US3486330A - Encased propellant for a rocket motor - Google Patents
Encased propellant for a rocket motor Download PDFInfo
- Publication number
- US3486330A US3486330A US725716A US3486330DA US3486330A US 3486330 A US3486330 A US 3486330A US 725716 A US725716 A US 725716A US 3486330D A US3486330D A US 3486330DA US 3486330 A US3486330 A US 3486330A
- Authority
- US
- United States
- Prior art keywords
- propellant
- rocket motor
- tube
- encased
- container
- 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
- 239000003380 propellant Substances 0.000 title description 21
- 239000000843 powder Substances 0.000 description 11
- 239000007788 liquid Substances 0.000 description 8
- 239000003795 chemical substances by application Substances 0.000 description 7
- 239000007787 solid Substances 0.000 description 7
- 239000012530 fluid Substances 0.000 description 5
- 239000000020 Nitrocellulose Substances 0.000 description 4
- 239000000446 fuel Substances 0.000 description 4
- 238000002347 injection Methods 0.000 description 4
- 239000007924 injection Substances 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 239000000203 mixture Substances 0.000 description 4
- 229920001220 nitrocellulos Polymers 0.000 description 4
- SNIOPGDIGTZGOP-UHFFFAOYSA-N Nitroglycerin Chemical compound [O-][N+](=O)OCC(O[N+]([O-])=O)CO[N+]([O-])=O SNIOPGDIGTZGOP-UHFFFAOYSA-N 0.000 description 3
- 229960003711 glyceryl trinitrate Drugs 0.000 description 3
- 239000002245 particle Substances 0.000 description 3
- 239000011230 binding agent Substances 0.000 description 2
- 238000007599 discharging Methods 0.000 description 2
- 239000008187 granular material Substances 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 239000000654 additive Substances 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 229920002301 cellulose acetate Polymers 0.000 description 1
- 239000003975 dentin desensitizing agent Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 229920001971 elastomer Polymers 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 150000002823 nitrates Chemical class 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 229920006395 saturated elastomer Polymers 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 239000003566 sealing material Substances 0.000 description 1
- 239000004449 solid propellant Substances 0.000 description 1
Images
Classifications
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B21/00—Apparatus or methods for working-up explosives, e.g. forming, cutting, drying
- C06B21/0008—Compounding the ingredient
- C06B21/0025—Compounding the ingredient the ingredient being a polymer bonded explosive or thermic component
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B65—CONVEYING; PACKING; STORING; HANDLING THIN OR FILAMENTARY MATERIAL
- B65B—MACHINES, APPARATUS OR DEVICES FOR, OR METHODS OF, PACKAGING ARTICLES OR MATERIALS; UNPACKING
- B65B3/00—Packaging plastic material, semiliquids, liquids or mixed solids and liquids, in individual containers or receptacles, e.g. bags, sacks, boxes, cartons, cans, or jars
- B65B3/04—Methods of, or means for, filling the material into the containers or receptacles
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B21/00—Apparatus or methods for working-up explosives, e.g. forming, cutting, drying
- C06B21/0033—Shaping the mixture
- C06B21/0058—Shaping the mixture by casting a curable composition, e.g. of the plastisol type
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/24—Charging rocket engines with solid propellants; Methods or apparatus specially adapted for working solid propellant charges
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B1/00—Explosive charges characterised by form or shape but not dependent on shape of container
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B65—CONVEYING; PACKING; STORING; HANDLING THIN OR FILAMENTARY MATERIAL
- B65B—MACHINES, APPARATUS OR DEVICES FOR, OR METHODS OF, PACKAGING ARTICLES OR MATERIALS; UNPACKING
- B65B2220/00—Specific aspects of the packaging operation
- B65B2220/14—Adding more than one type of material or article to the same package
Definitions
- the invention relates to a solid mass composed of granular particles and a hardened initially liquid binder and encased in a tubular container, and more particularly, the invention relates to a rocket motor propellant in the form of a solid body composed of granular particles such as nitrocellulose powder and an initially liquid gelatinization agent such as nitroglycerine and encased in a generally cylindrical container to effect burning of the propellant from one end only rather than along the wall of the propellant.
