US3181937A - Rocket hydrofuel container with chemical heating device - Google Patents
Rocket hydrofuel container with chemical heating device Download PDFInfo
- Publication number
- US3181937A US3181937A US475053A US47505354A US3181937A US 3181937 A US3181937 A US 3181937A US 475053 A US475053 A US 475053A US 47505354 A US47505354 A US 47505354A US 3181937 A US3181937 A US 3181937A
- Authority
- US
- United States
- Prior art keywords
- container
- heating
- hydrofuel
- composition
- rocket
- 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.)
- Expired - Lifetime
Links
- 238000010438 heat treatment Methods 0.000 title claims description 51
- 239000000126 substance Substances 0.000 title description 5
- 239000000203 mixture Substances 0.000 claims description 34
- 239000000446 fuel Substances 0.000 claims description 13
- 239000007787 solid Substances 0.000 claims description 12
- 229910052782 aluminium Inorganic materials 0.000 claims description 9
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 9
- 239000003380 propellant Substances 0.000 claims description 8
- QPLDLSVMHZLSFG-UHFFFAOYSA-N Copper oxide Chemical compound [Cu]=O QPLDLSVMHZLSFG-UHFFFAOYSA-N 0.000 claims description 7
- 239000005751 Copper oxide Substances 0.000 claims description 7
- 229910000431 copper oxide Inorganic materials 0.000 claims description 7
- 229910052751 metal Inorganic materials 0.000 claims description 7
- 239000002184 metal Substances 0.000 claims description 7
- AXZAYXJCENRGIM-UHFFFAOYSA-J dipotassium;tetrabromoplatinum(2-) Chemical compound [K+].[K+].[Br-].[Br-].[Br-].[Br-].[Pt+2] AXZAYXJCENRGIM-UHFFFAOYSA-J 0.000 claims description 5
- 229910001487 potassium perchlorate Inorganic materials 0.000 claims description 5
- 238000002485 combustion reaction Methods 0.000 claims description 4
- 238000005086 pumping Methods 0.000 claims description 3
- UQSXHKLRYXJYBZ-UHFFFAOYSA-N iron oxide Inorganic materials [Fe]=O UQSXHKLRYXJYBZ-UHFFFAOYSA-N 0.000 claims description 2
- LIKBJVNGSGBSGK-UHFFFAOYSA-N iron(3+);oxygen(2-) Chemical compound [O-2].[O-2].[O-2].[Fe+3].[Fe+3] LIKBJVNGSGBSGK-UHFFFAOYSA-N 0.000 claims 1
- 238000006243 chemical reaction Methods 0.000 description 7
- 239000004927 clay Substances 0.000 description 6
- 239000000463 material Substances 0.000 description 6
- 238000002844 melting Methods 0.000 description 6
- 230000008018 melting Effects 0.000 description 6
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 5
- 239000007788 liquid Substances 0.000 description 5
- 239000007789 gas Substances 0.000 description 4
- 229910052744 lithium Inorganic materials 0.000 description 4
- 239000003832 thermite Substances 0.000 description 4
- 229910000831 Steel Inorganic materials 0.000 description 3
- 239000010959 steel Substances 0.000 description 3
- 235000015842 Hesperis Nutrition 0.000 description 2
- 235000012633 Iberis amara Nutrition 0.000 description 2
- 239000004615 ingredient Substances 0.000 description 2
- 150000002739 metals Chemical class 0.000 description 2
- 239000007800 oxidant agent Substances 0.000 description 2
- 239000002245 particle Substances 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 229910018182 Al—Cu Inorganic materials 0.000 description 1
- OYPRJOBELJOOCE-UHFFFAOYSA-N Calcium Chemical compound [Ca] OYPRJOBELJOOCE-UHFFFAOYSA-N 0.000 description 1
- 241000251729 Elasmobranchii Species 0.000 description 1
- 229910000733 Li alloy Inorganic materials 0.000 description 1
- 235000014676 Phragmites communis Nutrition 0.000 description 1
- ZLMJMSJWJFRBEC-UHFFFAOYSA-N Potassium Chemical compound [K] ZLMJMSJWJFRBEC-UHFFFAOYSA-N 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 229910052791 calcium Inorganic materials 0.000 description 1
- 239000011575 calcium Substances 0.000 description 1
- 229910052570 clay Inorganic materials 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000011109 contamination Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009472 formulation Methods 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
- 238000010348 incorporation Methods 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 239000001989 lithium alloy Substances 0.000 description 1
- 229910001486 lithium perchlorate Inorganic materials 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- NDLPOXTZKUMGOV-UHFFFAOYSA-N oxo(oxoferriooxy)iron hydrate Chemical compound O.O=[Fe]O[Fe]=O NDLPOXTZKUMGOV-UHFFFAOYSA-N 0.000 description 1
- 229910052700 potassium Inorganic materials 0.000 description 1
- 239000011591 potassium Substances 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 238000005476 soldering Methods 0.000 description 1
- 230000002269 spontaneous effect Effects 0.000 description 1
Images
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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
Definitions
- This invention relates to rocket motors and more particularly to such motors utilizing molten metallic fuels.
