USH1144H - Solid propellant rocket motor with fusible end closure holder - Google Patents

Solid propellant rocket motor with fusible end closure holder Download PDF

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Publication number
USH1144H
USH1144H US07/593,725 US59372590A USH1144H US H1144 H USH1144 H US H1144H US 59372590 A US59372590 A US 59372590A US H1144 H USH1144 H US H1144H
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US
United States
Prior art keywords
solid propellant
motor
rocket motor
propellant rocket
fusible
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
Application number
US07/593,725
Inventor
Charles C. Cherry
Raymond E. Wiechering
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hercules LLC
Original Assignee
Hercules LLC
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Hercules LLC filed Critical Hercules LLC
Priority to US07/593,725 priority Critical patent/USH1144H/en
Assigned to HERCULES INCORPORATED, A CORP. OF DE reassignment HERCULES INCORPORATED, A CORP. OF DE ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: CHERRY, CHARLES C., WIECHERING, RAYMOND E.
Priority to GB9122949A priority patent/GB2263962A/en
Priority to FR9115525A priority patent/FR2690205A1/en
Application granted granted Critical
Publication of USH1144H publication Critical patent/USH1144H/en
Assigned to CHASE MANHATTAN BANK, THE reassignment CHASE MANHATTAN BANK, THE PATENT SECURITY AGREEMENT Assignors: ALLIANT TECHSYSTEMS INC.
Assigned to FEDERAL CARTRIDGE CO., COMPOSITE OPTICS, INC., ALLIANT TECHSYSTEMS INC., ORBITAL ATK, INC. (F/K/A ALLIANT TECHSYSTEMS INC.) reassignment FEDERAL CARTRIDGE CO. RELEASE BY SECURED PARTY (SEE DOCUMENT FOR DETAILS). Assignors: BANK OF AMERICA, N.A.
Abandoned legal-status Critical Current

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Classifications

    • 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
    • F02K9/38—Safety devices, e.g. to prevent accidental ignition
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B39/00—Packaging or storage of ammunition or explosive charges; Safety features thereof; Cartridge belts or bags
    • F42B39/20—Packages or ammunition having valves for pressure-equalising; Packages or ammunition having plugs for pressure release, e.g. meltable ; Blow-out panels; Venting arrangements

