US3732694A - Method for the catalytic decomposition of monopropellant hydrazine - Google Patents
Method for the catalytic decomposition of monopropellant hydrazine Download PDFInfo
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- US3732694A US3732694A US00698846A US3732694DA US3732694A US 3732694 A US3732694 A US 3732694A US 00698846 A US00698846 A US 00698846A US 3732694D A US3732694D A US 3732694DA US 3732694 A US3732694 A US 3732694A
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- hydrazine
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01J—CHEMICAL OR PHYSICAL PROCESSES, e.g. CATALYSIS OR COLLOID CHEMISTRY; THEIR RELEVANT APPARATUS
- B01J23/00—Catalysts comprising metals or metal oxides or hydroxides, not provided for in group B01J21/00
- B01J23/16—Catalysts comprising metals or metal oxides or hydroxides, not provided for in group B01J21/00 of arsenic, antimony, bismuth, vanadium, niobium, tantalum, polonium, chromium, molybdenum, tungsten, manganese, technetium or rhenium
- B01J23/32—Manganese, technetium or rhenium
- B01J23/36—Rhenium
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01J—CHEMICAL OR PHYSICAL PROCESSES, e.g. CATALYSIS OR COLLOID CHEMISTRY; THEIR RELEVANT APPARATUS
- B01J23/00—Catalysts comprising metals or metal oxides or hydroxides, not provided for in group B01J21/00
- B01J23/38—Catalysts comprising metals or metal oxides or hydroxides, not provided for in group B01J21/00 of noble metals
- B01J23/54—Catalysts comprising metals or metal oxides or hydroxides, not provided for in group B01J21/00 of noble metals combined with metals, oxides or hydroxides provided for in groups B01J23/02 - B01J23/36
- B01J23/56—Platinum group metals
- B01J23/64—Platinum group metals with arsenic, antimony, bismuth, vanadium, niobium, tantalum, polonium, chromium, molybdenum, tungsten, manganese, technetium or rhenium
- B01J23/656—Manganese, technetium or rhenium
- B01J23/6567—Rhenium
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01J—CHEMICAL OR PHYSICAL PROCESSES, e.g. CATALYSIS OR COLLOID CHEMISTRY; THEIR RELEVANT APPARATUS
- B01J23/00—Catalysts comprising metals or metal oxides or hydroxides, not provided for in group B01J21/00
- B01J23/38—Catalysts comprising metals or metal oxides or hydroxides, not provided for in group B01J21/00 of noble metals
- B01J23/54—Catalysts comprising metals or metal oxides or hydroxides, not provided for in group B01J21/00 of noble metals combined with metals, oxides or hydroxides provided for in groups B01J23/02 - B01J23/36
- B01J23/66—Silver or gold
- B01J23/68—Silver or gold with arsenic, antimony, bismuth, vanadium, niobium, tantalum, polonium, chromium, molybdenum, tungsten, manganese, technetium or rhenium
- B01J23/688—Silver or gold with arsenic, antimony, bismuth, vanadium, niobium, tantalum, polonium, chromium, molybdenum, tungsten, manganese, technetium or rhenium with manganese, technetium or rhenium
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01J—CHEMICAL OR PHYSICAL PROCESSES, e.g. CATALYSIS OR COLLOID CHEMISTRY; THEIR RELEVANT APPARATUS
- B01J23/00—Catalysts comprising metals or metal oxides or hydroxides, not provided for in group B01J21/00
- B01J23/70—Catalysts comprising metals or metal oxides or hydroxides, not provided for in group B01J21/00 of the iron group metals or copper
- B01J23/76—Catalysts comprising metals or metal oxides or hydroxides, not provided for in group B01J21/00 of the iron group metals or copper combined with metals, oxides or hydroxides provided for in groups B01J23/02 - B01J23/36
- B01J23/84—Catalysts comprising metals or metal oxides or hydroxides, not provided for in group B01J21/00 of the iron group metals or copper combined with metals, oxides or hydroxides provided for in groups B01J23/02 - B01J23/36 with arsenic, antimony, bismuth, vanadium, niobium, tantalum, polonium, chromium, molybdenum, tungsten, manganese, technetium or rhenium
- B01J23/889—Manganese, technetium or rhenium
- B01J23/8896—Rhenium
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06D—MEANS FOR GENERATING SMOKE OR MIST; GAS-ATTACK COMPOSITIONS; GENERATION OF GAS FOR BLASTING OR PROPULSION (CHEMICAL PART)
- C06D5/00—Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets
- C06D5/04—Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets by auto-decomposition of single substances
Definitions
- This invention relates to a low cost spontaneous decomposition catalyst for hydrazine or mixtures containing hydrazine hydrazine nitrate propellant fuels, which permits a low temperature ignition of the fuels and retains its activity after exposure to the propellant flame environment.
