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 |
|---|---|---|---|---|---|---|
| 61 | Aerodynamically stabilized projectile system for use against underwater objects | US993544 | 1997-12-18 | US5929370A | 1999-07-27 | Jeffrey A. Brown; Reed Copsey; Marshall Tulin; Roy Kline |
| A projectile is propelled from a location in air, through an air/water interface, and toward a submerged underwater object. The projectile includes a forward end that forms a cavitation void around the projectile in water, avoiding water drag on the remainder of the projectile. The projectile further includes an outwardly flared or finned rearward end that aerodynamically stabilizes the projectile in air and flare stabilizes it in water, in each case against yaw. | ||||||
| 62 | Method for reducing dispersion in gun launched projectiles | US221127 | 1994-03-31 | US5375792A | 1994-12-27 | John C. Grau |
| Disclosed is a method for reducing dispersion in gun launched projectiles.n axial thrust is applied to the projectile at a specific time in the yaw cycle to cancel the effect of aerodynamic jump which arises from the effect of yawing motion disturbance created by an initial disturbance. | ||||||
| 63 | Aerodynamically compliant projectile nose | US409900 | 1989-09-20 | US4998994A | 1991-03-12 | Edward M. Schmidt; William F. Donovan |
| A high velocity aerodynamic projectile having a central body with a forwardnd, a rearward end and a longitudinal axis, the forward end of the body has a pedestal coaxially extending outward from the body. The projectile has aft stabilizing fins or a flare rigidly affixed at its rearward end and a forward stablizing means pivotably attached to the pedestal of the central body. The forward stabilizing means consists of a self-aligning projectile nose having its rearward end separated from the forward end of the projectile's central body so as to allow the self-aligning projectile nose to pivot and align with the oncoming air stream. | ||||||
| 64 | Projectile stabilizer | US820482 | 1986-01-03 | USH112H | 1986-08-05 | William F. Donovan; Michael Nusca |
| A projectile comprises a nose ogive tapering outwardly to a cylindrical oronical body portion of caliber diameter. A reversely tapering stabilizer is connected to the rear of the body portion and is terminated at a tail stabilizer which tapers outwardly in the same direction as the nose ogive. The largest diameter of the tail stabilizer is at most equal to and preferably less than the caliber. Aerodynamic stabilization is thus achieved without the use of a sabot or complex stabilizer fin deployment mechanisms. | ||||||
| 65 | Infantry projectile | US637669 | 1975-12-02 | US4228973A | 1980-10-21 | Peter Klein |
| An infantry projectile includes an elongated projectile body having a cylindrical or frusto-conical surface concentrically arranged about its longitudinal axis. The projectile body has a leading end and a trailing end each extending transversely of the longitudinal axis. The leading end is disposed at an oblique angle to the longitudinal axis for affording a trimming action on the projectile when it is in flight. A flow control projection is provided on the surface of the projectile body between its ends so that the aerodynamic center of the projectile is located below its center of gravity when the flow control projection is located on the lower surface of the projectile body and in a vertical plane extending through the longitudinal axis of the body. | ||||||
| 66 | Deployable aerodynamic ring stabilizer | US3724782D | 1971-07-22 | US3724782A | 1973-04-03 | GAUZZA H; HORANOFF E |
| A foldable ring assembly for the aerodynamic stabilization of missiles. The ring assembly includes a plurality of arcuate segments pivotally interconnected by hinges between adjacent segments. Each segment is supported on the missile by a radial strut which is pivotally connected to both the missile and the segment. When in a missile launch tube, the struts are held in positions tangential to the missile and the interleaved segments partially overlap one another in close proximity to the missile case. Upon exit from the tube, torsion springs rotate the struts into radial positions causing the arcuate segments to unfold into a complete ring concentrically positioned around the missile.
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| 67 | Stabilizing retarder for bombs | US42951842 | 1942-02-04 | US2368258A | 1945-01-30 | MANSON FRANK G; MASKEY JAMES J |
| 68 | A w jld | US1663899D | US1663899A | 1928-03-27 | ||
| 69 | HIGH-MODULUS COATING FOR LOCAL STIFFENING OF AIRFOIL TRAILING EDGES | PCT/US2014045929 | 2014-07-09 | WO2015053832A3 | 2015-06-18 | TWELVES WENDELL V; COOK III GRANT O |
| An airfoil is disclosed. The airfoil may comprise a leading edge, a body portion and a trailing edge formed from a high-modulus plating. The body portion of the airfoil may be formed from a material having a lower elastic modulus than the high-modulus plating. The high-modulus plating may improve the stiffness of the trailing edge, allowing for thinner trailing edges with improved fatigue life to be formed. | ||||||
| 70 | Aircraft and missile forebody flow control device and method of controlling flow | US13151640 | 2011-06-02 | US10137979B1 | 2018-11-27 | Troy Prince; Frederick J. Lisy; Mehul P. Patel; Jack M. DiCocco; Reed Carver; Robert N. Schmidt |
| A forebody flow control system and more particularly an aircraft or missile flow control system for enhanced maneuverability and stabilization at high angles of attack. The present invention further relates to a method of operating the flow control system. In one embodiment, the present invention includes a missile or aircraft comprising an afterbody and a forebody; at least one deployable flow effector on the missile or aircraft forebody; at least one sensors each having a signal associated therewith, the at least one sensor being used for determining or estimating flow separation or side forces on the missile forebody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one deployable flow effector based on at least in part the signal of the at least one sensor. | ||||||