Definitions

  • the invention is a solid propellant rocket motor capable of withstanding the insensitive munitions cook-off test.
  • I.M. testing Insensitive munitions cook-off test
  • the test consists of heating the motor until autoignition occurs. To pass the test the ignited motor must remain passive while the propellant burns off, with no explosion, shrapnel or propulsion. This test ensures the safety of motors in case of fire or heat.
  • the invention is a solid propellant rocket motor comprising a motor case, solid propellant and at least one end closure, wherein at least one end closure is connected to the casing by at least one fusible connector which melts at temperatures below those that will cause autoignition of the motor but does not melt during normal propulsion of the motor, so that the end closure releases before the autoignition and is retained in place during normal propulsion.
  • FIG. 1 shows a motor having two end closures, one retained by a threaded fusible ring and the second retained by an unthreaded fusible ring.
  • end closure refers to devices used to close the opening or openings of a rocket motor case.
  • a nozzle assembly typically comprising a nozzle, blast tube and exit cone, is used on the aft end.
  • the nozzle assembly may be sealed, for instance, by a metal plate or foam igniter, or may be open. If the case has an opening at the forward end, a plate-like fixture is usually used to close it.
  • fusible it is meant that the material is capable of being melted by heat. Any fusible material capable of meeting the structural and melting requirements for the connector may be used. Preferred are fusible metals alloys.
  • connection By “connector”, reference is made to rings forming one or more interface of the case and end closure (which may be threaded (e.g., buttressed or so as to screw in) or unthreaded); receptacles with recesses provided for such retaining rings; pins or screws for securing the case to the end closure; and the like.
  • the connector may be in contact with both the case and end closure, but does not have to be. For instance, it may be connected to a support member.
  • fusible connector(s) be in position and of a material such that during normal operation the end closure is retained on the rocket motor and when the fusible material melts before autoignition, pressure is released due to release of the end closure. Release of the end closure results in the end closure falling off or being pushed off the motor during autoignition.
  • the specific melting temperature(s) suitable for materials useful in this invention depends on the autoignition temperature of the motor and the temperatures which the fusible connector will experience during propulsion and storage.
  • the motor configuration, insulation, propellant, load(s) and other well known design features will dictate the preferred melting temperature and material.
  • the autoignition temperature of the motor will be the autoignition temperature of the solid propellant. That is, if (a) the motor is stored without an igniter, (b) the igniter does not contain pyrotechnic material or (c) the igniter contains a pyrotechnic material having a higher autoignition temperature than the propellant, the fusible connector material may be selected based on the propellant autoignition temperature. However, if the igniter has a lower autoignition temperature than the propellant and either (a) the motor is stored with the igniter in place or (b) the motor may experience high temperatures after installation of the motor, the fusible connector material should be selected so that it has a lower melting temperature than the autoignition temperature of the igniter.
  • Suitable fusible materials will have a melting temperature of from 200° F. to 1000° F. For most applications, the melting temperature of the fusible material will be in the range of 250° F. to 550° F. Most conventional tactical motors will require fusible materials which melt at a temperature in the range of 270° F. to 320° F.
  • the motors of this invention are made with conventional rocket motor materials.
  • the case may be made of composites, metals or both, and may be insulated using conventional materials.
  • the nozzle and forward end closures are also made with conventional materials, such as composites and metals.
  • the propellant can be any conventional propellant, such as composite propellants.
  • Autoignition temperature is specific to the propellant used and may be in the range of 375° F. to 575° F. Generally, solid propellant autoignition occurs at temperatures of 450° F. to 500° F.
  • FIG. 1 is an illustration of a motor having two end closures, one retained by a threaded fusible ring and the second retained by an unthreaded fusible ring.
  • the motor is similar to that used by tactical applications, but has a reduced configuration for testing.
  • Case (1) is a metal case 15 inches long and 5 inches in diameter. The walls of the case are insulated with approximately 90 mil thick paper phenolic. (The insulation is now shown).
  • the forward end-closure (2) is plastic and is retained by unthreaded, fusible metal alloy retaining ring (3) (split ring).
  • the retaining ring is made of a eutectic metal alloy of bismuth and tin with a melting point of 281° F.
  • Rubber O-ring (4) is a pressure seal.
  • Thermoplastic insulation (5) protects the forward end closure from heat of propulsion. The insulation will be pushed from the case upon autoignition of the motor if the forward end-closure is released by melting of the retaining ring.
  • the propellant (6) is composite having an autoignition of 450° F.+.
  • the aft-end closure is nozzle assembly (7). It has a foam weatherseal and burst disc (this may be part of an assembly, including an igniter), which is not shown.
  • the nozzle assembly is composite and is retained by threaded, fusible metal alloy retaining ring (8).
  • the retaining ring is made of a eutectic metal alloy of bismuth and tin with a melting point of 281° F.
  • Nozzle support member (9) is made of plastic which is retained by the nozzle and fusible retaining ring.
  • Rubber O-ring (10) is a pressure seal.
  • An igniter is not shown, but normally would be located in the forward or aft end of the motor.

Abstract

A solid propellant rocket motor comprising a motor case, solid propellant and at least one end closure, wherein at least one end closure is connected to the casing by at least one fusible connector which melts at temperatures below those that will cause autoignition of the motor but does not melt during normal propulsion, so that the end closure releases before the antoignition and is retained in place during normal propulsion.