- the catalyst is produced by coating rhenium metal or a rhenium-molybdenum mixture on a support body such as alumina. Iron, nickel, copper, silver, gold, iridium, or ruthenium may be included as co-catalyst metals.
- Hydrazine spontaneous decomposition catalysts are produced by coating rhenium or mixtures of rhenium and molybdenum on a high surface area support, such as alumina, thoria, or zirconia.
- a high surface area support such as alumina, thoria, or zirconia.
- a certain degree of enhancement or synergism may be achieved by adding a minor amount of co-catalyst metals such as iron, nickel, copper, silver, gold, iridium, and uthenium.
- Rhenium or mixtures of rhenium and molybdenum may be employed in a range from 1-60 weight percent of the support particle, however, -35 weight percent is generally preferred.
- Cocatalysts, iron, nickel, copper, gold, silver, iridium, and ruthenium may be employed in amounts up to 50 weight percent of the support particle, however, they should be present in minor amounts with respect to the rhenium or the rhenium-molybdenum mixture and should never exceed the weight percent of the rhenium or the rhenium-molybdenum mixture present.
- preparation of the rhenium catalyst is ac complished by soaking the support body in a saturated solution of rhenium trichloride for at least one hour and decanting the excess solution. These support pellets are then removed and dried in vacuum at approximately 100C. Upon completion of the drying step, the catalyst is activated by reduction in a slow moving stream of dry hydrogen at approximately 700C.
- One or more promoters or co-catalysts such as iron, nickel, copper, silver, gold, iridium, or ruthenium are applied to the rhenium catalyst in a similar manner.
- Support bodies which have been coated with the rhenium catalyst are imm ersed in a dilute aqueous solution ofa soluble salt of the co-catalyst metal.
- the excess solution is decanted off and the catalyst impregnated pellets are dried and reduced in a manner similar to the rhenium.
- oxidizer-starters may be included into the catalyst bed.
- a low temperature hydrazine starter consisting of iodine pentoxide is described in U. S. Pat. No. 3,298,182.
- Other compounds which are suitable for use as ignition starters may be selected from the group consisting of ammonium dichromate, silver nitrate, chromic trioxide, potassium permanganate, and sodium cobaltinitrite. These starter compounds are used in an range of 5 to percent by weight of the total catalyst bed.
- the catalyst After the decomposition catalyst has been warmed by the initial firing of the engine, the catalyst exhibits an ignition delay in which time varies inversely with the temperature, i.e. as the temperature increases, the ignition time after the contact of the fuel and the catalyst is decreased.
- the following table sets forth the delays which can be expected at the listed temperatues using a 26 percent rhenium catalyst on a Reynolds RAl Alumina support.
- FIG. 1 is a time v. pressure trace of the fire valve (V), the injection pressure (P,-), and the chamber pressure (P at an initial chamber temperature of F;
- FIG. 2 is a time v. pressure trace of the three variables set forth in FIG. 1 above at an initial chamber temperature of 375F;
- FIG. 3 is a time v. pressure trace of the three variables set forth in FIG. 1 above at an initial chamber temperature of 540F;
- FIG. 4 is a time v. pressure trace of the three variables set forth at an initial chamber temperature of l290F.
