Longitudinally Rotating Patents (Class 244/3.28)
  • Patent number: 11365956
    Abstract: A pivot connection part for a flying machine includes an inner body, an outer body radially surrounding the inner body, and a set of connection elements configured to connect the inner body to the outer body. Breaking the connection elements detaches the inner body from the outer body. A first blocking assembly having a cam and a stop is configured to block relative rotation between the inner and outer bodies in a first rotational direction. A second blocking assembly having a pawl and a resilient stop blade is configured to block relative rotation between the inner and outer bodies in a second rotational direction.
    Type: Grant
    Filed: June 6, 2018
    Date of Patent: June 21, 2022
    Assignee: MBDA France
    Inventor: Clyde Laheyne
  • Patent number: 11353300
    Abstract: A projectile and deployment method ensures successful deployment of the projectile regardless of an external environment. Contacting engagement is maintained between a piston and deployable fins as the fins rotate from a folded position to a deployed position. The fins are pushed by the piston to rotate into a deployed position in which the fins are locked before the piston is able to eject from the assembly. Using the engaging tabs between the fins and the piston, and a modular pressure reservoir, the piston continues to push on the fins at least until the fins are deployed and locked. After locking, pressure in the projectile is equalized and the piston is launched off of the pressure reservoir. If the fins are not immediately deployed and locked, the piston will continue to push on the fins until the external environment enables full deployment or until the pressure is equalized.
    Type: Grant
    Filed: April 6, 2020
    Date of Patent: June 7, 2022
    Assignee: Raytheon Company
    Inventor: Timothy A. Murphy
  • Patent number: 11340052
    Abstract: A wing deployment initiator initiates penetration of frangible cover seals by missile guidance wings during wing deployment. The initiator includes a central, rotatable hub extending above a baseplate. Lobes extending from the hub prevent rotation of associated flippers by torsion springs. Locking and deployment tabs extend from the flippers into corresponding notches in proximal ends of the wings. The locking tabs prevent deployment of the wings until the central hub is rotated, whereupon the flippers are released, causing the deployment tabs to transfer deployment energy from the torsion springs to the wings. The hub can be rotated by an electrical actuator such as a solenoid or motor, or the lobes can be rotationally offset so that feedback pressure from the flippers applies a torque to the hub, and missile electronics can cause a wing control surface to inhibit and then enable hub rotation via a rocker link.
    Type: Grant
    Filed: August 27, 2019
    Date of Patent: May 24, 2022
    Assignee: BAE Systems Information and Electronic Systems Integration Inc.
    Inventor: Kenneth D. Cleveland
  • Patent number: 11313656
    Abstract: A fin deployment mechanism for a projectile to release the fins laterally or radially. This pop-out type of mechanism therefore avoids need for a sabot for projectile launching purposes. By avoiding the weight and space usage of a sabot, there can be increased length and volume for the warhead and projectile, at the same weight burden.
    Type: Grant
    Filed: January 30, 2020
    Date of Patent: April 26, 2022
    Assignee: United States of America as Represented by the Secretary of the Army
    Inventor: Seungeuk Han
  • Patent number: 11300390
    Abstract: A control surface deployment apparatus having a base part, a drive actuator operably installed adjacent to the base part and having a drive actuator shaft extending beyond the base part, a knuckle part installed on the drive actuator shaft so as to selectively rotate therewith, a hinge part pivotally installed on the knuckle part as through a hinge pin, a fin rigidly installed on the hinge part so as to extend away from the knuckle part, and a spring biasing element configured to pivotally bias the hinge part relative to the knuckle part.
    Type: Grant
    Filed: February 28, 2019
    Date of Patent: April 12, 2022
    Assignee: Dynamic Structures and Materials, LLC
    Inventors: Joshua J. Sesler, Bert K. McMahan, Mark C. McMahan
  • Patent number: 11067371
    Abstract: A tail kit assembly of a guided munition having a tail kit base connected to a trailing end of a projectile body. The tail kit base is rotatable relative to the projectile body. A trimmable rudder has forward and rearward ends. The forward end is pivotally coupled to the tail kit base, such that the trimmable rudder can, relative to the tail kit base, between retracted and extended orientations. An actuator is fixed between the tail kit base and the rearward end of the trimmable rudder. The actuator is electrically coupled to an onboard guidance system that controls actuation of the actuator to pivot the trimmable rudder between the retracted orientation and the extended orientation.
    Type: Grant
    Filed: March 22, 2019
    Date of Patent: July 20, 2021
    Assignee: BAE Systems Information and Electronic Systems Integration Inc.
    Inventors: Michael J. Choiniere, Jason T. Stockwell
  • Patent number: 11009323
    Abstract: A munition including: a casing having a first portion and the second portion; and an actuator comprising two or more pistons, each of the pistons being connected at a first end to the first portion of the casing and engaged at a second end to the second portion of the casing, each of the pistons being capable of having an extended and retracted position relative to the first and second ends, the retracted position resulting from an activation of each of the two or more pistons; wherein activation of one or more of the two or more pistons moves the first portion relative to the second portion.
    Type: Grant
    Filed: January 10, 2017
    Date of Patent: May 18, 2021
    Assignee: OMNITEK PARTNERS LLC
    Inventors: Jahangir S Rastegar, Jacques Fischer
  • Patent number: 10768703
    Abstract: The present disclosure is a touch-sensitive input detector having an operating unit with an input surface; a support; a fastener for mounting the operating unit to the support in a vibration direction so as to be displaceable from a resting position and elastically restorable; and an actuator for stimulating the operating unit to vibrate in the direction of vibration for a haptic feedback; wherein the fastener for attaching the operating unit includes leaf spring elements, which each form a first section for attaching to the support and a second section for attaching to the operating unit, and an intermediate middle section, so that the operating unit is mounted on the support in an elastically vibratable manner, and which are arranged at a distance from each other by the middle section, wherein at least one section from first section and second section is attached by a form-fit seat, such as overmolding.
    Type: Grant
    Filed: March 6, 2018
    Date of Patent: September 8, 2020
    Assignee: PREH GMBH
    Inventors: Benedikt Schmidt, Kai Lang, Mario Schmitt
  • Patent number: 10683079
    Abstract: A control system of a flight vehicle automatically varies the relationship between the center of gravity and the center of pressure of the flight vehicle. The control system automatically adjusts a center of pressure of the flight vehicle depending on a varying payload or payload type that is removably couplable to the flight vehicle. The control system automatically limits translational movement of the one or more wings of the flight vehicle in response to coupling of a payload to a fuselage of the flight vehicle.
    Type: Grant
    Filed: April 5, 2017
    Date of Patent: June 16, 2020
    Assignee: Raytheon Company
    Inventors: Jeffrey H. Koessler, Anthony O. Lee, Cody D. Tretschok, Gregory J. Artz
  • Patent number: 10641590
    Abstract: A lock block for use in a flight vehicle to deploy and lock wings in a deployed position with the lock block having a forward end and an aft end and including a support member, a resilient member adjacent the aft end of the lock block, a first deploy pin extending from the resilient member, a second deploy pin extending from the resilient member, and a wedge located on a bottom side of the resilient member. The first deploy pin and the second deploy pin are each configured to engage a groove in a wing of the flight vehicle to push each wing into a deployed position.
    Type: Grant
    Filed: October 26, 2016
    Date of Patent: May 5, 2020
    Assignee: Simmonds Precision Products, Inc.
    Inventor: Martin Edwy Buttolph
  • Patent number: 10495409
    Abstract: Representative implementations of devices and techniques provide a mounting dock to receive and to support an implement (such as a handgun, for example) or a carrier (such as a handgun holster, for example). The dock includes a cradle arranged to receive and to support the carrier. One or more spring-loaded lock buttons are disposed within the cradle and arranged to be activated when the carrier is pressed into the cradle. One or more spring-loaded latching fins are movably coupled to the cradle and arranged to catch the carrier when the one or more lock buttons are activated.
    Type: Grant
    Filed: November 18, 2017
    Date of Patent: December 3, 2019
    Inventors: Thomas Tedder, Jacob Shearer
  • Patent number: 10458764
    Abstract: A canard deployment mechanism includes a canard connected to a shaft that is hingedly attached to a rotatable hub that is moveable between a stowed and deployed position. The mechanism further includes a locking feature on the canard for restraining the canard in the stowed position. In an embodiment the mechanism further includes a pawl rotatably mounted on a drive gear to contact and restrain the canard in the stowed position.
    Type: Grant
    Filed: October 24, 2016
    Date of Patent: October 29, 2019
    Assignee: Rosemount Aerospace Inc.
    Inventors: Gary Willenbring, Steven W. Sorensen
  • Patent number: 10364007
    Abstract: An example underwater vehicle includes a first section detachably coupled to a second section that is positioned forward of the first section, and a hinge detachably coupling the first section to the second section, where the hinge creates a pivot between the first section and the second section. The underwater vehicle includes a lock having a locked position and an unlocked position, where, in the locked position, the lock couples the first section and the second section together, and where, in the unlocked position, the second section is capable of decoupling from the first section. The underwater vehicle also includes a drag fin associated with the second section that is movable to an extended position away from the second section to create a drag force which causes the second section to pivot about the hinge, away from the first section, when the underwater vehicle is traveling through a fluid medium.
    Type: Grant
    Filed: October 1, 2018
    Date of Patent: July 30, 2019
    Assignee: The Boeing Company
    Inventor: Randall L. Hoover
  • Patent number: 10184762
    Abstract: A device is provided. The device includes at least one SMM component fabricated from an SMM. The SMM component is configured to change shape in response to receiving a stimulus. The SMM component is also configured to deploy from a device body of the device allowing the device to change shape in an advantageous way. A method implemented by a device is also provided. The method includes changing a shape of an SMM component of the device in response to receiving a stimulus. The SMM component is fabricated from an SMM. The method also includes deploying the SMM component from a device body of the device allowing the device to change shape in an advantageous way.
    Type: Grant
    Filed: December 1, 2015
    Date of Patent: January 22, 2019
    Assignee: Raytheon Company
    Inventors: Matthew H. Summers, Frederick B. Koehler, Jeremy C. Danforth, James K. Villarreal
  • Patent number: 10112691
    Abstract: An example underwater vehicle includes a first section detachably coupled to a second section that is positioned forward of the first section, and a hinge detachably coupling the first section to the second section, where the hinge creates a pivot between the first section and the second section. The underwater vehicle includes a lock having a locked position and an unlocked position, where, in the locked position, the lock couples the first section and the second section together, and where, in the unlocked position, the second section is capable of decoupling from the first section. The underwater vehicle also includes a drag fin associated with the second section that is movable to an extended position away from the second section to create a drag force which causes the second section to pivot about the hinge, away from the first section, when the underwater vehicle is traveling through a fluid medium.
    Type: Grant
    Filed: June 12, 2017
    Date of Patent: October 30, 2018
    Assignee: The Boeing Company
    Inventor: Randall L. Hoover
  • Patent number: 9157702
    Abstract: A munition guidance system is disclosed. The system comprises a generally tubular enclosure, having an internal cavity adapted for receiving a munition, wherein an outer diameter of the enclosure is at most the largest outer diameter of the munition; and a processing and control unit enclosed within the enclosure and being configured for controlling guidance wings so as to maneuver the munition while flying.
    Type: Grant
    Filed: July 18, 2012
    Date of Patent: October 13, 2015
    Assignee: Elbit Systems Ltd.
    Inventors: Ami Elkayam, Zeev Azar
  • Patent number: 9068807
    Abstract: A rocket-propelled grenade includes a payload section, a selectable fuzing section joined to the payload section, and a propulsion section joined to the selectable fuzing section. A rocket-propelled grenade includes a propulsion section and a payload section operably associated with the propulsion section. The payload section includes a shell, one or more penetrators disposed in the shell, and a charge for compromising the shell to deploy the one or more penetrators when the charge is initiated.
    Type: Grant
    Filed: October 28, 2010
    Date of Patent: June 30, 2015
    Assignee: Lockheed Martin Corporation
    Inventors: Toby D. Thomas, Richard L. Green, Jonathan H. Record, Robbie S. Strauch, David L. Hunn
  • Patent number: 9004393
    Abstract: Embodiments of the present invention include an aircraft capable of sustained out-of-ground-effect hover flight and sustained supersonic flight. At least some embodiments includes two wings powered by an engine to counterrotate while hovering, and to not rotate and sweep while flying at transonic and supersonic speeds. Other embodiments include two rotating wings that generate a force per unit area of under 100 lb/ft2 within the rotating wing disk during hover. Still other embodiment include a vehicle with rotating wings that can increase pitch to accelerate the aircraft, align the chord line of the wings with the airstream, and sweep the wings. Still further embodiments include a power plant that powers unducted rotating wings during hover and disengages from the wings to propel the aircraft at supersonic speeds.
    Type: Grant
    Filed: October 24, 2011
    Date of Patent: April 14, 2015
    Assignee: University of Kansas
    Inventor: Ronald M. Barrett-Gonzales
  • Patent number: 8985504
    Abstract: A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.
    Type: Grant
    Filed: June 15, 2012
    Date of Patent: March 24, 2015
    Inventors: Tony Shuo Tao, Nathan Olson, Carlos Thomas Miralles, Robert Nickerson Plumb
  • Patent number: 8975566
    Abstract: By removing the aerodynamic fin forces from the fin lock mechanism, achieved by actuating the fin control system to apply a controlled force that counters the aerodynamic forces acting on the control fins, the system can reduce the transmission of aerodynamic forces onto the fin lock mechanism, which makes the fin lock mechanism easier to unlock with less force. Accordingly, a method for unlocking a fin lock mechanism that releasably holds one or more missile control fins in a locked position, where the control fins are prevented from rotating, includes the steps of (i) applying an alternating positive and negative rotational force to a control fin; (ii) monitoring the position of the control fin during the applying step; and (iii) while the position of the control fin does not exceed a predetermined value, repeating the applying step for a predetermined number of times or for a predetermined period.
    Type: Grant
    Filed: August 9, 2012
    Date of Patent: March 10, 2015
    Assignee: Raytheon Company
    Inventors: Thomas A. Black, David J. Reyes, Robert W. Von Mayr, Erik A. Fjerstad, John D. Willems
  • Patent number: 8952304
    Abstract: In one example, a rocket nozzle assembly is disclosed that has stowed and deployed positions, and includes a casing including an outer wall and an inner surface, at least a portion of the inner surface defining a diverging region, wherein the casing defines a plurality of fin slots, and wherein each of the plurality of fin slots extend through the outer wall of the casing and the inner surface of the casing, and wherein the diverging region defines a bell-shaped contour. The assembly further includes a plurality of fins pivotally engaged to the casing, wherein in the stowed position, each of the plurality of fins extends into the diverging region through a respective one of the fin slots, and wherein in the deployed position, each of the plurality of fins extend outwardly from the casing.
    Type: Grant
    Filed: July 14, 2011
    Date of Patent: February 10, 2015
    Assignee: Alliant Techsystems, Inc.
    Inventors: Joseph O. Bellotte, Thomas F. Farabaugh, Aaron C. Caba
  • Patent number: 8921749
    Abstract: A perpendicular drive mechanism for a missile control actuation system employs an electric motor and power shaft operatively coupled to a first spur gear. A lead screw is coupled to a second spur gear. The lead screw is oriented parallel to the motor and perpendicular to a central longitudinal axis. The first and second spur gears meshingly engage such that the second spur gear rotates in the opposite direction as the first spur gear. A lead nut threadingly engages with and is configured to move linearly along the central axis of the lead screw. A crank arm is coupled on one end to the lead nut and on the other end to the canard shaft of a canard assembly. As the lead nut moves linearly along the central axis of the lead screw, the crank arm follows the lead nut and causes the canard assembly to actuate.
    Type: Grant
    Filed: July 10, 2013
    Date of Patent: December 30, 2014
    Assignee: The United States of America as Represented by the Secretary of the Navy
    Inventor: Aaron M. Scott
  • Patent number: 8894004
    Abstract: Obliquely folding articulating wing mechanisms that include a wing rotatingly connected to a base.
    Type: Grant
    Filed: June 11, 2013
    Date of Patent: November 25, 2014
    Assignee: The United States of America as Represented by the Secretary of the Navy
    Inventors: Aaron Michael Scott, Philip Thomas Aberer, Neil Randall Japp, Nicholas Cody McGaha
  • Patent number: 8890043
    Abstract: A steering section for guided munition comprises a steering body having n control surfaces folded inside or deployed protruding from the external surface. The steering section comprises a locking mechanism for the n control surfaces folded inside the steering body having a lock support secured thereto, a fixed sleeve secured to the lock support comprising a locking barrel, a mobile sleeve surrounding the fixed sleeve and slideable longitudinally along the locking barrel, the mobile sleeve comprising, on the outside of the fixed sleeve, a free end collaborating with the n control surfaces to keep them folded inside the steering body, a translational-locking device locking the translational movement along the mobile sleeve along the locking barrel deactivatable by unlocking force to trigger translational sliding movement of the mobile sleeve along the locking barrel and release the n control surfaces which can then move from their folded position into their deployed position.
    Type: Grant
    Filed: January 25, 2013
    Date of Patent: November 18, 2014
    Assignee: TDA Armements
    Inventors: Patrick Cohe, Bertrand Dubois, Fabien Moreau
  • Patent number: 8876039
    Abstract: A folding wing for an aircraft comprises first and second inboard wing sections, and first and second outboard wing sections. The first and second inboard wing sections rotate about a centerline hinge, and a centerline spring applies force to the first and second inboard wing sections to rotate the first and second inboard wing sections from a stowed position to a deployed position. At least one of the first and second inboard wing sections translates along the axis of rotation of the first and second inboard wing sections as they move from the stowed to the deployed positions. The first and second outboard wing sections rotate between the stowed and the deployed positions about first and second outboard hinges.
    Type: Grant
    Filed: May 2, 2012
    Date of Patent: November 4, 2014
    Assignee: Stark Aerospace, Inc.
    Inventors: Jacob G. Lubenow, Andrew S. McComas, Jeremy A. Zanzig, Jeffrey A. Gerhart, Alan R. Klug, Jonathan P. Clark
  • Patent number: 8878111
    Abstract: Vehicles with bidirectional control surfaces and associated systems and methods are disclosed. In a particular embodiment, a rocket can include a plurality of bidirectional control surfaces positioned toward an aft portion of the rocket. In this embodiment, the bidirectional control surfaces can be operable to control the orientation and/or flight path of the rocket during both ascent, in a nose-first orientation, and descent, in a tail-first orientation for, e.g., a tail-down landing.
    Type: Grant
    Filed: February 24, 2010
    Date of Patent: November 4, 2014
    Assignee: Blue Origin, LLC
    Inventor: Mark Featherstone
  • Patent number: 8866057
    Abstract: An air vehicle that is launched from inside a launcher, includes a release mechanism for releasing fins of the vehicle from a stowed condition to a deployed condition. The release mechanism includes a pin that is located within a cavity in the fuselage of the air vehicle. Pressurized gasses initially fill the cavity in the fuselage. The launcher includes a reduced-pressure portion such as from a muzzle brake. When the air vehicle passes into the reduced-pressure portion of the launcher, the gas pressure behind the air vehicle is reduced. This causes the pressurized gas within the cavity to drive the release mechanism backwards out of the cavity. The length of the pin may be used to control the timing of the fin deployment, the delay between the initial movement of the release mechanism out of the cavity, and when the fins are released.
    Type: Grant
    Filed: October 17, 2011
    Date of Patent: October 21, 2014
    Assignee: Raytheon Company
    Inventor: Chris E. Geswender
  • Publication number: 20140291441
    Abstract: In one example, a rocket nozzle assembly is disclosed that has stowed and deployed positions, and includes a casing including an outer wall and an inner surface, at least a portion of the inner surface defining a diverging region, wherein the casing defines a plurality of fin slots, and wherein each of the plurality of fin slots extend through the outer wall of the casing and the inner surface of the casing, and wherein the diverging region defines a bell-shaped contour. The assembly further includes a plurality of fins pivotally engaged to the casing, wherein in the stowed position, each of the plurality of fins extends into the diverging region through a respective one of the fin slots, and wherein in the deployed position, each of the plurality of fins extend outwardly from the casing.
    Type: Application
    Filed: July 14, 2011
    Publication date: October 2, 2014
    Applicant: ALLIANT TECHSYSTEMS INC.
    Inventors: Joseph O. Bellotte, Thomas F. Farabaugh, Aaron C. Caba
  • Patent number: 8754352
    Abstract: A wing deploy initiator for deploying guidance wings of a rocket or missile, such as the APKWS, provides enhanced wing deploy performance with reduced complexity, cost, and likelihood of failure. The invention includes a cam which is driven between the stowed guidance wings by at least one compression spring, thereby forcing the guidance wings outward through slots in the fuselage of the rocket or missile. Oblique flat sides of the cam can push against beveled edges on the wings. The cam can be attached to spring mandrels, and the cam and mandrels can pass through a retaining plate as the springs decompress. Embodiments can exert sufficient push force to enable the wings to break through frangible slot covers. An embodiment applicable to the APKWS includes only 13 parts, and can exert up to 10 lb push force on each wing after 0.3 inches of wing travel.
    Type: Grant
    Filed: April 4, 2011
    Date of Patent: June 17, 2014
    Assignee: BAE Systems Information and Electronic Systems Integration Inc.
    Inventors: Amy Pietrzak, Michael J. Krueger
  • Patent number: 8738330
    Abstract: A scalable, inert munition data recorder cartridge. This inert cartridge allows users to record data from within a weapon system feed chute, breach, and extractor port. This cartridge is adaptable to any weapon system, packaging unit, environmental chamber, or other ammunition holding and storage device. Although the cartridge is designed to interface with a weapon and ammunition packaging based on its shape, it still functions as designed regardless of its location and application. This would allow the cartridge to be placed anywhere an actual live cartridge of ammunition could be placed.
    Type: Grant
    Filed: August 19, 2011
    Date of Patent: May 27, 2014
    Assignee: The United States of America as Represented by the Secretary of the Army
    Inventors: Daniel DiMartino, Jeffrey Darbig
  • Patent number: 8686330
    Abstract: The invention relates to a shell (1) arranged with extensible wings (3) having improved guidance characteristics during the gliding and final phase of the shell (1). The invention is characterized in that the extensible wings (3), via threaded wing fixtures (8), are movably arranged on rotatable axial guide shafts (6) on the shell body (2) for separate or simultaneous displacement of the wings (3) in the longitudinal direction A of the shell (1), for guidance of the shell (1) in the vertical and lateral directions during the trajectory phase of the shell, and in that the wings (3) are also rotatably arranged on radial guide shafts for controlling the angle of incidence of the wings (3) during the final phase of the shell (1).
    Type: Grant
    Filed: February 24, 2011
    Date of Patent: April 1, 2014
    Assignee: BAE Systems Bofors AB
    Inventor: Nils Johansson
  • Patent number: 8592737
    Abstract: A simultaneous deployment device for the control surfaces of a projectile for which each control surface is intended to be pivoted by a motor after its deployment to ensure the piloting, each control surface being held within the projectile and deployed towards the exterior of the projectile by the expansion of elastic means, each control surface being deployed by a rotation with respect to a control surface support and following a deployment axis that is crosswise to that of the projectile, wherein the elastic means are common means to ensure the deployment of all the control surfaces, the expansion of the elastic means generating a push stress directed along the axis of the projectile and being exerted on a push plate which transmits the push stress to as many slides as there are control surfaces to be deployed, each slide cooperating without slipping with a matching profile integral with a base of the control surface to make this pivot with respect to its support and first releasable locking means that mai
    Type: Grant
    Filed: January 18, 2011
    Date of Patent: November 26, 2013
    Assignee: Nexter Munitions
    Inventor: Geoffroy Deschatre
  • Patent number: 8569670
    Abstract: An advance is made in the art according to an aspect of the present invention disclosure directed to a pressure-activated, inertially locking base and fin mechanism for projectiles. Operationally, a base housing of a projectile contains both the fins, held within slots within the base, and a plunger. Which plunger has plurality of channels communicating with a chamber within base and which plunger is initially situated flush with the base. Upon firing the chamber is pressurized by the high-pressure firing gases being forced through the channels. When the projectile exits the barrel, the chamber's pressure vents through the channels, but, not fast enough to avoid a pressure differential that forces the plunger out of the base, causing a set of spring arms to flex upward and deploy the fins. When fully deployed, the fins are locked in place, in the deployed position, by a spring loaded pin.
    Type: Grant
    Filed: May 21, 2012
    Date of Patent: October 29, 2013
    Assignee: The United States of America as Represented by the Secretary of the Army
    Inventors: Donald Carlucci, David Geissler, John Thomas
  • Patent number: 8525089
    Abstract: Disclosed are a wing device for a flight vehicle and a flight vehicle having the same, the wing device including a fixing shaft disposed in a lengthwise direction of a main body of the flight vehicle, a wing rotatably mounted to the fixing shaft so as to be deployed from a state of being laid on an outer circumferential surface of the main body to an erected state, and slidable along the fixing shaft, a fixing groove formed to face the wing in a sliding direction of the wing, and a spring unit configured to apply a first elastic force in an outer circumferential direction of the main body for deployment of the wing, and apply a second elastic force in a lengthwise direction of the main body for inserting the wing into the fixing groove, whereby the wing can be fixed after deployment so as to enhance stability of the flight vehicle.
    Type: Grant
    Filed: April 11, 2011
    Date of Patent: September 3, 2013
    Assignee: Agency For Defense Development
    Inventors: Sang-Hun Shin, Hae-Yong Jeong
  • Publication number: 20130193265
    Abstract: A steering section for guided munition comprises a steering body having n control surfaces folded inside or deployed protruding from the external surface. The steering section comprises a locking mechanism for the n control surfaces folded inside the steering body having a lock support secured thereto, a fixed sleeve secured to the lock support comprising a locking barrel, a mobile sleeve surrounding the fixed sleeve and slideable longitudinally along the locking barrel, the mobile sleeve comprising, on the outside of the fixed sleeve, a free end collaborating with the n control surfaces to keep them folded inside the steering body, a translational-locking device locking the translational movement along the mobile sleeve along the locking barrel deactivatable by unlocking force to trigger translational sliding movement of the mobile sleeve along the locking barrel and release the n control surfaces which can then move from their folded position into their deployed position.
    Type: Application
    Filed: January 25, 2013
    Publication date: August 1, 2013
    Applicant: TDA ARMEMENTS S.A.S.
    Inventor: TDA ARMEMENTS S.A.S.
  • Patent number: 8450669
    Abstract: A projectile body intended to evolve in a fluid, such body equipped with at least two radially deployable control surfaces, such control surfaces being accommodated prior to their deployment in housings made in the body, such that the housings communicate at their intersection point, each housing being blocked by sealing device preventing any fluid from the exterior of the projectile body from passing through the housings when the control surfaces are deployed.
    Type: Grant
    Filed: November 10, 2010
    Date of Patent: May 28, 2013
    Assignee: Nexter Munitions
    Inventors: Richard Roy, Simon Huguenin
  • Patent number: 8415598
    Abstract: A stabilizing fin deployment apparatus may include a base assembly for attachment to the rear end of a projectile. The base assembly may include a base, a spacer, a fin mount, a gas cavity and an opening that extends from the rear end of the base to the gas cavity. A retention nut may engage the base and secure the fin mount and spacer to the base. A retention plug may be disposed in the opening in the base assembly. The retention plug may include at least one gas conduit between an outer surface of the retention plug and the gas cavity. A retention bolt may extend through the retention plug and may be fixed to the base. A plurality of fins hubs may be rotatably fixed to the base. A plurality of fins may be translatably connected to the fin hubs. When deployed, the fin hubs may rotate forward and the fins may translate outward far into the airstream.
    Type: Grant
    Filed: December 20, 2010
    Date of Patent: April 9, 2013
    Assignee: The United States of America as Represented by the Secretary of the Army
    Inventors: Robert Terhune, Michael Hollis
  • Patent number: 8378278
    Abstract: A foldable deployable panel device (12) attached to a body (16) of an object is disclosed. The device includes a panel pivotally attached to the body by a first pivot element (40/42) at a first pivot position and a second pivot element (29) at a second pivot position. The first pivot element (40/42) is disengageable from the first pivot position, when the panel (12) is aligned in a predetermined orientation. The second pivot element (29) is fixed at the second pivot position, when the first pivot element (40/42) is engaged at the first pivot position. The panel (12) is urged by an energy storing element (28), when the first pivot element (40/42) is disengaged from the first pivot position, to move into a deployed position.
    Type: Grant
    Filed: February 23, 2009
    Date of Patent: February 19, 2013
    Assignee: Elbit Systems Ltd.
    Inventor: Arie Ashkenazi
  • Patent number: 8367993
    Abstract: A missile has a flight termination system that includes deployable lift surfaces that deploy forward of a center of gravity of the missile. When deployed, the lift surfaces cause the missile to rotate about its longitudinal axis. This rotation eventually increases in rate until the missile nears a natural roll frequency of the missile. As the missile nears or reaches its natural roll frequency, the missile's nose pitches up, angle of attack diverges and the missile tumbles, resulting in rapid termination of flight by loss of aerodynamic lift, vertical plunging and crashing. The lift surfaces may be curved surfaces that conform to the shape of a fuselage of the missile, prior to the deployment of the lift surfaces. The lift surfaces may be canted slightly relative to a missile longitudinal axis when the lift surfaces are deployed, so as to provide a sufficient rolling moment to overcome aerodynamic damping or resistance (roll drag) of the missile.
    Type: Grant
    Filed: July 16, 2010
    Date of Patent: February 5, 2013
    Assignee: Raytheon Company
    Inventors: Javier Velez, Ralph H. Klestadt
  • Patent number: 8350200
    Abstract: A missile and a method for reducing the required control forces during the flight of a missile, comprising providing to the missile movable parts that adjust center of pressure of the missile as they move and as fuel in the missile is consumed, moving the movable parts so as to continuously move the center of pressure toward the moving center of gravity of the missile.
    Type: Grant
    Filed: March 26, 2009
    Date of Patent: January 8, 2013
    Assignee: Lockheed Martin Corporation
    Inventors: Andrew W. Hawkins, Christopher E. Willingham, Kit W. Grabbe
  • Patent number: 8324545
    Abstract: A foldable deployable panel device attached to a body of an object is disclosed. The device includes a panel pivotally attached to the body by a first pivot element at first pivot position and a second pivot element at a second pivot position. The first pivot element is disengageable from the first pivot position, when the panel is aligned in a predetermined orientation. The second pivot element is fixed at the second pivot position, when the first pivot element is engaged at the first pivot position. The panel is urged by an energy storing element, when the first pivot element is disengaged from the first pivot position, to move into the deployed position.
    Type: Grant
    Filed: October 27, 2011
    Date of Patent: December 4, 2012
    Assignee: Elbit Systems Ltd.
    Inventor: Arie Ashkenazi
  • Patent number: 8299411
    Abstract: Systems for controlling flow effector control surfaces. The system comprises a flow effector control coupled to an elongated bar at one end of the bar. The elongated bar is coupled at the other end to the middle of a T-shaped member. A compliant link is coupled to the bar between the control surface and the T-shaped member. At each end of the T-shaped member is coupled a shape memory alloy wire which acts as an actuating means. When one of the shape memory alloy wire contracts, the elongated bar pivots about the compliant link and activates or retracts the flow effector control surface.
    Type: Grant
    Filed: May 27, 2008
    Date of Patent: October 30, 2012
    Assignee: Her Majesty in Right of Canada as Represented by the Minister of National Defence
    Inventors: Frank Wong, Camille Alain Rabbath, Nicholas Lechevin, Olivier Boissonneault
  • Patent number: 8296053
    Abstract: A system and method are disclosed for determining relative motion between ship-based combat system elements using accelerometers. Relative motion between combat system elements can introduce error into the targeting information provided to the weapons system, and thus the system facilitates compensation for such relative motion. The system includes accelerometers mounted on radar systems, inertial navigation system (INS) sensors, and weapons systems. An algorithm is disclosed in which the raw accelerometer signals are filtered, then combined with ship INS attitude signals in a displacement calculation module (DCM). Within the DCM, the signals are manipulated to calculate, for each combat system element, the translational and rotational displacements due to hull modal vibration and the translational and rotational displacements due to force vibration. The sum of these values represent the movement of each of the affected combat system elements.
    Type: Grant
    Filed: October 9, 2007
    Date of Patent: October 23, 2012
    Assignee: Lockheed Martin Corporation
    Inventors: Edward M. Brennan, Carl V. Jannetti, John B. Stetson
  • Patent number: 8278612
    Abstract: Some embodiments pertain to a projectile that includes a body and a support attached to the body. The projectile further includes at least one partial fin that is rotatably attached to the support such that the partial fin moves between a stowed position and a deployed position. The support moves relative to the partial fin as the partial fin moves between the stowed position and the deployed position such that the partial fin and the support form a complete fin when the partial fin is in the deployed position. The support may form a portion of the front edge of the complete fin when the partial fin is in the deployed position. The support may lock the partial fin in place when the partial fin is in the deployed position.
    Type: Grant
    Filed: July 27, 2010
    Date of Patent: October 2, 2012
    Assignee: Raytheon Company
    Inventor: Randall S. Firor
  • Publication number: 20120175460
    Abstract: A multi-stage fin deployment assembly includes a rotary actuator configured to release a first spring-loaded stage that, when deployed, releases a second spring-loaded stage to deploy a set of deployable member or fins. By chaining these spring-loaded stages together, a relatively small input force, as provided by the rotary actuator, causes the second spring-loaded stage to generate a relatively large output force on the fins. This multistage force magnification makes it possible for the deployment assembly to utilize smaller actuators that require less power and take up less space, compared to conventional locking mechanisms.
    Type: Application
    Filed: June 2, 2010
    Publication date: July 12, 2012
    Applicant: WOODWARD HRT, INC.
    Inventors: Kumaraguru Poonamalli Palani, Raymond Lee Burt
  • Publication number: 20120074256
    Abstract: A wing deploy initiator for deploying guidance wings of a rocket or missile, such as the APKWS, provides enhanced wing deploy performance with reduced complexity, cost, and likelihood of failure. The invention includes a cam which is driven between the stowed guidance wings by at least one compression spring, thereby forcing the guidance wings outward through slots in the fuselage of the rocket or missile. Oblique flat sides of the cam can push against beveled edges on the wings. The cam can be attached to spring mandrels, and the cam and mandrels can pass through a retaining plate as the springs decompress. Embodiments can exert sufficient push force to enable the wings to break through frangible slot covers. An embodiment applicable to the APKWS includes only 13 parts, and can exert up to 10 lb push force on each wing after 0.3 inches of wing travel.
    Type: Application
    Filed: April 4, 2011
    Publication date: March 29, 2012
    Inventors: Amy Pietrzak, Michael J. Krueger
  • Publication number: 20120068002
    Abstract: A missile (10) comprising a projectile body (20), a payload (60) contained within the nose portion (30), wings (70) stowed within the mid portion (40), and fins (80) stored within the tail portion (50). The wings (70) can be deployed during intermediate stages of the flight path when lift is advantageous, and re-stowed during terminal stages when an almost vertical angle-of-attack is desired. The fins (80) function as stabilizing components during the early ballistic stage of the flight path and function as guiding components thereafter.
    Type: Application
    Filed: May 18, 2010
    Publication date: March 22, 2012
    Inventors: Michael P. Unger, Stephen D. Witherspoon, James T. Schleining
  • Publication number: 20120048993
    Abstract: A missile has a flight termination system that includes deployable lift surfaces that deploy forward of a center of gravity of the missile. When deployed, the lift surfaces cause the missile to rotate about its longitudinal axis. This rotation eventually increases in rate until the missile nears a natural roll frequency of the missile. As the missile nears or reaches its natural roll frequency, the missile's nose pitches up, angle of attack diverges and the missile tumbles, resulting in rapid termination of flight by loss of aerodynamic lift, vertical plunging and crashing. The lift surfaces may be curved surfaces that conform to the shape of a fuselage of the missile, prior to the deployment of the lift surfaces. The lift surfaces may be canted slightly relative to a missile longitudinal axis when the lift surfaces are deployed, so as to provide a sufficient rolling moment to overcome aerodynamic damping or resistance (roll drag) of the missile.
    Type: Application
    Filed: July 16, 2010
    Publication date: March 1, 2012
    Inventor: Javier Velez
  • Patent number: 8089034
    Abstract: A wing pivot mechanism that is configured to pivot two wings about a single pivot axis of a vehicle, such as an aircraft. The wing pivot mechanism includes a hub, a set of gears positioned at least partially within an interior region of the hub, and two wings that are rotatably connected to the hub. Each wings includes a gear surface extending therefrom. Each gear of the hub assembly engages a gear of a respective wing such that rotation of the gears of the hub assembly causes rotation of the gears of the wings and pivoting of the wings about the single pivot axis in opposite rotational directions between a stowed position and a deployed position. A releasable locking mechanism is provided for locking the wings in a fixed rotational position in both the deployed position and the stowed position.
    Type: Grant
    Filed: April 17, 2009
    Date of Patent: January 3, 2012
    Assignee: ITT Manufacturing Enterprises, Inc.
    Inventor: Robert E. Hammerquist
  • Patent number: 8049149
    Abstract: Methods and apparatus for an air brake system for a projectile according to various aspects of the present invention comprises a pivot and a protrusion mounted on the pivot. The protrusion is adapted to selectively translate outward from the projectile around a translation axis that is parallel to the longitudinal axis of the projectile. The methods and apparatus may further operate in conjunction with an actuation system engaging the protrusion, wherein the actuation system is configured to selectively facilitate the translation of the protrusion.
    Type: Grant
    Filed: December 17, 2008
    Date of Patent: November 1, 2011
    Assignee: Raytheon Company
    Inventors: Chris E. Geswender, James D. Streeter, Matthew A. Zamora, Jason J. Fink, Matthew O. Eisenbacher