US3688988A - Disposable rocket motor nozzle - Google Patents
Disposable rocket motor nozzle Download PDFInfo
- Publication number
- US3688988A US3688988A US97643A US3688988DA US3688988A US 3688988 A US3688988 A US 3688988A US 97643 A US97643 A US 97643A US 3688988D A US3688988D A US 3688988DA US 3688988 A US3688988 A US 3688988A
- Authority
- US
- United States
- Prior art keywords
- body portion
- nozzle body
- shaped charge
- nozzle
- rocket motor
- 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
- 239000000463 material Substances 0.000 claims description 15
- 230000004888 barrier function Effects 0.000 claims description 13
- 239000000945 filler Substances 0.000 claims description 8
- 239000006096 absorbing agent Substances 0.000 claims description 5
- 239000000919 ceramic Substances 0.000 claims description 5
- 239000002360 explosive Substances 0.000 claims description 5
- 230000035939 shock Effects 0.000 claims description 5
- 239000010425 asbestos Substances 0.000 claims description 4
- ISWSIDIOOBJBQZ-UHFFFAOYSA-N phenol group Chemical group C1(=CC=CC=C1)O ISWSIDIOOBJBQZ-UHFFFAOYSA-N 0.000 claims description 4
- 229910052895 riebeckite Inorganic materials 0.000 claims description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 3
- 239000004593 Epoxy Substances 0.000 claims description 3
- 239000006260 foam Substances 0.000 claims description 3
- 239000010439 graphite Substances 0.000 claims description 3
- 229910002804 graphite Inorganic materials 0.000 claims description 3
- 229910010293 ceramic material Inorganic materials 0.000 claims description 2
- 239000004794 expanded polystyrene Substances 0.000 claims description 2
- 239000002245 particle Substances 0.000 description 3
- 235000015842 Hesperis Nutrition 0.000 description 2
- 235000012633 Iberis amara Nutrition 0.000 description 2
- 238000005474 detonation Methods 0.000 description 2
- 239000012634 fragment Substances 0.000 description 2
- 239000011521 glass Substances 0.000 description 2
- 229920003002 synthetic resin Polymers 0.000 description 2
- 239000000057 synthetic resin Substances 0.000 description 2
- 239000004793 Polystyrene Substances 0.000 description 1
- 239000002196 Pyroceram Substances 0.000 description 1
- 229920006328 Styrofoam Polymers 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 230000001413 cellular effect Effects 0.000 description 1
- 239000003479 dental cement Substances 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 239000011152 fibreglass Substances 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 231100001261 hazardous Toxicity 0.000 description 1
- 239000003999 initiator Substances 0.000 description 1
- 239000004922 lacquer Substances 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 229920002223 polystyrene Polymers 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000004449 solid propellant Substances 0.000 description 1
- 239000008261 styrofoam Substances 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 239000011800 void material Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
- 239000002023 wood Substances 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
- F42B15/38—Ring-shaped explosive elements for the separation of rocket parts
-
- 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
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
Definitions
- ABSTRACT A disposable rocket motor nozzle that has a converging diverging throat portion with a shaped charge wound about the throat portion to be ignited by conventional igniter means to cause the throat portion to be broken up into small pieces when it is desired to destroy the nozzle.
- Another object of this invention is to provide a disposable rocket motor nozzle that can be safely handled by personnel.
- a further object of this invention is to completely fragment a nozzle section and contain'the explosive section entirely within a rocket motor case and restrict the hazardous area to a small area immediately behind the rocket.
- Still another object of this invention is to provide a disposable rocket motor nozzle that can be mounted on a rocket such as to enable one to safely handle the rocket without danger of blast in the event of accidental detonation of the explosive around the nozzle.
- a still further object of this invention is to provide means to explosively fragment a nozzle section and decrease the safety hazard to a degree which makes the design practical for use in meteorological systems.
- a disposable rocket motor nozzle that includes a converging diverging nozzle body with a throat insert therein.
- a thermal barrier such as asbestos paper is placed around the outer periphery of the nozzle body portion and a shaped charge is helically wound about the periphery of the nozzle body portion and the thermal barrier.