Description

The invention is a solid propellant rocket motor capable of withstanding the insensitive munitions cook-off test.
BACKGROUND OF THE INVENTION
Heat can cause solid propellant to autoignite, causing the motor to explode, burst or move. In order to improve safety of solid propellant motors a relatively new requirement, referred to as "insensitive munitions cook-off test" (hereinafter "I.M. testing"), will soon be standard for all rocket motors. The test consists of heating the motor until autoignition occurs. To pass the test the ignited motor must remain passive while the propellant burns off, with no explosion, shrapnel or propulsion. This test ensures the safety of motors in case of fire or heat.
Current solid propellant rocket motors are not designed to withstand I.M. testing. Consequently, if a motor is subjected to cook-off temperatures, autoignition occurs, and the motor either explodes, bursts or becomes propulsive. This results because the motor is unable to relieve pressure build-up from the ignited propellant.
SUMMARY OF THE INVENTION
The invention is a solid propellant rocket motor comprising a motor case, solid propellant and at least one end closure, wherein at least one end closure is connected to the casing by at least one fusible connector which melts at temperatures below those that will cause autoignition of the motor but does not melt during normal propulsion of the motor, so that the end closure releases before the autoignition and is retained in place during normal propulsion.
SUMMARY OF THE DRAWING
FIG. 1 shows a motor having two end closures, one retained by a threaded fusible ring and the second retained by an unthreaded fusible ring.
DETAILED DESCRIPTION OF THE INVENTION
The term "end closure" refers to devices used to close the opening or openings of a rocket motor case. A nozzle assembly, typically comprising a nozzle, blast tube and exit cone, is used on the aft end. The nozzle assembly may be sealed, for instance, by a metal plate or foam igniter, or may be open. If the case has an opening at the forward end, a plate-like fixture is usually used to close it.
By "fusible" it is meant that the material is capable of being melted by heat. Any fusible material capable of meeting the structural and melting requirements for the connector may be used. Preferred are fusible metals alloys.
By "connector", reference is made to rings forming one or more interface of the case and end closure (which may be threaded (e.g., buttressed or so as to screw in) or unthreaded); receptacles with recesses provided for such retaining rings; pins or screws for securing the case to the end closure; and the like. The connector may be in contact with both the case and end closure, but does not have to be. For instance, it may be connected to a support member. The key is that fusible connector(s) be in position and of a material such that during normal operation the end closure is retained on the rocket motor and when the fusible material melts before autoignition, pressure is released due to release of the end closure. Release of the end closure results in the end closure falling off or being pushed off the motor during autoignition.
The specific melting temperature(s) suitable for materials useful in this invention depends on the autoignition temperature of the motor and the temperatures which the fusible connector will experience during propulsion and storage. The motor configuration, insulation, propellant, load(s) and other well known design features will dictate the preferred melting temperature and material.
Generally, the autoignition temperature of the motor will be the autoignition temperature of the solid propellant. That is, if (a) the motor is stored without an igniter, (b) the igniter does not contain pyrotechnic material or (c) the igniter contains a pyrotechnic material having a higher autoignition temperature than the propellant, the fusible connector material may be selected based on the propellant autoignition temperature. However, if the igniter has a lower autoignition temperature than the propellant and either (a) the motor is stored with the igniter in place or (b) the motor may experience high temperatures after installation of the motor, the fusible connector material should be selected so that it has a lower melting temperature than the autoignition temperature of the igniter.
Suitable fusible materials will have a melting temperature of from 200° F. to 1000° F. For most applications, the melting temperature of the fusible material will be in the range of 250° F. to 550° F. Most conventional tactical motors will require fusible materials which melt at a temperature in the range of 270° F. to 320° F.
The motors of this invention are made with conventional rocket motor materials. The case may be made of composites, metals or both, and may be insulated using conventional materials. The nozzle and forward end closures are also made with conventional materials, such as composites and metals. The propellant can be any conventional propellant, such as composite propellants. Autoignition temperature is specific to the propellant used and may be in the range of 375° F. to 575° F. Generally, solid propellant autoignition occurs at temperatures of 450° F. to 500° F.
FIG. 1 is an illustration of a motor having two end closures, one retained by a threaded fusible ring and the second retained by an unthreaded fusible ring. The motor is similar to that used by tactical applications, but has a reduced configuration for testing.
Case (1) is a metal case 15 inches long and 5 inches in diameter. The walls of the case are insulated with approximately 90 mil thick paper phenolic. (The insulation is now shown).
The forward end-closure (2) is plastic and is retained by unthreaded, fusible metal alloy retaining ring (3) (split ring). The retaining ring is made of a eutectic metal alloy of bismuth and tin with a melting point of 281° F. Rubber O-ring (4) is a pressure seal. Thermoplastic insulation (5) protects the forward end closure from heat of propulsion. The insulation will be pushed from the case upon autoignition of the motor if the forward end-closure is released by melting of the retaining ring. The propellant (6) is composite having an autoignition of 450° F.+.
The aft-end closure is nozzle assembly (7). It has a foam weatherseal and burst disc (this may be part of an assembly, including an igniter), which is not shown.
The nozzle assembly is composite and is retained by threaded, fusible metal alloy retaining ring (8). The retaining ring is made of a eutectic metal alloy of bismuth and tin with a melting point of 281° F. Nozzle support member (9) is made of plastic which is retained by the nozzle and fusible retaining ring. Rubber O-ring (10) is a pressure seal.
An igniter is not shown, but normally would be located in the forward or aft end of the motor.
While the invention has been described with respect to specific embodiments, it should be understood that they are not intended to be limiting and that many variations and modifications are possible without departing from the scope and spirit of this invention.

