US20050115651A1 - High energy solid propellant - Google Patents
High energy solid propellant Download PDFInfo
- Publication number
- US20050115651A1 US20050115651A1 US10/712,340 US71234003A US2005115651A1 US 20050115651 A1 US20050115651 A1 US 20050115651A1 US 71234003 A US71234003 A US 71234003A US 2005115651 A1 US2005115651 A1 US 2005115651A1
- Authority
- US
- United States
- Prior art keywords
- fuel
- propellant
- high energy
- solid propellant
- lithium
- 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.)
- Abandoned
Links
- 239000004449 solid propellant Substances 0.000 title claims abstract description 39
- 239000000446 fuel Substances 0.000 claims abstract description 28
- 239000011230 binding agent Substances 0.000 claims abstract description 20
- 239000007800 oxidant agent Substances 0.000 claims abstract description 18
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims abstract description 16
- 229910052744 lithium Inorganic materials 0.000 claims abstract description 16
- 239000003380 propellant Substances 0.000 claims abstract description 16
- PAWQVTBBRAZDMG-UHFFFAOYSA-N 2-(3-bromo-2-fluorophenyl)acetic acid Chemical compound OC(=O)CC1=CC=CC(Br)=C1F PAWQVTBBRAZDMG-UHFFFAOYSA-N 0.000 claims abstract description 4
- GDDNTTHUKVNJRA-UHFFFAOYSA-N 3-bromo-3,3-difluoroprop-1-ene Chemical group FC(F)(Br)C=C GDDNTTHUKVNJRA-UHFFFAOYSA-N 0.000 claims abstract description 4
- BRUFJXUJQKYQHA-UHFFFAOYSA-O ammonium dinitramide Chemical compound [NH4+].[O-][N+](=O)[N-][N+]([O-])=O BRUFJXUJQKYQHA-UHFFFAOYSA-O 0.000 claims abstract description 4
- 229930195733 hydrocarbon Natural products 0.000 claims abstract description 4
- 150000002430 hydrocarbons Chemical class 0.000 claims abstract description 4
- 229920000642 polymer Polymers 0.000 claims abstract description 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 11
- 229910052782 aluminium Inorganic materials 0.000 claims description 11
- -1 polyethylene Polymers 0.000 claims description 8
- 229920001153 Polydicyclopentadiene Polymers 0.000 claims description 7
- 239000004698 Polyethylene Substances 0.000 claims description 6
- 229920000573 polyethylene Polymers 0.000 claims description 6
- 239000004793 Polystyrene Substances 0.000 claims description 3
- 229920002223 polystyrene Polymers 0.000 claims description 3
- 238000010944 pre-mature reactiony Methods 0.000 abstract 1
- 238000006243 chemical reaction Methods 0.000 description 3
- 239000008393 encapsulating agent Substances 0.000 description 3
- 239000004615 ingredient Substances 0.000 description 3
- 239000002245 particle Substances 0.000 description 3
- 239000002904 solvent Substances 0.000 description 3
- 229920002121 Hydroxyl-terminated polybutadiene Polymers 0.000 description 2
- 229920003006 Polybutadiene acrylonitrile Polymers 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000005538 encapsulation Methods 0.000 description 2
- 230000005514 two-phase flow Effects 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 101800000579 Pheromone biosynthesis-activating neuropeptide Proteins 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- LTMGJWZFKVPEBX-UHFFFAOYSA-N buta-1,3-diene;prop-2-enenitrile;prop-2-enoic acid Chemical compound C=CC=C.C=CC#N.OC(=O)C=C LTMGJWZFKVPEBX-UHFFFAOYSA-N 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000004090 dissolution Methods 0.000 description 1
- 239000012442 inert solvent Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000012280 lithium aluminium hydride Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 239000002244 precipitate Substances 0.000 description 1
- 239000000047 product Substances 0.000 description 1
- 230000009257 reactivity Effects 0.000 description 1
- 239000002002 slurry Substances 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B47/00—Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosives; Suspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase
- C06B47/02—Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosives; Suspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase the components comprising a binary propellant
- C06B47/10—Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosives; Suspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase the components comprising a binary propellant a component containing free boron, an organic borane or a binary compound of boron, except with oxygen
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B45/00—Compositions or products which are defined by structure or arrangement of component of product
- C06B45/04—Compositions or products which are defined by structure or arrangement of component of product comprising solid particles dispersed in solid solution or matrix not used for explosives where the matrix consists essentially of nitrated carbohydrates or a low molecular organic explosive
- C06B45/06—Compositions or products which are defined by structure or arrangement of component of product comprising solid particles dispersed in solid solution or matrix not used for explosives where the matrix consists essentially of nitrated carbohydrates or a low molecular organic explosive the solid solution or matrix containing an organic component
- C06B45/10—Compositions or products which are defined by structure or arrangement of component of product comprising solid particles dispersed in solid solution or matrix not used for explosives where the matrix consists essentially of nitrated carbohydrates or a low molecular organic explosive the solid solution or matrix containing an organic component the organic component containing a resin
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B45/00—Compositions or products which are defined by structure or arrangement of component of product
- C06B45/18—Compositions or products which are defined by structure or arrangement of component of product comprising a coated component
- C06B45/30—Compositions or products which are defined by structure or arrangement of component of product comprising a coated component the component base containing an inorganic explosive or an inorganic thermic component
- C06B45/32—Compositions or products which are defined by structure or arrangement of component of product comprising a coated component the component base containing an inorganic explosive or an inorganic thermic component the coating containing an organic compound
Definitions
- the present invention provides a solid propellant for use in rocket engines.
