Longitudinally Rotating Patents (Class 244/3.28)
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Patent number: 6761331Abstract: A missile in combination with a deployment mechanism that automatically pivots and rotates a fin from a stowed orientation to a deployed orientation. The deployment mechanism includes a spring that provides a biasing force that urges the fin to move quickly, simply and reliably from the stowed orientation to the deployed orientation. The deployment mechanism also includes one or more cams or the like for guiding the fin from the stowed orientation to the deployed orientation.Type: GrantFiled: March 19, 2002Date of Patent: July 13, 2004Assignee: Raytheon CompanyInventors: Rudolph Adolph Eisentraut, Martin Allen Kebschull, John Christopher Parine
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Patent number: 6758435Abstract: A missile includes a missile body and a guide assembly mounted on the missile body. The guide assembly has a plurality of pivots and a plurality of vanes mounted on respective pivots for a swinging motion between a folded position of rest and a deployed flight position. The vanes are arranged for free pivotal motion during flight in response to forces acting thereon to determine the flight position. In the folded position of each vane, its center of gravity is situated at a greater distance from the longitudinal axis of the missile body than the pivotal axis of the respective vanes. Abutments limit the flight position of the vanes to a maximum angle between the length dimension of the vanes and the longitudinal axis of the missile body. The maximum angle is greater than 90°.Type: GrantFiled: August 23, 2002Date of Patent: July 6, 2004Assignee: Rheinmetall W & M GmbHInventors: Torsten Niemeyer, Manfred Dieter Schwies, Uwe Naderhoff, Thomas Heitman, Michael Imdahl, Rudolf Rombach
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Patent number: 6745978Abstract: The center of pressure of a projectile is caused to move upon the occurrence of an event that changes the static margin, such as the jettisoning of a body previously attached to the projectile, as noted above. In particular embodiments, this is achieved by a flare disposed toward the rear of the projectile. The flare has petals that deploy from a first, stowed position to a second, deployed position upon the occurrence of the event. In the stowed position, the petals are aligned with the air stream, in order to minimize drag. In the deployed position, the petals project into the air stream in such a way as to move the lift center rearward. A slide ring within the flare has sufficient inertia that it shifts aft in response to an acceleration that occurs when the attached body and the projectile are separated from one another. The slide ring is linked to the petals in such a way that the petals are deployed by the displacement of the slide ring.Type: GrantFiled: March 24, 2003Date of Patent: June 8, 2004Assignee: AT&T Corp.Inventors: Hartley Hughes King, Thomas Louis Menna, Lawrence Steven Romero
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Patent number: 6726147Abstract: The improved multi-function actuator (20) broadly includes; a first mechanism (21) capable of bi-directional displacement; a motor (22) operatively arranged to selectively displace the first mechanism through a first displacement range; a second mechanism (24) capable of uni-directional displacement from a first position to a second position; a spring (25) operatively arranged to urge the second mechanism to move from the first position to the second position; a release mechanism (26) operatively arranged to release the spring when the first mechanism is moved beyond the first displacement range; a third mechanism (27) capable of bi-directional displacement; and a clutch (28) operated by the release of the spring to selectively disconnect the motor from the first mechanism and to selectively connect the motor to the third mechanism; whereby the motor may be operated to selectively control either the first mechanism or the third mechanism.Type: GrantFiled: May 15, 2003Date of Patent: April 27, 2004Assignee: Moog Inc.Inventors: Richard J. Perini, James K. Riedel, Michael D. Wantuck
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Patent number: 6695252Abstract: A missile or projectile tail section includes an outflow device and a number of deployable fins. The outflow device may be a base bleed device that includes a slow-burning propellant which fills the vacuum created by the projectile's motion through the air. Use of the outflow device may allow the projectile range to be extended by up to 20%. The fins are stowed canted relative to planes that include the axis of the tail section. By canting or tilting the fins relative to the axis of the tail section, increased space is made in the tail section for the outflow device. Although the fins are stowed canted relative to the tail section, they may be configured so as to be deployed such that the axis of the tail section is substantially within the planes of the fins.Type: GrantFiled: September 18, 2002Date of Patent: February 24, 2004Assignee: Raytheon CompanyInventor: Richard Dryer
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Publication number: 20040021034Abstract: The present invention relates to an artillery missile (1) intended for firing on a ballistic trajectory, with gliding characteristics which can be put into effect, after it has reached the summit of this trajectory, to increase the maximum range of the missile.Type: ApplicationFiled: July 29, 2003Publication date: February 5, 2004Inventor: Ulf Hellman
