US20130319211A1 - Plume exhaust management for vls - Google Patents
Plume exhaust management for vls Download PDFInfo
- Publication number
- US20130319211A1 US20130319211A1 US13/374,637 US201113374637A US2013319211A1 US 20130319211 A1 US20130319211 A1 US 20130319211A1 US 201113374637 A US201113374637 A US 201113374637A US 2013319211 A1 US2013319211 A1 US 2013319211A1
- Authority
- US
- United States
- Prior art keywords
- plenum
- gas
- exhaust gas
- plug
- upper portion
- 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.)
- Granted
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
- F41F3/0413—Means for exhaust gas disposal, e.g. exhaust deflectors, gas evacuation systems
Definitions
- the embodiments herein generally relate to weapons systems, and, more particularly, to equipment used for protection against the exhaust gases of missile launching systems.
- a vertical launching system consists of a number of cells for holding and firing missiles on surface ships and submarines used by many navies around the world.
- each cell can hold a number of different types of missiles, enabling the ship flexibility to load an appropriate set for a given mission and to enable replacement of earlier missiles with upgrades without expensive rework.
- the missile flies straight up long enough to clear the cell and the ship, and then turns on course.
- the most popular VLS system in the world is the MK 41, being used by eleven navies around the world. The United States Navy will employ the MK 57 VLS on the U.S.S. Zumwalt class destroyers.
- Both MK 41 and MK 57 VLS missile launchers primarily are configured as a plenum and uptake type gas management system.
- a plenum is a pressurized chamber holding fluids, and the uptake refers to the general upwards/vertical venting of pressurized gas from the plenum.
- These systems manage gases during a normal missile launch and also during retrained firing.
- a typical plenum and uptake approach results in substantial structural wear caused by normal missile launches, which decreases the ability to withstand a restrained firing, thus, limiting the number of missiles that can be launched prior to gas management system refurbishment.
- the MK 41 and MK 57 VLS gas management system plenums protect their plenum floors with ablative material. Additional protection is provided underneath the rocket motor by using a bi-layer ablative material stack. The material on top of the stack is exposed to the rocket motor plume during normal missile fly outs, and the material on the bottom of the stack is exposed only during a missile restrained firing. However, the material is generally inadequate to prevent burn-through when exposed to plume jetting and long burn times because the ablative material, which tends to be expensive, typically do not have sufficient mechanical strength to resist the forces produced by the plume impingement.
- the Mk 41 VLS gas management system also uses an aft closure, grid, and sill.
- the aft closure is a square multi-material, multilayer plate that has diagonal scores that allow it to “blow open” during a rocket motor firing.
- the sill keeps the aft closure from opening too far and the grid prevents the adjacent aft closures from opening in the opposite direction.
- this type of system requires a substantial number of components, the aft closure layup uses many different materials and a very process-intensive assembly, and the sill and grid are relatively difficult to manufacture and assemble.
- this system is not readily adaptable for use on a general plenum box assemblies because it requires more space above the top of the plenum and more intrusion into the inside of the plenum.
- an embodiment herein provides a system for directing a flow of gas, including a launching mechanism, a plenum, a layer of meltable material, and an open-ended uptake component.
- the launching mechanism is adapted to expel rocket exhaust gas.
- the plenum includes an upper portion having at least one fire resistant breachable plug.
- the upper portion is adjacent to the launching mechanism.
- the layer of meltable material is disposed on the upper portion.
- the heat generated by the gas melts the layer of meltable material.
- the open-ended uptake component operatively connects to the plenum.
- the plug moves onto a lower portion of the plenum due to force generated by the gas onto the plug, and the gas flows through the plenum and the uptake component to vent said gas in a controlled manner.
- FIG. 1 illustrates a schematic diagram of a gas management system
- FIG. 2 illustrates a schematic diagram of a missile launcher attached to a gas management system
- FIG. 3 illustrates a schematic diagram of a gas blast protector
- FIG. 4 illustrates a cross-sectional diagram of the gas blast protector of FIG. 3 attached to a plenum of a gas management system
- FIG. 5A illustrates a cross-sectional diagram of a breachable plenum plug gas management system in a closed state of operation
- FIG. 5B illustrates a magnified cross-sectional view of the encircled area ‘A’ of the breachable plenum plug gas management system of FIG. 5A ;
- FIG. 5C illustrates a cross-sectional diagram of a breachable plenum plug gas management system in an open state of operation
- FIG. 6 is a flow diagram illustrating a method according to an embodiment herein.
- FIGS. 1 through 6 where similar reference characters denote corresponding features consistently throughout the figures, there are shown preferred embodiments.
- FIG. 1 illustrates a schematic diagram of a gas management system 10 , which includes a plenum 15 connected to an uptake component 20 having an open end 25 to permit venting of gas that travels through the plenum 15 and then up through the uptake component 20 .