- the present invention provides a high energy solid propellant comprised of an oxidizer, fuel and binder, wherein the fuel is encapsulated or microencapsulated.
- This encapsulation or microencapsulation allows for use of a highly energetic fuel component, while avoiding uncontrollable reactivity, and provides a propellant having an exceptionally high specific impulse.
- a solid propellant is conventionally comprised of an oxidizer, fuel and a binder. Generally, in a solid propellant comprised of 72% oxidizer, 16% fuel and 12% binder, an I sp of around 272 seconds is common. Conventionally, solid propellant binders, such as PBAN (polybutadiene acrylonitrile copolymer) have been used, as well as HTPB (hydroxyl-terminated polybutadiene).
- PBAN polybutadiene acrylonitrile copolymer
- a significant problem with conventional solid propellants is the phenomena of two-phase flow.
- Aluminum is added to increase the thermodynamic energy of the propellant.
- the kinetics of the rocket combustion process can lead to liquid, unreacted aluminum emerging from the nozzle with a commensurate decrease in thrust.
- the particle size of the aluminum can be reduced such that this phenomena in principle is minimized, however, a passive oxide layer (ca. 20 A) is immediately formed on the small particles, which much be destroyed within the combustion chamber. Again, the energy gain is lost by the subsequent “after-burning”.
- a high energy solid propellant comprising:
- a high energy solid propellant according to the first embodiment above wherein the binder is PDCPD (polydicyclopentadiene), polyethylene, polystyrene, or low molecular weight polyethylene.
- PDCPD polydicyclopentadiene
- polyethylene polyethylene
- polystyrene polystyrene
- low molecular weight polyethylene low molecular weight polyethylene
- a high energy solid propellant according to the first embodiment above wherein the fuel is comprised of lithium hexahydridoborane and aluminum, or LHA (lithium hexahydridoalane) and aluminum.
- a high energy solid propellant according to the second embodiment above wherein fuel is comprised of lithium hexahydridoborane and aluminum, or LHA (lithium hexahydridoalane) and aluminum.
- the high energy solid propellant of the first embodiment is provided, wherein the propellant comprises 60-80 wt % oxidizer, 5-30 wt % fuel, and 5-15 wt % binder.
- the high energy solid propellant of the first embodiment is provided, wherein the propellant comprises 65-75 wt % oxidizer, 10-25 wt % fuel, and 10-15 wt % binder.
- the high energy solid propellant of the first embodiment is provided, wherein the propellant comprises 70-75 wt % oxidizer, 15-25 wt % fuel, and 12 wt % binder.
- I sp specific impulse
- specific impulse is defined as force/mass flow rate.
- the specific impulse is (force/mass of solid propellant) ⁇ time.
- Specific impulse is an important characteristic of a solid propellant, in that it defines the appropriate mission for a given rocket, as rockets are mass-limited devices. The more inherent energy that is present per mass, the greater the payload, or the greater the range of a given device.
- the present invention provides a solid propellant comprising PDCPD, LHA and an oxidizer.
- the I sp can be increased to as much as 310 seconds.
- oxidizer such as ammonium perchlorate, ammonium nitrate and ammonium dinitramide may be used.
- binder polymeric hydrocarbons are preferred.
- PDCPD polydicyclopentadiene
- polyethylene polyethylene
- polystyrene polystyrene
- LMWPE low molecular weight polyethylene
- LHB lithium hexahydridoborane
- LHA lithium hexahydridoalane
- the fuel component is encapsulated, or preferably microencapsulated such that the propellant grain is fabricated without diminution of its energetic properties.