- FIG. 1 is an elevational perspective view, partly in section, showing a container filled with propellant powder and a device for injecting a gelatinization agent into the container, said device being shown inactive;
- FIG. 2 is a perspective view similar to FIG. 1, but showing the injection device in operation;
- FIG. 3 is a view similar to FIGS. 1 and 2, but showing the injection device withdrawn from the container after completion of the operation.
- a container in the form of a cylindrical tube 1 having at one end, in practice the lower end, an inwardly directed peripheral flange 2, the other end being open.
- the tube and its flange are preferably integral but in any event preferably made of the same material such as cellulose acetate.
- the purpose of the tube is to prevent buming of the propellant material along its cylindrical surface and also to serve as heat insulation to protect a motor which may be located adjacent to the propellant.
- the center opening defined by flange 2 is covered with an elastic disk 3 made of a self-sealing material such as rubber, and secured to the flange, preferably to the outside thereof, by a suitable and conventional adhesive.
- the tube is filled through its open upper end by means of a con- Patented Dec. 30, 1969 ventional metering device with a suitable propellant powder 4 such as nitrocellulose powder plus additives as may be required in propellant powders.
- a disk 5 having apertures 6 is placed in the tube to hold the nitrocellulose powder filling in position.
- the filled tube now closed off at both ends, is placed, preferably in upright position, above the injecting device.
- This device is shown as comprising an. injection needle 7 having a pointed end 9 and an outlet aperture 8 below the point 9.
- the other end of the needle is extended into a hollow head which, via a pipe stub 11, communicates with a hose 12.
- This hose should be visualized as being connected to a pressurized supply of a hardening gelatinization agent such as nitroglycerine, or other nitrate esters with or without desensitizing agents.
- Head 10 is mounted on one end of a rod 13, the other end of which mounts a piston 14 slidable in a cylinder 15.
- the cylinder communicates at opposite ends with conduits 16 and 17 for feeding a pressurized gaseous or liquid fluid into the cylinder and discharging the same therefrom.
- the needle of the injection device Upon completion of the filling of the tube with the gelatinization agent, the needle of the injection device is lowered by feeding pressure fluid through conduit 17 and discharging fluid through conduit 16, as is indicated in FIG. 3. Upon withdrawal of the needle, the puncture made in the disk by the needle will automatically close itself.
- the gelatinization agent When the gelatinization agent has fully hardened the mixture in the tube becomes a solid body completely filling the same to the extent determined by the level of cover disk 5. No further operation is necessary either at the bottom end or the top end of the tube. In other words, the encased propellant is now ready for installation in a rocket motor.
- the invention is particularly suitable in connection with rocket motors requiring burning of the propellant from one end only, the invention can be advantageously used wherever it is necessary to fill a container with a powderized material which is then to be transformed into a solid body by adding a hardening binder thereto.
- a rocket motor fuel element comprising in combination:
- tubular member made of plastic, said member being open on one end and having an inwardly turned peripheral flange on the other end, said flanged end constituting the bottom end of the fuel element;
- a disk made of an elastic self-sealing sheet material adhered to said flange and covering the opening defined by said flange;
- a solid rocket motor propellant composed of a mixture of a granular material and a hardened liquid filling said tubular member
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Organic Chemistry (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Medicinal Preparation (AREA)
- Containers And Packaging Bodies Having A Special Means To Remove Contents (AREA)
- Basic Packing Technique (AREA)
Description
Dec.- 30, 1969 a R EDMAN ETAL ENCASED PROPELLANT FOR A ROCKET MOTOR Original Filed Jan. 10, 1967 1 N VEN TORS BJORN @0001. F EDMAN 0L OF OMAN Y MMEQW US. Cl. 6039.47
United States Patent 3,486,330 EN'CASED PROPELLANT FOR A ROCKET MOTOR Bjorn Rudolf Edman, Karlskoga, and Olof Oman, Valasen, Sweden, assignors to Aktiebolaget Bofors, Bofors, Sweden Original application Jan. 10, 1967, Ser. No. 608,358. Divided and this application May 1, 1968, Ser. No. 725,716
Claims priority, application Sweden, Jan. 21, 1966,
Int. Cl. F02k 9/04 3 Claims ABSTRACT OF THE DISCLOSURE A body of a solid propellant encased in a tubular container to eifect burning of the propellant from one of the ends of the propellant rather than along the entire wall surface of the propellant.
