US3630150A - Actuating mechanism - Google Patents

Actuating mechanism Download PDF

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Publication number
US3630150A
US3630150A US3630150DA US3630150A US 3630150 A US3630150 A US 3630150A US 3630150D A US3630150D A US 3630150DA US 3630150 A US3630150 A US 3630150A
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Prior art keywords
body portion
cavity
rigid body
end
closed end
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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
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Inventor
Edward L Rakowsky
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Singer Co
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Singer Co
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42AMMUNITION; BLASTING
    • F42CAMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/28Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges operated by flow of fluent material, e.g. shot, fluids
    • F42C15/31Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges operated by flow of fluent material, e.g. shot, fluids generated by the combustion of a pyrotechnic or explosive charge within the fuze
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K9/00Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/95Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42AMMUNITION; BLASTING
    • F42CAMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/28Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges operated by flow of fluent material, e.g. shot, fluids
    • F42C15/29Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges operated by flow of fluent material, e.g. shot, fluids operated by fluidic oscillators; operated by dynamic fluid pressure, e.g. ram-air operated
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00Function
    • F05D2260/99Ignition, e.g. ignition by warming up of fuel or oxidizer in a resonant acoustic cavity

Abstract

An actuating mechanism in which a source of fluid is directed against an end wall of a rigid body portion having an open cavity formed therein to create pressure waves of fluid which pass through the length of the cavity to the closed end thereof to cause a temperature rise at the closed end. This temperature rise is utilized to ignite an explosive device which, in turn, is utilized to accomplish work.

Description

United States Patent [72] Inventor Edward L. Rakowsky Kinnelon, NJ.

21 1 Appl. No. 869,487

[22] Filed Oct. 27, 1969 [45] Patented Dec. 28, 1971 73] Assignee The Singer Company New York, N.Y.

[54] AC TUATING MECHANISM 2 Claims, 2 Drawing Figs.

52 us. Cl 102 70, 60/26.1, 89/1 B, 89/7, 102/81 [51] Int. Cl F42c 5/00 [50] Field of Search 102/70, 81, 49.7, 27; 89/7; 124/1 1, 13; 60/26.1

[56] References Cited UNITED STATES PATENTS 2,725,048 11/1955 Koogle 124/11 3,064,381 11/1962 Vilbajo.. 89/7 X 3,238,876 3/1966 Al1en..... 102/70 3,277,825 l0/l966 Maillard l02/49.7

3,302,319 2/1967 Rosselet 89/7 3,302,523 2/1967 Van Langenhoven et 89/7 Primary Examiner-Samuel W. Engle AtrorneysS. A. Giarratana and S. Michael Bender ABSTRACT: An actuating mechanism in which a source of fluid is directed against an end wall of a rigid body portion having an open cavity formed therein to create pressure waves of fluid which pass through the length of the cavity to the closed end thereof to cause a temperature rise at the closed end. This temperature rise is utilized to ignite an explosive device which, in turn, is utilized to accomplish work.

ACTUATING MECHANISM BACKGROUND OF THE INVENTION The invention herein described was made in the course of or under a contract or subcontract thereunder, with the Department of the Army.

This invention relates to an actuating mechanism and, more particularly, to such a mechanism utilizing a fluidic device to produce thermal energy.

Many existing actuating mechanisms employ electrical devices, such as spark gaps or resistance wires, which require electrical inputs. For example, the igniter for an oil burner in a home heating system uses a high-voltage spark gap. Also, on many aerospace and ordinance systems it is desirable to initiate operations from a remote location, in which case pyrotechnic devices are used and the igniter thereof is energized by a hot resistance wire. Further, explosive-actuated valves, as well as solid grain hot gas generators, normally utilize an electrical initiated squib or exploding bridge to trigger the explosive charge. However, due to the low-power consumption of the electrical igniter in these devices, false triggering can be induced by lightning, static electricity, radiofrequency interference, nuclear radiation, etc.

SUMMARY OF THE INVENTION It is therefore an object of the present invention to provide an actuating mechanism which is free from electrical com ponents and connections, and which therefore eliminates the above disadvantages associated with an electrical actuating mechanism.

Toward the fulfillment of this object, the actuating mechanism of the present invention comprises a rigid body portion having a cavity formed therein, said cavity having an open end and a closed end, means to direct a source of fluid against an end wall of said body portion and toward said open end to create pressure waves of fluid which pass through the length of said cavity to said closed end to cause a temperature rise at said closed end, and means responsive to said temperature rise for accomplishing work.

BRIEF DESCRIPTION OF THE DRAWINGS Reference is now made to the accompanying drawings for a better understanding of the nature and objects of the present invention. The drawings illustrate the best mode presently contemplated for carrying out the objects of the invention and are not to be construed as restrictions or limitations on its scope. In the drawings:

FIG. I is a cross-sectional view depicting the actuating mechanism of the present invention used in conjunction with a valve; and

FIG. 2 is a view similar to FIG. 1 but showing the actuating mechanism of the present invention used in conjunction with a hot gas generator.

DESCRIPTION OF THE PREFERRED EMBODIMENTS Referring specifically to the embodiment of FIG. 1, the reference numeral refers to a housing in which a nozzle 12 is formed having an internally threaded entrance 14 adapted to accommodate a corresponding externally threaded tube or the like (not shown) for the introduction of pressurized fluid, such as gas, into the nozzle in the direction indicated by. the arrow. The exit end of the nozzle 12 converges as shown, and communicates with an opening 16 formed in the housing 10.

A tubular resonance cavity 18 is formed in a rigid body portion 19 of the housing 10, and the entrance to the cavity 18 communicates with the opening 16. The other end of the cavity I8 is closed by a pyrotechnic explosive 20, in the form of a lead azide, or other similar material, which is adapted to ignite upon the latter end portion of the cavity 18 reaching a certain temperature, as will be explained in detail later.

An additional housing 21 is provided which has one end threadably engaging end of the housing 10, and two chambers 22 and 24 formed therein. A piston 26 is reciprocally mounted in the chamber 22 with the stern of the piston slideably extending through a partition 28 formed through the housing 21 and into the chamber 24. A guillotine 30 is formed on the other end of the stem in the chamber 24 and is disposed in proximity' from the system in a direction at right angles to the direction of flow into the cavity 18. After a very short time the cavity fills up and the entire flow impinges off of the wall and exits from the housing. In this manner an unstable wave will be formed at the entrance to the cavity 18, which wave oscillates back and forth and causes small pressure waves to travel the length of the cavity 18 and compress the gas trapped at the closed end thereof, thus adding energy to the gas at every cycle of oscillation. Accumulation of this energy input per cycle causes the temperature at the closed end of the cavity 18 to rise appreciably to a point whereby it ignites the explosive The thermal energy thus created drives the piston 26 in a direction from left to right as viewed in FIG. I, and causes the guillotine 30 to sever the diaphragm 32'and thus permit flow of the additional fluid from the inlet port 34 through the chamber 24 and out the outlet port 36.

It is thus seen that an effective valve is formed in the chamber 24 which is actuated by gas flow into the nozzle 12, while all electrical components and connections are eliminated.

In the embodiment of FIG. 2, a housing is provided which is identical to the housing 10 of the embodiment of FIG. I and therefore will not be described in detail. As in the previous embodiment, a pyrotechnic explosive 20 closes the exit end of the cavity 18 formed in the housing 10.

According to this embodiment, an additional housing 40 is threadably engaged to an end of the housing l0, and houses a solid grain propellant 42 which may be in the form of an ammonium perchlorate. The propellant 42 is cast in the form of a I tube having a hollow portion 44 and is adapted to be ignited by the thermal energy created by the explosive charge 20, to produce a hot gas. In this manner, upon the temperature at the closed end of the cavity 18 reaching a temperature sufficient to ignite the explosive charge 20, the thermal energy created ignites the solid grain propellant 42, and generates the hot gas which passes from the housing 40 through an outlet port 46. The presence of the hollow portion 44 in the propellant 42 aids in the distribution of the thermal energy to the propellant 42 and in the flowing of the hot gas to the outlet port 46. The hot gas thus created may be used for many applications, such as to ignite a rocket engine, etc.

It is noted that, in each embodiment, the flow from the nozzle 12 can be supersonic, in which case the wave created at the entrance to the cavity 18 will be a shock wave.

It is thus seen that, by use of the actuating mechanism of the present invention, electrical inductions and other crosscoupling inputs from an adverse environment are eliminated, as well as the cost and vulnerability of spark gaps to outside weather environments. Also, since high-pressured air is normally readily available, the mechanism is relatively inexpensive in operation.

It can be appreciated that several variations in the above embodiments are possible without departing from the scope of the invention. For example, although the cavity 18 has been shown with a cylindrical cross section, it is understood that it can take other configurations such as rectangular, conical, etc. Also, various alternate configurations of the nozzle 12 may be employed such as a convergent-divergent type, and various stagings of the flow of the gas can be utilized.

Of course, other variations of the specific construction and arrangement of the mechanism disclosed above can be made by those skilled in the art without departing from the invention as defined in the appended claims.

lclaim:

1. An actuating mechanism comprising a first rigid body portion having a longitudinal axis having a cavity formed therein coaxially therewith, said cavity having an open end and a closed end, means to direct a source of fluid against a wall of said first body portion and towards said open end to create pressure waves of fluid which pass through the length of said cavity to said closed end to cause a temperature rise at said closed end, and means responsive to said temperature rise for accomplishing work, wherein said means to direct a source of fluid against the wall of said first rigid body portion includes a second rigid body portion fixedly connected to said first rigid body portion. said second rigid body portion having a longitudinal passage connected to said cavity coaxially therewith. said second rigid body portion having a transverse passage connected to said longitudinal passage and to said cavity and extending transverse to said longitudinal passage, said second rigid body portion having a radially outer surface, said longitudinal passage having a converging end portion having an outlet opening, said outlet opening facing said cavity open end coaxially therewith, said transverse passage having a radially inner inlet end disposed adjacent said cavity open end and having a radially outer outlet end having a vent opening extending through said exterior surface.

2. The mechanism of claim 1 wherein said means for accomplishing work comprising an explosive charge in heat exchange relation with said closed end, said temperature rise causing said explosive charge to ignite, and wherein said actuating mechanism is a one-piece rigid housing arranged so that said first rigid body portion and said second rigid body portion are axially spaced portions thereof, and wherein said transverse passage is disposed substantially at right angles to said longitudinal passage. and wherein said first body portion has an axially outer end face having a recess receiving said explosive charge forming said cavity closed end.

Claims (2)

1. An actuating mechanism comprising a first rigid body portion having a longitudinal axis having a cavity formed therein coaxially therewith, said cavity having an open end and a closed end, means to direct a source of fluid against a wall of said first body portion and towards said open end to create pressure waves of fluid which pass through the length of said cavity to said closed end to cause a temperature rise at said closed end, and means responsive to said temperature rise for accomplishing work, wherein said means to direct a source of fluid against the wall of said first rigid body portion includes a second rigid body portion fixedly connected to said first rigid body portion, said second rigid body portion having a longitudinal passage connected to said cavity coaxially therewith, said second rigid body portion having a transverse passage connected to said longitudinal passage and to said cavity and extending transverse to said longitudinal passage, said second rigid body portion having a radially outer surface, said longitudinal passage having a converging end portion having an outlet opening, said outlet opening facing said cavity open end coaxially therewith, said transverse passage having a radially inner inlet end disposed adjacent said cavity open end and having a radially outer outlet end having a vent opening extending through said exterior surface.
2. The mechanism of claim 1 wherein said means for accomplishing work comprising an explosive charge in heat exchange relation with said closed end, said temperature rise causing said explosive charge to ignite, and wherein said actuating mechanism is a one-piece rigid housing arranged so that said first rigid body portion and said second rigid body portion are axially spaced portions thereof, and wherein said transverse passage is disposed substantially at right angles to said longitudinal passage, and wherein said first body portion has an axially outer end face having a recess receiving said explosive charge forming said cavity closed end.
US3630150A 1969-10-27 1969-10-27 Actuating mechanism Expired - Lifetime US3630150A (en)

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US86948769 true 1969-10-27 1969-10-27

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FR (1) FR2073315A1 (en)
GB (1) GB1272719A (en)

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3811359A (en) * 1972-12-18 1974-05-21 Singer Co Apparatus for remote ignition of explosives
US3839094A (en) * 1972-06-30 1974-10-01 Us Army Fluidic thermoelectric generator
US3921945A (en) * 1974-07-25 1975-11-25 Us Navy Train resonant car-body rocking detector system
US3982488A (en) * 1975-02-19 1976-09-28 The United States Of America As Represented By The Secretary Of The Army Flueric through bulkhead rocket motor ignitor
US3985058A (en) * 1975-08-08 1976-10-12 The United States Of America As Represented By The Secretary Of The Army Self-sealing fluidic explosive initiator
US3994232A (en) * 1975-08-22 1976-11-30 The United States Of America As Represented By The Secretary Of The Army Pneumatic match through use of a conical nozzle flare
US3994226A (en) * 1975-12-18 1976-11-30 The United States Of America As Represented By The Secretary Of The Army Flueric explosive initiation device for a fuel-air explosive bomb
US4033267A (en) * 1976-10-01 1977-07-05 The United States Of America As Represented By The Secretary Of The Navy Flueric cartridge initiator
US4334478A (en) * 1980-03-03 1982-06-15 The United States Of America As Represented By The Secretary Of The Army Fluidic range-safe device
US4393783A (en) * 1980-03-03 1983-07-19 The United States Of America As Represented By The Secretary Of The Army Fluidic range-safe explosive device
US4843965A (en) * 1988-02-23 1989-07-04 The United States Of America As Represented By The Secretary Of The Navy Thermally activated triggering device
US5109669A (en) * 1989-09-28 1992-05-05 Rockwell International Corporation Passive self-contained auto ignition system
US5753849A (en) * 1996-09-19 1998-05-19 Propellex Corporation Gas-operated timing demolition delay
US20060174794A1 (en) * 2005-02-10 2006-08-10 Trw Vehicle Safety Systems Inc. Inflator having an ignition nozzle
US20080299504A1 (en) * 2007-06-01 2008-12-04 Mark David Horn Resonance driven glow plug torch igniter and ignition method
US20090173321A1 (en) * 2006-01-17 2009-07-09 United Technologies Corporation Piezo-resonance igniter and ignition method for propellant liquid rocket engine
US20090297999A1 (en) * 2008-06-02 2009-12-03 Jensen Jeff Igniter/thruster with catalytic decomposition chamber
US20100071343A1 (en) * 2008-09-22 2010-03-25 Tai Yu Compact cyclone combustion torch igniter
US20100314562A1 (en) * 2009-06-10 2010-12-16 Baker Hughes Incorporated Delay activated valve and method
US9470498B1 (en) * 2014-09-05 2016-10-18 The United States Of America As Represented By The Secretary Of The Army High pressure isolated latching safety switch device

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3621186A1 (en) * 1986-06-25 1988-01-07 Bbc Brown Boveri & Cie Method and device for driving a linearly movable component, in particular of the movable switch contact of an electrical high-voltage circuit breaker

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2725048A (en) * 1953-06-03 1955-11-29 John D Koogle Underwater gun
US3064381A (en) * 1959-10-28 1962-11-20 A V R Achat Ventes Representat Combination firearm and grenade
US3238876A (en) * 1963-10-08 1966-03-08 Mccormick Selph Associates Inc Method for through-bulkhead shock initiation
US3277825A (en) * 1963-11-07 1966-10-11 Brevets Aero Mecaniques Self-propelled armor-piercing shells
US3302523A (en) * 1961-05-03 1967-02-07 Daisy Mfg Co Air operated projectile firing apparatus
US3302319A (en) * 1964-04-22 1967-02-07 Corat S A Cie De Rech S Et D A Devices for firing objects of the class of projectiles, plugs, pins and nails

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2725048A (en) * 1953-06-03 1955-11-29 John D Koogle Underwater gun
US3064381A (en) * 1959-10-28 1962-11-20 A V R Achat Ventes Representat Combination firearm and grenade
US3302523A (en) * 1961-05-03 1967-02-07 Daisy Mfg Co Air operated projectile firing apparatus
US3238876A (en) * 1963-10-08 1966-03-08 Mccormick Selph Associates Inc Method for through-bulkhead shock initiation
US3277825A (en) * 1963-11-07 1966-10-11 Brevets Aero Mecaniques Self-propelled armor-piercing shells
US3302319A (en) * 1964-04-22 1967-02-07 Corat S A Cie De Rech S Et D A Devices for firing objects of the class of projectiles, plugs, pins and nails