- the gas management system 10 protects surrounding personnel and equipment from the harmful effects of a restrained firing for missile launcher systems that are ordinarily not specifically designed to withstand or protect against the effects of hot missile exhaust gases.
- a gas blast protector mechanism 30 Positioned inside the plenum 15 is a gas blast protector mechanism 30 , which is described in further detail below with reference to FIG. 3 .
- the view illustrated in FIG. 1 is a cut through view of the plenum 15 in order to illustrate the positioning of the gas blast protector mechanism 30 .
- the plenum 15 is generally configured as a box-type configuration with walls extending around all sides to prevent the inadvertent discharge of gas in an uncontrolled manner.
- FIG. 2 illustrates a schematic diagram of a missile launcher 35 adjacent to a gas management system 10 .
- the missile launcher 35 which houses or otherwise connects with a rocket/missile (e.g., rocket/missile 43 shown in FIG. 4 ) is connected to both the plenum 15 and uptake component 20 through a plurality of connecting mechanisms 40 , and the embodiments herein are not restricted to any particular type of connecting mechanism or configuration.
- the missile launcher 35 is in close proximity to the plenum 15 , which causes the exhaust gas from the launched rocket/missile to be directed upon the plenum 15 at elevated temperatures.
- FIG. 3 illustrates a schematic diagram of a gas blast protector mechanism 30 comprising a plate 31 and a plurality of raised bumps 32 extending from the plate 31 .
- the plate 31 and bumps 32 may be made from a variety of mechanically strong materials including ceramics.
- the gas blast protector mechanism 30 may or may not be utilized with respect to the embodiments herein.
- the plate 31 is placed on the lower portion (i.e., floor) 16 of the plenum 15 .
- FIG. 4 the various block arrows depict the flow of gas as a result of a rocket/missile 43 being launched.
- the initial exhaust gas 45 purges the upper portion 17 (i.e., ceiling) of the plenum 15 and then extends downward through the inner chamber 18 of the plenum 15 .
- the gas blast protector 30 the gas is diverted in a substantially horizontal direction in relation to the plenum 15 such that the diverted gas 50 flows through the chamber 18 and then through the connecting uptake component 20 (not shown in FIG. 4 ) to be vented in a controlled manner.
- the gas blast protector 30 assists in reducing the mechanical and thermal impact of the gas 45 on the floor 16 of the plenum 15 , thereby aiding in the maintenance of the structural integrity of the floor 16 of the plenum 15 .
- the gas blast protector 30 protects the floor 16 of the plenum 15 from burning through when exposed to the direct impingement of hot missile exhaust gas 45 .
- the gas blast protector 30 is an optional component of the embodiments herein.
- FIGS. 5A through 5C illustrate various cross-sectional diagrams of a breachable plenum plug gas management system 10 a.
- FIG. 5A illustrates the system 10 a in a closed state of operation while FIG. 5C illustrates the system 10 a in an open state of operation.
- FIG. 5B illustrates a magnified cross-sectional view of the encircled area ‘A’ of the breachable plenum plug gas management system 10 a of FIG. 5A .
- the gas management system 10 a includes a plenum 15 having an upper portion 17 with a plurality of breachable (i.e., movable) plugs 55 a , 55 b; a lower portion 16 ; and a chamber 18 separating the upper portion 17 from the lower portion 16 .
- the system 10 a also includes an uptake component 20 operatively connected to the plenum 15 .
- at least one gas blast protection component 30 may be positioned over the lower portion 16 of the plenum 15 .
- the plurality of breachable (i.e., movable) plugs 55 a, 55 b move in a direction from the upper portion 17 towards the lower portion 16 upon impact of rocket motor exhaust gas 45 directed thereon.
- the plugs 55 a, 55 b may incorporate a tapered shape or alternatively may comprise a stepped shape (not shown). While these two shapes/configurations are described with respect to the plugs 55 a, 55 b, the embodiments herein are not restricted to a particular geometric configuration of the plugs 55 a, 55 b, as any type of configuration that permits breach of the plugs 55 a , 55 b is permitted. Additionally, the system 10 a further includes a layer of meltable material 60 over the upper portion 17 of the plenum 15 , and a layer of fire resistant material 65 under the layer of meltable material 60 .
- the material used for the layer of fire resistant material 65 is the same material used for the plugs 55 a, 55 b.
- the plugs 55 a, 55 b are fire resistant, and the release of the plug 55 a is dictated by the force of the exhaust gas 45 rather than the heat generated by the gas 45 .
