US20140230636A1 - Dispenser pod - Google Patents
Dispenser pod Download PDFInfo
- Publication number
- US20140230636A1 US20140230636A1 US13/772,717 US201313772717A US2014230636A1 US 20140230636 A1 US20140230636 A1 US 20140230636A1 US 201313772717 A US201313772717 A US 201313772717A US 2014230636 A1 US2014230636 A1 US 2014230636A1
- Authority
- US
- United States
- Prior art keywords
- chassis
- expendable
- chamber
- launch canister
- dispenser
- 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
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D7/00—Arrangements of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft
- B64D7/08—Arrangements of rocket launchers or releasing means
-
- 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
- F41F3/06—Rocket or torpedo launchers for rockets from aircraft
- F41F3/065—Rocket pods, i.e. detachable containers for launching a plurality of rockets
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/02—Dropping, ejecting, or releasing articles
Definitions
- dispenser pods for launching expendables and for use on rocket launchers. These dispenser pods need to maintain the overall size, shape, and mass properties of the rocket launcher. The dispenser pods must also provide electromagnetic isolation, be able to be jettisoned, and withstand the ejection forces generated by a launch canister.
- the present invention is directed to a dispenser pod that meets the needs enumerated above and below.
- the present invention is directed to a dispenser pod, which includes a dispenser chassis with a first chassis end, a second chassis end, and a chassis chamber, and a first chassis end cover for covering the first chassis end, a second chassis end cover for covering the second chassis end, a launch system, and at least one sway brace.
- the first chassis end cover has at least one expendable passageway for accepting an expendable launch canister such that the expendable launch canister is alignable within the chassis chamber.
- the launch system is for expelling the expendable launch canister from the chassis chamber and through the expendable passageway.
- the at least one sway brace is for securing the expendable launch canister within the chassis chamber.
- FIG. 1 is an external perspective view of an embodiment of the dispenser pod
- FIG. 2 is an internal top view of an embodiment of the dispenser pod
- FIG. 3 is an internal side view of an embodiment of the dispenser pod
- FIG. 4 is a cross sectional view of an embodiment of the dispenser pod.
- FIG. 5 is an exploded view of an embodiment of the rail/sway brace configuration.
- the dispenser pod 10 includes a dispenser chassis 100 with a chassis chamber 104 , a first chassis end 105 and a second chassis end 110 , a first chassis end cover 200 for covering the first chassis end 105 , a second chassis end cover 300 for covering the second chassis end 110 , a launch system 400 , and at least one sway brace 500 .
- the first chassis end cover 200 has at least one expendable passageway for accepting an expendable launch canister 215 such that the expendable launch canister 215 enters the chassis chamber 104 .
- FIG. 1 the dispenser pod 10 includes a dispenser chassis 100 with a chassis chamber 104 , a first chassis end 105 and a second chassis end 110 , a first chassis end cover 200 for covering the first chassis end 105 , a second chassis end cover 300 for covering the second chassis end 110 , a launch system 400 , and at least one sway brace 500 .
- the first chassis end cover 200 has at least one expendable passageway for accepting an expendable launch canister 2
- chassis chambers 104 there are two chassis chambers 104 , one for a first expendable launch canister 215 and another for a second expendable launch canister 220 .
- first expendable passageway 205 on the first chassis end cover 200 for accepting the first expendable launch canister 215
- second expendable passageway 210 on the first chassis end cover 200 for accepting the second expendable launch canister 220 .
- the launch system 400 is for expelling an expendable launch canister(s) 215 , 220 from the chassis chamber(s) 104 and through the expendable passageway(s) 205 , 210 .
- the at least one sway brace 500 is for securing the expendable launch canister within the chassis chamber 104 .
- the expendable launch canisters 215 , 220 may be manufactured from fiberglass and can be expendable/disposable. Each expendable launch canister 215 , 220 contains a launch system 400 .
- the launch system 400 includes a cartridge actuated piston, an electrical harness, and a shear screw retainer system used to expel the expendable when actuated.