- FIG. 1 An inspection of the FIGS. shows two interesting effects which are related to the initial chamber temperature.
- the start of each run is timed from the slight dip near the top of the initial pressure rise on the the tire valve trace (V) which indicates the point the valve opens (V)
- V tire valve trace
- FIG. 2 a peak pressure of 64 psia was obtained when the initial chamber temperature was 165F
- FIG. 2 a peak pressure of 133 psia was obtained when the initial chamber temperature was 375F
- FIG. 3 a peak pressure of 147 psia was obtained when the initial chambertemperature was 540F
- FIG. 4 a peak pressure of psia was obtained when the initial chamber temperature was l290F.
- the decomposition catalyst described above may be employed for hydrazine, alone, or any hydrazinecontaining fuel mixture, such as hydrazine-hydrazine nitrate. Details of catalyst position known in the art may be applied here, i.e., no special considerations are necessary as a result of use of the instant catalysts. Generally, all that is required is that the catalysts come in contact with the hydrazine fuel prior to or during ignition of the fuel as the following example shows.
- a catalyst of the type which is the subject of this invention was used to ignite and decompose hydrazine in three-pound thrust engine hardware.
- the catalyst was prepared by the method cited above and contained 25.8 percent by weight rhenium on a high surface area support of Reynolds RA-l Alumina.
- the fuel used was a monopropellant containing 100 percent hydrazine. It was found that when the fuel was injected into the catalyst bed, smooth, rapid ignition occurred when the catalyst bed was initially at ambient temperature or near the hydrazine flame temperature.
- the test engine was operated in a pulsed mode of 80 millisecond firings each second and gave reproducible ignition and smooth decomposition of the fuel. In addition, the engine was operated at steady state for more than ten seconds and the catalyst continued to provide smooth decomposition of the hydrazine throughout the firing.
- Hydrazine decomposition catalysts are attractive not only because of the relative ease of preparation, but because of the relatively low cost of the materials employed.
- catalysts according to this invention do not decompose upon exposure to the propellant flame environment. This advantageous property permits multiple reignition of rocket engines, a feat of some difficulty and questionable reliability heretofore.
- a method for the spontaneous decomposition of hydrazine propellant fuels which comprises contacting propellant fuels selected from the class consisting of hydrazine and hydrazine-hydrazine nitrate at ambient temperatures with a catalyst consisting essentially of at least rhenium and a metal selected from the group consisting of molybdenum, iron, nickel, copper, silver, gold, iridium, and ruthenium coated on a high surface area support.
- the high surface area support is selected from the group consisting of alumina, thoria, and zirconia.
- the catalyst comprises l60 weight percent rhenium a minor amount of a metal selected from the group consisting of molybdenum, iron, nickel, copper, silver, gold, iridium, and ruthenium, and the balance inert ingredients.
- the catalyst comprises 5-35 weight percent rhenium, a minor amount of a metal selected from the group consisting of molybdenum, iron, nickel, copper, silver, gold, iridium, and ruthenium and the balance inert ingredients.
Abstract
This invention relates to a low cost spontaneous decomposition catalyst for hydrazine or mixtures containing hydrazine hydrazine nitrate propellant fuels, which permits a low temperature ignition of the fuels and retains its activity after exposure to the propellant flame environment. The catalyst is produced by coating rhenium metal or a rhenium-molybdenum mixture on a support body such as alumina. Iron, nickel, copper, silver, gold, iridium, or ruthenium may be included as co-catalyst metals.
Description
limited States Patent 91 Blumenthal et al,
[ 51 May 15,1973
[54] METHOD FOR THE CATALYTIC DECOMPOSITION OF MONOPROPELLANT HYDRAZINE [73] Assignee: TRW lnc., Redondo Beach, Calif.