- the layer of fire resistant material 65 may be configured to be substantially aligned with the plugs 55 a, 55 b. Due to the fire resistant qualities of the plugs 55 a, 55 b, the floor 16 of the plenum 15 is protected from the deleterious effects of the gas 45 without the need of a gas blast protector 30 . Additionally, once the plug 55 a hits the lower portion 16 of the plenum 15 , the plug 55 a provides the same gas diversion quality as the raised bumps 32 of a gas blast protector 30 . However, should additional protection of the floor 16 of the plenum 15 be desired, then the embodiments herein may incorporate a gas blast protector 30 in the plenum 15 .
- the uptake component 20 comprises a first open end 21 connected to the plenum 15 and a second open end 25 to permit controlled venting of the gas 50 .
- the plugs 55 a, 55 b move in substantially one direction only (i.e., generally in the direction from the upper portion 17 to the lower portion 16 of the plenum 15 ).
- the discharged plug 55 a caused by the hot missile exhaust gas 45 creates an opening 19 in the upper portion 17 of the plenum 15 located directly underneath the exhausting rocket motor (e.g., rocket/missile 43 of FIG. 4 ).
- non-discharged plug 55 b as well as the layer of fire resistant material 65 prevents exhaust gas 45 , 50 from leaking back underneath adjacent non-exhausting rocket motors (not shown).
- the rocket motor exhaust gas 45 flows into the inner chamber 18 of the plenum 15 and is ducted away to a safe location (e.g., through the uptake component 20 ).
- a safe location e.g., through the uptake component 20 .
- the non-exhausting rocket motors (not shown) are protected from the hot gases, due to the non-breached adjacent plug 55 b preventing sympathetic rocket motor ignition.
- plug 55 b since the non-exhausting rocket motors do not direct hot gas 50 onto plug 55 b, then the plug 55 b remains in place in the upper portion 17 of the plenum 15 without breaching. Therefore, only plug 55 a is breached because a rocket is launched directly above this location of the upper portion 17 of the plenum 15 .
- the gas 45 directed onto the plenum 15 first strikes the layer of meltable material 60 over the upper portion 17 of the plenum 15 .
- the heat capacity of the meltable material 60 is less than the temperature of the gas 45 thereby causing the material 60 to melt, which then allows the gas 45 to strike the plug 55 a at a force sufficient to cause the plug 55 a to dislodge from the upper portion 17 of the plenum and down towards the lower portion 16 of the plenum 15 .
- the layer of fire resistant material 65 restrains the gas 45 from causing the breach of adjacent plug 55 b and to maintain the structural integrity of the remaining areas of the upper portion 17 of the plenum 15 .
- the meltable material 60 and the fire resistant material 65 of the plugs 55 a, 55 b are not restricted to particular materials and need only be dictated by the thermal environment.
- the system 10 a protects a launcher 35 and surrounding equipment from the effects of a restrained firing even though the launcher 35 was not necessarily designed to mitigate a restrained firing. Due to the use of the fire resistant material 65 , the gas management system 10 a does not wear out due to the number of missile firings occurring.
- the embodiments herein achieve higher mechanical strength by combining the meltable material 60 and the heat resistant material 65 . This is because meltable materials are plentiful and can be selected for higher strength, whereas heat-resistant materials are more specialized and typically weaker mechanically. Furthermore, the plugs 55 a, 55 b are relatively easy to machine due to the materials that they constitute, which reduces manufacturing costs.
- the embodiments herein also permit the redirection of the exhaust gases 45 , 50 such that their detrimental effects on structural components (i.e., plenum 15 ) are mitigated.
- the embodiments herein require fewer components and fewer materials than conventional gas management systems because the system 10 a utilizes a less complex configuration by requiring less room above and inside the plenum 15 (e.g., the embodiments herein do not require an additional gas blast protector 30 ). This is because, the system 10 a does not use a grid, and since a sill is also not required, there are no required extraneous flow inhibiting items protruding into the plenum 15 .
- the gas management system 10 a may be made from a number of materials for the structural as well as the heat resistant aspects of the design.
- the materials used for the system 10 a can be chosen based on mechanical strength under high heating rates and long burn time, ease of machining, ease of availability, and cost.
- FIG. 6 is an exemplary flow diagram 70 illustrating a method according to an embodiment herein.
- exhaust gas 45 from a missile's rocket motor 43 is directed to an upper portion 17 of the plenum 15 having fire-resistant breachable plugs 55 a, 55 b.
- an upper layer of meltable material 60 melts in response to heat generated by the gas 45 in conjunction with step 73 of disposing a fire-resistant material 65 under the meltable material 60 .
- the plugs 55 a, 55 b are aligned with the fire-resistant material 65 .
- the plugs 55 a, 55 b are pushed down by the exhaust gas 50 being positioned directly above.
- the gas 50 is directed through the plenum 15 towards an uptake component 20 for venting.
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
Description
- The invention described was made in the performance of official duties by one or more employees of the Department of the Navy, and thus, the invention herein may be manufactured, used or licensed by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor.