The present application is a divisional application divided out of our copending application Ser. No. 608,358 filed Jan. 10, 1967.
The invention relates to a solid mass composed of granular particles and a hardened initially liquid binder and encased in a tubular container, and more particularly, the invention relates to a rocket motor propellant in the form of a solid body composed of granular particles such as nitrocellulose powder and an initially liquid gelatinization agent such as nitroglycerine and encased in a generally cylindrical container to effect burning of the propellant from one end only rather than along the wall of the propellant.
It is a broad object of the invention to provide a novel and improved encased propellant mixture in the form of a solid body which when ignited will burn from one end only, preferably the top end, rather than along its side wall, and which can be safely, economically and rapidly manufactured.
Other objects, features and advantages of the invention will be set forth in the appended claims constituting part of the application.
In the accompanying drawing, a preferred embodiment of a container filled with a propellant in the form of a solid body and the manner of filling the container with the propellant mixture are shown by way of illustration and not by way of limitation.
In the drawing:
FIG. 1 is an elevational perspective view, partly in section, showing a container filled with propellant powder and a device for injecting a gelatinization agent into the container, said device being shown inactive;
FIG. 2 is a perspective view similar to FIG. 1, but showing the injection device in operation; and
FIG. 3 is a view similar to FIGS. 1 and 2, but showing the injection device withdrawn from the container after completion of the operation.
Referring now to the figures more in detail, there is shown a container in the form of a cylindrical tube 1 having at one end, in practice the lower end, an inwardly directed peripheral flange 2, the other end being open. The tube and its flange are preferably integral but in any event preferably made of the same material such as cellulose acetate. The purpose of the tube is to prevent buming of the propellant material along its cylindrical surface and also to serve as heat insulation to protect a motor which may be located adjacent to the propellant.
The center opening defined by flange 2 is covered with an elastic disk 3 made of a self-sealing material such as rubber, and secured to the flange, preferably to the outside thereof, by a suitable and conventional adhesive. The tube is filled through its open upper end by means of a con- Patented Dec. 30, 1969 ventional metering device with a suitable propellant powder 4 such as nitrocellulose powder plus additives as may be required in propellant powders. After filling the tube with powder to the desired level, a disk 5 having apertures 6 is placed in the tube to hold the nitrocellulose powder filling in position.
The filled tube, now closed off at both ends, is placed, preferably in upright position, above the injecting device. This device is shown as comprising an. injection needle 7 having a pointed end 9 and an outlet aperture 8 below the point 9. The other end of the needle is extended into a hollow head which, via a pipe stub 11, communicates with a hose 12. This hose should be visualized as being connected to a pressurized supply of a hardening gelatinization agent such as nitroglycerine, or other nitrate esters with or without desensitizing agents. Head 10 is mounted on one end of a rod 13, the other end of which mounts a piston 14 slidable in a cylinder 15. The cylinder communicates at opposite ends with conduits 16 and 17 for feeding a pressurized gaseous or liquid fluid into the cylinder and discharging the same therefrom.
As shown in FIG. 2, feeding pressurized fluid into the cylinder through conduit 16 will cause the piston to be lifted in the cylinder, fluid in the space above the pist n being discharged through conduit 17. As a result, needle 7 will pierce disk 3 so that the discharge aperture 8 is now located within the enclosed space of the tube filled with powder. The liquid gelatinizing agent is now fed through hose 12 and head 10 into the tube, thereby gradually filling the interstices between the powder particles in the tube. After the powder has been sufliciently saturated, which manifests itself by liquid percolating through apertures 6, the feed of the liquid agent is discontinued.