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Publication number: 20040004156Abstract: A projectile (12) to be fired from a rifled barrel (66) is described. At its tail (10) it has control surface vanes (14) which can be pivoted out from a sub-calibre launch position into an over-calibre functional position. To protect the inwardly folded vanes (14) and to protect further ballistic and sensor structures at the tail end of the projectile (12), a securing pot (18) is temporarily fixed to the tail (10) of the projectile (12), the securing pot having a pot peripheral portion (22) and a pot bottom (24). There is a pressure chamber (32) between the tail end face (26) of the projectile (12) and the pot bottom (24) of the securing pot (18). The pot bottom (24) has at least one propellent gas inlet (34) which opens into the pressure chamber (32). When the projectile (12) is fired from the barrel propellent gas flows through the propellent gas inlet (34) into the pressure chamber (32) so that a correspondingly high propellent gas pressure is produced in the pressure chamber (32).Type: ApplicationFiled: December 10, 2002Publication date: January 8, 2004Applicant: Diehl Munitionssysteme GmbH & Co. KGInventors: Klaus Bar, Jurgen Bohl, Thomas Leidenberger
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Publication number: 20030178527Abstract: A missile (10) in combination with a deployment mechanism (14) that automatically pivots and rotates a fin (12) from a stowed orientation to a deployed orientation. The deployment mechanism (14) includes a spring (38) that provides a biasing force that urges the fin (12) to move quickly, simply and reliably from the stowed orientation to the deployed orientation. The deployment mechanism also includes one or more cams or other means for guiding the fin from the stowed orientation to the deployed orientation.Type: ApplicationFiled: March 19, 2002Publication date: September 25, 2003Inventors: Rudolph Adolph Eisentraut, Martin Allen Kebschull, John Christopher Parine
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Patent number: 6588700Abstract: A tactical base for a guided projectile includes a base structure, and an adaptor structure for securing the base structure to a forward section of the projectile. The base further includes a plurality of fin slots, with a plurality of insert structures fitted into corresponding ones of the fin slots. A plurality of deployable fins are pivotally mounted to the base structure and supported within the insert structures for movement between a stowed position and a deployed position.Type: GrantFiled: October 16, 2001Date of Patent: July 8, 2003Assignee: Raytheon CompanyInventors: James L. Moore, Gary H. Johnson, William S. Peterson, Rajesh H. Shah, Richard Dryer, Conlee O. Quortrup
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Patent number: 6578792Abstract: Described is a rudder blade mounting arrangement (10) for a missile comprising a rudder blade (12) and a mounting element (16) for the rudder blade. The rudder blade (12) is displaceable about a rudder blade axis member (36) of the mounting element (16) between a retracted inactive position and a deployed active position. The rudder blade foot (14) of the rudder blade (12) is connected in positively locking relationship to the rudder blade axis member (36) in such a way that, in the deployed active position of the rudder blade (12), the rudder blade foot (14) is forced against a front face (62) of a side portion (24) of the mounting element (16).Type: GrantFiled: April 4, 2002Date of Patent: June 17, 2003Assignee: Diehl Munitionssysteme GmbH & Co. KGInventor: Josef Dommer
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Patent number: 6557798Abstract: In the missile containing a predeterminate number of swing wings made of a flexible, resiliently elastic, substantially flat material, the substantially flat material contains a closed cavity. Pressurized as can be infed into the closed cavity from a pressurized gas source in the swung out condition of the swing wings. In one embodiment the substantially flat material of the swing wing directly forms the closed cavity. The substantially flat material is made of thin sheet of spring steel. The swing wings are connected at their base to the missile body via respective swivel joints. Each swivel joint comprises a pressurized as cartridge constituting the pressurized gas source for inflating the swing wing. Each swing wing contains two tongue-shaped members of the substantially flat material. The two tongue-shaped members have respective substantially straight base edges and substantially U-shaped external rim portions and are interconnected in the region of their external rim portions.Type: GrantFiled: May 23, 1990Date of Patent: May 6, 2003Assignee: Bodenseewerk Geratetechnik GmbHInventors: Peter Joachim Wilhelm Giesenberg, Otto-Paul Jakob
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Patent number: 6559370Abstract: A submarine countermeasure vehicle includes an elongated body for supporting a countermeasure device, and a propulsion assembly mounted on an after end of the body. The propulsion assembly includes a rotatable propeller hub, propeller blades mounted on the hub and moveable between a first position wherein the blades extend substantially radially outwardly from the hub, and a second position wherein the blades extend generally axially of the hub. A spring is mounted on each of the blades and in the hub, the spring biasing the blades toward the first position, but of sufficient flexibility to permit the blades to move to the second position upon launch of the vehicle from an underwater launch tube.Type: GrantFiled: August 6, 2002Date of Patent: May 6, 2003Assignee: The United States of America as represented by the Secretary of the NavyInventor: William P. Barker
