US20040083878A1 - Launcher closure with bearing retainer and pressure pulse operation - Google Patents

Launcher closure with bearing retainer and pressure pulse operation Download PDF

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Publication number
US20040083878A1
US20040083878A1 US10283174 US28317402A US2004083878A1 US 20040083878 A1 US20040083878 A1 US 20040083878A1 US 10283174 US10283174 US 10283174 US 28317402 A US28317402 A US 28317402A US 2004083878 A1 US2004083878 A1 US 2004083878A1
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Patent type
Prior art keywords
canister
apparatus
closure
outer cover
protrusion
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
US10283174
Inventor
Buddy Paul
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Lockheed Martin Corp
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Lockheed Martin Corp
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

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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41WEAPONS
    • F41FAPPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00Rocket or torpedo launchers
    • F41F3/04Rocket or torpedo launchers for rockets
    • F41F3/077Doors or covers for launching tubes

Abstract

The launcher closure with outer cover is adapted to fit on a canister that contains a missile or the like thereby sealing the inside of the canister from the external environment and allowing the missile to be tested. The closure is designed to move only in the event of a fast rise in pressure caused by launch, but to remain in place in the occurrence of a slow pressure leak. The closure is in a predetermined shape such as a cylinder or the like with one end of the tube containing an O-ring to seal the canister and closure, and the other end of the closure with a surface. The closure, when attached to the canister, seals the inside of the canister from the external environment.