- a housing is placed around the nozzle body portion to define a void between the nozzle body portion and the housing.
- a cushioning filler material is used to back up the shaped charge and provide shock absorber and thermal barrier protection to the housing.
- a conventional igniter cap is placed at one end of the shaped charge to ignite the charge at the appropriate time.
- FIGURE of the drawing is a perspective view in section of the disposable rocket motor nozzle
- converging diverging nozzle body portion 1 has a throat insert 3 mounted therein in a conventional manner. That is, throat insert 3 is secured in nozzle body portion 1 by conventional securing means.
- Nozzle body portion 1 has a thermal barrier layer 5 about the outer periphery thereof, and over the thermal barrier 5 is helically wound a shaped charge in the form of a flexible linear shaped charge 7.
- Shaped charge 7 is helically wound about the outer periphery by first making one complete turn at one end of the nozzle body portion of the helical shaped charge and thereafter helically winding the shaped charge about the remainder of the nozzle body portion so as to terminate the helical wound charge in one complete turn at the opposite end of the nozzle body portion.
- the shaped charge is bound by adhesives such as dental adhesive to the thermal barrier to initially hold the shaped charge in place.
- the ends of shaped charge 7 are coated with a lacquer to seal the ends.
- the shaped charge at the aft end of the rocket nozzle has a plastic tube 8 placed thereover and a conventional igniter cap 9 is placed in the tube.
- An electrical lead 11 is connected to cap 9 to cause detonation of the cap and shaped charge.
- a rocket motor housing 13 in the form of a fiberglass sheath is placed around the outer periphery of the nozzle body portion and cushioning filler material 15 is placed between the outer housing and the shaped charge to form a backup for the shaped charge and provide shock absorber and thermal barrier protection for the motor housing.
- the nozzle may be connected to the rocket motor structure in any conventional manner.
- Nozzle body portion 1 is perferably made of a material such as asbestos-phenolic, paper-phenolic, glass-phenolic or ceramic such as Pyroceram, and throat insert 3 is made of graphite.
- Shaped charge 7 is preferably a flexible linear shaped charge but may be other explosive cord such as Primacord. The amount of shaped charge to be used to dispose of the nozzle body portion and throat will depend upon the type material used in the nozzle body portion. That is, if an asbestosphenolic is used, more shaped charge will be needed than if a ceramic is used. This is true since it takes a greater force to break up the nozzle body portion if it is made of a material other than the ceramic.
- Thermalv barrier sheath 5 is made of asbestos, and filler material 15 which acts as a shock absorber and thermal barrier may be selected from the materials including expanded, cellular polystyrene (Styrofoam), epoxy foam and phenolic microballoon.
- the phenolic microballoon filler material is composed of a plurality of synthetic resins and glass. This combination of synthetic resins and glass materials make finely divided, whole free, low density particles.
- the disposable rocket motor nozzle acts as an aft motor closure of a solid fuel rocket motor and limits the hot gas motor flow during motor burning.
- the shaped charge is detonated by initiator 9 and nozzle body portion I and throat insert 3 are fragmented intosmall particles of .1 pound or less. These particles will then float back to the ground harmlessly.
- a disposable rocket motor nozzle comprising a converging diverging nozzle body portion, a shaped charge wound about the outer periphery of said nozzle body portion for directing its explosive force toward said nozzle body portion, a thermal barrier of asbestos mounted on the outer periphery of said nozzle body portion to separate said shaped charge from said nozzle body portion, a housing about said nozzle body portion so as to inclose said shaped charge relative to said nozzle body portion, and a filler material between said shaped charge and said housing to act as shock absorber and thermal barrier to protect the housing when the shaped charge is detonated.
- a disposable rocket motor nozzle as set forth in claim 1 wherein, said nozzle body portion outer periphery converges radially inwardly from one end of said nozzle body portion and then diverges radially outwardly to the other end of said nozzle body portion, and said shaped charge is a flexible linear shaped charge with said shaped charge being wound about said nozzle body portion by being wound one complete revolution near each end of said nozzle body portion, the remainder of said shaped charge being wound about said nozzle body portion in the form of a helix.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
A disposable rocket motor nozzle that has a converging diverging throat portion with a shaped charge wound about the throat portion to be ignited by conventional igniter means to cause the throat portion to be broken up into small pieces when it is desired to destroy the nozzle.