- any type of launch system that is practicable may be utilized.
- the dispenser pod 10 may also include a dispenser pod heating system 600 .
- the heating system 600 allows the dispenser pod 10 to maintain the expendable launch canisters 215 , 220 between ⁇ 34 degrees C. and 71 degrees C.
- each heating system 600 includes four heating elements 601 and a corresponding heat sink 602 .
- the heating elements 601 and heat sinks 602 sets are disposed on opposite sides of the expendable launch canister, as shown in FIGS. 2 through 4 , and are stacked on top of each other, with the heat sink 602 on top of the heating element 601 .
- each heating element 601 is a wire resistor encased in a thin rectangular silicon rubber mat. Each mat is covered by an extruded aluminum finned heat sink 602 .
- the heating elements 601 produce and conduct heat, while the heat sinks 602 transfer the heat to the surrounding air within the chassis chamber 104 such that a certain temperature is maintained in the chassis chamber 104 .
- the dispenser pod 10 may also include thermostatic control switches, thermostatic safety switches, and relays. These components may communicate with an exterior control panel that may be installed in an aircraft at a sensor station.
- the control panel may include a heater power switch, a panel dimmer, system circuit breakers, a reset switch, and/or a hot/cold indicator.
- the dispenser pod 10 may also include an electrical tray 700 .
- the electrical tray 700 is able to electrically support bus interference wiring and the heating systems 600 .
- each chassis chamber 104 includes a corresponding electrical tray 700 .
- Each electrical tray 700 is designed to support store bus wiring and a heating system 600 .
- Each electrical tray 700 may have a disconnect which allows it to be removed from the dispenser pod 10 for separate assembly and maintenance.
- Each electrical tray 700 may also include a fan 603 disposed near the heating elements 601 such that the fan 603 can circulate the air within the chassis chamber 104 .
- each electrical tray 700 may include the heating elements 601 and the fan 603 integrated within. As seen in FIG. 4 , the electrical tray 700 may be curved.
- a rail assembly 800 is disposed within each chassis chamber 104 .
- the expendable launch canisters ride along the rail assembly 800 such that when actuated each expendable launch canister(s) passes through its corresponding expendable passageway and out the dispenser pod 10 .
- each expendable launch canister 215 , 220 may include a set of yokes 230 .
- the yokes 230 correspond to the rail assembly 800 .
- each sway brace 500 , 505 includes a head 510 , a screw portion 520 , and a pawl 530 .
- the head 510 is disposed outside the dispenser chassis 100 , while the screw portion 520 passes through the dispenser chamber 100 , and the chassis chamber 104 , then aligned with the rail assembly 800 such that end of the screw portion 520 corresponds to the pawl 530 which presses on the yoke 230 , such that the expendable canisters can be more tightly or less tightly secured within the chamber chassis 104 .
Abstract
Description
- The invention described herein may be manufactured and used by or for the Government of the United States of America for governmental purposes without payment of any royalties thereon or therefore.
- United States Navy aircraft often utilize dispenser pods for launching expendables and for use on rocket launchers. These dispenser pods need to maintain the overall size, shape, and mass properties of the rocket launcher. The dispenser pods must also provide electromagnetic isolation, be able to be jettisoned, and withstand the ejection forces generated by a launch canister.
- The present invention is directed to a dispenser pod that meets the needs enumerated above and below.
- The present invention is directed to a dispenser pod, which includes a dispenser chassis with a first chassis end, a second chassis end, and a chassis chamber, and a first chassis end cover for covering the first chassis end, a second chassis end cover for covering the second chassis end, a launch system, and at least one sway brace. The first chassis end cover has at least one expendable passageway for accepting an expendable launch canister such that the expendable launch canister is alignable within the chassis chamber. The launch system is for expelling the expendable launch canister from the chassis chamber and through the expendable passageway. The at least one sway brace is for securing the expendable launch canister within the chassis chamber.
- It is a feature of the present invention to provide a dispenser pod that maintains overall size, shape, and mass properties of a particular rocket launcher.