- 1. Technical Field
- The embodiments herein generally relate to weapons systems, and, more particularly, to equipment used for protection against the exhaust gases of missile launching systems.
- 2. Description of the Related Art
- A vertical launching system (VLS) consists of a number of cells for holding and firing missiles on surface ships and submarines used by many navies around the world. Typically, each cell can hold a number of different types of missiles, enabling the ship flexibility to load an appropriate set for a given mission and to enable replacement of earlier missiles with upgrades without expensive rework. When the command is given, the missile flies straight up long enough to clear the cell and the ship, and then turns on course. The most popular VLS system in the world is the MK 41, being used by eleven navies around the world. The United States Navy will employ the MK 57 VLS on the U.S.S. Zumwalt class destroyers.
- Both MK 41 and MK 57 VLS missile launchers primarily are configured as a plenum and uptake type gas management system. A plenum is a pressurized chamber holding fluids, and the uptake refers to the general upwards/vertical venting of pressurized gas from the plenum. These systems manage gases during a normal missile launch and also during retrained firing. However, a typical plenum and uptake approach results in substantial structural wear caused by normal missile launches, which decreases the ability to withstand a restrained firing, thus, limiting the number of missiles that can be launched prior to gas management system refurbishment.
- The MK 41 and MK 57 VLS gas management system plenums protect their plenum floors with ablative material. Additional protection is provided underneath the rocket motor by using a bi-layer ablative material stack. The material on top of the stack is exposed to the rocket motor plume during normal missile fly outs, and the material on the bottom of the stack is exposed only during a missile restrained firing. However, the material is generally inadequate to prevent burn-through when exposed to plume jetting and long burn times because the ablative material, which tends to be expensive, typically do not have sufficient mechanical strength to resist the forces produced by the plume impingement.
- The Mk 41 VLS gas management system also uses an aft closure, grid, and sill. The aft closure is a square multi-material, multilayer plate that has diagonal scores that allow it to “blow open” during a rocket motor firing. The sill keeps the aft closure from opening too far and the grid prevents the adjacent aft closures from opening in the opposite direction. However, this type of system requires a substantial number of components, the aft closure layup uses many different materials and a very process-intensive assembly, and the sill and grid are relatively difficult to manufacture and assemble. Moreover, this system is not readily adaptable for use on a general plenum box assemblies because it requires more space above the top of the plenum and more intrusion into the inside of the plenum.
- Therefore, it is desirable to develop an improved gas management system that utilizes the plenum and uptake configuration and is readily adaptable in current weapon systems at reduced cost and complexity. In view of the foregoing, an embodiment herein provides a system for directing a flow of gas, including a launching mechanism, a plenum, a layer of meltable material, and an open-ended uptake component. In various exemplary embodiments, the launching mechanism is adapted to expel rocket exhaust gas.
- In various exemplary embodiments, the plenum includes an upper portion having at least one fire resistant breachable plug. The upper portion is adjacent to the launching mechanism. The layer of meltable material is disposed on the upper portion. The heat generated by the gas melts the layer of meltable material. The open-ended uptake component operatively connects to the plenum. The plug moves onto a lower portion of the plenum due to force generated by the gas onto the plug, and the gas flows through the plenum and the uptake component to vent said gas in a controlled manner.
- These and other aspects of the embodiments herein will be better appreciated and understood when considered in conjunction with the following description and the accompanying drawings. It should be understood, however, that the following descriptions, while indicating preferred embodiments and numerous specific details thereof, are given by way of illustration and not of limitation. Many changes and modifications may be made within the scope of the embodiments herein without departing from the spirit thereof, and the embodiments herein include all such modifications.
- The embodiments herein will be better understood from the following detailed description with reference to the drawings, in which:
-
FIG. 1 illustrates a schematic diagram of a gas management system; -
FIG. 2 illustrates a schematic diagram of a missile launcher attached to a gas management system; -
FIG. 3 illustrates a schematic diagram of a gas blast protector; -
FIG. 4 illustrates a cross-sectional diagram of the gas blast protector ofFIG. 3 attached to a plenum of a gas management system; -
FIG. 5A illustrates a cross-sectional diagram of a breachable plenum plug gas management system in a closed state of operation; -
FIG. 5B illustrates a magnified cross-sectional view of the encircled area ‘A’ of the breachable plenum plug gas management system ofFIG. 5A ; -
FIG. 5C illustrates a cross-sectional diagram of a breachable plenum plug gas management system in an open state of operation; and -
FIG. 6 is a flow diagram illustrating a method according to an embodiment herein. - The embodiments herein and the various features and advantageous details thereof are explained more fully with reference to the non-limiting embodiments that are illustrated in the accompanying drawings and detailed in the following description. Descriptions of well-known components and processing techniques are omitted so as to not unnecessarily obscure the embodiments herein. The examples used herein are intended merely to facilitate an understanding of ways in which the embodiments herein may be practiced and to further enable those of skill in the art to practice the embodiments herein. Accordingly, the examples should not be construed as limiting the scope of the embodiments herein.