Description
United States Patent Howison et al.
DISPOSABLE ROCKET MOTOR NOZZLE Inventors: James F. Howison, Huntsville, Ala.; Chester A. Friend, Jr., Ridgely, W. Va. I
Assignee: The United States of America as represented by the Secretary of the Army.
Filed: Dec. 14, 1970 Appl. No.: 97,643
US. Cl ..239/265.15', 102/495 Int. Cl. ..B64d 33/04 Field of Search ....239/265.15, 265.11; 102/49.5
References Cited UNITED STATES PATENTS 7/1967 Oss et a1. ..102/49.5
[ 1 Sept. 5, 1972 3,427,698 2/1969 Guzewicz ..239/265. 15 X 2,937,595 5/1960 Margulis et a1 ..102/49.5 3,447,465 6/1969 White ..102/49.5 3,351,691 11/1967 Wilford ..239/265.15 X
Primary Examiner-M. Henson Wood, Jr.
Assistant ExaminerJohn J. Love Att0rney1-larry M. Saragovitz, Edward J. Kelly, Herbert Bell and James T. Deaton [5 7] ABSTRACT A disposable rocket motor nozzle that has a converging diverging throat portion with a shaped charge wound about the throat portion to be ignited by conventional igniter means to cause the throat portion to be broken up into small pieces when it is desired to destroy the nozzle.
8 Claims, 1 Drawing Figure PATENTEB SEP 5 I972 3.68 8 98 8 James F. Howison Chester riend,Jr. 2/ IN NTOBS.
DISPOSAIBLE ROCKET MOTOR NOZZLE BACKGROUND OF THE INVENTION Since the advent of high altitude sounding rockets, users have been plagued with prediction of impact points for expended rocket components. The unguided rocket has been known to provide its user with bad moments when an erratic flight made the eventual impact locale somewhat questionable. Because of these falling mass hazards, the use of sounding rockets for obtaining high altitude meteorological data for research, development, tests, and evaluation has been restricted to missile ranges where the air lanes are controlled and large tracts of land or water are available for impact areas. Firings in populated locales of the globe, where such data are most often needed, have not been possible. Therefore there is a need for rocket components that can either be destroyed or burned up so that they can be'used in populated locales without adversely effecting property or personnel of theselocales.
In accordance with the need, it is an object of this invention to provide a rocket motor nozzle that can be disposed of in a safe manner.
Another object of this invention is to provide a disposable rocket motor nozzle that can be safely handled by personnel.
A further object of this invention is to completely fragment a nozzle section and contain'the explosive section entirely within a rocket motor case and restrict the hazardous area to a small area immediately behind the rocket.
Still another object of this invention is to provide a disposable rocket motor nozzle that can be mounted on a rocket such as to enable one to safely handle the rocket without danger of blast in the event of accidental detonation of the explosive around the nozzle.
A still further object of this invention is to provide means to explosively fragment a nozzle section and decrease the safety hazard to a degree which makes the design practical for use in meteorological systems.
SUMMARY OF THE INVENTION In accordance with this invention, a disposable rocket motor nozzle is provided that includes a converging diverging nozzle body with a throat insert therein. A thermal barrier such as asbestos paper is placed around the outer periphery of the nozzle body portion and a shaped charge is helically wound about the periphery of the nozzle body portion and the thermal barrier. With the shaped charge in place, a housing is placed around the nozzle body portion to define a void between the nozzle body portion and the housing. A cushioning filler material is used to back up the shaped charge and provide shock absorber and thermal barrier protection to the housing. A conventional igniter cap is placed at one end of the shaped charge to ignite the charge at the appropriate time.
