子分类：
| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 121 | Lenkflugkörper | EP02011222.3 | 2002-05-18 | EP1281927A1 | 2003-02-05 | Fisch, Peter Gerd; Elsner, Gerd |
Die Erfindung betrifft ein Lenkflugkörper (46) mit einer Flugkörpernase und einem in der Flugkörpernase angeordneten Sucher. Es ist erkannt worden, daß viele bei einem Lenkflugkörper (46) auftretenden Probleme durch unerwünschte mechanische Schwingungen ausgelöst werden und daß diese Probleme durch den Einsatz von schwingungsdämpfenden Mitteln behoben werden können. Zu diesem Zweck werden schwingungsdämpfende Mittel zum Verringern der Schwingungen des Lenkflugkörpers im Flug vorgesehen. Die schwingungsdämpfenden Mittel können einen Schwingungstilger (48) aufweisen, welcher beispielsweise in einem Gasflaschen-Aufnahmeraum (44) des Lenkflugkörpers (46) angeordnet sein kann. |
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| 122 | PROJECTILES HAVING CONTROLLABLE DENSITY AND MASS DISTRIBUTION | EP96917176 | 1996-06-05 | EP0779967A4 | 1998-01-07 | LOWDEN RICHARD A; MCCOIG THOMAS M; DOOLEY JOSEPH B; SMITH CYRUS M |
| A projectile (36) achieves inherent aerodynamic characteristics through differential mass density, which places the center of gravity in a desired location relative to the center of pressure. | ||||||
| 123 | GYROSCOPICALLY STABILIZED PROJECTILE SYSTEM FOR USE AGAINST UNDERWATER OBJECTS | EP96918101.0 | 1996-06-04 | EP0774104A1 | 1997-05-21 | BROWN, Jeffrey, A.; COPSEY, Reed; TULIN, Marshall; KLINE, Roy |
| A projectile (50) is propelled from a location in air, through an air/water interface, and toward an underwater object (24). The projectile (50) includes a forward end (52) that forms a cavitation void (30) around the projectile (50) in water, avoiding water drag on the remainder of the projectile (50). The projectile (50) further includes a lateral stabilizer (90) that contacts the side of the cavitation void in the event that the projectile (50) yaws into a wall of the cavitation void (30) as it passes through water, producing a restoring force that prevents the projectile (50) from tumbling. | ||||||
| 124 | Lochkegelleitwerk für ein Geschoss, insbesondere ein Übungsgeschoss | EP83105036.4 | 1983-05-20 | EP0126173B1 | 1987-12-09 | |
| 125 | Hierarchical closed-loop flow control system for aircraft, missiles and munitions | US15057211 | 2016-03-01 | US10139209B1 | 2018-11-27 | Troy S Prince; Richard Kolacinski; Mehul Patel |
| The present invention relates to a missile or aircraft with a hierarchical, modular, closed-loop flow control system and more particularly to aircraft or missile with a flow control system for enhanced aerodynamic control, maneuverability and stabilization and methods of operating the flow control system. Various embodiments of the flow control system of the present invention involve flow sensors, active flow control device or activatable flow effectors and/or logic devices with closed loop control architecture. The sensors are used to estimate or determine flow conditions on surfaces of a missile or aircraft. The active flow control device or activatable flow effectors of these various embodiments create on-demand flow disturbances, preferably micro-disturbances, at different points along various aerodynamic surfaces of the missile or aircraft to achieve a desired stabilization or maneuverability effect. The logic devices are embedded with a hierarchical control structure allowing for rapid, real-time control at the flow surface. | ||||||
| 126 | .308 Subsonic Bullet | US16026226 | 2018-07-03 | US20180335284A1 | 2018-11-22 | Charles Edmond McWilliam, SR.; Jamie George McWilliam |
| The invention here described of novel aerodynamics and construction has been shown to alleviate the problems inherent in subsonic ballistics, such as, but not limited to, tumbling in flight, loss of impact energy, as well as the changes in both accuracy and precision of the firearm shots fired at subsonic speeds. The subsonic bullet herein described has three main aerodynamic components that aid in subsonic flight: 1) a parabolic or hemispherical nose; 2) a cylindrical center length with parallel sides; 3) a cone-like parabolic tail with an optimized tail geometry to slowly converge the laminar flow around the bullet without introducing turbulence. These features serve to reduce air pressure and turbulent airflow around the bullet during flight. | ||||||
| 127 | FEATHERS OF AN ARROW | US15607428 | 2017-05-26 | US20170350680A1 | 2017-12-07 | YEON KIM |
| The present invention relates to the improved feathers of an arrow, and more particularly, to the improved feathers of an arrow, which prevent instability of flight caused by a vortex generated during the flight of the arrow by forming a plurality of arrow feathers attached to the arrow, which has a cross section which is a curved surface and integrally forming an auxiliary surface having one surface which is the curved surface with the arrow feather to guarantee stable flight. | ||||||
| 128 | LAUNCH VEHICLES WITH RING-SHAPED EXTERNAL ELEMENTS, AND ASSOCIATED SYSTEMS AND METHODS | US15342501 | 2016-11-03 | US20170327249A1 | 2017-11-16 | Mark Featherstone; John Michael Sanders; Roger E. Ramsey; Eric David Wetzel |