- The embodiments herein provide a gas management system that utilizes the plenum and uptake configuration to provide protection from the deleterious effects of a rocket plume. Referring now to the drawings, and more particularly to
FIGS. 1 through 6 , where similar reference characters denote corresponding features consistently throughout the figures, there are shown preferred embodiments. -
FIG. 1 illustrates a schematic diagram of agas management system 10, which includes aplenum 15 connected to anuptake component 20 having anopen end 25 to permit venting of gas that travels through theplenum 15 and then up through theuptake component 20. Thegas management system 10 protects surrounding personnel and equipment from the harmful effects of a restrained firing for missile launcher systems that are ordinarily not specifically designed to withstand or protect against the effects of hot missile exhaust gases. Positioned inside theplenum 15 is a gasblast protector mechanism 30, which is described in further detail below with reference toFIG. 3 . The view illustrated inFIG. 1 is a cut through view of theplenum 15 in order to illustrate the positioning of the gasblast protector mechanism 30. However, theplenum 15 is generally configured as a box-type configuration with walls extending around all sides to prevent the inadvertent discharge of gas in an uncontrolled manner. -
FIG. 2 , with reference toFIG. 1 , illustrates a schematic diagram of amissile launcher 35 adjacent to agas management system 10. As shown, themissile launcher 35, which houses or otherwise connects with a rocket/missile (e.g., rocket/missile 43 shown inFIG. 4 ) is connected to both theplenum 15 anduptake component 20 through a plurality of connectingmechanisms 40, and the embodiments herein are not restricted to any particular type of connecting mechanism or configuration. Themissile launcher 35 is in close proximity to theplenum 15, which causes the exhaust gas from the launched rocket/missile to be directed upon theplenum 15 at elevated temperatures. -
FIG. 3 , with reference toFIGS. 1 and 2 , illustrates a schematic diagram of a gasblast protector mechanism 30 comprising aplate 31 and a plurality of raisedbumps 32 extending from theplate 31. Theplate 31 and bumps 32 may be made from a variety of mechanically strong materials including ceramics. As described below, the gasblast protector mechanism 30 may or may not be utilized with respect to the embodiments herein. As shown inFIG. 4 , with reference toFIGS. 1 through 3 , theplate 31 is placed on the lower portion (i.e., floor) 16 of theplenum 15. - In
FIG. 4 , the various block arrows depict the flow of gas as a result of a rocket/missile 43 being launched. Theinitial exhaust gas 45 purges the upper portion 17 (i.e., ceiling) of theplenum 15 and then extends downward through theinner chamber 18 of theplenum 15. Thereafter, upon contacting thegas blast protector 30, the gas is diverted in a substantially horizontal direction in relation to theplenum 15 such that the divertedgas 50 flows through thechamber 18 and then through the connecting uptake component 20 (not shown inFIG. 4 ) to be vented in a controlled manner. Thegas blast protector 30 assists in reducing the mechanical and thermal impact of thegas 45 on thefloor 16 of theplenum 15, thereby aiding in the maintenance of the structural integrity of thefloor 16 of theplenum 15. In other words, thegas blast protector 30 protects thefloor 16 of theplenum 15 from burning through when exposed to the direct impingement of hotmissile exhaust gas 45. As mentioned above, thegas blast protector 30 is an optional component of the embodiments herein. -
FIGS. 5A through 5C , with reference toFIGS. 1 through 4 , illustrate various cross-sectional diagrams of a breachable plenum pluggas management system 10 a.FIG. 5A illustrates thesystem 10 a in a closed state of operation whileFIG. 5C illustrates thesystem 10 a in an open state of operation.FIG. 5B illustrates a magnified cross-sectional view of the encircled area ‘A’ of the breachable plenum pluggas management system 10 a ofFIG. 5A . - As illustrated, the
gas management system 10 a includes aplenum 15 having anupper portion 17 with a plurality of breachable (i.e., movable) plugs 55 a, 55 b; alower portion 16; and achamber 18 separating theupper portion 17 from thelower portion 16. Thesystem 10 a also includes anuptake component 20 operatively connected to theplenum 15. In an optional embodiment, at least one gas blast protection component 30 (not shown inFIGS. 5A through 5C ) may be positioned over thelower portion 16 of theplenum 15. The plurality of breachable (i.e., movable) plugs 55 a, 55 b move in a direction from theupper portion 17 towards thelower portion 16 upon impact of rocketmotor exhaust gas 45 directed thereon. - As shown in
FIG. 5B , theplugs plugs plugs plugs system 10 a further includes a layer ofmeltable material 60 over theupper portion 17 of theplenum 15, and a layer of fireresistant material 65 under the layer ofmeltable material 60. In one embodiment, the material used for the layer of fireresistant material 65 is the same material used for theplugs plugs plug 55 a is dictated by the force of theexhaust gas 45 rather than the heat generated by thegas 45. - The layer of fire