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Publication number: 20030071166Abstract: A tactical base for a guided projectile includes a base structure, and an adaptor structure for securing the base structure to a forward section of the projectile. The base further includes a plurality of fin slots, with a plurality of insert structures fitted into corresponding ones of the fin slots. A plurality of deployable fins are pivotally mounted to the base structure and supported within the insert structures for movement between a stowed position and a deployed position.Type: ApplicationFiled: October 16, 2001Publication date: April 17, 2003Inventors: James L. Moore, Gary H. Johnson, William S. Peterson, Rajesh H. Shah, Richard Dryer, Conlee O. Quortrup
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Publication number: 20030042356Abstract: In order to provide that the braking elements (16), which are to be deployed radially under the effect of centrifugal force, of the braking arrangement in the region of the ogival head of a spin-stabilised artillery projectile (12) are secured in the rest position and can then be released in a defined manner when reaching the braking point of the ballistic trajectory, the stowage space (14) for accommodating the braking elements (16) is radially covered by a hood (22) which is fitted on to the projectile fuse (11) in the afflux direction and is axially fixed between a recess (24) in the rear wall (25) of the stowage space and a front-end holding ring (26) connected to the ogival head.Type: ApplicationFiled: August 29, 2002Publication date: March 6, 2003Applicant: Diehl Munitionssysteme GmbH & Co. KGInventors: Klaus Bar, Jurgen Bohl
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Publication number: 20030038212Abstract: A missile includes a missile body and a guide assembly mounted on the missile body. The guide assembly has a plurality of pivots and a plurality of vanes mounted on respective pivots for a swinging motion between a folded position of rest and a deployed flight position. The vanes are arranged for free pivotal motion during flight in response to forces acting thereon to determine the flight position. In the folded position of each vane, its center of gravity is situated at a greater distance from the longitudinal axis of the missile body than the pivotal axis of the respective vanes. Abutments limit the flight position of the vanes to a maximum angle between the length dimension of the vanes and the longitudinal axis of the missile body. The maximum angle is greater than 90°.Type: ApplicationFiled: August 23, 2002Publication date: February 27, 2003Inventors: Torsten Niemeyer, Manfred Dieter Schwies, Uwe Naderhoff, Thomas Heitman, Michael Imdahl, Rudolf Rombach
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Patent number: 6502785Abstract: A three axis control system employing four flaps is disclosed. The flaps are of uniform design, which decreases machining and manufacturing costs. The flaps are positioned on a vehicle orthogonally, but offset from a vehicle centerline. The system provides not only pitch and yaw control, but also bi-directional roll control with a minimum number of parts and minimal infringement of packaging envelope. The system provides quick response and increased capability for difficult maneuvers and is useable for hypersonic/supersonic applications.Type: GrantFiled: November 17, 2000Date of Patent: January 7, 2003Assignee: Lockheed Martin CorporationInventors: Roger D. Teter, Dean A. Kudlick, Richard M. Williams
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Patent number: 6474594Abstract: Accordingly, a shaft assembly for coupling a control fin to a missile includes outer and inner shaft portions which are detachably coupled together, allowing removal of one of the shaft portions while the other shaft portion remains in the missile. In an exemplary embodiment, the inner shaft portion, to which the control fin is coupled, is removable. The shaft assembly includes a pair of preload nuts to adjust the position of the control fin relative to the skin of the missile, the preload nuts being for example engaged on opposite threaded ends of the outer shaft portion.Type: GrantFiled: May 11, 2001Date of Patent: November 5, 2002Assignee: Raytheon CompanyInventors: Gary H. Johnson, Christopher P. Owan, William M. Hatalsky, Wayne Lee Sunne
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Patent number: 6454205Abstract: A fin-stabilized projectile includes a projectile body having a rear portion defining a rearwardly open cavity and a stabilizing assembly which has an axially slidable fin support in the cavity. The fin support has a retracted position in which the fin support is withdrawn into the cavity and an outwardly shifted position in which the fin support projects from the projectile body. A plurality of fins are pivotally held in the fin support. Each fin has a folded state in which it is withdrawn in the fin support when the latter is in the retracted position and a deployed state in which it is unfolded and extends substantially externally of the fin support when the latter is in its outwardly shifted position. When the projectile has left the weapon barrel, the fin support is axially shifted and the fins move into the deployed state.Type: GrantFiled: March 30, 2001Date of Patent: September 24, 2002Assignee: Rheinmetall W & M GmbHInventors: Torsten Niemeyer, Frank Guischard, Horst Fritsch