BRIEF DESCRIPTION OF THE DRAWING The single FIGURE of the drawing is a perspective view in section of the disposable rocket motor nozzle,
DETAILED DESCRIPTION OF THE INVENTION Referring now to the drawing, converging diverging nozzle body portion 1 has a throat insert 3 mounted therein in a conventional manner. That is, throat insert 3 is secured in nozzle body portion 1 by conventional securing means. Nozzle body portion 1 has a thermal barrier layer 5 about the outer periphery thereof, and over the thermal barrier 5 is helically wound a shaped charge in the form of a flexible linear shaped charge 7. Shaped charge 7 is helically wound about the outer periphery by first making one complete turn at one end of the nozzle body portion of the helical shaped charge and thereafter helically winding the shaped charge about the remainder of the nozzle body portion so as to terminate the helical wound charge in one complete turn at the opposite end of the nozzle body portion. The shaped charge is bound by adhesives such as dental adhesive to the thermal barrier to initially hold the shaped charge in place. The ends of shaped charge 7 are coated with a lacquer to seal the ends. The shaped charge at the aft end of the rocket nozzle has a plastic tube 8 placed thereover and a conventional igniter cap 9 is placed in the tube. An electrical lead 11 is connected to cap 9 to cause detonation of the cap and shaped charge. A rocket motor housing 13 in the form of a fiberglass sheath is placed around the outer periphery of the nozzle body portion and cushioning filler material 15 is placed between the outer housing and the shaped charge to form a backup for the shaped charge and provide shock absorber and thermal barrier protection for the motor housing. The nozzle may be connected to the rocket motor structure in any conventional manner.
Nozzle body portion 1 is perferably made of a material such as asbestos-phenolic, paper-phenolic, glass-phenolic or ceramic such as Pyroceram, and throat insert 3 is made of graphite. Shaped charge 7 is preferably a flexible linear shaped charge but may be other explosive cord such as Primacord. The amount of shaped charge to be used to dispose of the nozzle body portion and throat will depend upon the type material used in the nozzle body portion. That is, if an asbestosphenolic is used, more shaped charge will be needed than if a ceramic is used. This is true since it takes a greater force to break up the nozzle body portion if it is made of a material other than the ceramic. Thermalv barrier sheath 5 is made of asbestos, and filler material 15 which acts as a shock absorber and thermal barrier may be selected from the materials including expanded, cellular polystyrene (Styrofoam), epoxy foam and phenolic microballoon. The phenolic microballoon filler material is composed of a plurality of synthetic resins and glass. This combination of synthetic resins and glass materials make finely divided, whole free, low density particles.
In operation, the disposable rocket motor nozzle acts as an aft motor closure of a solid fuel rocket motor and limits the hot gas motor flow during motor burning. At some selected time after motor burn out, either by pyrotechnic delay or electrical time delay, the shaped charge is detonated by initiator 9 and nozzle body portion I and throat insert 3 are fragmented intosmall particles of .1 pound or less. These particles will then float back to the ground harmlessly.
We claim:
1. A disposable rocket motor nozzle comprising a converging diverging nozzle body portion, a shaped charge wound about the outer periphery of said nozzle body portion for directing its explosive force toward said nozzle body portion, a thermal barrier of asbestos mounted on the outer periphery of said nozzle body portion to separate said shaped charge from said nozzle body portion, a housing about said nozzle body portion so as to inclose said shaped charge relative to said nozzle body portion, and a filler material between said shaped charge and said housing to act as shock absorber and thermal barrier to protect the housing when the shaped charge is detonated.
2. A disposable rocket motor nozzle as set forth in claim 1 wherein, said nozzle body portion is made of a material selected from the group consisting of an asbestos-phenolic, a paper-phenolic, a glass-phenolic, and ceramic, and wherein said nozzle body portion has a throat insert secured therein and said throat insert is made of graphite.
3. A disposable rocket motor nozzle as set forth in claim 2 wherein, said shaped charge is a flexible linear shaped charge and said shaped charge is wound about said nozzle body portion by being wound one complete revolution near each end of said nozzle body portion, the remainder of said shaped charge being wound about said nozzle body portion in the form of a helix.
4. A disposable rocket motor nozzle as set forth in claim 3 wherein, said filler material is selected from the group consisting of expanded polystyrene epoxy foam, and phenolic microballoon.
5. A disposable rocket motor nozzle as set forth in claim 3 wherein, said nozzle body portion is made of asbestos-phenolic.