resistant material 65 may be configured to be substantially aligned with theplugs plugs floor 16 of theplenum 15 is protected from the deleterious effects of thegas 45 without the need of agas blast protector 30. Additionally, once theplug 55 a hits thelower portion 16 of theplenum 15, theplug 55 a provides the same gas diversion quality as the raised bumps 32 of agas blast protector 30. However, should additional protection of thefloor 16 of theplenum 15 be desired, then the embodiments herein may incorporate agas blast protector 30 in theplenum 15. Theuptake component 20 comprises a firstopen end 21 connected to theplenum 15 and a secondopen end 25 to permit controlled venting of thegas 50. - The
plugs upper portion 17 to thelower portion 16 of the plenum 15). The discharged plug 55 a caused by the hotmissile exhaust gas 45 creates anopening 19 in theupper portion 17 of theplenum 15 located directly underneath the exhausting rocket motor (e.g., rocket/missile 43 ofFIG. 4 ). However,non-discharged plug 55 b as well as the layer of fireresistant material 65 preventsexhaust gas plug 55 a underneath the exhausting rocket motor functions (i.e., is released), the rocketmotor exhaust gas 45 flows into theinner chamber 18 of theplenum 15 and is ducted away to a safe location (e.g., through the uptake component 20). However, the non-exhausting rocket motors (not shown) are protected from the hot gases, due to the non-breachedadjacent plug 55 b preventing sympathetic rocket motor ignition. - Accordingly, since the non-exhausting rocket motors do not direct
hot gas 50 ontoplug 55 b, then theplug 55 b remains in place in theupper portion 17 of theplenum 15 without breaching. Therefore, only plug 55 a is breached because a rocket is launched directly above this location of theupper portion 17 of theplenum 15. Thegas 45 directed onto theplenum 15 first strikes the layer ofmeltable material 60 over theupper portion 17 of theplenum 15. - The heat capacity of the
meltable material 60 is less than the temperature of thegas 45 thereby causing thematerial 60 to melt, which then allows thegas 45 to strike theplug 55 a at a force sufficient to cause theplug 55 a to dislodge from theupper portion 17 of the plenum and down towards thelower portion 16 of theplenum 15. The layer of fireresistant material 65 restrains thegas 45 from causing the breach ofadjacent plug 55 b and to maintain the structural integrity of the remaining areas of theupper portion 17 of theplenum 15. Themeltable material 60 and the fireresistant material 65 of theplugs - The
system 10 a protects alauncher 35 and surrounding equipment from the effects of a restrained firing even though thelauncher 35 was not necessarily designed to mitigate a restrained firing. Due to the use of the fireresistant material 65, thegas management system 10 a does not wear out due to the number of missile firings occurring. - By utilizing the
plugs upper portion 17 of theplenum 15, the embodiments herein achieve higher mechanical strength by combining themeltable material 60 and the heatresistant material 65. This is because meltable materials are plentiful and can be selected for higher strength, whereas heat-resistant materials are more specialized and typically weaker mechanically. Furthermore, theplugs - The embodiments herein also permit the redirection of the
exhaust gases system 10 a utilizes a less complex configuration by requiring less room above and inside the plenum 15 (e.g., the embodiments herein do not require an additional gas blast protector 30). This is because, thesystem 10 a does not use a grid, and since a sill is also not required, there are no required extraneous flow inhibiting items protruding into theplenum 15. - While various material descriptions are described herein, the
gas management system 10 a may be made from a number of materials for the structural as well as the heat resistant aspects of the design. The materials used for thesystem 10 a can be chosen based on mechanical strength under high heating rates and long burn time, ease of machining, ease of availability, and cost. -
FIG. 6 , with reference toFIGS. 1 through 5C , is an exemplary flow diagram 70 illustrating a method according to an embodiment herein. Atstep 71,exhaust gas 45 from a missile'srocket motor 43 is directed to anupper portion 17 of theplenum 15 having fire-resistant breachable plugs 55 a, 55 b. Atstep 72, an upper layer ofmeltable material 60 melts in response to heat generated by thegas 45 in conjunction withstep 73 of disposing a fire-resistant material 65 under themeltable material 60. Atstep 74, theplugs resistant material 65. Atstep 75, theplugs exhaust gas 50 being positioned directly above. Atstep 76, thegas 50 is directed through theplenum 15 towards anuptake component 20 for venting. - The foregoing description of the specific embodiments will so fully reveal the general nature of the embodiments herein that others can, by applying current knowledge, readily modify and/or adapt for various applications such specific embodiments without departing from the generic concept, and, therefore, such adaptations and modifications should and are intended to be comprehended within the meaning and range of equivalents of the disclosed embodiments. It is to be understood that the phraseology or terminology employed herein is for the purpose of description and not of limitation. Therefore, while the embodiments herein have been described in terms of preferred embodiments, those skilled in the art will recognize that the embodiments herein can be practiced with modification within the spirit and scope of the appended claims.