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Patent number: 6398156Abstract: A rudder of a missile, particularly an aircraft born ramjet missile, is attached to the missile by a plug and socket mounting. A bearing socket (B1) is attached to a base plate (B0) which is secured to the missile body (FK). The socket (B1) has a conical cavity (B3) tapering toward the base plate (B0). The plug (W1) is formed by a rudder shaft (W) also tapering toward the base plate and rotatably fitting into the conical cavity (B3). Bearings (L1, L2) in the cavity (B3) hold the plug end (W1) of the rudder shaft axially and permit rotation of the rudder shaft (W) relative to the bearing socket (B1). The socket thus holds the bearings and has an at least partly outer cylindrical contour with a diameter (B2) that fits into a standard 41 mm wide slot (S) in an aircraft that carries the missile, whereby the rudder (R) is recessed in the slot (S) when the missile is mounted to an aircraft.Type: GrantFiled: December 12, 2000Date of Patent: June 4, 2002Assignee: LFK Lenkflugkoerpersysteme GmbHInventors: Walter Hetzer, Ernst Lenz
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Publication number: 20010039898Abstract: A spin-stabilized artillery projectile (11) can be easily subsequently fitted with an axially symmetrical aerodynamic braking device for reducing the ballistic trajectory if the tip (14) which is equipped with the fuse (13) and which is easily removable from the projectile body (12) is equipped at approximately half its height with flap-shaped sectors (24) which are pivotably mounted in such a way that they can be pivotably extended and which in their launch position fit snugly into the conical peripheral surface of the tip (14) and in the operative position are pivotably extended to form a radial ring which is closed or which has gaps.Type: ApplicationFiled: May 10, 2001Publication date: November 15, 2001Applicant: Diehl Munitionssysteme GmbH & Co. KGInventors: Klaus Bar, Jurgen Bohl, Karl Kautzsch
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Patent number: 6314886Abstract: A projectile to be fired from a weapon barrel includes a projectile body and a plurality of stabilizing wings circumferentially distributed about a rearward portion of the projectile body. A pin pivotally attaches each stabilizing wing to the projectile body for pivotal motion about a pivot axis to assume a folded state and an outwardly pivoted, deployed state. In the folded state of the stabilizing wings the center of gravity of the respective stabilizing wings is at a greater radial distance from the longitudinal axis of the projectile body than the pivot axis. A gliding body is releasably mounted on each stabilizing wing. Each gliding body has a wing-shaped extension for contacting an inner surface of the barrel in the folded state of the stabilizing wings as the projectile travels in the barrel upon firing.Type: GrantFiled: February 22, 2000Date of Patent: November 13, 2001Assignee: Rheinmetall W & M GmbHInventors: Joachim Kuhnle, Thomas Heitmann, Torsten Niemeyer, Norbert Arendt
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Publication number: 20010015397Abstract: A missile includes a missile body and a guide assembly mounted on the missile body. The guide assembly has a plurality of pivots and a plurality of vanes mounted on respective pivots for a swinging motion between a folded position of rest and a deployed flight position. The vanes are arranged for free pivotal motion during flight in response to forces acting thereon to determine the flight position. Abutments limit the flight position of the vanes to a maximum angle between the length dimension of the vanes and the longitudinal axis of the missile body. The maximum angle is greater than 90°.Type: ApplicationFiled: December 11, 2000Publication date: August 23, 2001Inventors: Torsten Niemeyer, Manfred Dieter Schwies, Uwe Naderhoff, Thomas Heitmann, Michael Imdahl, Rudolf Rombach
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Patent number: 6220544Abstract: A guided missile (12), in particular a projectile which can be fired through a propellent charge gas pressure, having rudder blades (18) which cross each other and which can be pivoted open to steer the missile (12). Each rudder blade (18) is mounted in a guide slot (22) which is closed at the front end by an end portion (26). Each end portion (26) has a spoiler end face (28). Each end portion (26) projects radially beyond the lateral longitudinal ribs (24). At its distal end portion (32) the associated rudder blade (18) is provided with laterally mutually opposite, narrow guide ribs (36) which project out of the rudder blade profile (34).Type: GrantFiled: June 15, 1999Date of Patent: April 24, 2001Assignee: Diehl Stiftung & Co.Inventors: Josef Dommer, Werner Schroppel, Martin Staudenmeir
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Patent number: 6202958Abstract: To maintain control accuracy for the pivotable rudder blades (14), which lie in a combustion chamber, of a guided projectile (12) which can be fired by means of propellent charge, there is provide a mounting arrangement in which the trunnions (20) of the rudder blade holders (16) of the diametrally mutually opposite rudder blades (14) are torsionally stiffly rigidly connected through an associated coupling element (32) which is limitedly resilient in the radial direction of the guided projectile (12).Type: GrantFiled: June 15, 1999Date of Patent: March 20, 2001Assignee: Diehl Stiftung & Co.Inventors: Josef Dommer, Werner Schroppel, Martin Staudenmeir