| 71 | QUICK-DETACHABLE MULTI-PURPOSE ACCESSORY MOUNTING PLATFORM | US15995446 | 2018-06-01 | US20180299237A1 | 2018-10-18 | Darrel R. Barnette |
| Accessories may be mounted using a quick-detachable multi-purpose accessory mounting platform. The platform may include one or more clamps to receive an object, such as a firearm. The platform also may include at least one recessed mounting pad, at least one rear shelf, and other surfaces to provide different mounting points for accessories. | ||||||
| 72 | CALIBER SHELL WITH RIGID MOUNTING TO HOUSING OF STABILIZING FINS | US15321018 | 2014-08-26 | US20170205213A1 | 2017-07-20 | RENAT ABDULBEROVICH YUSUPOV |
| The invention relates to ammunition for firearms, as smooth and a rifled barrel. The projectile with rigid attached to the housing stabilizing fletching block, plates of fletching block have a continuation on the housing, centering the projectile in the barrel. In the offered variant, on the friction and heat of the bullet and the barrel takes about 1% of the shot energy, besides low vibration. The rest of energy escapes to destination, and that's good. Erasing minimal of the barrel. Application of the projectile in the shotgun and rifle barrels increases the service life of barrels. Use of such projectiles increases the initial speed, and with the sleeve-nozzle and a second charge, allows to increase the speed and specialization of the projectile. At the expense of the aerodynamic and gyroscopic effects, increases the lethal effect over long distances, due to the greater energy saved, improve the close grouping of shots and flat trajectory. | ||||||
| 73 | Air vehicle with control system mechanical coupler | US14451696 | 2014-08-05 | US09546853B2 | 2017-01-17 | 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. | ||||||
| 74 | Tactical missile and balance weight for said missile | US14384836 | 2013-03-18 | US09441929B2 | 2016-09-13 | Patrick Barthelemy; Phillippe Dubois; Laurent Carton; Nicholas Sibillaud; Marc Ferrat; Frederic Paintendre |
| According to the invention, the balance weights of the missile are made from pellets whereof the particle size is at most equal to 1 mm which is enclosed in a closed package. | ||||||
| 75 | VENTED PLATED POLYMER | US14903898 | 2014-07-09 | US20160251760A1 | 2016-09-01 | Glenn Levasseur; Joseph Parkos; Grant O. Cook; Charles R. Watson |
| A vented plated polymer component is disclosed. The vented plated polymer component may comprise a polymer substrate, a metal plating deposited on a surface of the polymer substrate, and at least one vent formed through the metal plating. The at least one vent may extend from an outer surface of the metal plating to the surface of the polymer substrate, and it may be sized to allow an escape of a gas from the polymer substrate to an external environment surrounding the plated polymer component. | ||||||
| 76 | Flow control device and method for aircraft and missile forebody | US12615218 | 2009-11-09 | US09429400B1 | 2016-08-30 | Zak Sowle; Srikanth Vasudevan; Russell Stucke; Frederick J. Lisy; Robert N. Schmidt |
| A forebody flow control system and more particularly an aircraft or missile flow control system for enhanced maneuverability and stabilization utilizes various types of sensors and various types of activatable flow effectors to maneuver the aircraft or missile with the help of a control system. A method of operating the flow control system is also disclosed. | ||||||
| 77 | Hunting arrow having one release passage | US14545206 | 2015-04-06 | US09383177B1 | 2016-07-05 | Kim Eric Kallmes |
| A hunting arrow having an interior passage that permits both air and blood to flow freely therethrough. A broadhead at the front of the arrow has an intake opening that permits the flow to enter a tubular shaft of the arrow, and a nock at the rear has a discharge opening that permits the air and blood to exit the shaft. The blades of the broadhead are radially spaced to permit air and blood to enter the intake opening. The nock includes internal vanes that react with the flow of air exiting the discharge opening to impart rotation to the arrow. The nock also includes vents that allow a portion of the air to escape so as to react with channels on the exterior of the nock to further stabilize the arrow during flight. | ||||||
| 78 | SHELL | US14728093 | 2015-06-02 | US20160187112A1 | 2016-06-30 | 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. | ||||||
| 79 | INTERLOCKED PLATED POLYMERS | US14903861 | 2014-07-09 | US20160160353A1 | 2016-06-09 | Michael S. Miarecki; Charles R. Watson; Grant O. Cook; Joseph Parkos |
| A plated polymer component is disclosed. The plated polymer component may comprise a polymer substrate having an outer surface, a metal plating attached to the outer surface of the polymer substrate, and at least one interlocking feature connecting the polymer substrate and the metal plating. The interlocking feature may improve the interfacial bond strength between the polymer substrate and the metal plating. | ||||||
| 80 | Method for automatically managing a pitch rate gyroscope mounted on a flying device | US14115999 | 2012-05-09 | US09086284B2 | 2015-07-21 | François De Picciotto |
| The invention relates to a flying device (1), in particular an air missile, which is of the inertial navigation type, which is rotatable and includes a pitch rate gyroscope (2), wherein said device also comprises automatic control means (8) for rotating same about the longitudinal axis (3) thereof, regularly alternating the direction of rotation, so as to cancel the effect of the scale factor of the pitch rate gyroscope (2), in addition to correcting ordinary drifts. | ||||||
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