| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 101 | System and method for minimizing wave drag through bilaterally asymmetric design | US13687483 | 2012-11-28 | US08979018B2 | 2015-03-17 | William Pflug; Brian J. Tillotson |
| An air vehicle having a bilaterally asymmetric configuration for reducing wave drag may include a body having a longitudinal axis. The air vehicle may further include longitudinally offset engine nacelles, asymmetrically lengthened engine nacelles, and/or longitudinally offset protruding aerodynamic surfaces for reducing wave drag. | ||||||
| 102 | Conductive multilayer stack, coated substrates including the same, and methods of making the same | US13631773 | 2012-09-28 | US08956730B2 | 2015-02-17 | Krishna K. Uprety; Alexander Bimanand; Khushroo H. Lakdawala |
| An electrically conductive multilayer stack including a first metal oxide layer including titanium oxide, a metal layer on the first metal oxide layer, and a second metal oxide layer including titanium oxide on the metal layer, at least one of the first metal oxide layer and the second metal oxide layer including a first region, a second region on the first region, and a third region on the second region, the first region and the third region each having a higher oxygen concentration than that of the second region is disclosed. Methods of manufacturing an electrically conductive multilayer stack are also disclosed. | ||||||
| 103 | PROTECTIVE MATERIAL ARRANGEMENT | US14358779 | 2012-11-06 | US20140311327A1 | 2014-10-23 | Michael Dunleavy; Sajad Haq; Caroline Joleen Morley |
| According to the invention there is provided an arrangement of protective material for dissipating the kinetic energy of a moving object including one or more layers of fibrous armour material encased within a sealed encasement, in which the sealed encasement is formed from a textile armour material which is impregnated with a polymeric substance. | ||||||
| 104 | WEAPON INTERFACE SYSTEM AND DELIVERY PLATFORM EMPLOYING THE SAME | US13975609 | 2013-08-26 | US20140230637A1 | 2014-08-21 | Steven D. Roemerman; John P. Volpi; Joseph Edward Tepera |
| A weapon interface system, and methods of operating the same. The weapon interface system is coupled to an electrical interconnection system of a delivery platform and a weapon system coupled to a rack system. The weapon interface system includes a translation interface configured to provide an interface between the electrical interconnection system and an inductive power and data circuit. The weapon interface system also includes a weapon coupler, coupled to the translation interface, configured to provide an inductive coupling to the weapon system to provide mission information thereto. | ||||||
| 105 | Temporarily installed aircraft observer door plug, chair, sonotube ejection and control system | US12734158 | 2008-10-15 | US08807482B2 | 2014-08-19 | Richard Woodland; Ross James Neyedly |
| The system and apparatus of the present invention is generally comprised of a non-dedicated, temporarily-installed, aircraft observer bubble door, chair, sonotube ejection system, mission electronics LRU rack and workstation assembly which are affixed to the Air Deployment System (ADS) rails, cargo tie down “D” rings, seat belt restraint ring bolt sockets, and litter bar of a host aircraft, thereby precluding the requirement for dedicated airframe modifications. One embodiment of the present invention also utilizes a multi-axis, articulated, foldable chair temporarily-installed in conjunction with a segmented or one piece pressurized observer bubble door plug and door retraction system. Once installed the subject apparatus can be stowed outboard of the fuselage cargo transit envelope to permit use of the ADS rail system in-flight, without affecting normal air drop operations, crew egress, the flight performance envelope, or emergency procedures of the host aircraft. | ||||||
| 106 | SYSTEM AND METHOD FOR MINIMIZING WAVE DRAG THROUGH BILATERALLY ASYMMETRIC DESIGN | US13687483 | 2012-11-28 | US20140145040A1 | 2014-05-29 | William Pflug; Brian J. Tillotson |
| An air vehicle having a bilaterally asymmetric configuration may include a body having a longitudinal axis. The air vehicle may further include longitudinally offset engine nacelles, asymmetrically lengthened engine nacelles, and/or longitudinally offset protruding aerodynamic surfaces. | ||||||
| 107 | CONDUCTIVE MULTILAYER STACK, COATED SUBSTRATES INCLUDING THE SAME, AND METHODS OF MAKING THE SAME | US13631773 | 2012-09-28 | US20140093696A1 | 2014-04-03 | Krishna K. Uprety; Alexander Bimanand; Khushroo H. Lakdawala |
