassium perchlorate removed from the propellant can be replaced in volume with a corresponding amount of lead nitrate. Potassium perchlorate has a specific ( gravity of approximately 2.5298 grams/cubic centimeter whereas lead nitrate has a specific gravity of approximately 4.53 grams/cubic centimeter. The replacement of the potassium perchlorate by lead nitrate accordingly produces an increase in specific gravity of approximately seventy-nine percenc (79 % ) in a given volume.
  • the combustion enthalpy decreases more rapidly than the increase in density. This causes some reduction in density-impulse to occur.
  • the reduction in the temperature of the exhaust gases from the combustion may facilitate design economy and simplicity within an acceptable level of density-impulse performance to warrant the use of such propellants with reduced amounts of aluminum.
  • Formulations having reduced levels of aluminum are plotted in Figure 4 in triangular coordinates.
  • the amount of the oxidizer is plotted in the vertical direction, with the apex of the triangle indicating an amount of one hundred percent (100%) and the base of the triangle indicating an amount of zero percent (0%).
  • the amount of the hydrocarbon binder is plotted from the left leg of the triangle representing zero percent (0%) as a base and the lower right corner representing one hundred percent (100%).
  • the amount of aluminum is also plotted from the right leg of the triangle representing zero percent (0%) as a base and the lower left corner representing one hundred percent (100%).
  • the levels of aluminum can be varied between approximately zero percent (0%) and twenty percent (20%) by weight.
  • the minimal amount of aluminum is preferably at least two percent (2%) by weight for beneficial effects and less than approximately eighteen percent (18%) by weight. This preferred range provides for ease of mixing, processing and casting.
  • the percentage of the hydrocarbon by weight is preferably between approximately eight percent (8%) and ten percent (10%) to provide optimal density-impulse performance for the propellants. This range of weights for the hydrocarbon carbon also facilitates mixing and processing since the binder is a liquid polymer during the mixing and casting processes.
  • Specific formulas can be developed at any point selected along the curve illustrated in Figure 4.
  • Specific performance criteria such as burning rate, specific impulse and density-impulse can be formulated by extrapolating from established data points or by interpolating between established data points. It will be appreciated, however, that the invention is not to be limited to the formulations along the curve of Figure 4 or the extrapolations or interpolations along the points of such curve.
  • Carbon can be added to the formulations having reduced levels of aluminum.
  • the carbon acts as a heat transfer mechanism to increase the burning rate of the propellant.
  • Carbon also acts as a physical reinforcing agent in the synthetic rubber matrix. Adding carbon also alters the interior ballistics of the propellant by increasing the mols of gas. This results from an increase in the production of carbon monoxide in the combustion gases.
  • the relatively low heat of formation (approximately -26.4 kilocalories per mol) of carbon monoxide provides an additional cooling effect on the combustion gases.
  • Combinations of aluminum and carbon as fuel additives expand the spectrum of useful propellant formulations. Specific performance parameters can be modified or tailored to fit. an exacting application by ranging the levels of the two (2) additives and by changing their weight ratio.
  • the formulations constituting this invention provide certain important advantages.
  • One distinct advantage is the production of lead oxide, rather than lead, in the combustion gases. This has resulted from the reduction in the amount of aluminum oxide produced in the combustion gases. This is an unexpected result since aluminum oxide is the highest enthalpy species produced in the combustion gases.
  • Propellant formulations having high density-impulses and containing less than the stoichiometric ratio of aluminum fuel have demonstrated improvements in ballistic performance in rocket motors.
  • the chemically improved exhaust gases of these propellants have caused substantial improvements in their containment to be obtained and have significantly reduced problems of heat transfer and insulation. These problems have been associated with previous propellants and have been based upon stoichiometric levels of aluminum in the formulations.
  • propellants include a fuel such as aluminum.
  • the propellants of the second embodiment of this invention do not include the fuel such as aluminum.
  • one formulation of this invention may be as follows:
  • This formulation represents a reduction in specific impulse of approximately twenty-two percent (22%) from the propellants which include aluminum. However, since aluminum has been eliminated, the relative amount of the lead nitrate in the formulation is proportionately increased. This causes the formulation of equation (4) to be increased in density by approximately eleven percent (11%). This at least partially compensates for the decrease in the specific impulse of the formulation.
  • the formulation of equation (4) has a number of the advantages discussed above. For example, it produces lead oxide, rather than lead, as an end product during combustion.
  • the formulation of equation (4) also has other advantages in addition to those discussed above. For example, it produces, during combustion, temperatures considerably lower than the conventional propellants of the prior art and the propellants of equations (1), (2) and (3). This enables the throat of the propulsion chamber to be made of a conventional material such as steel or copper. It also enables significant reductions to be provided in the volume and weight of the propulsion chamber. It also provides for significant reductions in the volume and weight of the insulation materials in the propulsion chamber, and particularly at the nozzle exit from the chamber.
  • the temperatures of the propellant exhaust gases can be further reduced by including carbon as a fuel to obtain a propellant such as set forth below:
  • This propellant has a high density and burns at a relatively low temperature. It can be considered as a high density "cool” gas generator. It provides an estimated heat of combustion of approximately -360 gram-calories/gram with an average density or specific gravity of approximately 0.099 pounds (lb)/(in 3 ).
  • the propellant may be as specified below:
  • H f -94.05 kilocalories/mol.
  • all of the oxygen in the propellant is used to generate carbon dioxide in the combustion, except for the one half (1/2) mole of oxygen used to generate lead oxide (Pb0). This produces the maximum heat of combustion from the available oxygen.
  • a comparison of equations (6) and (7) indicates that two (2) moles of carbon monoxide are produced in the propellant of equation (6) in comparison to each mole of carbon dioxide produced by the propellant of equation (7).
  • the addition of carbon to the propellant tends to be advantageous since it facilitates the use of oxygen in the formation of carbon monoxide. This produces an increase in the moles of exhaust gases produced in the combustion, a decrease in the average molecular weight of such exhaust gases and a reduction in the combustion enthalpy. It also tends to cool the exhaust gases.
  • carbon monoxide in the exhaust gases also has other important advantages in the production of gas generators in addition to those discussed above.
  • carbon monoxide is chemically stable and is not chemically reactive. It also has a low oxidizing potential and a low heat of formation of approximately -26.4 kilocalories/mol. Because of this low heat formation, it would appear that oxygen can be easily removed from the carbon monoxide. However, the heat of formation of carbon vapor is approximately 17.17 kilocalories/ mol. Because of the considerable difference between the heat of formation of carbon monoxide and the heat of formation of carbon vapor, carbon monoxide is quite resistant to thermal disassociation.
  • the range of practical formulations of propellants including a hydrocarbon binder, oxidizers and carbon is shown in Figure 5.
  • the hydrocarbon binder has a range of approximately eight percent (8%) to ten percent (10%) by weight
  • the oxidizers have a range of approximately eighty-four percent (84%) to ninety-one percent (91%) by weight
  • the carbon has a range of approximately zero percent (0%) to eight percent (8%) by weight.
  • the propellants disclosed above as being included in this inventon have certain important advantages. They produce lead oxide, rather than lead, in the exhaust gases. This allows the walls of the combustion chamber to be made from conventional materials such as iron or steel without damaging such walls during the combustion.
  • the propellants produce the exhaust gases at relatively low temperatures during the combustion. For example, some of the propellants of this invention even produce exhaust gases with temperatures below 1000° F during the combustion. This allows the walls of the chamber to be made from such materials as copper and it further allows the amount of insulation in the chamber to be minimized.
  • the propellants of this invention also produce, during the combustion, a relatively high energy per cubic inch of the propellant.