| Launch vehicles with ring-shaped external elements, and associated systems and methods are disclosed. An aerospace system in accordance with a particular embodiment includes a launch vehicle having a first end and a second end generally opposite the first end, with the launch vehicle being elongated along a vehicle axis extending between the first and second ends, and having an external, outwardly facing surface. The system can further include an annular element carried by the launch vehicle, the annular element having an external, inwardly-facing surface radially spaced apart from, and extending at least partially circumferentially around, the vehicle axis. The annular element can have a first edge surface facing a first direction along the vehicle axis, and a second edge surface facing a second direction along the vehicle axis, the second direction being opposite the first direction. A propulsion system can be carried by the launch vehicle, and can have at least one nozzle positioned toward the first end of the vehicle to launch the vehicle. A controller can be in communication with the launch vehicle and programmed to direct the vehicle in the first direction during vehicle ascent, and in the second direction during vehicle descent. | ||||||
| 129 | Shell | US14728093 | 2015-06-02 | US09541361B2 | 2017-01-10 | Ju Hyun Bae; Wan Joo Kim |
| Provided is a shell including: a shell body; a steering wing including a drive shaft and that mounted on an external surface of the shell body; an auxiliary wing including a shaft connection portion which is connected to the drive shaft and moving in the lengthwise direction of the drive shaft within the drive shaft to be inserted into and be spread outward from within the steering wing; an auxiliary-wing holding unit including a holding protrusion which is fixedly arranged in a direction of intersecting the shaft connection portion to selectively hold the auxiliary wing in place; and an auxiliary-wing spreading unit installed within the drive shaft, and that provides driving force for spreading the auxiliary wing outward from within the steering wing when the holding protrusion is disengaged with the shaft connection portion. | ||||||
| 130 | Subsonic Bullet | US15167251 | 2016-05-27 | US20170003107A1 | 2017-01-05 | Charles Edmond McWilliam, SR.; Jamie George McWilliam |
| A bullet whose aerodynamics is suitable for stable subsonic flight, including a parabolic or hemispherical nose section, cylindrical midsection, and a parabolic into conical tail section. It is constructed of a copper shell filled, in the tail, with a material having a density less than or equal to 3.0 g/cm3, and in the nose with a material having a density greater than or equal to 11 g/cm3. The bullet further includes a length sufficient to fill an appropriate standard casing combined with the proper amount of smokeless powder for subsonic flight. These characteristics allow for the bullet's stable and accurate flight at speeds below 343.2 m/s. | ||||||
| 131 | PLATING A COMPOSITE TO ENHANCE BONDING OF METALLIC COMPONENTS | US14903872 | 2014-07-09 | US20160369635A1 | 2016-12-22 | JinQuan XU; Grant O. COOK, III |
| A composite component is disclosed. The composite component may comprise a metal plating deposited on a surface of the composite component, and a metallic feature adhesively bonded to the metal plating. The composite component may further comprise an adhesive layer between the metal plating and the metallic feature. The metal plating may provide a metal-to-metal interface between the surface of the composite component and the metallic feature. | ||||||
| 132 | PLATING ADHESION PROMOTION | US14903866 | 2014-07-09 | US20160369419A1 | 2016-12-22 | Michael S. Miarecki; Charles R. Watson; James T. Roach |
| A plated polymer component is disclosed. The plated polymer component may comprise a polymer substrate having an outer surface, and a metal plating deposited on the outer surface of the polymer substrate. The plated polymer component may further comprise an adhesion promoter at an interface between the polymer substrate and the metal plating. | ||||||
| 133 | EROSION AND WEAR PROTECTION FOR COMPOSITES AND PLATED POLYMERS | US14903880 | 2014-07-09 | US20160368238A1 | 2016-12-22 | William Bogue; Grant O. Cook, III; Gary M. Lomasney; Joseph Parkos; Colin J. Kling; Charles R. Watson |
| A composite component and a plated polymer component are disclosed. The composite component may comprise a body portion formed from an organic matrix composite, a first metal coating applied to a surface of the body portion, and an outer metal layer on the first metal coating that is erosion-resistant. The plated polymer component may comprise a polymer substrate, a metal plating layer applied to a surface of the polymer substrate, and at least one selectively thickened region in the metal plating layer. The at least one selectively thickened region may assist in protecting the plated polymer component against wear and/or erosion. | ||||||
| 134 | Launch vehicles with ring-shaped external elements, and associated systems and methods | US13833985 | 2013-03-15 | US09487308B2 | 2016-11-08 | Mark Featherstone; John Michael Sanders; Roger E. Ramsey; Eric David Wetzel |