- It is a feature of the present invention to provide a dispenser pod that provides electromagnetic isolation of greater than 29 db between its interior and exterior.
- It is a feature of the present invention to provide a dispenser pod that maintains launch canisters between −34 and 71 degrees Celsius.
- It is a feature of the present invention to provide a dispenser pod that can withstand the ejection forces generated by a launch canister and is able to be jettisoned.
- These and other features, aspects and advantages of the present invention will become better understood with reference to the following description and appended claims, and accompanying drawings wherein:
-
FIG. 1 is an external perspective view of an embodiment of the dispenser pod; -
FIG. 2 is an internal top view of an embodiment of the dispenser pod; -
FIG. 3 is an internal side view of an embodiment of the dispenser pod; -
FIG. 4 is a cross sectional view of an embodiment of the dispenser pod; and -
FIG. 5 is an exploded view of an embodiment of the rail/sway brace configuration. - The preferred embodiments of the present invention are illustrated by way of example below and in
FIGS. 1-5 . As shown inFIGS. 1-4 , thedispenser pod 10 includes adispenser chassis 100 with achassis chamber 104, afirst chassis end 105 and asecond chassis end 110, a firstchassis end cover 200 for covering thefirst chassis end 105, a secondchassis end cover 300 for covering thesecond chassis end 110, alaunch system 400, and at least onesway brace 500. The firstchassis end cover 200 has at least one expendable passageway for accepting anexpendable launch canister 215 such that theexpendable launch canister 215 enters thechassis chamber 104. In the preferred embodiment, as shown inFIG. 3 , there are twochassis chambers 104, one for a firstexpendable launch canister 215 and another for a secondexpendable launch canister 220. Correspondingly, there is a firstexpendable passageway 205 on the firstchassis end cover 200 for accepting the firstexpendable launch canister 215 and a secondexpendable passageway 210 on the firstchassis end cover 200 for accepting the secondexpendable launch canister 220. Thelaunch system 400 is for expelling an expendable launch canister(s) 215, 220 from the chassis chamber(s) 104 and through the expendable passageway(s) 205, 210. The at least onesway brace 500 is for securing the expendable launch canister within thechassis chamber 104. In the preferred embodiment, there is are twofirst sway braces 505 and twosecond sway braces 500, such that thefirst sway braces 505 correspond to the firstexpendable launch canister 215, and thesecond sway braces 500 correspond to the secondexpendable launch canister 220. - In the description of the present invention, the invention will be discussed in a military environment; however, this invention can be utilized for any type of application that requires use of a dispenser pod.
- In the preferred embodiment, the
expendable launch canisters expendable launch canister launch system 400. In the preferred embodiment, thelaunch system 400 includes a cartridge actuated piston, an electrical harness, and a shear screw retainer system used to expel the expendable when actuated. However, any type of launch system that is practicable may be utilized. - The dispenser pod 10 may also include a dispenser
pod heating system 600. Theheating system 600 allows the dispenser pod 10 to maintain theexpendable launch canisters FIGS. 2 , 3, and 4, within eachchassis chamber 104 there is aheating system 600 corresponding to eachexpendable launch canister heating system 600 includes fourheating elements 601 and acorresponding heat sink 602. Theheating elements 601 andheat sinks 602 sets are disposed on opposite sides of the expendable launch canister, as shown inFIGS. 2 through 4 , and are stacked on top of each other, with theheat sink 602 on top of theheating element 601. In the preferred embodiment, eachheating element 601 is a wire resistor encased in a thin rectangular silicon rubber mat. Each mat is covered by an extruded aluminum finnedheat sink 602. Theheating elements 601 produce and conduct heat, while theheat sinks 602 transfer the heat to the surrounding air within thechassis chamber 104 such that a certain temperature is maintained in thechassis chamber 104. - The