Claims (25)

We claim:
1. A solid propellant rocket motor comprising a motor case, a propellant and at least one end closure, wherein at least one end closure is connected to the casing by at least one fusible connector which melts at temperatures below those that will cause autoignition of the motor but does not melt during normal propulsion of the motor, so that the end closure releases before the autoignition and is retained in place during the normal propulsion, wherein the fusible connector melts at a temperature in the range of 270° F. to 320° F.
2. A solid propellant rocket motor as claimed in claim 1 wherein the end-closure connected to the casing by a fusible connector is a nozzle assembly.
3. A solid propellant rocket motor as claimed in claim 1 wherein the end-closure connected to the casing by a fusible connector is a plate-like fixture in the forward end of the motor.
4. A solid propellant rocket motor as claimed in claim 1 wherein the fusible connector is selected from the group consisting of rings, recesses for retaining rings, pins and screws.
5. A solid propellant rocket motor as claimed in claim 4 wherein the fusible connector is made of a fusible metal alloy.
6. A solid propellant rocket motor as claimed in claim 1 wherein the fusible connector is selected from the group consisting of threaded or unthreaded rings.
7. A solid propellant rocket motor as claimed in claim 1 wherein the fusible connector is selected from the group consisting of pins and screws.
8. A solid propellant rocket motor as claimed in claim 1 wherein the fusible connector is a pin.
9. A solid propellant rocket motor as claimed in claim 1 wherein the fusible connector is made of a fusible metal alloy.
10. A solid propellant rocket motor as claimed in claim 9 wherein the metals alloy is a eutectic mixture of bismuth and tin.
11. A solid propellant rocket motor as claimed in claim 1 wherein the fusible metal melts at a temperature lower than the autoignition temperature of the solid propellant.
12. A solid propellant rocket motor as claimed in claim 1 wherein the motor contains an igniter comprising a pyrotechnic material that has an autoignition temperature lower than that of the propellant and the fusible connector melts at a temperature lower than the autoignition temperature of the pyrotechnic material.
13. A solid propellant rocket motor as claimed in claim 1 wherein the fusible connector is selected from the group consisting of recesses for retaining rings.
14. A solid propellant rocket motor as claimed in claim 1 wherein the fusible connector is selected from the group consisting of screws.
15. A solid propellant rocket motor comprising a motor case, a propellant and at least one end closure, wherein at least one end closure is connected to the casing by at least one fusible connector which melts at temperatures below those that will cause autoignition of the motor but does not melt during normal propulsion of the motor selected from the group consisting of threaded or unthreaded rings, so that the end closure releases before the autoignition and is retained in place during the normal propulsion.
16. A solid propellant rocket motor as claimed in claim 15 wherein the end-closure connected to the casing by a fusible connector is a nozzle assembly.
17. A solid propellant rocket motor as claimed in claim 15 wherein the end-closure connected to the casing by a fusible connector is as plate-like fixture in the forward end of the motor.
18. A solid propellant rocket motor as claimed in claim 15 wherein the fusible connector is made of a fusible metal alloy.
19. A solid propellant rocket motor as claimed in claim 18 wherein the metals alloy is a eutectic mixture of bismuth and tin.
20. A solid propellant rocket motor as claimed in claim 18 wherein the metal alloy melts at a temperature in the range of 250° F. to 550° F.
21. A solid propellant rocket motor as claimed in claim 15 wherein the fusible connector melts at a temperature in the range of 200° F. to 1000° F.
22. A solid propellant rocket motor as claimed in claim 15 wherein the fusible connector melts at a temperature in the range of 250° F. to 550° F.
23. A solid propellant rocket motor as claimed in claim 18 wherein the metal alloy melts at a temperature in the range of 200° F. to 1000° F.
24. A solid propellant rocket motor as claimed in claim 15 wherein the fusible metal melts at a temperature lower than the autoignition temperature of the solid propellant.
25. A solid propellant rocket motor as claimed in claim 15 wherein the motor contains an igniter comprising a pyrotechnic material that has an autoignition temperature lower than that of the propellant and the fusible connector melts at a temperature lower than the autoignition temperature of the pyrotechnic material.
US07/593,725 1990-10-04 1990-10-04 Solid propellant rocket motor with fusible end closure holder Abandoned USH1144H (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US07/593,725 USH1144H (en) 1990-10-04 1990-10-04 Solid propellant rocket motor with fusible end closure holder
GB9122949A GB2263962A (en) 1990-10-04 1991-10-30 Solid propellant rocket motor with fusible end closure holder
FR9115525A FR2690205A1 (en) 1990-10-04 1991-12-13 Solid rocket motor capable of withstanding high temperatures.