Upon completion of the filling of the tube with the gelatinization agent, the needle of the injection device is lowered by feeding pressure fluid through conduit 17 and discharging fluid through conduit 16, as is indicated in FIG. 3. Upon withdrawal of the needle, the puncture made in the disk by the needle will automatically close itself.
When the gelatinization agent has fully hardened the mixture in the tube becomes a solid body completely filling the same to the extent determined by the level of cover disk 5. No further operation is necessary either at the bottom end or the top end of the tube. In other words, the encased propellant is now ready for installation in a rocket motor.
While the invention is particularly suitable in connection with rocket motors requiring burning of the propellant from one end only, the invention can be advantageously used wherever it is necessary to fill a container with a powderized material which is then to be transformed into a solid body by adding a hardening binder thereto.
What is claimed is:
1. A rocket motor fuel element comprising in combination:
a tubular member made of plastic, said member being open on one end and having an inwardly turned peripheral flange on the other end, said flanged end constituting the bottom end of the fuel element;
a disk made of an elastic self-sealing sheet material adhered to said flange and covering the opening defined by said flange;
a solid rocket motor propellant composed of a mixture of a granular material and a hardened liquid filling said tubular member; and
a perforated cover plate covering said propellant at the open end of the tubular member.
2. The fuel element according to claim 1 wherein said granular material is granulated nitrocellulose powder and said hardened liquid is hardened nitroglycerine.
' 3 4 3. The fuel element according to claim 1 wherein said 3,202,730 8/1965 Gordon et al. 264-3 disk is adhered to the outside of said flange overlapping 3,205,286 9/1965 Black 86-1 XR the same. 3,222,433 12/ 1965 Makay 264-3 References Cited UNITED STATES PATENTS 5 CARLTON R. CROYLE, Primary Examiner U.S. Cl. X.R.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
SE760/66A SE306900B (en) | 1966-01-21 | 1966-01-21 |
Publications (1)
Publication Number | Publication Date |
---|---|
US3486330A true US3486330A (en) | 1969-12-30 |
Family
ID=20257063
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US608358A Expired - Lifetime US3419644A (en) | 1966-01-21 | 1967-01-10 | Method of filling a tubular part with a solid, granular substance and a liquid substance |
US725716A Expired - Lifetime US3486330A (en) | 1966-01-21 | 1968-05-01 | Encased propellant for a rocket motor |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US608358A Expired - Lifetime US3419644A (en) | 1966-01-21 | 1967-01-10 | Method of filling a tubular part with a solid, granular substance and a liquid substance |
Country Status (5)
Country | Link |
---|---|
US (2) | US3419644A (en) |
DE (1) | DE1561938A1 (en) |
FR (1) | FR1508743A (en) |
GB (1) | GB1157212A (en) |
SE (1) | SE306900B (en) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2442813A1 (en) * | 1978-06-27 | 1980-06-27 | Poudres & Explosifs Ste Nale | HOT MOLDING PROCESS FOR DOUBLE BASE PROPERGOL BLOCKS |
US5212946A (en) * | 1991-05-20 | 1993-05-25 | Industrial Solid Propulsion | Reloadable/modular solid propellant rocket motor |
US20070135671A1 (en) * | 2004-04-09 | 2007-06-14 | Clean Earth Technologies, Llc | Method for defeat of bulk chemical warfare agents |
US20100024428A1 (en) * | 2006-07-31 | 2010-02-04 | Rosenfield Gary C | Rocket Apparatus and/or Method |
US20100237197A1 (en) * | 2005-07-15 | 2010-09-23 | Rosenfield Gary C | Rocket ejection delay apparatus and/or method |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4764329A (en) * | 1987-06-12 | 1988-08-16 | The United States Of American As Represented By The Secretary Of The Army | Producing explosive material in granular form |
CN104554841B (en) * | 2014-11-21 | 2018-03-23 | 程鹏志 | A kind of radiopharmaceutical agent automatic subpackaging process and system |
FR3081299B1 (en) * | 2018-05-23 | 2020-09-11 | Oreal | DEVICE FOR PREPARING A COSMETIC COMPOSTION, AND ASSOCIATED PROCESS |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2892377A (en) * | 1955-02-25 | 1959-06-30 | Ici Ltd | Packages containing a material for use in blasting |
US2985104A (en) * | 1955-01-03 | 1961-05-23 | Phillips Petroleum Co | Improved cartridge for producing gas |
US3027597A (en) * | 1948-05-20 | 1962-04-03 | Hercules Powder Co Ltd | Method and apparatus for manufacture of cast plastic compositions |
US3202730A (en) * | 1961-03-07 | 1965-08-24 | Ici Ltd | Process for making propellant charges |
US3205286A (en) * | 1946-06-08 | 1965-09-07 | Donald H Black | Smokeless powder manufacture |
US3222433A (en) * | 1961-07-18 | 1965-12-07 | Jr Nicolas Makay | Method of casting propellant within a rocket motor casing |
Family Cites Families (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3189946A (en) * | 1956-12-26 | 1965-06-22 | Modern Shoe Making Machine Cor | Apparatus for preforming shoe upper parts by injection molding principles |
-
1966
- 1966-01-21 SE SE760/66A patent/SE306900B/xx unknown
-
1967
- 1967-01-09 DE DE19671561938 patent/DE1561938A1/en active Pending
- 1967-01-10 US US608358A patent/US3419644A/en not_active Expired - Lifetime
- 1967-01-16 GB GB2241/67A patent/GB1157212A/en not_active Expired
- 1967-01-20 FR FR92018A patent/FR1508743A/en not_active Expired
-
1968
- 1968-05-01 US US725716A patent/US3486330A/en not_active Expired - Lifetime
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3205286A (en) * | 1946-06-08 | 1965-09-07 | Donald H Black | Smokeless powder manufacture |
US3027597A (en) * | 1948-05-20 | 1962-04-03 | Hercules Powder Co Ltd | Method and apparatus for manufacture of cast plastic compositions |
US2985104A (en) * | 1955-01-03 | 1961-05-23 | Phillips Petroleum Co | Improved cartridge for producing gas |
US2892377A (en) * | 1955-02-25 | 1959-06-30 | Ici Ltd | Packages containing a material for use in blasting |
US3202730A (en) * | 1961-03-07 | 1965-08-24 | Ici Ltd | Process for making propellant charges |
US3222433A (en) * | 1961-07-18 | 1965-12-07 | Jr Nicolas Makay | Method of casting propellant within a rocket motor casing |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2442813A1 (en) * | 1978-06-27 | 1980-06-27 | Poudres & Explosifs Ste Nale | HOT MOLDING PROCESS FOR DOUBLE BASE PROPERGOL BLOCKS |
US5212946A (en) * | 1991-05-20 | 1993-05-25 | Industrial Solid Propulsion | Reloadable/modular solid propellant rocket motor |
US20070135671A1 (en) * | 2004-04-09 | 2007-06-14 | Clean Earth Technologies, Llc | Method for defeat of bulk chemical warfare agents |
US7256320B2 (en) * | 2004-04-09 | 2007-08-14 | Clean Earth Technologies, Llc | Method for defeat of bulk chemical warfare agents |
US20100237197A1 (en) * | 2005-07-15 | 2010-09-23 | Rosenfield Gary C | Rocket ejection delay apparatus and/or method |
US7918419B2 (en) | 2005-07-15 | 2011-04-05 | Rcs Rocket Motor Components, Inc. | Rocket ejection delay apparatus and/or method |
US20100024428A1 (en) * | 2006-07-31 | 2010-02-04 | Rosenfield Gary C | Rocket Apparatus and/or Method |
Also Published As
Publication number | Publication date |
---|---|
DE1561938A1 (en) | 1970-05-21 |
FR1508743A (en) | 1968-01-05 |
US3419644A (en) | 1968-12-31 |
SE306900B (en) | 1968-12-09 |
GB1157212A (en) | 1969-07-02 |
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