Externally Mounted Stabilizing Appendage (e.g., Fin) Patents (Class 244/3.24)
  • Patent number: 10556672
    Abstract: A strake may comprise a plate, wherein the plate extends between a forward end and an aft end along a first direction and the plate extends between a root end and a tip end along a second direction, a first tab extending from the root end of the plate, wherein a first fastening aperture is disposed in the first tab, and a second tab extending from the root end of the plate, wherein a second fastening aperture is disposed in the second tab.
    Type: Grant
    Filed: August 22, 2017
    Date of Patent: February 11, 2020
    Assignee: Rohr, Inc.
    Inventors: Thomas Paolini, Nicholas Hedges
  • Patent number: 10288397
    Abstract: A method for deploying a control surface from an exterior surface of a spinning projectile during flight is provided. The method including: at least partially retracting the control surface into an interior of the projectile for a portion of a full revolution of the spinning projectile and extending the control surface from the interior of the projectile for another portion of the full revolution of the spinning projectile; and maintaining the control surface in a same plane during the full revolution of the spinning projectile.
    Type: Grant
    Filed: April 5, 2017
    Date of Patent: May 14, 2019
    Assignee: OMNITEK PARTNERS LLC
    Inventors: Jahangir S Rastegar, Jacques Fischer
  • Patent number: 9354025
    Abstract: A dart tail fin assembly includes a cylindrical dart body with a nose, a tail opposite the nose and an outer surface extending from the nose to the tail. A plurality of tail fins is attached to and spaced around the outer surface of the dart body. Each one of the tail fins includes a trailing edge aligned with the tail of the dart, a leading edge opposite the trailing edge toward the nose of the tail, a length from the trailing edge to the leading edge and a flat portion disposed at leading edge extending perpendicularly outward from the outer surface a first width. Each tail fin is detached from the outer surface of the dart body along a portion of the length extending back from the leading edge.
    Type: Grant
    Filed: September 15, 2014
    Date of Patent: May 31, 2016
    Assignee: The United States of America as Represented by the Secretary of the Navy
    Inventor: Raafat Guirguis
  • Patent number: 9278756
    Abstract: A rotor blade assembly includes a rotor blade and a rotatable flap portion located along a span of the rotor blade. A linear actuator located inside the rotor blade is operably connected to the flap portion to rotate the flap portion about a flap axis and is absent oil, grease or other fluid lubricant. A rotary-winged aircraft includes an airframe and a main rotor assembly operably connected to the airframe. The main rotor assembly includes a plurality of rotor blade assemblies rotatable about a rotor assembly axis. At least one rotor blade assembly of the plurality of rotor blade assemblies includes a rotor blade and a rotatable flap portion located along a span of the rotor blade. A linear actuator positioned inside the rotor blade is operably connected to the flap portion to rotate the flap portion about a flap axis and is absent oil, grease or other fluid lubricant.
    Type: Grant
    Filed: August 30, 2012
    Date of Patent: March 8, 2016
    Assignee: CLAVERHAM LTD
    Inventors: Paul R. Brewer, Reg R. Raval, Suat Bekircan
  • Patent number: 9040885
    Abstract: The invention is a projectile, device and system having a roll control device which may be fixed or deployable, for providing torque counter to the spin of the projectile and providing drag on the projectile. The roll control device includes a guidance collar rotatably attached to the projectile located near a front end of the projectile wherein the guidance collar includes one or more guidance collar aero-surfaces shaped to provide torque counter to the spin on the projectile. The guidance collar aero-surfaces may be controlled by a brake and guidance electronics on the projectile. The invention also includes a body collar fixedly attached to the projectile aft of the guidance collar, wherein the body collar includes one or more body collar aero-surfaces and fixed or deployable drag devices. Another embodiment use only a guidance collar aero-surfaces to orient a fixed drag device relative to an Earth inertial reference frame to create asymmetrical drag on the projectile and thereby altering its trajectory.
    Type: Grant
    Filed: November 12, 2009
    Date of Patent: May 26, 2015
    Assignee: General Dynamics Ordnance and Tactical Systems, Inc.