| Launch vehicles with ring-shaped external elements, and associated systems and methods. A representative aerospace system includes a launch vehicle having a first end and a second end generally opposite the first end, with the launch vehicle being elongated along a vehicle axis extending between the first and second ends, and having an external, outwardly facing surface. The system can further include an annular element carried by the launch vehicle, the annular element having an external, inwardly-facing surface radially spaced apart from, and extending at least partially circumferentially around, the vehicle axis. The annular element can have a first edge surface facing a first direction along the vehicle axis, and a second edge surface facing a second direction along the vehicle axis, the second direction being opposite the first direction. A propulsion system can be carried by the launch vehicle, and can have at least one nozzle positioned toward the first end of the vehicle to launch the vehicle. A controller can be in communication with the launch vehicle and programmed to direct the vehicle in the first direction during vehicle ascent, and in the second direction during vehicle descent. | ||||||
| 135 | Passive stability system for a vehicle moving through a fluid | US14306772 | 2014-06-17 | US09429401B2 | 2016-08-30 | David A Corder; Paul A Merems |
| A stability system for a vehicle moving through a fluid includes stabilizers each having a drive surface that follows the position of the fluid stream perceived by the vehicle. The movement of the drive surface positions control surfaces of the stabilizers, which are coupled to the drive surfaces by mechanical linkages. Lift forces on the drive surfaces provide the force that is used in positioning the control surfaces. The deflection of the control surfaces provides a force on the vehicle that affects stability of the vehicle, for instance in making an inherently unstable vehicle more stable. The stability system may work completely passively, without any active control, and without the need for power to operate it. | ||||||
| 136 | CERAMIC-ENCAPSULATED THERMOPOLYMER PATTERN OR SUPPORT WITH METALLIC PLATING | US14903903 | 2014-07-09 | US20160158964A1 | 2016-06-09 | Michael S. Miarecki; Joseph Parkos; Gary M. Lomasney; Charles R. Watson |
| A method for fabricating a ceramic component is disclosed. The method may comprise: 1) forming a polymer template having a shape that is an inverse of a shape of the ceramic component, 2) placing the polymer template in a mold; 3) injecting the polymer template with a ceramic slurry, 4) firing the ceramic slurry at a temperature to produce a green body, and 5) sintering the green body at an elevated temperature to provide the ceramic component. | ||||||
| 137 | AIR VEHICLE WITH CONTROL SYSTEM MECHANICAL COUPLER | US14451696 | 2014-08-05 | US20160040967A1 | 2016-02-11 | Bruce E. Morgan; Stevie Alejandro; Jerry D. Robichaux; Alfredo Ramos; Heinz D. Klemm; Bryan W. Nickel; Andrew P. Douglas |
| An air vehicle, such as a munition like a guided bomb or missile, has a control system that allows control surfaces to be mechanically uncoupled from one or more actuators to allow the control surfaces to freely move (rotate) relative to a fuselage of the vehicle, for example allowing the control surfaces to “weather vane” by assuming an orientation corresponding to the direction of airflow past the air vehicle (direction of airflow relative to the air vehicle). When active positioning of the control surfaces is desired, the control surfaces may be mechanically coupled to one or more actuators that are used to position the control surfaces. The selective coupling of the actuator(s) and the control surfaces may be accomplished by selectively coupling together a sleeve that is mechanically coupled to the control surfaces, and a nut that moves along a shaft of an actuator, for example using a resilient device. | ||||||
| 138 | PASSIVE STABILITY SYSTEM FOR A VEHICLE MOVING THROUGH A FLUID | US14306772 | 2014-06-17 | US20150362301A1 | 2015-12-17 | David A. Corder; Paul A. Merems |
| A stability system for a vehicle moving through a fluid includes stabilizers each having a drive surface that follows the position of the fluid stream perceived by the vehicle. The movement of the drive surface positions control surfaces of the stabilizers, which are coupled to the drive surfaces by mechanical linkages. Lift forces on the drive surfaces provide the force that is used in positioning the control surfaces. The deflection of the control surfaces provides a force on the vehicle that affects stability of the vehicle, for instance in making an inherently unstable vehicle more stable. The stability system may work completely passively, without any active control, and without the need for power to operate it. | ||||||
| 139 | Rocket-propelled grenade | US12914803 | 2010-10-28 | US09068807B1 | 2015-06-30 | Toby D. Thomas; Richard L. Green; Jonathan H. Record; Robbie S. Strauch; David L. Hunn |
| 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. | ||||||
| 140 | Cavity flow shock oscillation damping mechanism | US12623412 | 2009-11-21 | US08436284B1 | 2013-05-07 | David J. Kirshman; David A. Deamer |
| A pressure oscillation damping mechanism comprises a cavity having an entrance exposed to fluid flowing on an exterior of the cavity. The damping mechanism may include a constriction positioned adjacent to the entrance and being sized to dampen an amplitude of the pressure oscillations occurring within the cavity. | ||||||
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