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US07/593,725 USH1144H (en) 1990-10-04 1990-10-04 Solid propellant rocket motor with fusible end closure holder

Publications (1)

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USH1144H true USH1144H (en) 1993-03-02

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US (1) USH1144H (en)
FR (1) FR2690205A1 (en)
GB (1) GB2263962A (en)

Cited By (19)

* Cited by examiner, † Cited by third party
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US5398498A (en) * 1994-05-06 1995-03-21 Bei Electronics, Inc. Joint construction between components of military projectile and releasable by melting of fusible eutectic helical member
US5735114A (en) * 1991-08-15 1998-04-07 Thiokol Corporation Thermostatic bimetallic retaining ring for use in rocket motor assembly
WO1998019127A1 (en) 1996-10-28 1998-05-07 Cordant Technologies, Inc. Design for a gun-launched rocket
US5792982A (en) * 1992-10-27 1998-08-11 Atlantic Research Corporation Two-part igniter for gas generating compositions
US5976293A (en) * 1997-02-10 1999-11-02 Universal Propulsion Company, Inc. Method for making a case for combustible materials
US6035631A (en) * 1995-07-04 2000-03-14 Royal Ordnance Public Limited Company Safety in solid fuel rocket motors
US6321656B1 (en) * 2000-03-22 2001-11-27 The United States Of America As Represented By The Secretary Of The Navy Thermally actuated release mechanism
US6619029B2 (en) 2001-11-01 2003-09-16 Alliant Techsystems Inc. Rocket motors with insensitive munitions systems
US20030205161A1 (en) * 2002-05-06 2003-11-06 Roach Eric E. Method and apparatus for releasably attaching a closure plate to a casing
US20060054046A1 (en) * 2002-08-12 2006-03-16 Qinetiq Limited Temperature responsive safety devices for munitions
US7331292B1 (en) 2004-03-23 2008-02-19 The United States Of America As Represented By The Secretary Of The Navy Venting system for explosive warheads
EP2009386A1 (en) * 2007-06-28 2008-12-31 S.E.I. Societa Esplosivi Industriali S.p.A. Safety device for explosive containers, explosive containers and method for making explosive containers safe
US7484353B1 (en) * 1997-02-26 2009-02-03 Aerojet-General Corporation Rocket motor case using plank sections and methods of manufacturing
US20100089272A1 (en) * 2002-08-12 2010-04-15 Qinetiq Limited Temperature Responsive Safety Devices for Munitions
US20100126887A1 (en) * 2007-07-25 2010-05-27 Abdul-Salam Kaddour Rupturing devices
US20110044751A1 (en) * 2009-08-21 2011-02-24 General Dynamics Armament And Technical Products, Inc. Rocket Motor Tube With Safety Features
US8550004B1 (en) * 2009-10-21 2013-10-08 The United States Of America As Represented By The Secretary Of The Army Riveted cartridge venting
US20150330757A1 (en) * 2014-05-14 2015-11-19 Fike Corporation Vented-at-temperature igniter
US9964387B2 (en) * 2009-08-19 2018-05-08 Orbital Atk, Inc. Insensitive munitions swaged vent plug

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US5036658A (en) * 1990-03-05 1991-08-06 The United States Of America As Represented By The Secretary Of The Army Pressure relief device for solid propellant motors subjected to high external temperatures