[22] Filed: Jan. 18, 1968 21 Appl. No.: 698,846
[52] US. Cl. ..60/218, 60/219, 149/36, 252/454 [51] Int. Cl. ..C06d 5/04, C06d 5/10 [58] Field of Search ..60/218-220; 252/434, 467, 454; 149/36 [56] References Cited UNITED STATES PATENTS 2,925,709 2/1960 Mantell et al 260/218 X 2,930,184 3/1960 Plescia et a1 ..60/218 X 3,021,667 2/1962 Griffin et al. ..60/218 3,081,595 3/1963 Rose ..60/218 X 3,165,382 1/1965 Forte ..60/218 X Primary Examiner-Benjamin R. Padgett Att0rney- Daniel T. Anderson, Gerald Singer and Alfons Valukonis This invention relates to a low cost spontaneous decomposition catalyst for hydrazine or mixtures containing hydrazine hydrazine nitrate propellant fuels, which permits a low temperature ignition of the fuels and retains its activity after exposure to the propellant flame environment. The catalyst is produced by coating rhenium metal or a rhenium-molybdenum mixture on a support body such as alumina. Iron, nickel, copper, silver, gold, iridium, or ruthenium may be included as co-catalyst metals.
6 Claims, 4 Drawing Figures PATENTEUMAY 15 m5 3.732.694
SHEEI1UF4 S, V g a S K I z 2 aun'ssaad- Jack Blumenfh ol Eugene D. Gu
INVI'ENTORS AGENT v PATENTEB W 1 51973 3. 732.694
TIME Fig-2 Jock L.Blumenrho| Eugene D. Guth INVENTORS AGENT P QMAY 1 51978 I 3. 7 32 694 SHEET 3 BF 4 PRESSURE TIME AGYENT PATENTEUW 5W 3.732.694 v TIME Fig.4
* Jack L.B|umenrho| Eugene D.Gurh
INVENTORS i/ H N BY (U [7 AGENT METHOD FOR THE CATALYTIC DECOMPOSITION OF MONOPROPELLANT HYDRAZINE Problems with prior-art hydrazine decomposition catalysts have frequently come from the fact that the catalytic materials are decomposed or reacted at the flame temperature of the propellant. Several catalysts containing cobalt, copper, and alkali metals are known to decompose hydrazine at ambient temperatures, however they are deactivated by flame temperature and thus are suitable for only one start. The transition group metal salts and silver salts also suffer the undesirable property of decomposing at hydrazine flame temperatures. These problems with catalysts did not arise until rocket engine art was extended to include more than one start.
Hydrazine spontaneous decomposition catalysts, according to this invention are produced by coating rhenium or mixtures of rhenium and molybdenum on a high surface area support, such as alumina, thoria, or zirconia. When desired, a certain degree of enhancement or synergism may be achieved by adding a minor amount of co-catalyst metals such as iron, nickel, copper, silver, gold, iridium, and uthenium.
Proportions of the catalytic ingredients are effective over a wide range. Rhenium or mixtures of rhenium and molybdenum may be employed in a range from 1-60 weight percent of the support particle, however, -35 weight percent is generally preferred. Cocatalysts, iron, nickel, copper, gold, silver, iridium, and ruthenium, may be employed in amounts up to 50 weight percent of the support particle, however, they should be present in minor amounts with respect to the rhenium or the rhenium-molybdenum mixture and should never exceed the weight percent of the rhenium or the rhenium-molybdenum mixture present.
Preferably, preparation of the rhenium catalyst is ac complished by soaking the support body in a saturated solution of rhenium trichloride for at least one hour and decanting the excess solution. These support pellets are then removed and dried in vacuum at approximately 100C. Upon completion of the drying step, the catalyst is activated by reduction in a slow moving stream of dry hydrogen at approximately 700C. One or more promoters or co-catalysts such as iron, nickel, copper, silver, gold, iridium, or ruthenium are applied to the rhenium catalyst in a similar manner. Support bodies which have been coated with the rhenium catalyst are imm ersed in a dilute aqueous solution ofa soluble salt of the co-catalyst metal. The excess solution is decanted off and the catalyst impregnated pellets are dried and reduced in a manner similar to the rhenium.