Description

  • [0001] This invention was made with Government support under Contract No. DASG60-00-C-0072 awarded by the Department of Defense. The Government has certain rights in this invention.
  • FIELD OF INVENTION
  • The invention relates to a missile canister and, in particular, to a missile canister having a pressure sensitive cover. [0002]
  • BACKGROUND OF THE INVENTION
  • Weapons such as missiles whether on land or on naval vessels are currently stored in canisters that protect the weapon from the external environment during transportation. The canister that houses the missile is, typically, an elongated tube having at least one opening wherein a cap is placed on the opening effectively sealing the canister. [0003]
  • When the missile, or the like, is launched, several methods have been proposed allowing the missile to egress from the canister. One system has a cap composed of a lightweight material attached to the canister. When the missile is launched and egresses from the canister, the missile strikes the cap thus causing the cap to fracture. However, this cap which permits moisture and other external elements inside the canister may cause the missile to malfunction. Additionally, when the missile strikes the cap, the cap projects debris in a random manner with ensuing damage to the missile. [0004]
  • Another method has a pyrotechnic device within, or near, the cap, wherein the device is operatively coupled to the missile. As the missile is launched, the pyrotechnic device is activated causing the cap to decouple from the canister allowing the missile to egress from the canister unencumbered. Unlike the first method wherein fragments of the cap are projected in a random manner, the entire cap is released from the canister. By fitting a cap with a pyrotechnic device, the missile cannot be periodically tested since the pyrotechnic device activates upon the firing of the missile. [0005]
  • The problem is that no canister and cap allows the missile, or the like, to be tested or to be protected from the external environment. [0006]
  • SUMMARY OF THE INVENTION
  • The present invention features a cap covering an opening of an elongated canister wherein the canister has at least one open end. The cap has an inner cover with two ends. A first end of the inner cover is enclosed and an outer cover has two ends wherein a first end of the outer cover is enclosed. Both the inner cover and outer cover are operatively coupled to each other. Between the first and second end of the outer cover is a surface having at least one hole wherein at least one protrusion projects from the hole. [0007]
  • In another embodiment, the present invention features a cap wherein the cap has a pressure sensitive system and at least one protrusion protruding in a radial direction to the cap. The pressure sensitive system is operatively coupled to at least one protrusion.[0008]
  • BRIEF DESCRIPTION OF THE DRAWINGS
  • The above and other advantages and features of the present invention will be better understood from the following detailed description of the preferred embodiments of the invention, which is provided in connection with the accompanying drawings. The various features of the drawings may not be to scale. Included in the drawing are the following figures: [0009]
  • FIG. 1 is a perspective view of the launcher closure. [0010]
  • FIG. 2 is a perspective view of the outer cover of the launcher closure. [0011]
  • FIG. 3 is a perspective view of the bearing seal that is within the outer cover of the launcher closure. [0012]
  • FIGS. 4[0013] a and 4 b are a view of the launcher closure attached to a canister.
  • DETAILED DESCRIPTION
  • FIG. 1 details the launcher closure [0014] 10 having inner cover 11 and outer cover 21. While FIG. 1 shows that inner cover 11 and outer cover 21 are substantially circular in shape, other shapes can be utilized without departing from the spirit of the present invention. For example, inner cover 11 and outer cover 21 can be in the shape of rectangles known within the art or inner cover 11 and outer cover 21 can be any polygon shape.
  • Inner cover [0015] 11, as shown in FIG. 1, has two ends wherein the first end is substantially enclosed and the second end is, preferably, not enclosed (not shown in FIG. 1). The first end of inner cover 11 has a plurality of holes and the surface that intersects between the two ends is tapered (See FIGS. 4a and 4 b).
  • Outer cover [0016] 21 features a substantially continuous surface having two ends. The first end of the outer cover 21 is substantially enclosed by a second surface and the second end is not enclosed. Preferably, formed, by means well known in the art, to the second end of the outer cover 21 is at least one groove 23 that is substantially the same shape as the opening of a canister (not shown in FIG. 1). While groove 23 is described as being attached to outer cover 21, it would not depart from the spirit of the present invention to have groove 23 and outer cover 21 to be of unitary construction. Groove 23 is substantially continuous and, preferably, an O-ring or the like is placed within thereby effectively sealing the inside of the canister when launcher closure 10 is attached. Additionally, the O-ring protects the contents of the canister from electro magnetic interference.
  • The outer cover [0017] 21 also features a plurality of protrusions 22 substantially perpendicular to the enclosed second surface. The protrusions 22 substantially align with the holes in the first surface of the inner cover 11 allowing both the inner cover 11 and the outer cover 21 to be attached by a conventional means. For example, a hole can be cut at a predetermined place within the protrusions 22 and a cotter pin, or the like, can be used to fasten the inner cover 11 to the outer cover 21.
  • Projecting in the radial direction with respect to outer cover [0018] 21 is a plurality of ball bearings 14, or the like. Preferably, the open end of the canister (not shown in FIG. 1) features a continuous groove within the inside of the canister or the groove can be placed on the outside of the canister. In other embodiments, holes, divots, or the like can be placed at predetermined points around the inside of the canister. The holes or continuous grove allow the ball bearings 14, or the like, to create a frictional attachment permitting the launcher closure 10 to be releasably attached to the open end of an elongated canister. While the launcher closure 10 describes the use of ball bearings 14 that releasably attach it to the open end of an elongated canister, other embodiments can exist. For example, roller bearings, or the like, can project in the radial direction to the outer cover 21 allowing the closure 10 to releasably attach to the open end of an elongated canister.
  • While not shown in FIG. 1, it is to be understood inner cover [0019] 11 fits within outer cover 21 and these elements are operatively coupled together, which is described below.
  • FIG. 2 is a detailed view of outer cover [0020] 21 having protrusions 22, groove 23 and a plurality of holes 24, as substantially described above. Outer cover 21 is a substantially continuous surface, as described above, which fits inside the opening of a canister (not shown). Holes 24 are cut within the surface of outer cover 11 allowing the ball bearings 14, or the like, to project in a radial direction. While not detailed in FIG. 2, holes 24 may be cut at an angle allowing the ball bearings 14, or the like, to retract easily.
  • FIG. 3 is a detailed view of bearing ring [0021] 30. While bearing ring 30 is shown as being substantially circular in shape, it is to be understood that bearing ring 30 can be any shape known within the art and additionally, bearing ring 30 can be substantially the same shape as outer cover 21 since bearing ring 30 fits within inner cover 11, thereby integrating the feature of bearing ring 30 within inner cover 11. Bearing ring 30 is a substantially continuous surface wherein a plurality of spring holes 31 is cut into its surface. It should be appreciated, that spring holes 31 can be cut entirely through bearing ring 30 or that spring holes 31 can be cut partially through the bearing ring 30. Additionally, a plurality of protrusion holes 32 is cut through the surface of the bearing ring 30. Protrusion 22 is aligned and placed through protrusion hole 32 allowing bearing ring 30 to be connected to outer cover 21. The overall width of bearing ring 30, shown in FIG. 3 as Wb, is smaller than the width of outer cover 21. Therefore, when the launcher closure 10 is attached to the open end of a canister, there will be a gap within the closure 10, which is described below.
  • While bearing ring [0022] 30 is described as a separate element that attaches to outer cover 21 by the protrusion 22, it would not depart from the spirit of the present invention to integrate the features of bearing ring 30 within inner cover 11.
  • FIG. 4[0023] a details the launcher closure 10 attached to the open end of canister 41. While launcher closure 10 is shown as being attached to the inside surface of canister 41, the launcher closure 10 may be attached to the outside of the canister 41. Canister 41 is a conventional canister notoriously well known within the art.
  • The launcher closure [0024] 10 features inner cover 11, ball bearing 14, outer cover 21, protrusion 22, groove 23, bearing ring 30, spring cavity 31, canister 41, canister groove 42 and spring 43. As shown in FIG. 4a and discussed above, it is to be understood that bearing ring 30 is placed within inner cover 11 and inner cover 11 and bearing ring 30 are aligned enabling the protrusion 22 to slide through protrusion hole 32 and the hole within inner cover 11 allowing the system to be secured together. While bearing ring 30 and inner cover 11 are described as being two distinct elements, it would not depart from the scope of the present invention to integrate bearing ring 30 within inner cover 11, that is, there may be only one ring and bearings sit directly on it.
  • As shown in FIG. 4[0025] a, it is to be understood that little pressure is being exerted against inner cover 11. Ball bearing 14 is within canister groove 42 since the tapered edge of inner cover 11 is substantially pressing ball bearing 14 into canister groove 42. The edge of inner cover 11 prevents ball bearing 14 from moving thereby creating a frictional connection between the launcher closure 10 and canister 41. Groove 23 contains an O-ring, or the like, effectively sealing the inside of the container from the external environment.
  • Spring [0026] 43 is contained within spring cavity 31 and is placed against the bottom of outer cover 21 and either bearing seal 30. Since there is little pressure being exerted upon inner cover 11, spring 43 is not substantially compressed and a gap 44 is formed. Typically, a missile (not shown) or the like held in canister 41 leaks a toxic missile propellant. During these leaks, the pressure within the canister slowly rises. However, ball bearings 14 will not disengage from the canister groove 42 allowing launcher closure 10 to be attached to canister 41. While the launcher closure 10 is described as utilizing a spring, it would not depart from the spirit of the present invention to use other pressure sensing devices.
  • FIG. 4[0027] b details the launcher closure 10 has a pressure, P, exerted against inner cover 11. The launcher closure 10 is designed to release from the opening of the canister 41 when the missile (not shown) is fired and a pressure pulse is exerted against the inner cover 11. This pressure causes spring 43 to compress against outer cover 21 and bearing seal 30. Inner cover 11 moves in an upwardly direction thereby causing gap 44 shown in FIG. 4a to decrease until inner cover 21 is substantially touching outer cover 21. When there is little, or no, gap 44 between inner cover 11 and outer cover 21, the tapered edge of inner cover 11 is no longer pressing against ball bearing 14 causing ball bearing 14 to retract from its position. Once ball bearing 14 retracts, launcher closure 10 is removed from the opening of canister 41 by the pressure exerted on it.
  • Although illustrated and described herein with reference to certain specific embodiments, the present invention is nevertheless not intended to be limited to the details shown. Rather, various modifications may be made in the details within the scope and range of equivalents of the claims without departing from the spirit of the invention. [0028]