- the propellant is comprised of 60-80% oxidizer, 5-30% fuel, and 5-15% binder; more preferably 65-75% oxidizer, 10-25% fuel, and 10-15% binder; most preferably 70-75% oxidizer, 15-25% fuel, and 12% binder.
- microencapsulation of the solid propellant is preferred. Microencapsulation may be achieved by, for example:
- the high energy solid fuel ingredient is precipitated out of solution upon reaction with the alkyl lithium compound and dissolved lithium aluminum hydride in appropriate solvents. If an appropriate polymer, wax, or compound is dissolved in the solvent system, the high energy solid propellant will microencapsulate as it precipitates.
- the high energy solid fuel ingredient is manufactured as detailed in 1) above, without the encapsulating agent.
- the reaction mass is filtered, rinsed multiple times and suspended in an appropriate inert solvent into which an encapsulating agent (see above) is added by dissolution. This slurry is then spray-dried to its final state in warm air.
- All three of the above methods may form a free-flowing powder of LHA or LHB that is atmospherically unreactive, and thus useful in making the high-energy solid propellant of the present invention.
Landscapes
- Chemical & Material Sciences (AREA)
- Organic Chemistry (AREA)
- Crystallography & Structural Chemistry (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Dispersion Chemistry (AREA)
- Molecular Biology (AREA)
- Inorganic Chemistry (AREA)
- Solid Fuels And Fuel-Associated Substances (AREA)
Abstract
The present invention provides a high energy solid propellant containing an oxidizer, binder and fuel, wherein the fuel and/or the propellant as a whole is encapsulated or microencapsulated so as prevent premature reaction while still maintaining the energetic properties thereof. The oxidizer is preferably ammonium perchlorate, ammonium nitrate or ammonium dinitramide. The binder is preferably polymeric hydrocarbons or polymers. The fuel is preferably lithium hexahydridoborane or lithium hexahydridoalane.
Description
- The present invention provides a solid propellant for use in rocket engines. In particular, the present invention provides a high energy solid propellant comprised of an oxidizer, fuel and binder, wherein the fuel is encapsulated or microencapsulated. This encapsulation or microencapsulation allows for use of a highly energetic fuel component, while avoiding uncontrollable reactivity, and provides a propellant having an exceptionally high specific impulse.
- A solid propellant is conventionally comprised of an oxidizer, fuel and a binder. Generally, in a solid propellant comprised of 72% oxidizer, 16% fuel and 12% binder, an Isp of around 272 seconds is common. Conventionally, solid propellant binders, such as PBAN (polybutadiene acrylonitrile copolymer) have been used, as well as HTPB (hydroxyl-terminated polybutadiene).
- A significant problem with conventional solid propellants is the phenomena of two-phase flow. Aluminum is added to increase the thermodynamic energy of the propellant. However, the kinetics of the rocket combustion process can lead to liquid, unreacted aluminum emerging from the nozzle with a commensurate decrease in thrust. The particle size of the aluminum can be reduced such that this phenomena in principle is minimized, however, a passive oxide layer (ca. 20 A) is immediately formed on the small particles, which much be destroyed within the combustion chamber. Again, the energy gain is lost by the subsequent “after-burning”.
- It is an object of the present inventors to overcome the deficiencies of the conventional solid propellants, as mentioned above. In particular, it is an object of the present invention to provide a highly reactive solid propellant that avoids the problems traditionally associated with two-phase flow.
- In order to achieve the object of the present invention, as described above, the present inventors provide, in a first embodiment, a high energy solid propellant comprising:
-
- (a) an oxidizer comprised of ammonium perchlorate, ammonium nitrate or ammonium dinitramide;
- (b) a binder comprised of polymeric hydrocarbons or polymers; and
- (c) a fuel comprised of lithium hexahydridoborane or lithium hexahydridoalane,
- wherein the fuel and/or solid propellant is encapsulated or microencapsulated such that the propellant grain is fabricated without diminution of its energetic properties.
- In a second embodiment, a high energy solid propellant according to the first embodiment above is provided, wherein the binder is PDCPD (polydicyclopentadiene), polyethylene, polystyrene, or low molecular weight polyethylene.
- In a third embodiment, a high energy solid propellant according to the first embodiment above is provided, wherein the fuel is comprised of lithium hexahydridoborane and aluminum, or LHA (lithium hexahydridoalane) and aluminum.