- An object of this invention is to provide a means of readying jet motors utilizing solid metallic fuels for operation in a relatively short time.
- the invention is carried out by positioning a heating tube in the hydrofuel tank in such a manner as to melt the hydrofuel when the heating tube is operated.
- a feature is the provision of a non-gaseous heating composition which upon combustion emits a relatively large quantity of heat to effect rapid melting of the hydrofuel.
- FIG. 1 is a cross-section view taken at line 11 of FIG. 2 of a hydrofuel storage tank containing a heating tube in accordance with this invention.
- FIG. 2 shows a cross-section view taken at line 22 of FIG. 1.
- the heating tube 12 contains a charge 13 of a substance which can be burned or reacted to produce heat and the tank 16 can be filled almost to the top with a solid hydrofuel 17 such as lithium or any of the other hydrofuels mentioned above, cast in the annular space around the heating tube 12.
- the tank 16 is closed by top 22 and bottom 23 so that when the hydrofuel is in liquid condition, gas pressure can be applied at the inlet 18 to force the liquid out the outlet 19.
- propellant outlet 19 may be positioned at or near the top of the tank to permit the pumping of propellant as soon as melting begins.
- a small amount of space is left empty inside fuel tank 16 to provide space for thermal expansion of the hydrofuel.
- the heating tube 12 is closed at the bottom and the top opening is closed by a cap 21 through which there is passed a cable 20 leading to an igniting squib 24 related to the heating composition 13.
- the heating composition used in the heating tube should be one which does not produce gas during its reaction; otherwise some provision would have to be made for releasing the gas which may not always be convenient or desirable when the tank is used in a device under Water.
- the heating unit of this invention occupy only a minimum amount of space and be capable of releasing large quantities of heat per unit volume. These requirements preclude the use of common commercially available heating compositions such as thermite and others used for such purposes as soldering, etc. because of their relatively low heat release per unit weight. At the same time, it is essential that the amount of heat liberated is not so high as to result in damage to the heating tube itself.
- a uniform mixture of from 65 to 36% by weight of aluminum and copper oxide in stoichiometric proportions, from 25 to 60% by weight of thermite, and from 4 to 10% by weight of clay provides a heating com position having the thermal and uniform burning characteristics required for use as the heating composition of this invention.
- a second formulation also useful as the heating composition of this invention which comprises from to 92% by weight of aluminum and copper oxide in stoichiometric proportions, from 3 to 15% by weight of aluminum and potassium perchlorate in stoichiometric proportions, and from 5 to 15 by weight of clay.
- Example I Ingredients: Percent by wt. Al-Cu (stoichiometric) 56.1 Thermite 37.4 Clay 6.5
- the foregoing heating substances are powdered, dried, and mixed thoroughly, after which they can be pressed in sections in a suitable tube, such as a steel tube, at pressures in the range of about 40,000 to 80,000 pounds per square inch until a solid grain is obtained.
- a preferred compacting pressure is about 67,000 pounds per square inch.
- the high degree of compression not only increases the density of the grain, but also tends to reduce the burning rate which is highly advantageous in the case of a high energy burning mixture which has the tendency to melt the heating tube.
- this tube itself should be composed of a heat-resistant metal, such as steel.
- the tube material should have high thermal conductivity and ability to Withstand the extremely high temperature developed by the combustion of the high-energy heating grains 13.
- the reaction or burning of the heating composition will be initiated by electrical ignition of the squib 24.
- the heating composition 13 will then commence burning at the end adjacent to the squib, and the entire exposed surface area will react. This reaction will progress down the length of the cylindrical grain of the heating composition.
- the hydrofuel 17 in tank 16 will commence to melt in the region adjacent the burning heating composition, this being the region immediately surrounding the cylinder 12.
- the flow of the propellant will, of course, be initiated by applying pressure at conduit 18 to force the liquid out the outlet 19 into the rocket motor for use in a Well known manner.
- the heating compositions of this invention burn at a rate of approximately 0.12 in./sec., hence an entire 80- 4- pound tank of hydrofuel, such as lithium, can be melted in as little as three minutes.
- a small wire mesh screen may be interposed at propellant outlet 19 to separate such particles from the fuel.
- the outlet 18 can conveniently be carried into the interior of the tank 16 into proximity with tube 12.
- the heating tubes of this invention may be used either individually or in groups of two or more when it is desired to melt larger volumes or higher melting metals.
- a fuel unit for rockets which comprises a container substantially filled with normally solid metal rocket hydrofuel, an inlet and an outlet in said container, a heating tube within said container, a solid self-sustaining heating composition within said container, means for igniting said heating composition and pressurization means communicable with said inlet for pumping said hydrofuel out of said container after it has been converted to molten state by combustion of said self-sustaining heating composition.
- a fuel unit for a normally solid metallic rocket propellant fuel which comprises a container for said fuel, an inlet and an outlet in said container, a heating tube within the said container, said heating tube containing a solid self-sustaining heating composition and means for igniting said heating composition, said composition comprising a uniform mixture and stoichiometric proportions of clay, copper oxide, aluminum, and an oxidizer selected from the group consisting of potassium perchlorate and ferric oxide.
Description
ROCKET HYDROFUEL CONTAINER WITH CHEMICAE HEATING DEVICE Filed 1m. 14, 1954 INVENTOR. ROBERT E. COX
wan/M ATTOR Y United States Patent Ohio Filed Dec. '14, 1954, Ser. No. 475,053 2 Claims. (Cl. 44-2) This invention relates to rocket motors and more particularly to such motors utilizing molten metallic fuels. An object of this invention is to provide a means of readying jet motors utilizing solid metallic fuels for operation in a relatively short time.
It has been proposed to employ metallic hydrofuels such as lithium, potassium, calcium, etc. and alloys of such metals as propellants for such rocket motors. These substances are referred to as hydrofuels because of their spontaneous reaction with Water to produce gases useful for propulsion. Such metallic hydrofuels are solids at oldinary temperatures; hence in order to render them useful as rocket hydrofuels they must be heated to the liquid state prior to operation. Thus, the fuel chambers of such rocket engines, as they have been used or proposed up to the present time, have required elaborate arrangements of electrical heating coils or other similar devices which require long periods of time to complete the melting. For example, the melting of the hydrofuel in a typical tank of about 80 lbs. capacity has hitherto required about two hours. i
The invention is carried out by positioning a heating tube in the hydrofuel tank in such a manner as to melt the hydrofuel when the heating tube is operated.
A feature is the provision of a non-gaseous heating composition which upon combustion emits a relatively large quantity of heat to effect rapid melting of the hydrofuel.
The foregoing and other features of the invention will be better understood from the following detailed description and the accompanying drawing of which:
FIG. 1 is a cross-section view taken at line 11 of FIG. 2 of a hydrofuel storage tank containing a heating tube in accordance with this invention; and
FIG. 2 shows a cross-section view taken at line 22 of FIG. 1.
Referring to the drawing, there is shown a storage tank 16 of a generally cylindrical shape containing a centrally located cylindrical heating tube 12. Although the cylindrical shape for tanks will ordinarily be preferred, it should be understood that some other shape such as a square cross-section could be used. The heating tube 12 contains a charge 13 of a substance which can be burned or reacted to produce heat and the tank 16 can be filled almost to the top with a solid hydrofuel 17 such as lithium or any of the other hydrofuels mentioned above, cast in the annular space around the heating tube 12.
The tank 16 is closed by top 22 and bottom 23 so that when the hydrofuel is in liquid condition, gas pressure can be applied at the inlet 18 to force the liquid out the outlet 19.
Alternatively, propellant outlet 19 may be positioned at or near the top of the tank to permit the pumping of propellant as soon as melting begins.
A small amount of space is left empty inside fuel tank 16 to provide space for thermal expansion of the hydrofuel.
The heating tube 12 is closed at the bottom and the top opening is closed by a cap 21 through which there is passed a cable 20 leading to an igniting squib 24 related to the heating composition 13.
The heating composition used in the heating tube should be one which does not produce gas during its reaction; otherwise some provision would have to be made for releasing the gas which may not always be convenient or desirable when the tank is used in a device under Water.