Claims (13)

    What is claimed is:
  1. 1. An apparatus for connecting a cap to a container comprising:
    a cap wherein at least one protrusion is disposed in a radial direction to said cap;
    wherein said cap has a pressure sensitive system; and
    wherein said pressure sensitive system is operatively coupled to said at least one protrusion.
  2. 2. The apparatus, as claimed in claim 1, wherein the cap forms a seal within a canister.
  3. 3. The apparatus, as claimed in claim 1, wherein at least one protrusion is operatively coupled to an outside surface of a canister.
  4. 4. The apparatus, as claimed in claim 1, wherein at least one protrusion is operatively coupled to an inside surface of a canister.
  5. 5. An apparatus which covers an opening of an elongated canister wherein the canister has at least one open end comprising:
    an inner cover having two ends wherein said first end is enclosed;
    an outer cover having two ends wherein said first end is enclosed and in between said first end and said second end is a surface having at least one hole;
    wherein at least one protrusions protrude out from the at least one hole; and
    wherein said inner cover and said outer cover are operatively coupled to each other.
  6. 6. The apparatus, as claimed in claim 5, wherein said outer cover has a recessed groove.
  7. 7. The apparatus, as claimed in claim 6, wherein contained in said recessed groove is an O-ring.
  8. 8. The apparatus, as claimed in claim 5, wherein at least one protrusion is operatively coupled to an outside surface of a canister.
  9. 9. The apparatus, as claimed in claim 5, wherein at least one protrusion is operatively coupled to an inside surface of a canister.
  10. 10. The apparatus, as claimed in claim 5, wherein a spring operatively couples said outer cover to said inner cover.
  11. 11. The apparatus, as claimed in claim 5, wherein the plurality of protrusions is operatively coupled to an inside surface of the first end of the canister.
  12. 12. The apparatus, as claimed in claim 5, wherein at least one protrusion is at least one ball bearing.
  13. 13. The apparatus, as claimed in claim 12, wherein an edge of said inner cover substantially presses against said at least one ball bearing.
US10283174 2002-10-30 2002-10-30 Launcher closure with bearing retainer and pressure pulse operation Abandoned US20040083878A1 (en)

Priority Applications (1)

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US10283174 US20040083878A1 (en) 2002-10-30 2002-10-30 Launcher closure with bearing retainer and pressure pulse operation

Applications Claiming Priority (2)

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US10283174 US20040083878A1 (en) 2002-10-30 2002-10-30 Launcher closure with bearing retainer and pressure pulse operation
US11141165 US7685920B2 (en) 2002-10-30 2005-05-31 Article comprising a canister closure with pressure-pulse release

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US11141165 Continuation-In-Part US7685920B2 (en) 2002-10-30 2005-05-31 Article comprising a canister closure with pressure-pulse release

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US20040083878A1 true true US20040083878A1 (en) 2004-05-06

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060207416A1 (en) * 2005-03-04 2006-09-21 Lockheed Martin Corporation Article comprising a missile canister cover
US20140008497A1 (en) * 2012-07-09 2014-01-09 Hamilton Sundstrand Corporation Appartus and method for preventing gas turbine engine freezing
US20160000263A1 (en) * 2009-02-17 2016-01-07 Douglas Palmer Cooking Pan Apparatus and System with Integral Cooking Liquid Drain, and Method of Use

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2967640A (en) * 1957-02-06 1961-01-10 Flight Refueling Ltd Plugs or closures
US3128009A (en) * 1959-01-28 1964-04-07 Geartight Unions Ltd Closure means for pressure vessels
US4134328A (en) * 1975-08-25 1979-01-16 Aktiebolaget Bofors Device for a missile
US4294376A (en) * 1980-01-03 1981-10-13 Keller Russell D Fuel tank cap
US4567778A (en) * 1984-09-17 1986-02-04 Modular Data Systems, Inc. Coupling assembly for engine dynamometer
US4572011A (en) * 1982-12-08 1986-02-25 Her Majesty The Queen In Right Of Canada, As Represented By The Minister Of National Defence Mechanical thruster
US4575136A (en) * 1984-02-13 1986-03-11 Keller Russell D Tank cap having air actuated latch
US4964659A (en) * 1988-01-11 1990-10-23 Baldwin William C Diaphragm latch mechanism
USRE36557E (en) * 1993-01-14 2000-02-08 Stant Manufacturing Inc. Filler neck closure cap

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2967640A (en) * 1957-02-06 1961-01-10 Flight Refueling Ltd Plugs or closures
US3128009A (en) * 1959-01-28 1964-04-07 Geartight Unions Ltd Closure means for pressure vessels
US4134328A (en) * 1975-08-25 1979-01-16 Aktiebolaget Bofors Device for a missile
US4294376A (en) * 1980-01-03 1981-10-13 Keller Russell D Fuel tank cap
US4572011A (en) * 1982-12-08 1986-02-25 Her Majesty The Queen In Right Of Canada, As Represented By The Minister Of National Defence Mechanical thruster
US4575136A (en) * 1984-02-13 1986-03-11 Keller Russell D Tank cap having air actuated latch
US4567778A (en) * 1984-09-17 1986-02-04 Modular Data Systems, Inc. Coupling assembly for engine dynamometer
US4964659A (en) * 1988-01-11 1990-10-23 Baldwin William C Diaphragm latch mechanism
USRE36557E (en) * 1993-01-14 2000-02-08 Stant Manufacturing Inc. Filler neck closure cap

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060207416A1 (en) * 2005-03-04 2006-09-21 Lockheed Martin Corporation Article comprising a missile canister cover
US8256340B2 (en) 2005-03-04 2012-09-04 Lockheed Martin Corporation Article comprising a missile canister cover
US20160000263A1 (en) * 2009-02-17 2016-01-07 Douglas Palmer Cooking Pan Apparatus and System with Integral Cooking Liquid Drain, and Method of Use
US20140008497A1 (en) * 2012-07-09 2014-01-09 Hamilton Sundstrand Corporation Appartus and method for preventing gas turbine engine freezing
US8777154B2 (en) * 2012-07-09 2014-07-15 United Technologies Corporation Apparatus and method for preventing gas turbine engine freezing

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Date Code Title Description
AS Assignment

Owner name: LOCKHEED MARTIN CORPORATION, MARYLAND

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:PAUL, BUDDY R.;REEL/FRAME:013454/0098

Effective date: 20021028