dispenser pod 10 may also include thermostatic control switches, thermostatic safety switches, and relays. These components may communicate with an exterior control panel that may be installed in an aircraft at a sensor station. The control panel may include a heater power switch, a panel dimmer, system circuit breakers, a reset switch, and/or a hot/cold indicator. - As shown in
FIGS. 2 , 3 and 4, thedispenser pod 10 may also include anelectrical tray 700. Theelectrical tray 700 is able to electrically support bus interference wiring and theheating systems 600. In the preferred embodiment, eachchassis chamber 104 includes a correspondingelectrical tray 700. Eachelectrical tray 700 is designed to support store bus wiring and aheating system 600. Eachelectrical tray 700 may have a disconnect which allows it to be removed from the dispenser pod 10 for separate assembly and maintenance. Eachelectrical tray 700 may also include afan 603 disposed near theheating elements 601 such that thefan 603 can circulate the air within thechassis chamber 104. In the preferred embodiment, eachelectrical tray 700 may include theheating elements 601 and thefan 603 integrated within. As seen inFIG. 4 , theelectrical tray 700 may be curved. - In the preferred embodiment, a
rail assembly 800 is disposed within eachchassis chamber 104. The expendable launch canisters ride along therail assembly 800 such that when actuated each expendable launch canister(s) passes through its corresponding expendable passageway and out the dispenser pod 10. As seen inFIGS. 4 and 5 , eachexpendable launch canister yokes 230. Theyokes 230 correspond to therail assembly 800. As seen inFIG. 5 , eachsway brace head 510, ascrew portion 520, and apawl 530. Thehead 510 is disposed outside thedispenser chassis 100, while thescrew portion 520 passes through thedispenser chamber 100, and thechassis chamber 104, then aligned with therail assembly 800 such that end of thescrew portion 520 corresponds to thepawl 530 which presses on theyoke 230, such that the expendable canisters can be more tightly or less tightly secured within thechamber chassis 104. - When introducing elements of the present invention or the preferred embodiment(s) thereof, the articles “a,” “an,” “the,” and “said” are intended to mean there are one or more of the elements. The terms “comprising,” “including,” and “having” are intended to be inclusive and mean that there may be additional elements other than the listed elements.
- Although the present invention has been described in considerable detail with reference to certain preferred embodiments thereof, other embodiments are possible. Therefore, the spirit and scope of the appended claims should not be limited to the description of the preferred embodiment(s) contained herein.
Claims (4)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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US13/772,717 US8789453B1 (en) | 2013-02-21 | 2013-02-21 | Dispenser pod |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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US13/772,717 US8789453B1 (en) | 2013-02-21 | 2013-02-21 | Dispenser pod |
Publications (2)
Publication Number | Publication Date |
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US8789453B1 US8789453B1 (en) | 2014-07-29 |
US20140230636A1 true US20140230636A1 (en) | 2014-08-21 |
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US13/772,717 Expired - Fee Related US8789453B1 (en) | 2013-02-21 | 2013-02-21 | Dispenser pod |
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Citations (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2458476A (en) * | 1946-01-04 | 1949-01-04 | Charles C Lauritsen | Rocket launcher |
US2971731A (en) * | 1955-03-10 | 1961-02-14 | Graw Messgerate G M B H Dr | Ejection container for radio probes |
US3106132A (en) * | 1961-03-06 | 1963-10-08 | Earl E Biermann | Launcher |