Because of weight and volume limitations in torpedoes, rockets, and other guided missiles it is necessary that the heating unit of this invention occupy only a minimum amount of space and be capable of releasing large quantities of heat per unit volume. These requirements preclude the use of common commercially available heating compositions such as thermite and others used for such purposes as soldering, etc. because of their relatively low heat release per unit weight. At the same time, it is essential that the amount of heat liberated is not so high as to result in damage to the heating tube itself.
I have found that an excellent composition for use as the heat generating element is provided by a mixture of finely divided aluminum and copper oxide. These substances react according to the following equation:
2Al+ 3CuO- 3Cu+Al O +294 kilocalories This is equivalent to 1.0 kilocalorie per gram or 5.1 kilocalories per cubic centimeter.
Other mixtures such as aluminum and lithium or potassium perchlorate, for example, will yield more energy, but unfortunately, it has been found impossible to contain this reaction in a sealed metal tube without the use of special materials in the tube construction. The reaction of a stoichiometric mixture of aluminum and copper oxide is also diflicult to contain without the use of costly high melting metal containers, however, I have found that the reaction rate of aluminum and copper oxide can be slowed sufficiently by the incorporation of inert materials such as clay to permit its use in a tube composed of ordinary steel.
The admixture of such materials, however, may in some cases produce difiiculties in the burning rate characteristics of the grain, in that burning may be irregular or incomplete due to the presence of such inert materials. I have found that the inclusion of small amounts of other oxidizing materials such as thermite and potassium perchlorate as well as oxidizing agents of comparable strength will correct this defect to provide a grain which will burn in a uniform fashion and emit heat within usable limits.
I have found that a uniform mixture of from 65 to 36% by weight of aluminum and copper oxide in stoichiometric proportions, from 25 to 60% by weight of thermite, and from 4 to 10% by weight of clay, provides a heating com position having the thermal and uniform burning characteristics required for use as the heating composition of this invention. In addition, I have found a second formulation also useful as the heating composition of this invention which comprises from to 92% by weight of aluminum and copper oxide in stoichiometric proportions, from 3 to 15% by weight of aluminum and potassium perchlorate in stoichiometric proportions, and from 5 to 15 by weight of clay.
The following examples are provided to more clearly illustrate the heating compositions useful in the practice of this invention.
3 Example I Ingredients: Percent by wt. Al-Cu (stoichiometric) 56.1 Thermite 37.4 Clay 6.5
Example ll Ingredients:
Al-CuO (stoichiometric) 83.3 AlKClO (stoichiometric) 4.4 Clay 12.3
For use in the heating tube, the foregoing heating substances are powdered, dried, and mixed thoroughly, after which they can be pressed in sections in a suitable tube, such as a steel tube, at pressures in the range of about 40,000 to 80,000 pounds per square inch until a solid grain is obtained. A preferred compacting pressure is about 67,000 pounds per square inch. The high degree of compression not only increases the density of the grain, but also tends to reduce the burning rate which is highly advantageous in the case of a high energy burning mixture which has the tendency to melt the heating tube.
Since great heat is developed at the heating tube 12, this tube itself should be composed of a heat-resistant metal, such as steel. The tube material should have high thermal conductivity and ability to Withstand the extremely high temperature developed by the combustion of the high-energy heating grains 13.
In operation the reaction or burning of the heating composition will be initiated by electrical ignition of the squib 24. The heating composition 13 will then commence burning at the end adjacent to the squib, and the entire exposed surface area will react. This reaction will progress down the length of the cylindrical grain of the heating composition. Immediately upon ignition, the hydrofuel 17 in tank 16 will commence to melt in the region adjacent the burning heating composition, this being the region immediately surrounding the cylinder 12. Thus, even though all of the hydrofuel in the tank 16 has not yet melted, there will nevertheless be enough of it in molten condition between the inlet and outlet conduits 18 and 19 so that the liquid hydrofuel propellant is immediately available for use. This will permit substantially instantaneous use of the rocket engine with which it is associated. The flow of the propellant will, of course, be initiated by applying pressure at conduit 18 to force the liquid out the outlet 19 into the rocket motor for use in a Well known manner.
The heating compositions of this invention burn at a rate of approximately 0.12 in./sec., hence an entire 80- 4- pound tank of hydrofuel, such as lithium, can be melted in as little as three minutes.
In order to eliminate the possibility of contamination of the fuel by small particles of the heating composition such as those which might result from failure of the Wall of the heating tube, a small wire mesh screen may be interposed at propellant outlet 19 to separate such particles from the fuel.
To facilitate the flow of the molten hydrofuel even before it is completely molten, the outlet 18 can conveniently be carried into the interior of the tank 16 into proximity with tube 12.