Claims (19)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/374,637 US8584569B1 (en) | 2011-12-06 | 2011-12-06 | Plume exhaust management for VLS |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/374,637 US8584569B1 (en) | 2011-12-06 | 2011-12-06 | Plume exhaust management for VLS |
Publications (2)
Publication Number | Publication Date |
---|---|
US8584569B1 US8584569B1 (en) | 2013-11-19 |
US20130319211A1 true US20130319211A1 (en) | 2013-12-05 |
Family
ID=49555630
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/374,637 Expired - Fee Related US8584569B1 (en) | 2011-12-06 | 2011-12-06 | Plume exhaust management for VLS |
Country Status (1)
Country | Link |
---|---|
US (1) | US8584569B1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11889674B2 (en) | 2014-04-25 | 2024-01-30 | Taiwan Semiconductor Manufacturing Company, Ltd. | Structure and method for SRAM FinFET device having an oxide feature |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9874420B2 (en) | 2013-12-30 | 2018-01-23 | Bae Systems Land & Armaments, L.P. | Missile canister gated obturator |
Family Cites Families (29)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2679467A (en) * | 1951-07-21 | 1954-05-25 | Pittsburgh Plate Glass Co | Pressure blowout safety closure |
CH527405A (en) * | 1970-07-10 | 1972-08-31 | Sarmac Sa | Set comprising a self-propelled fletched projectile and its case |
US4044648A (en) * | 1975-09-29 | 1977-08-30 | General Dynamics Corporation | Rocket exhaust plenum flow control apparatus |
US4134327A (en) * | 1977-12-12 | 1979-01-16 | General Dynamics Corporation | Rocket launcher tube post-launch rear closure |
US4173919A (en) * | 1977-12-12 | 1979-11-13 | General Dynamics Corporation | Two-way rocket plenum for combustion suppression |
US4186647A (en) * | 1978-08-09 | 1980-02-05 | General Dynamics Corporation, Pomona Division | Multiple area rear launch tube cover |
US4324167A (en) * | 1980-04-14 | 1982-04-13 | General Dynamics, Pomona Division | Flexible area launch tube rear cover |
US4373420A (en) * | 1980-10-06 | 1983-02-15 | General Dynamics, Pomona Division | Combustion suppressor |
US4498261A (en) * | 1981-12-07 | 1985-02-12 | Continental Disc Corporation | Low pressure venting panel |
US4455917A (en) * | 1982-03-15 | 1984-06-26 | General Dynamics, Pomona Division | Shock wave end cap removal device |
US4683798A (en) * | 1985-12-27 | 1987-08-04 | General Dynamics, Pomona Division | Gas management transition device |
US4686884A (en) * | 1985-12-27 | 1987-08-18 | General Dynamics, Pomona Division | Gas management deflector |
US4796510A (en) * | 1987-11-09 | 1989-01-10 | General Dynamics, Pomona Division | Rocket exhaust recirculation obturator for missile launch tube |
US4934241A (en) * | 1987-11-12 | 1990-06-19 | General Dynamics Corp. Pomona Division | Rocket exhaust deflector |
US4949618A (en) * | 1989-12-19 | 1990-08-21 | The United States Of America | Missile protection system |
US5136922A (en) * | 1991-05-13 | 1992-08-11 | General Dynamics Corporation, Air Defense Systems Division | Self-actuating rocket chamber closures for multi-missile launch cells |
US5191162A (en) * | 1991-09-05 | 1993-03-02 | Newport News Shipbuilding And Dry Dock Company | Method and apparatus for a ship-based rocket launching structure |
US5162605A (en) * | 1992-01-16 | 1992-11-10 | General Dynamics Corporation | Self-activated rocket launcher cell closure |
US5194688A (en) * | 1992-01-31 | 1993-03-16 | Hughes Missile Systems Company | Apparatus for limiting recirculation of rocket exhaust gases during missile launch |
US6079310A (en) * | 1996-12-05 | 2000-06-27 | The United States Of America As Represented By The Secretary Of The Navy | Portable launcher |
US6755111B2 (en) * | 2001-06-27 | 2004-06-29 | Lockheed Martin Corporation | Missile launcher cell with exhaust gas uptake ducts, and array of such missile launcher cells |
US20060117940A1 (en) * | 2004-12-06 | 2006-06-08 | Lockheed Martin Corporation | Adjustable adaptable vertical launching system |
US7389717B1 (en) * | 2005-04-21 | 2008-06-24 | Lockheed Martin Corporation | Missile launch system with high-volume assault capability |