- In a fourth embodiment, a high energy solid propellant according to the second embodiment above is provided, wherein fuel is comprised of lithium hexahydridoborane and aluminum, or LHA (lithium hexahydridoalane) and aluminum.
- In a fifth embodiment of the present invention, the high energy solid propellant of the first embodiment is provided, wherein the propellant comprises 60-80 wt % oxidizer, 5-30 wt % fuel, and 5-15 wt % binder.
- In a sixth embodiment of the present invention, the high energy solid propellant of the first embodiment is provided, wherein the propellant comprises 65-75 wt % oxidizer, 10-25 wt % fuel, and 10-15 wt % binder.
- In a seventh embodiment of the present invention, the high energy solid propellant of the first embodiment is provided, wherein the propellant comprises 70-75 wt % oxidizer, 15-25 wt % fuel, and 12 wt % binder.
- Isp, specific impulse, is defined as force/mass flow rate. In the context of solid propellants used in rocket engines, the specific impulse is (force/mass of solid propellant)×time. Specific impulse is an important characteristic of a solid propellant, in that it defines the appropriate mission for a given rocket, as rockets are mass-limited devices. The more inherent energy that is present per mass, the greater the payload, or the greater the range of a given device.
- Conventional solid propellants have attained Isp's of as much as 272 seconds. In contrast, the present invention provides a solid propellant comprising PDCPD, LHA and an oxidizer. In such a composition, the Isp can be increased to as much as 310 seconds.
- In the present invention, oxidizer such as ammonium perchlorate, ammonium nitrate and ammonium dinitramide may be used. For the binder, polymeric hydrocarbons are preferred. In particular, PDCPD (polydicyclopentadiene), polyethylene, polystyrene and LMWPE (low molecular weight polyethylene) are preferred. As the fuel component of the solid propellant, LHB (lithium hexahydridoborane) and LHA (lithium hexahydridoalane) are used.
- Lastly, it is essential that the fuel component is encapsulated, or preferably microencapsulated such that the propellant grain is fabricated without diminution of its energetic properties. The propellant is comprised of 60-80% oxidizer, 5-30% fuel, and 5-15% binder; more preferably 65-75% oxidizer, 10-25% fuel, and 10-15% binder; most preferably 70-75% oxidizer, 15-25% fuel, and 12% binder.
- As the high energy solid propellant is very reactive, an air barrier or coating is applied to either the fuel component alone, or to the entire propellant, so as to encapsulate same, to prevent reaction thereof with foreign sources. In particular, microencapsulation of the solid propellant is preferred. Microencapsulation may be achieved by, for example:
- 1) The high energy solid fuel ingredient is precipitated out of solution upon reaction with the alkyl lithium compound and dissolved lithium aluminum hydride in appropriate solvents. If an appropriate polymer, wax, or compound is dissolved in the solvent system, the high energy solid propellant will microencapsulate as it precipitates.
- 2) The high energy solid fuel ingredient is manufactured as detailed in 1) above, without the encapsulating agent. The reaction mass is filtered, rinsed multiple times and suspended in an appropriate inert solvent into which an encapsulating agent (see above) is added by dissolution. This slurry is then spray-dried to its final state in warm air.
- 3) The high energy solid fuel ingredient suspension formed in 2) above is added to an immiscible solvent which contains the dissolved encapsulating agent (see above). This two-phase system is shaken to cause the particles to contact the encapsulation agent and thus form the microencapsulated system. The product is filtered and dried as normal.
- All three of the above methods may form a free-flowing powder of LHA or LHB that is atmospherically unreactive, and thus useful in making the high-energy solid propellant of the present invention.
Claims (8)
1. A high energy solid propellant comprising:
(a) an oxidizer comprised of ammonium perchlorate, ammonium nitrate or ammonium dinitramide;
(b) a binder comprised of polymeric hydrocarbons or polymers; and
(c) a fuel comprised of lithium hexahydridoborane or lithium hexahydridoalane,
wherein the fuel is encapsulated or microencapsulated such that the propellant grain is fabricated without diminution of its energetic properties.
2. The high energy solid propellant according to claim 1 , wherein the binder is PDCPD (polydicyclopentadiene), polyethylene, polystyrene, or low molecular weight polyethylene.
3. The high energy solid propellant according to claim 1 , wherein the fuel is comprised of lithium hexahydridoborane and aluminum, or LHA (lithium hexahydridoalane) and aluminum.