Cited By (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5735114A (en) * 1991-08-15 1998-04-07 Thiokol Corporation Thermostatic bimetallic retaining ring for use in rocket motor assembly
US5792982A (en) * 1992-10-27 1998-08-11 Atlantic Research Corporation Two-part igniter for gas generating compositions
US5398498A (en) * 1994-05-06 1995-03-21 Bei Electronics, Inc. Joint construction between components of military projectile and releasable by melting of fusible eutectic helical member
US6035631A (en) * 1995-07-04 2000-03-14 Royal Ordnance Public Limited Company Safety in solid fuel rocket motors
US5792981A (en) * 1996-10-28 1998-08-11 Thiokol Corporation Gun-launched rocket
US6094906A (en) * 1996-10-28 2000-08-01 Cordant Technologies Inc. Design for a gun-launched rocket
WO1998019127A1 (en) 1996-10-28 1998-05-07 Cordant Technologies, Inc. Design for a gun-launched rocket
US5976293A (en) * 1997-02-10 1999-11-02 Universal Propulsion Company, Inc. Method for making a case for combustible materials
US7484353B1 (en) * 1997-02-26 2009-02-03 Aerojet-General Corporation Rocket motor case using plank sections and methods of manufacturing
US6321656B1 (en) * 2000-03-22 2001-11-27 The United States Of America As Represented By The Secretary Of The Navy Thermally actuated release mechanism
US6966264B2 (en) 2001-11-01 2005-11-22 Alliant Techsystems Inc. Rocket motors with insensitive munitions systems and projectiles including same
US6619029B2 (en) 2001-11-01 2003-09-16 Alliant Techsystems Inc. Rocket motors with insensitive munitions systems
US20040050282A1 (en) * 2001-11-01 2004-03-18 Solberg Mark A. Rocket motors with insensitive munitions systems and projectiles including same
US20030205161A1 (en) * 2002-05-06 2003-11-06 Roach Eric E. Method and apparatus for releasably attaching a closure plate to a casing
US6752085B2 (en) * 2002-05-06 2004-06-22 Lockheed Martin Corporation Method and apparatus for releasably attaching a closure plate to a casing
WO2003095931A3 (en) * 2002-05-06 2004-04-15 Lockheed Corp Method and apparatus for releasably attaching a closure plate to a casing
US20060054046A1 (en) * 2002-08-12 2006-03-16 Qinetiq Limited Temperature responsive safety devices for munitions
US8082846B2 (en) 2002-08-12 2011-12-27 Qinetiq Limited Temperature responsive safety devices for munitions
US20100089272A1 (en) * 2002-08-12 2010-04-15 Qinetiq Limited Temperature Responsive Safety Devices for Munitions
US7549375B2 (en) * 2002-08-12 2009-06-23 Qinetiq Limited Temperature responsive safety devices for munitions
US7331292B1 (en) 2004-03-23 2008-02-19 The United States Of America As Represented By The Secretary Of The Navy Venting system for explosive warheads
EP2009386A1 (en) * 2007-06-28 2008-12-31 S.E.I. Societa Esplosivi Industriali S.p.A. Safety device for explosive containers, explosive containers and method for making explosive containers safe
US20100126887A1 (en) * 2007-07-25 2010-05-27 Abdul-Salam Kaddour Rupturing devices
US8616131B2 (en) 2007-07-25 2013-12-31 Qinetiq Limited Rupturing devices
US9964387B2 (en) * 2009-08-19 2018-05-08 Orbital Atk, Inc. Insensitive munitions swaged vent plug
US20110044751A1 (en) * 2009-08-21 2011-02-24 General Dynamics Armament And Technical Products, Inc. Rocket Motor Tube With Safety Features
US8578855B2 (en) * 2009-08-21 2013-11-12 General Dynamics Armament And Technical Products, Inc. Rocket motor tube with safety features
US8919254B2 (en) 2009-08-21 2014-12-30 General Dynamics-Ots, Inc. Pressure vessel with safety features
US9851188B2 (en) 2009-08-21 2017-12-26 General Dynamics-Ots, Inc. Decoupling assembly for a plumbing network
US8550004B1 (en) * 2009-10-21 2013-10-08 The United States Of America As Represented By The Secretary Of The Army Riveted cartridge venting
US20150330757A1 (en) * 2014-05-14 2015-11-19 Fike Corporation Vented-at-temperature igniter
US9784548B2 (en) * 2014-05-14 2017-10-10 Fike Corporation Vented-at-temperature igniter

Also Published As

Publication number Publication date
GB2263962A (en) 1993-08-11
FR2690205A1 (en) 1993-10-22
GB9122949D0 (en) 1993-06-16

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