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  • Chemical & Material Sciences (AREA)
  • Organic Chemistry (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Solid Fuels And Fuel-Associated Substances (AREA)
  • Liquid Carbonaceous Fuels (AREA)
EP19840110646 1983-09-12 1984-09-06 Treibladungszusammensetzung Expired EP0141163B1 (de)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US530956 1983-09-12
US06/530,956 US4619722A (en) 1983-09-12 1983-09-12 Propellant material with oxidizer reduction to lead oxide
US54785483A 1983-11-02 1983-11-02
US547854 1995-10-25

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EP0141163A1 true EP0141163A1 (de) 1985-05-15
EP0141163B1 EP0141163B1 (de) 1988-11-30

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EP (1) EP0141163B1 (de)
BR (1) BR8404538A (de)
DE (2) DE3475398D1 (de)
ES (1) ES535857A0 (de)
IL (1) IL72838A (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2725012A1 (fr) * 1990-03-26 1996-03-29 Marconi Co Ltd Reacteur a lithium et eau

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1571251A1 (de) * 1966-08-24 1971-09-30 Bundesrep Deutschland Nicht-hygroskopischer und perchloratfreier bzw.perchloratarmer Composite-Double-Base-Festtreibstoff
US3834956A (en) * 1967-08-08 1974-09-10 Hercules Inc Solid propellant composition containing lead and lead compounds
US3945202A (en) * 1970-08-27 1976-03-23 Universal Propulsion Co. Rocket containing lead oxidizer salt-high density propellant

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1571251A1 (de) * 1966-08-24 1971-09-30 Bundesrep Deutschland Nicht-hygroskopischer und perchloratfreier bzw.perchloratarmer Composite-Double-Base-Festtreibstoff
US3834956A (en) * 1967-08-08 1974-09-10 Hercules Inc Solid propellant composition containing lead and lead compounds
US3945202A (en) * 1970-08-27 1976-03-23 Universal Propulsion Co. Rocket containing lead oxidizer salt-high density propellant

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2725012A1 (fr) * 1990-03-26 1996-03-29 Marconi Co Ltd Reacteur a lithium et eau

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BR8404538A (pt) 1985-08-06
ES8603163A1 (es) 1985-12-16
IL72838A (en) 1989-01-31
DE3475398D1 (en) 1989-01-05
ES535857A0 (es) 1985-12-16
DE141163T1 (de) 1986-04-30
EP0141163B1 (de) 1988-11-30

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