For the initial start with hydrazine at temperatures as low as 3C, oxidizer-starters may be included into the catalyst bed. A low temperature hydrazine starter consisting of iodine pentoxide is described in U. S. Pat. No. 3,298,182. Other compounds which are suitable for use as ignition starters may be selected from the group consisting of ammonium dichromate, silver nitrate, chromic trioxide, potassium permanganate, and sodium cobaltinitrite. These starter compounds are used in an range of 5 to percent by weight of the total catalyst bed.
After the decomposition catalyst has been warmed by the initial firing of the engine, the catalyst exhibits an ignition delay in which time varies inversely with the temperature, i.e. as the temperature increases, the ignition time after the contact of the fuel and the catalyst is decreased. The following table sets forth the delays which can be expected at the listed temperatues using a 26 percent rhenium catalyst on a Reynolds RAl Alumina support.
T A B L E Temperature Ignition Delay F Milli seconds 72 167 30 205 10 340 5 A better understanding of the rhenium catalyst performance may be obtained by reference to the drawings which are traces of a 3 lb. thrust engine using 0.014 lb. of hydrazine per second for a duration of 80 milliseconds, wherein:
FIG. 1 is a time v. pressure trace of the fire valve (V), the injection pressure (P,-), and the chamber pressure (P at an initial chamber temperature of F;
FIG. 2 is a time v. pressure trace of the three variables set forth in FIG. 1 above at an initial chamber temperature of 375F;
FIG. 3 is a time v. pressure trace of the three variables set forth in FIG. 1 above at an initial chamber temperature of 540F; and
FIG. 4 is a time v. pressure trace of the three variables set forth at an initial chamber temperature of l290F.
An inspection of the FIGS. shows two interesting effects which are related to the initial chamber temperature. The start of each run is timed from the slight dip near the top of the initial pressure rise on the the tire valve trace (V) which indicates the point the valve opens (V It may be noted that there is a comparative longer delay in FIG. 1 between the valve opening and a noticeable pressure rise than there is in the other FIGS. It may be noted also that greater pressures in the combustion chamber are achieved by the increase in initial temperatues in the chamber. In FIG. 1 a peak pressure of 64 psia was obtained when the initial chamber temperature was 165F; in FIG. 2 a peak pressure of 133 psia was obtained when the initial chamber temperature was 375F; in FIG. 3 a peak pressure of 147 psia was obtained when the initial chambertemperature was 540F; and in FIG. 4 a peak pressure of psia was obtained when the initial chamber temperature was l290F.
The decomposition catalyst described above may be employed for hydrazine, alone, or any hydrazinecontaining fuel mixture, such as hydrazine-hydrazine nitrate. Details of catalyst position known in the art may be applied here, i.e., no special considerations are necessary as a result of use of the instant catalysts. Generally, all that is required is that the catalysts come in contact with the hydrazine fuel prior to or during ignition of the fuel as the following example shows.
EXAMPLE A catalyst of the type which is the subject of this invention was used to ignite and decompose hydrazine in three-pound thrust engine hardware. The catalyst was prepared by the method cited above and contained 25.8 percent by weight rhenium on a high surface area support of Reynolds RA-l Alumina. The fuel used was a monopropellant containing 100 percent hydrazine. It was found that when the fuel was injected into the catalyst bed, smooth, rapid ignition occurred when the catalyst bed was initially at ambient temperature or near the hydrazine flame temperature. The test engine was operated in a pulsed mode of 80 millisecond firings each second and gave reproducible ignition and smooth decomposition of the fuel. In addition, the engine was operated at steady state for more than ten seconds and the catalyst continued to provide smooth decomposition of the hydrazine throughout the firing.