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3839094A (en) * 1972-06-30 1974-10-01 Us Army Fluidic thermoelectric generator
US3811359A (en) * 1972-12-18 1974-05-21 Singer Co Apparatus for remote ignition of explosives
US3921945A (en) * 1974-07-25 1975-11-25 Us Navy Train resonant car-body rocking detector system
US3982488A (en) * 1975-02-19 1976-09-28 The United States Of America As Represented By The Secretary Of The Army Flueric through bulkhead rocket motor ignitor
US3985058A (en) * 1975-08-08 1976-10-12 The United States Of America As Represented By The Secretary Of The Army Self-sealing fluidic explosive initiator
US3994232A (en) * 1975-08-22 1976-11-30 The United States Of America As Represented By The Secretary Of The Army Pneumatic match through use of a conical nozzle flare
US3994226A (en) * 1975-12-18 1976-11-30 The United States Of America As Represented By The Secretary Of The Army Flueric explosive initiation device for a fuel-air explosive bomb
US4033267A (en) * 1976-10-01 1977-07-05 The United States Of America As Represented By The Secretary Of The Navy Flueric cartridge initiator
US4334478A (en) * 1980-03-03 1982-06-15 The United States Of America As Represented By The Secretary Of The Army Fluidic range-safe device
US4393783A (en) * 1980-03-03 1983-07-19 The United States Of America As Represented By The Secretary Of The Army Fluidic range-safe explosive device
US4843965A (en) * 1988-02-23 1989-07-04 The United States Of America As Represented By The Secretary Of The Navy Thermally activated triggering device
US5109669A (en) * 1989-09-28 1992-05-05 Rockwell International Corporation Passive self-contained auto ignition system
US5753849A (en) * 1996-09-19 1998-05-19 Propellex Corporation Gas-operated timing demolition delay
US7703395B2 (en) * 2005-02-10 2010-04-27 Trw Vehicle Safety Systems Inc. Inflator having an ignition nozzle
US20060174794A1 (en) * 2005-02-10 2006-08-10 Trw Vehicle Safety Systems Inc. Inflator having an ignition nozzle
US20090173321A1 (en) * 2006-01-17 2009-07-09 United Technologies Corporation Piezo-resonance igniter and ignition method for propellant liquid rocket engine
US7565795B1 (en) 2006-01-17 2009-07-28 Pratt & Whitney Rocketdyne, Inc. Piezo-resonance igniter and ignition method for propellant liquid rocket engine
US8438831B2 (en) 2006-01-17 2013-05-14 Pratt & Whitney Rocketdyne, Inc. Piezo-resonance igniter and ignition method for propellant liquid rocket engine
US20080299504A1 (en) * 2007-06-01 2008-12-04 Mark David Horn Resonance driven glow plug torch igniter and ignition method
US8814562B2 (en) 2008-06-02 2014-08-26 Aerojet Rocketdyne Of De, Inc. Igniter/thruster with catalytic decomposition chamber
US20090297999A1 (en) * 2008-06-02 2009-12-03 Jensen Jeff Igniter/thruster with catalytic decomposition chamber
US8161725B2 (en) 2008-09-22 2012-04-24 Pratt & Whitney Rocketdyne, Inc. Compact cyclone combustion torch igniter
US20100071343A1 (en) * 2008-09-22 2010-03-25 Tai Yu Compact cyclone combustion torch igniter
US20100314562A1 (en) * 2009-06-10 2010-12-16 Baker Hughes Incorporated Delay activated valve and method
US8397741B2 (en) * 2009-06-10 2013-03-19 Baker Hughes Incorporated Delay activated valve and method
US9470498B1 (en) * 2014-09-05 2016-10-18 The United States Of America As Represented By The Secretary Of The Army High pressure isolated latching safety switch device

Also Published As

Publication number Publication date Type
DE2050058A1 (en) 1971-05-06 application
DE2050058C3 (en) 1980-04-10 grant
FR2073315A1 (en) 1971-10-01 application
GB1272719A (en) 1972-05-03 application
DE2050058B2 (en) 1979-08-02 application

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