6. A disposable rocket motor nozzle as set forth in claim 3 wherein, said nozzle body portion is made of a glass-phenolic.
7. A disposable rocket motor nozzle as set forth in claim 1 wherein, said nozzle body portion is made of ceramic material.
8. A disposable rocket motor nozzle as set forth in claim 1 wherein, said nozzle body portion outer periphery converges radially inwardly from one end of said nozzle body portion and then diverges radially outwardly to the other end of said nozzle body portion, and said shaped charge is a flexible linear shaped charge with said shaped charge being wound about said nozzle body portion by being wound one complete revolution near each end of said nozzle body portion, the remainder of said shaped charge being wound about said nozzle body portion in the form of a helix.
Claims (8)
1. A disposable rocket motor nozzle comprising a converging diverging nozzle body portion, a shaped charge wound about the outer periphery of said nozzle body portion for directing its explosive force toward said nozzle body portion, a thermal barrier of asbestos mounted on the outer periphery of said nozzle body portion to separate said shaped charge from said nozzle body portion, a housing about said nozzle body portion so as to inclose said shaped charge relative to said nozzle body portion, and a filler material between said shaped charge and said housing to act as shock absorber and thermal barrier to protect the housing when the shaped charge is detonated.
2. A disposable rocket motor nozzle as set forth in claim 1 wherein, said nozzle body portion is made of a material selected from the group consisting of an asbestos-phenolic, a paper-phenolic, a glass-phenolic, and ceramic, and wherein said nozzle body portion has a throat insert secured therein and said throat insert is made of graphite.
3. A disposable rocket motor nozzle as set forth in claim 2 wherein, said shaped charge is a flexible linear shaped charge and said shaped charge is wound about said nozzle body portion by being wound one complete revolution near each end of said nozzle body portion, the remainder of said shaped charge being wound about said nozzle body portion in the form of a helix.
4. A disposable rocket motor nozzle as set forth in claim 3 wherein, said filler material is selected from the group consisting of expanded polystyrene epoxy foam, and phenolic microballoon.
5. A disposable rocket motor nozzle as set forth in claim 3 wherein, said nozzle body portion is made of asbestos-phenolic.
6. A disposable rocket motor nozzle as set forth in claim 3 wherein, said nozzle body portion is made of a glass-phenolic.
7. A disposable rocket motor nozzle as set forth in claim 1 wherein, said nozzle body portion is made of ceramic material.
8. A disposable rocket motor nozzle as set forth in claim 1 wherein, said nozzle body portion outer periphery converges radially inwardly from one end of said nozzle body portion and then diverges radially outwardly to the other end of said nozzle body portion, and said shaped charge is a flexible linear shaped charge with said shaped charge being wound about said nozzle body portion by being wound one complete revolution near each end of said nozzle body portion, the remainder of said shaped charge being wound about said nozzle body portion in the form of a helix.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US9764370A | 1970-12-14 | 1970-12-14 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US3688988A true US3688988A (en) | 1972-09-05 |
Family
ID=22264435
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US97643A Expired - Lifetime US3688988A (en) | 1970-12-14 | 1970-12-14 | Disposable rocket motor nozzle |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US3688988A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3990344A (en) * | 1975-01-13 | 1976-11-09 | The United States Of America As Represented By The Secretary Of The Navy | Underwater expendable explosive link |
| US4022129A (en) * | 1976-01-16 | 1977-05-10 | The United States Of America As Represented By The Secretary Of The Air Force | Nozzle ejection system |