Hydrazine decomposition catalysts, according to this invention, are attractive not only because of the relative ease of preparation, but because of the relatively low cost of the materials employed. In addition catalysts according to this invention, do not decompose upon exposure to the propellant flame environment. This advantageous property permits multiple reignition of rocket engines, a feat of some difficulty and questionable reliability heretofore.
We claim:
1. A method for the spontaneous decomposition of hydrazine propellant fuels which comprises contacting propellant fuels selected from the class consisting of hydrazine and hydrazine-hydrazine nitrate at ambient temperatures with a catalyst consisting essentially of at least rhenium and a metal selected from the group consisting of molybdenum, iron, nickel, copper, silver, gold, iridium, and ruthenium coated on a high surface area support.
2. A method according to claim 1 wherein the high surface area support is selected from the group consisting of alumina, thoria, and zirconia.
3. A method according to claim 1 wherein the catalyst comprises 1-60 weight percent rhenium and the balance inert ingredients.
4. A method according to claim 1 wherein the catalyst comprises 5-35 weight percent rhenium and the balance inert ingredients.
5. A method according to claim 1 wherein the catalyst comprises l60 weight percent rhenium a minor amount of a metal selected from the group consisting of molybdenum, iron, nickel, copper, silver, gold, iridium, and ruthenium, and the balance inert ingredients.
6. A method according to claim 1 wherein the catalyst comprises 5-35 weight percent rhenium, a minor amount of a metal selected from the group consisting of molybdenum, iron, nickel, copper, silver, gold, iridium, and ruthenium and the balance inert ingredients.
Claims (5)
- 2. A method according to claim 1 wherein the high surface area support is selected from the group consisting of alumina, thoria, and zirconia.
- 3. A method according to claim 1 wherein the catalyst comprises 1-60 weight percent rhenium and the balance inert ingredients.
- 4. A method according to claim 1 wherein the catalyst comprises 5-35 weight percent rhenium and the balance inert ingredients.
- 5. A method according to claim 1 wherein the catalyst comprises 1-60 weight percent rhenium a minor amount of a metal selected from the group consisting of molybdenum, iron, nickel, copper, silver, gold, iridium, and ruthenium, and the balance inert ingredients.
- 6. A method according to claim 1 wherein the catalyst comprises 5-35 weight percent rhenium, a minor amount of a metal selected from the group consisting of molybdenum, iron, nickel, copper, silver, gold, iridium, and ruthenium and the balance inert ingredients.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US69884668A | 1968-01-18 | 1968-01-18 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US3732694A true US3732694A (en) | 1973-05-15 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US00698846A Expired - Lifetime US3732694A (en) | 1968-01-18 | 1968-01-18 | Method for the catalytic decomposition of monopropellant hydrazine |
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| US (1) | US3732694A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4157270A (en) * | 1977-09-12 | 1979-06-05 | The United States Of America As Represented By The Secretary Of The Army | Hydrogen gas generator from hydrazine/ammonia |
| US4620415A (en) * | 1983-09-29 | 1986-11-04 | Rocket Research Company | Method for initiating decomposition of hydrazine fuels |
| US4737482A (en) * | 1983-07-25 | 1988-04-12 | Exxon Research & Engineering Co. | Catalysts for oxidation of olefins to ketones |
| US4876392A (en) * | 1982-09-21 | 1989-10-24 | Exxon Research & Engineering Company | Process for preparation of keystones by oxidation of secondary alcohols using a trimetallic catalyst comprising molybdenum, rhenium and a group VIII noble metal |