4. The high energy solid propellant according to claim 2 , wherein fuel is comprised of lithium hexahydridoborane and aluminum, or LHA (lithium hexahydridoalane) and aluminum.
5. The high energy solid propellant of claim 1 , wherein the propellant comprises 60-80 wt % oxidizer, 5-30 wt % fuel, and 5-15 wt % binder.
6. The high energy solid propellant of claim 1 , wherein the propellant comprises 65-75 wt % oxidizer, 10-25 wt % fuel, and 10-15 wt % binder.
7. The high energy solid propellant of claim 1 , wherein the propellant comprises 70-75 wt % oxidizer, 15-25 wt % fuel, and 12 wt % binder.
8. The high energy solid propellant of claim 1 , wherein the entire propellant is encapsulated or microencapsulated such that the propellant grain is fabricated without diminution of its energetic properties.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US10/712,340 US20050115651A1 (en) | 2003-11-14 | 2003-11-14 | High energy solid propellant |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US10/712,340 US20050115651A1 (en) | 2003-11-14 | 2003-11-14 | High energy solid propellant |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US20050115651A1 true US20050115651A1 (en) | 2005-06-02 |
Family
ID=34619852
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US10/712,340 Abandoned US20050115651A1 (en) | 2003-11-14 | 2003-11-14 | High energy solid propellant |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US20050115651A1 (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090114319A1 (en) * | 2007-06-08 | 2009-05-07 | Jebrail Farzaneh F | Micro-encapsulation of components and incorporation of such into energetic formulations |
| RU2481319C1 (en) * | 2011-12-02 | 2013-05-10 | Открытое акционерное общество "Федеральный научно-производственный центр "Алтай" | Solid-fuel gas-generating composition |
| US11028675B2 (en) | 2014-08-15 | 2021-06-08 | Global Oil EOR Systems, Ltd. | Hydrogen peroxide steam generator for oilfield applications |
| EP3939952A1 (en) | 2020-07-17 | 2022-01-19 | Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. | Fast burning solid propellant comprising an oxidizer, an energetic binder and a metallic burn-off modifier and method for its preparation |
| CN116553987A (en) * | 2023-06-27 | 2023-08-08 | 哈尔滨工业大学 | Method for preparing zirconium hydride coated ammonium perchlorate composite energetic material through solvent anti-solvent |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3441455A (en) * | 1961-01-13 | 1969-04-29 | Continental Oil Co | Encapsulated propellants and method for their preparation from fluorinated monomers using radiation |
| US5714711A (en) * | 1990-12-31 | 1998-02-03 | Mei Corporation | Encapsulated propellant grain composition, method of preparation, article fabricated therefrom and method of fabrication |
-
2003
- 2003-11-14 US US10/712,340 patent/US20050115651A1/en not_active Abandoned
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3441455A (en) * | 1961-01-13 | 1969-04-29 | Continental Oil Co | Encapsulated propellants and method for their preparation from fluorinated monomers using radiation |
| US5714711A (en) * | 1990-12-31 | 1998-02-03 | Mei Corporation | Encapsulated propellant grain composition, method of preparation, article fabricated therefrom and method of fabrication |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090114319A1 (en) * | 2007-06-08 | 2009-05-07 | Jebrail Farzaneh F | Micro-encapsulation of components and incorporation of such into energetic formulations |
| RU2481319C1 (en) * | 2011-12-02 | 2013-05-10 | Открытое акционерное общество "Федеральный научно-производственный центр "Алтай" | Solid-fuel gas-generating composition |
| US11028675B2 (en) | 2014-08-15 | 2021-06-08 | Global Oil EOR Systems, Ltd. | Hydrogen peroxide steam generator for oilfield applications |
| EP3939952A1 (en) | 2020-07-17 | 2022-01-19 | Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. | Fast burning solid propellant comprising an oxidizer, an energetic binder and a metallic burn-off modifier and method for its preparation |
| DE102020118962A1 (en) | 2020-07-17 | 2022-01-20 | Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung eingetragener Verein | Fast-burning solid propellant with an oxidizer, an energetic binder and a metallic burn-up modifier and method for its production |
| CN116553987A (en) * | 2023-06-27 | 2023-08-08 | 哈尔滨工业大学 | Method for preparing zirconium hydride coated ammonium perchlorate composite energetic material through solvent anti-solvent |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| AS | Assignment |
Owner name: SWIFT ENTERPRISES, LTD., INDIANA Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:RUSEK, JOHN;MALMER, KENNETH;REEL/FRAME:014705/0132 Effective date: 20031107 |
|
| STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |