WO2023137255A1 - Effecteur ayant une cellule de transformation et procédé - Google Patents

Effecteur ayant une cellule de transformation et procédé Download PDF

Info

Publication number
WO2023137255A1
WO2023137255A1 PCT/US2023/060284 US2023060284W WO2023137255A1 WO 2023137255 A1 WO2023137255 A1 WO 2023137255A1 US 2023060284 W US2023060284 W US 2023060284W WO 2023137255 A1 WO2023137255 A1 WO 2023137255A1
Authority
WO
WIPO (PCT)
Prior art keywords
effector
center body
outer body
center
deployed position
Prior art date
Application number
PCT/US2023/060284
Other languages
English (en)
Inventor
Paul A. Merems
Shawn Patrick Burke
Original Assignee
Raytheon Company
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
Priority claimed from US17/842,200 external-priority patent/US11796291B2/en
Application filed by Raytheon Company filed Critical Raytheon Company
Publication of WO2023137255A1 publication Critical patent/WO2023137255A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B5/00—Cartridge ammunition, e.g. separately-loaded propellant charges
    • F42B5/02—Cartridges, i.e. cases with charge and missile
    • F42B5/10—Cartridges, i.e. cases with charge and missile with self-propelled bullet
    • F42B5/105—Cartridges, i.e. cases with charge and missile with self-propelled bullet propelled by two propulsive charges, the rearwardly situated one being separated from the rest of the projectile during flight or in the barrel; Projectiles with self-ejecting cartridge cases
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B30/00—Projectiles or missiles, not otherwise provided for, characterised by the ammunition class or type, e.g. by the launching apparatus or weapon used
    • F42B30/003—Closures or baseplates therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B5/00—Cartridge ammunition, e.g. separately-loaded propellant charges
    • F42B5/02—Cartridges, i.e. cases with charge and missile
    • F42B5/045—Cartridges, i.e. cases with charge and missile of telescopic type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B5/00—Cartridge ammunition, e.g. separately-loaded propellant charges
    • F42B5/02—Cartridges, i.e. cases with charge and missile
    • F42B5/10—Cartridges, i.e. cases with charge and missile with self-propelled bullet
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means

Definitions

  • the disclosure relates to an effector having an extendable range and a method of extending the range of an effector.
  • Various applications use effectors.
  • Exemplary applications include military applications that use effectors, such as projectiles or missiles.
  • Other non-military applications or commercial applications may also use effectors.
  • Extending the range of an effector may be challenging.
  • One prior attempt to increase the effector range includes increasing the powder charge.
  • increasing the powder charge may be limited due to excessive setback acceleration g’s and a maximum allowable launcher pressure.
  • Another prior attempt to increase the range of an effector includes adding a rocket motor, wings, and ramjet to the system.
  • a ramjet is advantageous in adding a propulsion system to the effector, but conventional ramjets place the fuel behind subsystems of the effector, e.g., Seeker, Guidance Electronics Unit (GEU), Control Actuation System (CAS), Warhead, etc., and the effector may also be limited in length due to launch constraints (host airframe, gun systems, launcher, and loading equipment requirements). Additionally, ramjet ducting requires additional volume in the effector which may provide packaging limitations.
  • the present application provides an effector having an extendible range.
  • the effector has a telescoping airframe formed of an axially translatable center body that is movable from a stowed position, in which the center body is stowed within an outer body of the effector, to a deployed position in which the center body extends out of the outer body to extend the axial length of the effector.
  • the subsystems of the effector are contained in the center body.
  • the effector further includes a ramjet assembly. The movement of the center body exposes radially positioned ramjet fuel in the outer body to provide additional fuel and thus propulsion for the effector, such that the range for the effector is increased.
  • an effector has a telescoping airframe to extend an axial length of the effector.
  • an effector has an axially translatable center body that is movable relative to an outer body.
  • an effector has an axially translatable center body that is movable relative to an outer body and contains a plurality of subsystems of the effector.
  • an effector has an axially translatable center body that is movable to expose radially positioned ramjet fuel.
  • an effector has a ramjet assembly and a telescoping airframe that is movable for fluid communication with a ramjet fuel chamber and a ramjet inlet for additional fuel for the effector.
  • an effector has an axially translatable center body that is movable relative to an outer body and includes deployable control surfaces in addition to deployable fins of the outer body.
  • an effector has an outer body and an axially translatable center body that each include mechanical locking interfaces.
  • an effector has an outer body and an axially translatable center body that have conical locking interfaces.
  • a gun-launched effector assembly includes a launcher and an effector that is fired from the launcher, the effector having an outer body and a center body that is movable from a stowed position, in which the outer body is stowed within the outer body, to a deployed position, in which the center body is moved out of the outer body to extend an axial length of the effector, the center body moving from the stowed position to the deployed position after an exit of the effector from the launcher.
  • a method of increasing a range of an effector includes axially translating a center body relative to an outer body of the effector to extend an axial length of the effector.
  • a method of increasing a range of an effector includes axially translating a center body relative to an outer body of the effector to expose radially positioned ramjet fuel that provides additional fuel for a ramjet assembly.
  • an effector includes: an outer body; and a center body movable from a stowed position, in which the center body is stowed in the outer body, to a deployed position, in which the center body extends out of the outer body to extend an axial length of the effector.
  • the center body is axially translatable relative to the outer body.
  • the effector includes a ramjet assembly.
  • the outer body contains a ramjet fuel chamber that is opened when the center body is moved to the deployed position.
  • the ramjet fuel chamber is formed as an axially extending chamber that is radially spaced from a longitudinal axis of the effector.
  • the center body and the outer structure have corresponding interfaces that engage when the center body is moved to the deployed position to lock the center body and the outer structure together.
  • the corresponding interfaces are formed as conical interfaces that have a tapering shape in an axial direction.
  • the conical interfaces are circumferentially spaced about a longitudinal axis of the effector.
  • the conical interfaces of the outer body are arranged at a forward end of the outer body and the conical interfaces of the center body are arranged at an aft end of the center body.
  • the effector further includes a ramjet inlet having ducting.
  • the ducting is arranged proximate an aft end of the center body when the center body is moved to the deployed position.
  • an aft portion of the center body is arranged radially inwardly relative to the ramjet ducting and includes locking interfaces that engage with corresponding locking interfaces of the outer body when the center body is moved to the deployed position.
  • the aft portion of the center body is surrounded by the outer body when the center body is in the deployed position.
  • the ramjet inlet is in fluid communication with a ramjet fuel chamber arranged in the outer body when the center body is in the deployed position.
  • the center body includes deployable control surfaces that are deployed when the center body moves to the deployed position.
  • the center body includes a plurality of subsystems of the effector.
  • the center body includes at least one of a warhead subsystem, a seeker subsystem, a Guidance Electronics Unit (GEU), or a Control Actuation System (CAS).
  • a warhead subsystem e.g., a warhead subsystem
  • a seeker subsystem e.g., a Guidance Electronics Unit (GEU)
  • GEU Guidance Electronics Unit
  • CAS Control Actuation System
  • the center body moves in a forward direction relative to a direction of travel of the effector.
  • an axial length of the center body is more than half of an axial length of the outer body.
  • the effector further includes a pusher plate that is released from an aft end of the effector after the center body moves to the deployed position.
  • the effector includes fins that are arranged at the aft end of the effector and are deployed after the pusher plate is released.
  • a gun-launched effector assembly includes an effector according to any paragraph(s) of this summary.
  • a gun-launched effector assembly includes: a launcher; and an effector that is fired from the launcher, the effector having an outer body and a center body that is movable from a stowed position, in which the outer body is stowed in the outer body, to a deployed position, in which the center body is moved out of the outer body to extend an axial length of the effector, the center body moving from the stowed position to the deployed position after a muzzle exit of the effector from the launcher.
  • the effector includes a pusher plate that is released after the center body moves to the deployed position.
  • the effector includes fins that are deployed after the pusher plate is released.
  • a method of increasing a range of an effector includes axially translating a center body relative to an outer body of the effector to extend an axial length of the effector.
  • the method further includes moving the center body after exit of the effector from a launcher.
  • the method further includes opening a ramjet fuel chamber for fluid communication with a ramjet duct of the effector via movement of the center body relative to the outer body.
  • the method further includes mechanically locking the center body and the outer body after the center body has moved outwardly from the center body to a deployed position.
  • the method further includes deploying control surfaces of the center body after the center body has moved outwardly from the center body to a deployed position.
  • the method further includes releasing a pusher plate of the effector after the center body has moved outwardly from the center body to a deployed position.
  • the method further includes deploying fins of the effector after the pusher plate is released.
  • an effector includes a telescoping airframe configured to extend an axial length of the effector.
  • an effector includes a ramjet assembly and a telescoping airframe configured to expose a ramjet fuel chamber.
  • an effector includes a telescoping airframe including an outer body and an axially translatable center body, wherein the axially translatable center body has integrally formed locking surfaces that are engageable with corresponding locking surfaces that are integrally formed on the outer body.
  • Fig. 1 shows a cross-sectional view of an effector having an outer body and an axially translatable center body that is in a stowed position in which the center body is stowed within the outer body.
  • Fig. 2 shows a forward view of a ramjet inlet for the effector of Fig. 1 .
  • Fig. 3 shows the effector of Fig. 1 having the center body in a deployed position in which the center body has moved out of the outer body to extend an axial length of the effector.
  • Fig. 4 shows an oblique view of the outer body and the center body of Fig. 1.
  • Fig. 5 shows an exploded oblique view of the outer body and the center body of Fig. 1 .
  • Fig. 6A shows a first step in a launch sequence of the effector of Fig. 1 from a launcher (in this case a gun).
  • a launcher in this case a gun
  • Fig. 6B shows a second step in the launch sequence.
  • Fig. 6C shows a third step in the launch sequence.
  • Fig. 6D shows a fourth step in the launch sequence.
  • effector and effector deployment systems such as in tube-launched or gun-launched projectiles or missiles and launcher.
  • the effector and method of deploying the center body described herein may be suitable for use in military applications.
  • Non-lethal applications and non-military applications may also be suitable, such as surveillance systems.
  • the effector is suitable for deployment in any environment and may be carried on any suitable platform.
  • Exemplary environments include air, space, and sea
  • exemplary platforms include aircraft, hypersonic or supersonic vehicles, land vehicles, or watercraft.
  • an effector 20 has an outer body 22 and a center body 24.
  • Each of the outer body 22 and the center body 24 may be formed as an elongated cylindrical body.
  • the center body 24 is movable from a stowed position in which the center body 24 is stowed in the outer body 22, as shown in Fig. 1 , to a deployed position, in which the center body 24 is moved out of the outer body 22 to extend an axial length of the effector 20.
  • the center body 24 may be axially translatable relative to the outer body 22 and movable in a forward direction relative to the direction of travel of the effector 20.
  • the movement of the center body 24 relative to the outer body 24 may provide a telescoping-type arrangement for the airframe of the effector 20.
  • the effector 20 may include a ramjet assembly 26.
  • the ramjet assembly 26 may be defined by a ramjet inlet formed in the outer body 24 that receives airflow during flight of the effector 20.
  • the center body 24 may include any number of subsystems of the effector 20.
  • the center body 24 may include at least one of a warhead subsystem 28, a seeker subsystem, a Guidance Electronics Unit (GEU), or a Control Actuation System (CAS).
  • GEU Guidance Electronics Unit
  • CAS Control Actuation System
  • all of the subsystems of the effector 20 may be contained in the center body 24, such that all of the subsystems are shifted with the center body 24.
  • the effector 20 may include a rocket motor such that the effector 20 is rocket assisted.
  • Many other subsystems may be suitable and the subsystems implemented in the effector 20 may be dependent on the application.
  • the translating center body 24 is stowed within the defined length of the effector 20.
  • the center body 24 is translated forward within the outer body 22 immediately after a muzzle exit of the effector 20 from a gun to extend the axial length of the effector 20.
  • the movement of the center body 24 also exposes or opens a radially positioned ramjet fuel chamber to enable additional fuel to be provided to a ramjet of the effector 20.
  • a range of the effector 20 is extended using a telescoping or morphing airframe that is able to fit within the existing packaging requirements of the effector 20.
  • the translating center body configuration increases the fuel gain mass and length by packaging fuel where the air ducts of traditional systems would be located, which significantly increases the effector range.
  • the outer diameter of the center body 24 may match an inner diameter of the outer body 22 such that the center body 24 is centered in the outer body 22 as the center body 24 moves through the outer body 22.
  • the center body 24 may include locating or guide features 29 formed on an outer periphery of the effector 20.
  • the locating or guide features 29 are engageable with a corresponding feature of the outer body 22 to enable movement of the center body 24 along the outer body 22.
  • the locating or guide features may include any suitable tabs, ribs, protrusions, rails, guides, grooves, etc.
  • the locating or guide features may have any suitable shape.
  • An axial length of the center body 24 may be more than half of an axial length of the outer body 22.
  • the axial length of the center body 24 is less than the entire axial length of the outer body 22.
  • An entire axial length of the center body 24 may be encompassed and surrounded by the outer body 22 when the center body 24 is in the stowed position shown in Fig. 1 .
  • the center body 24 may include a plurality of control surfaces 30 that are disposed on an outer periphery of the center body 24 and retained in a folded position against the center body 24 when the center body 24 is in the stowed position.
  • the center body 24 is axially translatable to the deployed position shown in Fig. 3 when the effector 20 is fired from a launcher.
  • the center body 24 moves out of the outer body 22 via a center body deployment mechanism via propellent within the center body 24, gas pressure generated by external burning propellent, explosive charges, etc.
  • the outer body 22 may also contain a ramjet fuel chamber 32 that is opened by the axial translation of the center body 24.
  • the ramjet fuel chamber 32 may be formed as an axially extending chamber that is radially spaced from a longitudinal axis of the effector 20.
  • Fig. 2 shows a forward view of the effector 20 and a ramjet inlet 34 having ducting 36 that is defined by the outer body 22 and in fluid communication with the ramjet fuel chamber 32 when the ramjet fuel chamber 32 is opened by the axial translation of the center body 24.
  • the movement of the center body 24 exposes the radially positioned ramjet fuel in the outer body 22, such that the air entering the ramjet inlet 34 may be heated by combusting the air with the fuel for additional fuel and thus propulsion of the effector 20.
  • the ramjet inlet 34 may include at least one duct. For example, three ducts that are symmetrically disposed about a radially outer circumference of the ramjet inlet 34 may be suitable.
  • the ramjet ducting 36 may be arranged proximate an aft portion 39 of the center body 24 and/or radially surround the aft portion 39 when the center body 24 is in the deployed position.
  • the outer body 22 may surround the aft portion 39 of the center body 24 when the center body 24 is in the deployed position.
  • the effector 20 may also include a pusher plate 40 that is arranged at an aft end of the effector 20 for gun launched applications.
  • the pusher plate 40 is configured to absorb force associated with the initial movement of the effector 20 in the gun barrel by the expanding gases and may push the effector 20 out of the barrel. After the center body 24 is moved to the deployed position, the pusher plate 40 is released from the effector 20 which consequently enables aft fins 41 to deploy as shown in Fig. 2.
  • the pusher plate subsystem may be configured to apply a force that translates the center body 24 after launch.
  • the center body 24 and the outer body 22 may have any suitable corresponding mechanical locking features to lock the center body 24 and the outer body 22 together after the center body 24 reaches the deployed position.
  • the outer body 22 and the center body 24 have corresponding interfaces 42, 44 that engage when the center body 24 moves.
  • the corresponding interfaces 42, 44 may be formed as conical interfaces that taper in an axial direction.
  • the interfaces 42, 44 may be integrally formed as one piece with the corresponding body.
  • any number of interfaces 42, 44 may be provided and the interfaces 42, 44 may be circumferentially spaced about a longitudinal axis of the effector 20.
  • the conical interfaces of the outer body 42 may be arranged at a forward end of the outer body 42 and the conical interfaces 44 of the center body 24 may be arranged at an aft end of the center body 24.
  • the conical shape provides a play-free, self-locking, centering joint, such that when the center body 24 is extended, the center body 24 remains centered relative to the outer body 22.
  • Other shapes for the interfaces may also be suitable.
  • the effector 20 may be launched from a barrel 46 of a gun-launched effector assembly by a propellant.
  • Fig. 6A shows the effector 20 emerging from the barrel 46.
  • the center body 24 may be translated in the forward direction out from the outer body 22 as the effector 20 also moves in the forward direction.
  • Fig. 6C after the center body 24 is moved to the deployed position out of the outer body 22, the pusher plate 40 may be released from the effector 20 in the rearward direction and discarded from the effector 20. The movement of the pusher plate 40 may also enable the fins 41 of the effector 20 to deploy for flight of the effector 20, as shown in Fig. 6D.
  • the effector according to the present application is advantageous as compared with a conventional ramjet effector that does not have an extendable axial length or extended range.
  • the effector according to the present application has an increased fuel length and weight as compared with known ramjets.
  • the effector according to the present application may be formed of any suitable materials and formed by any suitable manufacturing and assembly methods.
  • the disclosure includes certain preferred embodiment or embodiments, it is obvious that equivalent alterations and modifications will occur to others skilled in the art upon the reading and understanding of this specification and the annexed drawings.
  • the terms (including a reference to a "means") used to describe such elements are intended to correspond, unless otherwise indicated, to any element which performs the specified function of the described element (i.e., that is functionally equivalent), even though not structurally equivalent to the disclosed structure which performs the function in the herein illustrated exemplary embodiment or embodiments.
  • a particular feature of the disclosure may have been described above with respect to only one or more of several illustrated embodiments, such feature may be combined with one or more other features of the other embodiments, as may be desired and advantageous for any given or particular application.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Toys (AREA)

Abstract

Effecteur ayant une plage extensible et procédé pour étendre la plage d'un effecteur consistant à utiliser un corps central pouvant se déplacer axialement qui est mobile d'une position rangée, dans laquelle le corps central est rangé dans un corps externe de l'effecteur, à une position déployée dans laquelle le corps central s'étend hors du corps externe pour étendre la longueur axiale de l'effecteur. L'effecteur comprend un ensemble statoréacteur et les sous-systèmes de l'effecteur sont contenus dans le corps central. Le mouvement du corps central fait apparaître un carburant de statoréacteur positionné radialement dans le corps externe, de telle sorte que l'air entrant dans l'entrée de statoréacteur peut être chauffé par combustion de l'air avec le carburant à des fins de carburant supplémentaire et de propulsion de l'effecteur.
PCT/US2023/060284 2022-01-11 2023-01-09 Effecteur ayant une cellule de transformation et procédé WO2023137255A1 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US202263298362P 2022-01-11 2022-01-11
US63/298,362 2022-01-11
US17/842,200 US11796291B2 (en) 2022-01-11 2022-06-16 Effector having morphing airframe and method
US17/842,200 2022-06-16

Publications (1)

Publication Number Publication Date
WO2023137255A1 true WO2023137255A1 (fr) 2023-07-20

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2023/060284 WO2023137255A1 (fr) 2022-01-11 2023-01-09 Effecteur ayant une cellule de transformation et procédé

Country Status (1)

Country Link
WO (1) WO2023137255A1 (fr)

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2935946A (en) * 1957-07-19 1960-05-10 Elia A Gallo Telescoping ram jet construction
EP0151676B1 (fr) * 1983-08-03 1990-06-13 Rheinmetall GmbH Projectile comprenant une partie propulsion et une partie charge utile
US9823053B1 (en) * 2016-08-29 2017-11-21 The Boeing Company Solid-fuel ramjet ammunition

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2935946A (en) * 1957-07-19 1960-05-10 Elia A Gallo Telescoping ram jet construction
EP0151676B1 (fr) * 1983-08-03 1990-06-13 Rheinmetall GmbH Projectile comprenant une partie propulsion et une partie charge utile
US9823053B1 (en) * 2016-08-29 2017-11-21 The Boeing Company Solid-fuel ramjet ammunition

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