| US5542704A (en) * | 1994-09-20 | 1996-08-06 | Oea, Inc. | Automotive inflatable safety system propellant with complexing agent |
| US5746050A (en) * | 1996-01-19 | 1998-05-05 | Primex Technologies, Inc. | Gaseous product delivery system |
| US20020173054A1 (en) * | 2001-05-03 | 2002-11-21 | Hynix Semiconductor Inc. | Method for fabricating ruthenium thin layer |
| US20130327015A1 (en) * | 2012-06-12 | 2013-12-12 | Pamela Pollet | Dual use hydrazine propulsion thruster system |
| CN111646870A (en) * | 2020-05-06 | 2020-09-11 | 北京航天试验技术研究所 | Catalyst applied to low-temperature starting monopropellant and preparation method thereof |
| CN112108145A (en) * | 2019-06-19 | 2020-12-22 | 中国科学院大连化学物理研究所 | Alumina-supported iridium cluster catalyst and preparation and application thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2925709A (en) * | 1949-02-12 | 1960-02-23 | Kellogg M W Co | Decomposition of hydrazine |
| US2930184A (en) * | 1949-05-13 | 1960-03-29 | Kellogg M W Co | Method and apparatus for hydrazine decomposition |
| US3021667A (en) * | 1953-06-02 | 1962-02-20 | Olin Mathieson | Method for initiating the combustion of hydrazine |
| US3081595A (en) * | 1960-06-15 | 1963-03-19 | Thompson Ramo Wooldridge Inc | Rocket propulsion method employing catalytic decomposition of hydrazine |
| US3165382A (en) * | 1961-07-06 | 1965-01-12 | Specialties Dev Corp | Decomposition of hydrazine |
-
1968
- 1968-01-18 US US00698846A patent/US3732694A/en not_active Expired - Lifetime
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2925709A (en) * | 1949-02-12 | 1960-02-23 | Kellogg M W Co | Decomposition of hydrazine |
| US2930184A (en) * | 1949-05-13 | 1960-03-29 | Kellogg M W Co | Method and apparatus for hydrazine decomposition |
| US3021667A (en) * | 1953-06-02 | 1962-02-20 | Olin Mathieson | Method for initiating the combustion of hydrazine |
| US3081595A (en) * | 1960-06-15 | 1963-03-19 | Thompson Ramo Wooldridge Inc | Rocket propulsion method employing catalytic decomposition of hydrazine |
| US3165382A (en) * | 1961-07-06 | 1965-01-12 | Specialties Dev Corp | Decomposition of hydrazine |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4157270A (en) * | 1977-09-12 | 1979-06-05 | The United States Of America As Represented By The Secretary Of The Army | Hydrogen gas generator from hydrazine/ammonia |
| US4876392A (en) * | 1982-09-21 | 1989-10-24 | Exxon Research & Engineering Company | Process for preparation of keystones by oxidation of secondary alcohols using a trimetallic catalyst comprising molybdenum, rhenium and a group VIII noble metal |
| US4737482A (en) * | 1983-07-25 | 1988-04-12 | Exxon Research & Engineering Co. | Catalysts for oxidation of olefins to ketones |
| US4620415A (en) * | 1983-09-29 | 1986-11-04 | Rocket Research Company | Method for initiating decomposition of hydrazine fuels |
| US5542704A (en) * | 1994-09-20 | 1996-08-06 | Oea, Inc. | Automotive inflatable safety system propellant with complexing agent |
| US5746050A (en) * | 1996-01-19 | 1998-05-05 | Primex Technologies, Inc. | Gaseous product delivery system |
| US20020173054A1 (en) * | 2001-05-03 | 2002-11-21 | Hynix Semiconductor Inc. | Method for fabricating ruthenium thin layer |
| US6800542B2 (en) | 2001-05-03 | 2004-10-05 | Hynix Semiconductor Inc. | Method for fabricating ruthenium thin layer |
| US20130327015A1 (en) * | 2012-06-12 | 2013-12-12 | Pamela Pollet | Dual use hydrazine propulsion thruster system |
| CN112108145A (en) * | 2019-06-19 | 2020-12-22 | 中国科学院大连化学物理研究所 | Alumina-supported iridium cluster catalyst and preparation and application thereof |
| CN111646870A (en) * | 2020-05-06 | 2020-09-11 | 北京航天试验技术研究所 | Catalyst applied to low-temperature starting monopropellant and preparation method thereof |
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