US7350451B2 (en) * | 2005-11-10 | 2008-04-01 | Lockheed Martin Corporation | Apparatus comprising an exhaust duct and anti-fratricide shield |
AU2008351349B2 (en) * | 2007-11-20 | 2012-01-19 | Lockheed Martin Corporation | Adaptable launching system |
FR2926360B1 (en) * | 2008-01-11 | 2012-10-19 | Dcns | DEFORMABLE REAR OPERATOR FOR MISSILE CONTAINER, COMPRISING A FRONT SUPPORT FRAME |
US8181561B2 (en) * | 2008-06-02 | 2012-05-22 | Causwave, Inc. | Explosive decompression propulsion system |
US8443707B2 (en) * | 2010-08-24 | 2013-05-21 | Lockheed Martin Corporation | Self-contained munition gas management system |
US8468926B2 (en) * | 2010-10-15 | 2013-06-25 | Corvid Technologies | Ballistic armor system |
-
2011
- 2011-12-06 US US13/374,637 patent/US8584569B1/en not_active Expired - Fee Related
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11889674B2 (en) | 2014-04-25 | 2024-01-30 | Taiwan Semiconductor Manufacturing Company, Ltd. | Structure and method for SRAM FinFET device having an oxide feature |
Also Published As
Publication number | Publication date |
---|---|
US8584569B1 (en) | 2013-11-19 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US10203180B2 (en) | Missile canister gated obturator | |
US9134098B1 (en) | Countermeasure system and method for defeating incoming projectiles | |
US11421963B2 (en) | Lightweight enhanced ballistic armor system | |
US4324167A (en) | Flexible area launch tube rear cover | |
EP1659360B1 (en) | An explosionproof container for the storage and transport of in particular pyrotechnic material | |
US8584569B1 (en) | Plume exhaust management for VLS | |
JP4058042B2 (en) | Missile launcher cells with exhaust gas intake ducts and rows of these missile launcher cells | |
EP1552239B1 (en) | Controlled-harm explosive reactive armor (cohera) | |
US8485098B2 (en) | Decoy with a simple safety device | |
NO146883B (en) | DISPOSAL UNIT FOR A NUMBER OF REACTIVE ROCKET BODIES AND SIMILAR | |
KR20150015974A (en) | Device for Intercepting VLS’s Blast for Protecting CIWS in Warship | |
RU2557123C1 (en) | Modular multi-seat shipboard vertical launcher | |
KR20240051230A (en) | A blank shooting bullet trap device for use with firearms. | |
RU2560181C1 (en) | Tank automatic loading system "scoropeya-3" | |
KR20170038204A (en) | Metal container for propelling charge | |
RU2612037C2 (en) | Reconnaissance and fire weapon system of tank armament | |
GB2290856A (en) | Missile storage apparatus | |
KR102302860B1 (en) | Combustion gas recirculation device | |
RU2745889C1 (en) | Method for assessing the resistance of ammunition to dangerous external influence | |
KR20210101503A (en) | Combat equipment cover and aircraft having the same | |
EP4345409A1 (en) | Unmanned turret having a ballistic protection system in the roof structure and in the floor | |
KR102020254B1 (en) | Smoke grenade for training which move and belch out smoke | |
JPH11264697A (en) | Projectile launcher | |
WO2014175982A1 (en) | Training ammunition cartridge with a gaseous plume signature | |
IT201800006489A1 (en) | SAFETY DEVICE FOR LOADING AND UNLOADING WEAPONS |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: NAVY, UNITED STATES OF AMERICA, REPRESENTED BY SEC Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:WHITNEY, M. RYAN;ATKINSON, PAUL G.;FRIDLEY JR., PERRY L.;AND OTHERS;SIGNING DATES FROM 20111201 TO 20111205;REEL/FRAME:027599/0277 |
|
STCF | Information on status: patent grant |
Free format text: PATENTED CASE |
|
CC | Certificate of correction | ||
CC | Certificate of correction | ||
FPAY | Fee payment |
Year of fee payment: 4 |
|
FEPP | Fee payment procedure |
Free format text: MAINTENANCE FEE REMINDER MAILED (ORIGINAL EVENT CODE: REM.); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY |
|
LAPS | Lapse for failure to pay maintenance fees |
Free format text: PATENT EXPIRED FOR FAILURE TO PAY MAINTENANCE FEES (ORIGINAL EVENT CODE: EXP.); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY |
|
STCH | Information on status: patent discontinuation |
Free format text: PATENT EXPIRED DUE TO NONPAYMENT OF MAINTENANCE FEES UNDER 37 CFR 1.362 |
|
FP | Lapsed due to failure to pay maintenance fee |
Effective date: 20211119 |