US3216322A (en) * | 1964-03-09 | 1965-11-09 | Maurice J Wenger | Bomb rack adapter |
US3295410A (en) * | 1964-10-29 | 1967-01-03 | William R Edwards | Retro eject bomb rack |
US3315565A (en) * | 1965-01-15 | 1967-04-25 | Chromcraft Corp | Air-borne rocket launchers |
US3412640A (en) * | 1967-05-19 | 1968-11-26 | Alsco Inc | Rocket launcher |
US3504593A (en) * | 1968-10-25 | 1970-04-07 | Us Army | Airborne rocket launcher |
US3719120A (en) * | 1970-06-29 | 1973-03-06 | Us Navy | Rocket launching system |
US3754497A (en) * | 1970-08-06 | 1973-08-28 | Sarmac Sa | Transporting and firing chest for self-propelled projectiles |
US3769876A (en) * | 1972-08-02 | 1973-11-06 | Us Navy | Missile launching canister |
US3893366A (en) * | 1973-10-29 | 1975-07-08 | Us Navy | Missile launcher guide assembly |
US3988961A (en) * | 1975-08-08 | 1976-11-02 | The United States Of America As Represented By The Secretary Of The Army | Integrated rocket shipping container and launcher |
US4429611A (en) * | 1982-01-29 | 1984-02-07 | General Dynamics, Pomona Division | Airborne missile launcher |
US5400689A (en) * | 1993-02-16 | 1995-03-28 | Deutsche Aerospace | Device for storing a missle in a launcher tube |
US6227096B1 (en) * | 1999-06-22 | 2001-05-08 | The Boeing Company | Universal warhead adapter, and missile and method incorporating same |
US6655254B1 (en) * | 2001-07-11 | 2003-12-02 | Raytheon Company | Multiple airborne missile launcher |
-
2013
- 2013-02-21 US US13/772,717 patent/US8789453B1/en not_active Expired - Fee Related
Patent Citations (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2458476A (en) * | 1946-01-04 | 1949-01-04 | Charles C Lauritsen | Rocket launcher |
US2971731A (en) * | 1955-03-10 | 1961-02-14 | Graw Messgerate G M B H Dr | Ejection container for radio probes |
US3106132A (en) * | 1961-03-06 | 1963-10-08 | Earl E Biermann | Launcher |
US3216322A (en) * | 1964-03-09 | 1965-11-09 | Maurice J Wenger | Bomb rack adapter |
US3295410A (en) * | 1964-10-29 | 1967-01-03 | William R Edwards | Retro eject bomb rack |
US3315565A (en) * | 1965-01-15 | 1967-04-25 | Chromcraft Corp | Air-borne rocket launchers |
US3412640A (en) * | 1967-05-19 | 1968-11-26 | Alsco Inc | Rocket launcher |
US3504593A (en) * | 1968-10-25 | 1970-04-07 | Us Army | Airborne rocket launcher |
US3719120A (en) * | 1970-06-29 | 1973-03-06 | Us Navy | Rocket launching system |
US3754497A (en) * | 1970-08-06 | 1973-08-28 | Sarmac Sa | Transporting and firing chest for self-propelled projectiles |
US3769876A (en) * | 1972-08-02 | 1973-11-06 | Us Navy | Missile launching canister |
US3893366A (en) * | 1973-10-29 | 1975-07-08 | Us Navy | Missile launcher guide assembly |
US3988961A (en) * | 1975-08-08 | 1976-11-02 | The United States Of America As Represented By The Secretary Of The Army | Integrated rocket shipping container and launcher |
US4429611A (en) * | 1982-01-29 | 1984-02-07 | General Dynamics, Pomona Division | Airborne missile launcher |
US5400689A (en) * | 1993-02-16 | 1995-03-28 | Deutsche Aerospace | Device for storing a missle in a launcher tube |
US6227096B1 (en) * | 1999-06-22 | 2001-05-08 | The Boeing Company | Universal warhead adapter, and missile and method incorporating same |
US6655254B1 (en) * | 2001-07-11 | 2003-12-02 | Raytheon Company | Multiple airborne missile launcher |
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US8789453B1 (en) | 2014-07-29 |
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AS | Assignment |
Owner name: DEPARTMENT OF THE NAVY (NAWCAD), MARYLAND Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:MORRISON, MATTHEW;SCHILDER, ROBERT;REEL/FRAME:029849/0155 Effective date: 20130219 |
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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 |
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STCH | Information on status: patent discontinuation |
Free format text: PATENT EXPIRED DUE TO NONPAYMENT OF MAINTENANCE FEES UNDER 37 CFR 1.362 |
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FP | Lapsed due to failure to pay maintenance fee |
Effective date: 20180729 |