The heating tubes of this invention may be used either individually or in groups of two or more when it is desired to melt larger volumes or higher melting metals.
I have found that each heating tube will melt approximately 15 times its own volume of hydrofuels such as lithium and lithium alloys.
I claim:
1. A fuel unit for rockets which comprises a container substantially filled with normally solid metal rocket hydrofuel, an inlet and an outlet in said container, a heating tube within said container, a solid self-sustaining heating composition within said container, means for igniting said heating composition and pressurization means communicable with said inlet for pumping said hydrofuel out of said container after it has been converted to molten state by combustion of said self-sustaining heating composition.
2. A fuel unit for a normally solid metallic rocket propellant fuel which comprises a container for said fuel, an inlet and an outlet in said container, a heating tube within the said container, said heating tube containing a solid self-sustaining heating composition and means for igniting said heating composition, said composition comprising a uniform mixture and stoichiometric proportions of clay, copper oxide, aluminum, and an oxidizer selected from the group consisting of potassium perchlorate and ferric oxide.
References Cited by the Examiner UNITED STATES PATENTS 1,167,944 1/ 16 Shurnan.
1,838,357 12/31 Bottrill.
2,016,407 10/35 WentZel.
2,020,101 11/35 Brown 266-39 2,040,407 5/3 6 Reed 44-3 2,152,446 3/39 Temple 26639 2,352,951 7/44 Geria 443 X 2,680,063 6/54 Shapiro 44-3 CARL D. QUARFORTH, Primary Examiner.
ROGER L. CAMPBELL, WILLIAM G. WILES, REU- BEN EPSTEIN, Examiners.
Claims (2)
1. A FUEL UNIT FOR ROCKETS WHICH COMPRISES A CONTAINER SUBSTANTIALLY FILLED WITH NORMALLY SOLID METAL ROCKET HYDROFUEL, AN INLET AND AN OUTLET IN SAID CONTAINER, A HEATING TUBE WITHIN SAID CONTAINER, A SOLID SELF-SUSTAINING HEATING COMPOSITION WITHIN SAID CONTAINER, MEANS FOR IGNITING SAID HEATING COMPOSITION AND PRESSURIZATION MEANS COMMUNICABLE WITH SAID INLET FOR PUMPING SAID HYDROFUEL OUT OF SAID CONTAINER AFTER IT HAS BEEN CONVERTED TO MOLTEN STATE BY COMBUSTION OF SAID SELF-SUSTAINING HEATING COMPOSITION.
2. A FUEL UNIT FOR A NORMALLY SOLID METALLIC ROCKET PROPELLANT FUEL WHICH COMPRISES A CONTAINER FOR SAID FUEL, AN INLET AND AN OUTLET IN SAID CONTAINER, A HEATING TUBE WITHIN THE SAID CONTAINER, SAID HEATING TUBE CONTAINING A SOLID SELF-SUSTAINING HEATING COMPOSITION AND MEANS FOR IGNITING SAID HEATING COMPOSITION, SAID COMPOSITION COMPRISING A UNIFORM MIXTURE AND STOICHIOMETRIC PROPORTIONS OF CLAY, COPPER OXIDE, ALUMINUM, AND AN XOIDIZER SELECTED FROM THE GROUP CONSISTING OF POTASSIUM PERCHLORATE AND FERRIC OXIDE.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US475053A US3181937A (en) | 1954-12-14 | 1954-12-14 | Rocket hydrofuel container with chemical heating device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US475053A US3181937A (en) | 1954-12-14 | 1954-12-14 | Rocket hydrofuel container with chemical heating device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US3181937A true US3181937A (en) | 1965-05-04 |
Family
ID=23886057
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US475053A Expired - Lifetime US3181937A (en) | 1954-12-14 | 1954-12-14 | Rocket hydrofuel container with chemical heating device |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US3181937A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3811422A (en) * | 1972-10-05 | 1974-05-21 | Us Navy | Chemical heater tube |
| JPS5167535A (en) * | 1974-12-09 | 1976-06-11 | Hitachi Shipbuilding Eng Co | Kinzokunenryono shunjojuho |
| US4804520A (en) * | 1983-11-03 | 1989-02-14 | Rockwell International Corporation | Warm gas accumulator |
| US9341456B2 (en) * | 2014-01-21 | 2016-05-17 | Spectre Enterprises, Inc. | Self-propelled projectile having a fuel-rich propellant that reacts with water |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1167944A (en) * | 1909-07-20 | 1916-01-11 | Frank Shuman | Method of and means for melting metals. |