    Inventors: Joseph P. Morris, Douglas L. Smith
  • Patent number: 9024238
    Abstract: A ground surface reconnaissance projectile includes a tube-launched 60 mm inert mortar round, which remotely relays reconnaissance and surveillance data back to an operator, after it has landed and uprighted itself. The types of collected data include for example, visual imagery of the target area in 360 degrees, acoustic target tracking and voice recognition, infra-red motion detection, and magnetic field disturbance sensing.
    Type: Grant
    Filed: March 13, 2013
    Date of Patent: May 5, 2015
    Assignee: The United States of America as Represented by the Secretary of the Army
    Inventors: Pavol Stofko, Pasquale Carlucci, Mark Mellini, Christopher Mougeotte
  • Patent number: 9012825
    Abstract: Disclosed are systems and methods for retaining and deploying a plurality of canards and canard covers on a projectile. The projectile includes a projectile housing defining an interior chamber and a longitudinal axis, canards rotatably mounted to the housing, canard covers, a bobbin movably disposed in the interior chamber of the housing along the longitudinal axis, and rocker arms. The canards mounted for movement from a stowed position to a deployed position. The canard covers have a hook element and are adapted to cover respective slots formed in the housing. The bobbin has first and second ends and a retaining surface proximate the second end. Rocker arms have a first and second arm end, with a canard retaining slot defined therebetween. The first arm end includes a latch element for engaging with the canard cover element, and the second arm end is positioned proximate the retaining surface.
    Type: Grant
    Filed: January 23, 2013
    Date of Patent: April 21, 2015
    Assignee: Simmonds Precision Products, Inc.
    Inventors: Matt Plumer, Jeff Gibson, Jim Byrne, Brian Richardson
  • Patent number: 9012824
    Abstract: A low-heat-transfer coupling or assembly is configured to mechanically couple together a pair of mating parts, one of which may be in a heat-producing environment. By roughening at least part of the surface of one of the parts, the contact area between the mating parts can be reduced, while still maintaining the structural integrity of the connection. The roughening can be a knurling process of all or part of the mating surface on one of the parts. This can produce a series of recesses on the surface that are in contact with the other part. The recesses can be small enough, interspersed with non-etched areas of the contact surface, that structural integrity of the coupling between the parts is still maintained. The coupling may be between a leading edge of an aircraft control surface, such as a missile fin, and a body of the control surface.
    Type: Grant
    Filed: March 16, 2011
    Date of Patent: April 21, 2015
    Assignee: Raytheon Company
    Inventor: Kyriakos C. Christou
  • Patent number: 8993948
    Abstract: A spinning, rolling, or roll-stabilized vehicle, such as a projectile, includes a fuselage that rotates about its longitudinal axis (spins) during flight. A collar is positionable relative to the fuselage to steer the projectile, with the collar having ailerons to provide a roll force to position the collar. The collar also has elevators to provide lateral force to steer the projectile. The positioning of the collar may be accomplished by moderating the roll force of the ailerons to hold the position of the collar substantially constant with regard to a longitudinal axis of the projectile. The ailerons passively change angle of attack with changes in the dynamic pressure of the projectile. At low speeds the ailerons have a relatively large angle of attack, and at high speeds, the ailerons resiliently reduce their angles of attack, avoiding large rolling forces on the collar.
    Type: Grant
    Filed: August 23, 2011
    Date of Patent: March 31, 2015
    Assignee: Raytheon Company
    Inventors: Chris E. Geswender, Paul Vesty, Geoffrey W. Frost, Bruce E. Morgan, Doron Strassman
  • Patent number: 8975565
    Abstract: An interceptor is provided with an integrated propulsion and attitude control system (ACS) in which propellant burn forms a common pressure vessel for high-pressure gas. An aft port in the rocket motor directs gas through one or more main nozzles that expel high-velocity gas in a generally axial direction to propel the interceptor. A forward port directs gas through one or more attitude control nozzles that expel high-velocity gas in a generally radial direction to control the attitude of the interceptor. The main nozzle(s) and stabilization fins are fixed, there is no servo control to the main nozzles or fins to affect attitude control. The use of a common pressure vessel enables an integrated propulsion and ACS that can be compact, lightweight and inexpensive.