| US4301707A (en) * | 1979-10-29 | 1981-11-24 | Mcdonnell Douglas Corporation | Embedded explosive severance of non-metallic materials |
| US6422148B1 (en) * | 2000-08-04 | 2002-07-23 | Schlumberger Technology Corporation | Impermeable and composite perforating gun assembly components |
| US6711901B1 (en) | 2000-01-21 | 2004-03-30 | Alliant Techsystems Inc. | Rocket motor nozzle assemblies having vacuum plasma-sprayed refractory metal shell throat inserts, methods of making, and rocket motors including same |
| US20060064984A1 (en) * | 2004-09-27 | 2006-03-30 | Gratton Jason A | Throat retention apparatus for hot gas applications |
| US20080011483A1 (en) * | 2006-05-26 | 2008-01-17 | Owen Oil Tools Lp | Perforating methods and devices for high wellbore pressure applications |
| US20160341151A1 (en) * | 2014-05-05 | 2016-11-24 | Aerojet Rocketdyne, Inc. | Fragmenting nozzle system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2937595A (en) * | 1955-05-18 | 1960-05-24 | Alco Products Inc | Rocket boosters |
| US3331324A (en) * | 1965-08-25 | 1967-07-18 | Atlantic Res Corp | Frangible motor |
| US3351691A (en) * | 1963-08-20 | 1967-11-07 | Paul B Wilford | Nozzle assembly and method of molding same |
| US3427698A (en) * | 1965-11-26 | 1969-02-18 | Chandler Evans Inc | Rocket nozzle |
| US3447465A (en) * | 1964-10-06 | 1969-06-03 | Us Army | Missile with variable area nozzle and control means therefor |
-
1970
- 1970-12-14 US US97643A patent/US3688988A/en not_active Expired - Lifetime
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2937595A (en) * | 1955-05-18 | 1960-05-24 | Alco Products Inc | Rocket boosters |
| US3351691A (en) * | 1963-08-20 | 1967-11-07 | Paul B Wilford | Nozzle assembly and method of molding same |
| US3447465A (en) * | 1964-10-06 | 1969-06-03 | Us Army | Missile with variable area nozzle and control means therefor |
| US3331324A (en) * | 1965-08-25 | 1967-07-18 | Atlantic Res Corp | Frangible motor |
| US3427698A (en) * | 1965-11-26 | 1969-02-18 | Chandler Evans Inc | Rocket nozzle |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3990344A (en) * | 1975-01-13 | 1976-11-09 | The United States Of America As Represented By The Secretary Of The Navy | Underwater expendable explosive link |
| US4022129A (en) * | 1976-01-16 | 1977-05-10 | The United States Of America As Represented By The Secretary Of The Air Force | Nozzle ejection system |
| US4301707A (en) * | 1979-10-29 | 1981-11-24 | Mcdonnell Douglas Corporation | Embedded explosive severance of non-metallic materials |
| US6904755B2 (en) | 2000-01-21 | 2005-06-14 | Alliant Techsystems, Inc. | Rocket motor nozzle assemblies having vacuum plasma-sprayed refractory metal shell throat inserts, methods of making, and rocket motors including same |
| US6711901B1 (en) | 2000-01-21 | 2004-03-30 | Alliant Techsystems Inc. | Rocket motor nozzle assemblies having vacuum plasma-sprayed refractory metal shell throat inserts, methods of making, and rocket motors including same |
| US20050000218A1 (en) * | 2000-01-21 | 2005-01-06 | Canfield Alan R. | Rocket motor nozzle assemblies having vacuum plasma-sprayed refractory metal shell throat inserts, methods of making, and rocket motors including same |
| US6422148B1 (en) * | 2000-08-04 | 2002-07-23 | Schlumberger Technology Corporation | Impermeable and composite perforating gun assembly components |
| US20060064984A1 (en) * | 2004-09-27 | 2006-03-30 | Gratton Jason A | Throat retention apparatus for hot gas applications |
| US7269951B2 (en) * | 2004-09-27 | 2007-09-18 | Honeywell International, Inc. | Throat retention apparatus for hot gas applications |
| US20080011483A1 (en) * | 2006-05-26 | 2008-01-17 | Owen Oil Tools Lp | Perforating methods and devices for high wellbore pressure applications |
| US7610969B2 (en) | 2006-05-26 | 2009-11-03 | Owen Oil Tools Lp | Perforating methods and devices for high wellbore pressure applications |
| US20160341151A1 (en) * | 2014-05-05 | 2016-11-24 | Aerojet Rocketdyne, Inc. | Fragmenting nozzle system |
| US10598129B2 (en) * | 2014-05-05 | 2020-03-24 | Aerojet Rocketdyne, Inc. | Fragmenting nozzle system |
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