| US1838357A (en) * | 1929-05-18 | 1931-12-29 | Bottrill David Hughes | Soldering device |
| US2016407A (en) * | 1932-06-22 | 1935-10-08 | Sauerstoff Central Fur Medizin | Method of spraying liquid materials |
| US2020101A (en) * | 1931-11-25 | 1935-11-05 | John W Brown | Melting and holding furnace |
| US2040407A (en) * | 1933-06-17 | 1936-05-12 | Kendall & Co | Chemical heating composition |
| US2152446A (en) * | 1939-01-18 | 1939-03-28 | Victor Metal Products Corp | Melting pot |
| US2352951A (en) * | 1941-08-27 | 1944-07-04 | Geria Andrew | Chemically heated liquid container |
| US2680063A (en) * | 1952-01-21 | 1954-06-01 | Us Army | Chemical heating composition |
-
1954
- 1954-12-14 US US475053A patent/US3181937A/en not_active Expired - Lifetime
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1167944A (en) * | 1909-07-20 | 1916-01-11 | Frank Shuman | Method of and means for melting metals. |
| US1838357A (en) * | 1929-05-18 | 1931-12-29 | Bottrill David Hughes | Soldering device |
| US2020101A (en) * | 1931-11-25 | 1935-11-05 | John W Brown | Melting and holding furnace |
| US2016407A (en) * | 1932-06-22 | 1935-10-08 | Sauerstoff Central Fur Medizin | Method of spraying liquid materials |
| US2040407A (en) * | 1933-06-17 | 1936-05-12 | Kendall & Co | Chemical heating composition |
| US2152446A (en) * | 1939-01-18 | 1939-03-28 | Victor Metal Products Corp | Melting pot |
| US2352951A (en) * | 1941-08-27 | 1944-07-04 | Geria Andrew | Chemically heated liquid container |
| US2680063A (en) * | 1952-01-21 | 1954-06-01 | Us Army | Chemical heating composition |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3811422A (en) * | 1972-10-05 | 1974-05-21 | Us Navy | Chemical heater tube |
| JPS5167535A (en) * | 1974-12-09 | 1976-06-11 | Hitachi Shipbuilding Eng Co | Kinzokunenryono shunjojuho |
| JPS5521930B2 (en) * | 1974-12-09 | 1980-06-13 | ||
| US4804520A (en) * | 1983-11-03 | 1989-02-14 | Rockwell International Corporation | Warm gas accumulator |
| US9341456B2 (en) * | 2014-01-21 | 2016-05-17 | Spectre Enterprises, Inc. | Self-propelled projectile having a fuel-rich propellant that reacts with water |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US5212343A (en) | Water reactive method with delayed explosion | |
| USH464H (en) | Metal hydride explosive system | |
| US5634341A (en) | System for generating hydrogen | |
| US1532930A (en) | Method and means of producing heat | |
| US8245640B1 (en) | Melted metal dispersal warhead | |
| US3143446A (en) | Propellant charge containing fluid encapsulations | |
| US3204560A (en) | Solid rocket propellant containing metal encapsulated gas | |
| US3437534A (en) | Explosive composition containing aluminum,potassium perchlorate,and sulfur or red phosphorus | |
| US3181937A (en) | Rocket hydrofuel container with chemical heating device | |
| US3158993A (en) | Solid fuels and formulations | |
| US3942443A (en) | Rocket assisted projectile | |
| US3749024A (en) | Outgassing technique | |
| US3754511A (en) | Fuel and fuel igniter for ram jet and rocket | |
| US3160097A (en) | Molybdenum trioxide-aluminum explosive and exploding bridgewire detonator therefor | |
| US3137127A (en) | Method of developing high energy thrust | |
| US3791889A (en) | Fuel composition containing lithium, calcium and fluorocarbon | |
| US2455015A (en) | Means for igniting propellant in rocket motors | |
| US3044911A (en) | Propellant system | |
| US3009800A (en) | Solid rocket propellants containing boron carbide as fuel | |
| US2732800A (en) | coursen | |
| US5175022A (en) | Method of making oxidizer coated metal fuels | |
| US2079777A (en) | Safety igniter for blasting explosive devices | |
| US3180770A (en) | Propellant fuel containing magnesium aluminum alloy | |
| US3742859A (en) | Explosive charge | |
| US3383860A (en) | Low flame temperature gas generant containing ammonium iodate and methode of operatin a gas generator |