    Type: Grant
    Filed: July 17, 2012
    Date of Patent: March 10, 2015
    Assignee: Raytheon Company
    Inventors: Doron Strassman, Mark E. Elkanick
  • 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
  • Publication number: 20150034759
    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: Application
    Filed: October 7, 2014
    Publication date: February 5, 2015
    Inventor: Mark Featherstone
  • Patent number: 8933383
    Abstract: A system and method of trajectory correction includes a voice coil coupled to the projectile and providing a linear force; a linkage assembly coupled to the voice coil and comprising: a linkage shaft; a slot coupled to the linkage shaft; and a pin loosely coupled to the slot to form a first pivot point, wherein the linkage assembly converts the linear force to a torque force through the first pivot point; and a canard assembly coupled to the linkage assembly and including a canard shaft coupled to the linkage shaft to form a second pivot point; and at least one canard coupled to the canard shaft, wherein the torque force is transmitted to canard shaft by the linkage shaft, and wherein the canard shaft transmits the torque force to the canard to correct the trajectory of the projectile.
    Type: Grant
    Filed: September 1, 2010
    Date of Patent: January 13, 2015
    Assignee: The United States of America as represented by the Secretary of the Army
    Inventor: Ilmars Celmins
  • Patent number: 8921748
    Abstract: An optical window for a detection system and method of employing the same. In one embodiment, the detection system includes an optical window configured to internally channel external incident radiation to an exit surface for emission. The detection system also includes a detector oriented to receive emitted radiation from the exit surface.
    Type: Grant
    Filed: May 18, 2012
    Date of Patent: December 30, 2014
    Assignee: Lockheed Martin Corporation
    Inventors: Umang R. Patel, Kurt Schuder
  • 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: 8895908
    Abstract: A low cost, lightweight frangible wing slot seal can be applied to a guidance wing slot of a folding fin aerial rocket or missile, providing a barrier against exposure of internal missile components to external contaminants, while allowing unhindered deployment of missile guidance wings simply by bursting through the seals. The simple design is nearly foolproof, and has no impact the likelihood of weapon failure. The seal is a flexible sheet which is sufficiently thin so as not to exceed the required volume envelope of the missile. The sheet includes a burst seam, which is breached when impacted by the leading edge of a deploying wing. No additional wing deployment force is required, and after deployment the seal has minimal impact on the aerodynamic performance of the wing.
    Type: Grant
    Filed: April 7, 2011
    Date of Patent: November 25, 2014
    Assignee: BAE Systems Information and Electronic Systems Integration Inc.
    Inventors: William D. Barry, Robert Winkler, John R. Franzini, Kenneth D. Cleveland, Adam Butland
  • 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: 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: 8872082
    Abstract: Disclosed is a flying object in which a covering unit and a wing unit installed in a nozzle assembly are integrally formed to form a smooth outer surface of the flying object, thus minimizing drag, and the covering unit and the nozzle assembly are fastened by using a fastening member having one end fastened to a slit, thereby preventing the flying object from being damaged by thermal deformation.
    Type: Grant
    Filed: February 27, 2013
    Date of Patent: October 28, 2014
    Assignee: Agency for Defense Development
    Inventors: Sung Han Park, Kyung Yong Lee, Yeung Cheol Kim, Kyoung Tai Kang
  • Publication number: 20140312163
    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: Application
    Filed: December 11, 2013
    Publication date: October 23, 2014
    Applicant: BLUE ORIGIN, LLC
    Inventor: Mark Featherstone
  • Patent number: 8847134
    Abstract: A system for actuating a control surface of a deployable member is provided. The system includes an actuator disposed within a fuselage structure of a missile; a double joint having a distal end for connecting to the actuator and a proximal end for engaging the control surface, wherein the double joint further includes a first and second pivot; and a mechanical brake configured to controllably prevent rotation of the actuator.
    Type: Grant
    Filed: February 16, 2012
    Date of Patent: September 30, 2014
    Assignee: Lockheed Martin Corporation
    Inventor: Michael Gaudette
  • Patent number: 8829401
    Abstract: A projectile and associated method are provided for seeking a target that has been laser designated even though the projectile does not include a laser receiver. A projectile includes an aerodynamic body and a GPS receiver configured to receive GPS signals indicative of a location of the aerodynamic body. The projectile also includes a radio receiver configured to receive radio signals from an offboard laser receiver that provide information relating to a location of the target based upon laser designation of the target. Further, the projectile includes a processor configured to direct flight of the aerodynamic body toward the target based upon the location of the aerodynamic body as determined from the GPS signals and the location of the target based upon the information provided by the offboard laser receiver.
    Type: Grant
    Filed: June 16, 2011
    Date of Patent: September 9, 2014
    Assignee: The Boeing Company
    Inventors: Kevin Lutke, Aaron J. Kutzmann
  • Patent number: 8825231
    Abstract: A method and system for piloting a craft with a rear propulsion unit are disclosed. The method can include a servo loop where the attitude (?M) of the craft (1) is measured in the vicinity of the rear end (1R) of the craft, then the orientation (?) of the propulsion means (2), which can be oriented relative to the rear end (1R), is adjusted as a function of the attitude measurement (?M) in such a way that the craft (1) is stabilized on its flight path.
    Type: Grant
    Filed: January 20, 2012
    Date of Patent: September 2, 2014
    Assignee: Astrium SAS
    Inventors: Paul Caye, James Caillaud, Guillaume Laporte
  • Patent number: 8816261
    Abstract: Control surfaces secured tangentially to a round projectile, such that the lift force generated by the control surfaces is generated through the projectiles centerline. This eliminates the need for an opposing fin to counter roll moment. Sizing the control surfaces to form an equilateral triangle gives each panel equal span, and enables the force generated by two panels to be equal and opposite to that of the opposing panel. The end effect is that each panel only has two active states (neutral and positive deflection). Thus, a solenoid and a return spring may be used to control the canards. Additionally, the control panels may fold along the surface of the projectile, which frees up internal volume and minimizes the length of the control section.
    Type: Grant
    Filed: June 29, 2011
    Date of Patent: August 26, 2014
    Assignee: Raytheon Company
    Inventors: Jesse H. Blake, Matthew G. Murphy
  • Patent number: 8816260
    Abstract: Embodiments of a flight-control system and methods of reducing the probability of a roll-control reversal in a canard-controlled flight vehicle are generally described herein. In some embodiments, the flight-control system may monitor angular velocities of the flight vehicle to detect the onset of instability and adaptively control an acceleration limit of the flight vehicle based on the detected instability to reduce the probability of a roll-control reversal. The onset of instability may be detected by persistently high angular velocities. The acceleration limit may be further adaptively controlled based on an approach of a vehicle trim limit.
    Type: Grant
    Filed: December 1, 2010
    Date of Patent: August 26, 2014
    Assignee: Raytheon Company
    Inventors: Richard E. Hindman, Kyle David Andringa, Darrell B. Ridgely
  • Publication number: 20140231577
    Abstract: The subject-matter of the invention is a method for controlling the control surfaces of a projectile and the associated projectile comprising incidence steerable control surfaces and comprising at least two control surfaces, each one being rotatable with respect to the projectile around a pivot axis perpendicular to the longitudinal axis X of the projectile, wherein the projectile comprises central means for controlling the control surfaces having at least a spherical shape, a control arm secured to the spherical shape and adapted to rotate the spherical shape, for each control surface a transmission member cooperating with the spherical shape and adapted to transmit to the control surface the rotation movements of the spherical shape, and means for positioning the arm.
    Type: Application
    Filed: February 14, 2014
    Publication date: August 21, 2014
    Applicant: NEXTER MUNITIONS
    Inventor: Richard ROY
  • Patent number: 8789366
    Abstract: A shape memory stored energy assembly includes a projectile housing having a projectile lumen. A projectile is within the projectile lumen and the projectile is movable relative to the projectile housing. A shape memory actuator is coupled between the projectile anchored end and the projectile housing. The shape memory actuator is configured to transition from a strained energy stored configuration to a fractured kinetic delivery configuration at a specified temperature range to propel the projectile through the projectile lumen. A method includes storing energy in a shape memory actuator coupled with a projectile. The stored energy in the shape memory actuator is released and propels the projectile. Releasing the stored energy includes heating the shape memory actuator, tensioning the shape memory actuator, and fracturing the tensioned shape memory actuator at a fracture locus to propel the projectile away from the fracture locus.
    Type: Grant
    Filed: June 8, 2011
    Date of Patent: July 29, 2014
    Assignee: Raytheon Company
    Inventors: Ward D. Lyman, Frederick B. Koehler
  • Patent number: 8766152
    Abstract: The present invention includes, in various aspects and embodiments, a method and apparatus for guiding a laser guided munition to an offset aim point relative to the laser spot. In one aspect, the laser guided munition comprises a propelled explosive ordnance; an optical sensor; means for indicating an offset from a laser designation; and a flight control system. The flight control system is responsive to an output from the optical sensor to: home on the laser designation during the descent of an arcing trajectory for the propelled explosive ordnance; determine that the propelled explosive ordnance traversed a predetermined point in the descending trajectory; and upon traversing the predetermined point, guide the propelled explosive ordnance to the position defined by the offset indicator. In a second aspect, the laser guided munition is deployed as part of a system that also includes a laser designator.
    Type: Grant
    Filed: July 15, 2010
    Date of Patent: July 1, 2014
    Assignee: Lockheed Martin Corporation
    Inventors: Edward Max Flowers, Chad Nathan Chegwidden, Christopher L. Gould
  • Patent number: 8735789
    Abstract: A statically stabilized projectile may include a fixed tail boom that may be disposed in the through-bore of a sliding tail boom. The sliding tail boom may translate or extend rearward with respect to the fixed tail boom before the projectile exits a launch tube. The through-bore of the sliding tail boom may include a tapered portion. A tail boom sleeve may be fixed to a rear portion of the fixed tail boom. The tail boom sleeve may include a tapered portion that abuts the tapered portion of the through-bore when the sliding tail boom is in an extended position.
    Type: Grant
    Filed: September 20, 2010
    Date of Patent: May 27, 2014
    Assignee: The United States of America as Represented by the Secretary of the Army
    Inventors: Gregory Malejko, Keith Fulton, Ductri Nguyen
  • Patent number: 8729442
    Abstract: Technology for predicting and correcting a trajectory is described. The technology can create a model to predict a position of the reusable launch vehicle at a time in the future; observe a wind condition during ascent of the reusable launch vehicle; store the observed wind condition in a wind map; predict during ascent a position and a terminal lateral velocity of the reusable launch vehicle at a terminal altitude; and correct a flight trajectory of the reusable launch vehicle based on the wind map.
    Type: Grant
    Filed: June 15, 2010
    Date of Patent: May 20, 2014
    Assignee: Blue Origin, LLC
    Inventors: Frederick W. Boelitz, Mark O. Hilstad
  • 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: 8686329
    Abstract: A compact, purely mechanical wing deployment assisting mechanism uses torsion springs and lever arms to apply a deploying force to a guidance wing during its initial deployment through a wing slot in a rocket or missile, thereby assisting the wing to burst through a cover seal protecting the wing slot. The wings are then fully deployed by centrifugal force. Various embodiments include two “extreme duty” springs and two lever arms per wing, working in parallel. Embodiments provide a total of at least 24 pounds of force per wing at the end of a spring travel of 0.30 inches. In some embodiments, the entire mechanism weighs less than 0.5 pounds and/or occupies less than 2.5 cubic inches per wing. In embodiments, an assembled group, including two springs and two lever arms, is located between each pair of wings, whereby each assembled group applies one lever arm to each adjoining wing.
    Type: Grant
    Filed: April 8, 2011
    Date of Patent: April 1, 2014
    Assignee: BAE Systems Information and Electronic Systems Integration Inc.
    Inventors: William D. Barry, Michael J. Krueger, Amy Pietrzak
  • Patent number: 8686325
    Abstract: A method for guiding a gun-fired or mortared round towards an intended target. The method including: capturing image data from an image pick-up device during a descent of the round; transmitting the image data to a control platform remotely located from the round; transmitting guidance information to the round from the remote platform based on the captured image data; varying a flight path of the round based on the guidance information to guide the round towards its intended target.
    Type: Grant
    Filed: March 22, 2011
    Date of Patent: April 1, 2014
    Assignee: Omnitek Partners LLC
    Inventors: Jahangir S. Rastegar, Andre Rastegar, Thomas Spinelli
  • Patent number: 8686328
    Abstract: A fin lock assembly 12 for locking and unlocking missile fins 20 includes a piston 34 movable along a piston axis 44 between a locked position for preventing a fin from rotating and an unlocked position for allowing the fin to rotate. The fin lock assembly includes a camshaft 46 rotatable between a locked position and a relatively-rotated unlocked position about a cam axis 50 that is transverse the piston axis. The camshaft has an eccentric portion 66 connected to the piston such that rotation of the camshaft between the locked position and the unlocked position moves the piston between its corresponding locked and unlocked positions. The fin lock assembly includes a torsion spring 72 connected to the camshaft to bias the camshaft toward its unlocked position. A latch mechanism 100 holds a plurality of camshafts in their locked positions and simultaneously releases the camshafts to release their fins.
    Type: Grant
    Filed: July 20, 2012
    Date of Patent: April 1, 2014
    Assignee: Raytheon Company
    Inventors: John F. Bugge, John D. Willems
  • Patent number: 8686327
    Abstract: A missile nose fairing system includes sections attached at an aft end thereof to a missile body, a restraint for normally preventing aftward displacement of the plurality of sections, and a drive unit for releasing the restraint in response to a received signal. Each of the sections has an outer surface that converges to a common forward pointed tip for enclosing and protecting a guidance head when in an extended position and is retractable into a corresponding recessed region formed within a missile nose when the drive unit is activated releasing the restraint.
    Type: Grant
    Filed: October 14, 2010
    Date of Patent: April 1, 2014
    Assignee: Rafael Advanced Defense Systems Ltd.
    Inventor: Yacov Yacobovitch
  • Patent number: 8674277
    Abstract: There is disclosed a collar (100) which may be attached to a munition in order to control the trajectory of the munition. The collar (100) has a collar body (10); a surface (12) for capturing the projectile as it leaves the barrel; a sill (14) for supporting the surface (12) at the muzzle of the barrel; and a guidance means (20a, 20b, 21a, 21b) for altering the flow of air around the collar (100). The collar (100) supports itself at the muzzle and may attach to the projectile at the surface (12) to integrate with the projectile as the projectile is fired. The collar (100) is particularly suited for attachment to mortar rounds. Such a collar (100) gives a weapon operator the option of increasing the precision of a munition without having to carry a plurality of munition types.
    Type: Grant
    Filed: November 11, 2010
    Date of Patent: March 18, 2014
    Assignee: BAE SYSTEMS plc
    Inventors: Richard Desmond Joseph Axford, Kevin William Beggs
  • Publication number: 20140061365
    Abstract: The invention relates to a steering method of a projectile and to the associated projectile with incidence steerable fins, comprising at least three fins, each being pivotable with respect to the projectile around a pivot axis perpendicular to the longitudinal axis X of the projectile, wherein the projectile comprises a fin orientation ring, the ring comprising as many arms as there are fins, wherein the ring can translate in a plan P perpendicular to the longitudinal axis X of the projectile and following at least two directions of this plan P, wherein the orientation ring can rotate on itself around its centre parallel to the longitudinal axis X of the projectile, each arm comprising means cooperating with an orientation lever fixed to a fin to be able to pivot the fin around its pivot axis during translation of the ring by positioning means.
    Type: Application
    Filed: August 29, 2013
    Publication date: March 6, 2014
    Applicant: NEXTER MUNITIONS
    Inventor: Richard ROY
  • Patent number: 8664575
    Abstract: A miniature lightweight high-maneuverability missile (10) has a missile body (12) with three sets of at least two aerodynamic control surfaces (14, 16, 18) for independent control of roll, pitch and yaw of the missile. Each set of control surfaces (14, 16, 18) is independently controlled by a corresponding actuator (20) deployed within the missile body (12). Other preferred features include selection of an elevation angle of incidence at a target, and switching between explosive and kinetic modes of operation.
    Type: Grant
    Filed: August 16, 2007
    Date of Patent: March 4, 2014
    Assignee: Rafael Advanced Defense Systems Ltd.
    Inventors: Yariv Bril, Yakov Hetz, Oded Yehezkeli, Ehud Chishinsky
  • Patent number: 8664576
    Abstract: A vehicle for launching from a gun such as a gas gun and having a housing; preferably incorporating a precessional attitude control system; and utilizing a flared base, fins, or active use of the attitude control system during passage through the atmosphere. Subtly canting the fins can produce desired spinning of the vehicle. The propulsion system can employ liquid, hybrid, or solid fuel. A removable aero-shell assists atmospheric flight with thermal protection being provided by anticipated ablation, an ablative aero-spike, or transpirational cooling. And a releasable sabot enhances the effectiveness of the launch.
    Type: Grant
    Filed: August 9, 2013
    Date of Patent: March 4, 2014
    Assignee: Quicklaunch, Inc.
    Inventors: John William Hunter, Harry E. Cartland, Philip James Sluder, Richard Edward Twogood
  • Publication number: 20140042267
    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: Application
    Filed: August 15, 2013
    Publication date: February 13, 2014
    Applicant: BLUE ORIGIN, LLC
    Inventor: Mark Featherstone
  • Publication number: 20140042266
    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: Application
    Filed: August 9, 2012
    Publication date: February 13, 2014
    Applicant: RAYTHEON COMPANY
    Inventors: Thomas A. Black, David J. Reyes, Robert W. Von Mayr, Erik A. Fjerstad, John D. Willems
  • Patent number: 8648285
    Abstract: A system for guiding a gun-fired or mortared round towards an intended target, the system including a round having: a forward facing image pick-up device for capturing image data; a first transceiver; guidance device for varying a flight path of the round; and a first processor. The system further including a control platform remotely located from the round, the control platform having: a second transceiver; a second processor; an input device; and a display. Where the first processor transmits image data from the image pick-up device through the first transceiver to the second processor through the second transceiver, the second processor transmits guidance information from the second transceiver to the first processor through the first transceiver and the first processor controls the guidance device based on the guidance information to guide the round towards the intended target.
    Type: Grant
    Filed: March 22, 2011
    Date of Patent: February 11, 2014
    Assignee: Omnitek Partners LLC
    Inventors: Jahangir S Rastegar, Andre Rastegar, Thomas Spinelli, Qing Tu
  • Publication number: 20140027563
    Abstract: A guidance unit system is configured to be used for a ground-launched projectile. The system includes a housing configured to be attached to a ground-launched projectile. The housing is coupled to an attachment region that attaches to the projectile, wherein the housing is configure to rotate relative to the attachment region. A motor is contained within the housing and a bearing surrounding the motor. The bearing is rigidly attached to the housing such that the motor rotates with the housing and shields the motor from inertial loads experienced by the housing.
    Type: Application
    Filed: May 10, 2012
    Publication date: January 30, 2014
    Inventor: Gordon Harris
  • Publication number: 20140021289
    Abstract: A fin lock assembly 12 for locking and unlocking missile fins 20 includes a piston 34 movable along a piston axis 44 between a locked position for preventing a fin from rotating and an unlocked position for allowing the fin to rotate. The fin lock assembly includes a camshaft 46 rotatable between a locked position and a relatively-rotated unlocked position about a cam axis 50 that is transverse the piston axis. The camshaft has an eccentric portion 66 connected to the piston such that rotation of the camshaft between the locked position and the unlocked position moves the piston between its corresponding locked and unlocked positions. The fin lock assembly includes a torsion spring 72 connected to the camshaft to bias the camshaft toward its unlocked position. A latch mechanism 100 holds a plurality of camshafts in their locked positions and simultaneously releases the camshafts to release their fins.
    Type: Application
    Filed: July 20, 2012
    Publication date: January 23, 2014
    Applicant: RAYTHEON COMPANY
    Inventors: John F. Bugge, John D. Willems
  • Patent number: 8624172
    Abstract: A shift lock assembly includes a drive member carried by a drive shaft and configured to rotatably couple to a drive motor and a shift mechanism disposed between the drive member and a ground plate, the shift mechanism configured to move between a first position and a second position relative to the drive member and the ground plate. When disposed in the first position, the shift mechanism is configured to couple the drive shaft to the ground plate and decouple the drive shaft from the drive member to allow rotation of the drive member relative to the drive shaft. When disposed in the second position, the shift mechanism is configured to couple the drive shaft to the drive member and decouple the drive shaft from the ground plate to allow rotation of the drive shaft in response to rotation of the drive member.
    Type: Grant
    Filed: October 13, 2010
    Date of Patent: January 7, 2014
    Assignee: Woodward HRT, Inc.
    Inventor: Grant Sweer
  • Patent number: 8624171
    Abstract: A system and method for guiding a projectile is presented. A nozzle system includes a boom assembly body that can be attached to a rear end of a projectile. A gas tank in the boom assembly contains pressurized gas. Fins are attached to the boom assembly body to guide the projectile. A valve lets a pulse of gas out of the gas tank. A nozzle expels the pulse of gas to control an angle of attack and lift of the projectile to guide the projectile to a target.
    Type: Grant
    Filed: March 9, 2011
    Date of Patent: January 7, 2014
    Assignee: BAE Systems Information and Electronic Systems Integration Inc.
    Inventor: Robert D. Frey, Jr.
  • Publication number: 20130334358
    Abstract: A system and method of trajectory correction includes a voice coil coupled to the projectile and providing a linear force; a linkage assembly coupled to the voice coil and comprising: a linkage shaft; a slot coupled to the linkage shaft; and a pin loosely coupled to the slot to form a first pivot point, wherein the linkage assembly converts the linear force to a torque force through the first pivot point; and a canard assembly coupled to the linkage assembly and including a canard shaft coupled to the linkage shaft to form a second pivot point; and at least one canard coupled to the canard shaft, wherein the torque force is transmitted to canard shaft by the linkage shaft, and wherein the canard shaft transmits the torque force to the canard to correct the trajectory of the projectile.
    Type: Application
    Filed: September 1, 2010
    Publication date: December 19, 2013
    Applicant: UNITED STATES GOVERNMENT AS REPRESENTED BY THE SECRETARY OF THE ARMY
    Inventor: Ilmars Celmins
  • Patent number: 8610042
    Abstract: A fin retention and deployment mechanism includes a detent in each of a plurality of fins, a mechanism that engages the detent, and at least one spring clip that maintains each of the fins in a non-deployed position. The mechanism also includes a gas generator, a manifold, coupled to the gas generator and having a plurality of cylinders in fluid communication with gas from the gas generator, and a plurality of pistons disposed in the cylinders. A bottom of each of the pistons is coupled to each of the fins to provide deployment thereof when a corresponding top of each of the pistons is acted upon by gas from the gas generator. In response to the gas generator expelling gas, the pistons may move the fins to a deployed position.
    Type: Grant
    Filed: November 10, 2010
    Date of Patent: December 17, 2013
    Assignee: Simmonds Precision Products, Inc.
    Inventor: John R. Sankovic
  • 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