| An electrically conductive multilayer stack including a first metal oxide layer including titanium oxide, a metal layer on the first metal oxide layer, and a second metal oxide layer including titanium oxide on the metal layer, at least one of the first metal oxide layer and the second metal oxide layer including a first region, a second region on the first region, and a third region on the second region, the first region and the third region each having a higher oxygen concentration than that of the second region is disclosed. Methods of manufacturing an electrically conductive multilayer stack are also disclosed. | ||||||
| 108 | Bomb Rack Lock | US13532446 | 2012-06-25 | US20140007757A1 | 2014-01-09 | Roy P. McMahon; Michael R. Hlavek; Andrew L. Nelson |
| A bomb rack lock, as part of a bomb rack, comprising a plunger movable to engage a bomb rack linkage to be alternately secured and released and a solenoid body coupled to and operable to support the plunger. The plunger and the solenoid body are movable relative to each other and the bomb rack linkage and the solenoid body is movable between a first position and a second position. The bomb rack lock also includes a sensor to determine whether the solenoid body is in the first position. The plunger is movable to engage and disengage the bomb rack linkage with the solenoid body in the first position. In the second position, the solenoid body prevents engagement between the plunger and the bomb rack linkage. | ||||||
| 109 | Ducted fan VTOL vehicles | US12938444 | 2010-11-03 | US08622335B2 | 2014-01-07 | Raphael Yoeli |
| A vehicle including a fuselage having a longitudinal axis and a transverse axis, two Ducted Fan lift-producing propellers carried by the fuselage on each side of the transverse axis, a pilot's compartment formed in the fuselage between the lift-producing propellers and substantially aligned with one side of the fuselage, a payload bay formed in the fuselage between the lift-producing propellers and opposite the pilot's compartment, and two pusher fans located at the rear of the vehicle. Many variations are described enabling the vehicle to be used not only as a VTOL vehicle, but also as a multi-function utility vehicle for performing many diverse functions including hovercraft and ATV functions. Also described is an Unmanned version of the vehicle. Also described are unique features applicable in any single or multiple ducted fans and VTOL vehicles. | ||||||
| 110 | Arrangement for storing and launching payloads | US13266062 | 2009-04-23 | US08549976B2 | 2013-10-08 | Christer Zätterqvist |
| An arrangement for storing and launching payloads. An elongate body includes at least one launch opening. The elongate body is configured to store the payloads in compartments. The compartments include openings. The arrangement is configured to be mounted on a vehicle with a longitudinal direction of the elongate body essentially coinciding with a direction of motion of the vehicle. The elongate body includes deflectors configured to act on an air stream and to permanently create an air covering layer across and over the compartment openings during use. | ||||||
| 111 | De-mold liner based injection tool | US13096370 | 2011-04-28 | US08439663B2 | 2013-05-14 | Rick A. Luepke; Matthew A. Sodergren |
| A mold apparatus comprising a release liner removably securable to a mold tool face by a liner vacuum system configured to hold the release liner in place against the tool face, the liner vacuum system comprising at least one liner vacuum port extending and providing fluid communication between the mold face and a vacuum source. The liner vacuum system is actuable to hold the release liner in place against the tool face in advance of and during material injection and during curing and may be further actuable to subsequently release the tool from the liner, leaving the release liner to be peeled from the cured material. | ||||||
| 112 | Gunner Accessory Package | US13250852 | 2011-09-30 | US20130081534A1 | 2013-04-04 | Kyle L. Greenwood; Devin Gerland |
| A protected firing platform protection system protects personnel from contact with the protected firing platform. In an embodiment, the protected firing platform protection system is adapted for use with a protected firing platform of a military vehicle. The protected firing platform protection system includes a blanket. The blanket has a carrier and a protective insert. The carrier has an interior. The protective insert is disposed in the interior. The blanket is attached to the protected firing platform. | ||||||
| 113 | SYSTEM, A METHOD AND A COMPUTER PROGRAM PRODUCT FOR REDUCING DAMAGE BY MISSILES | US13246429 | 2011-09-27 | US20120222545A1 | 2012-09-06 | Shaul Eliahou NIV |
| Provided is a system for reducing damage by missiles to a vehicle, the system including: (a) a detector operable to detect a missile and to generate detection information indicative of a motion of the missile; (b) a processor, configured to analyze the detection information and to selectively trigger activation of a jetting system that is mounted on the vehicle in response to a result of the analysis; and (c) the jetting system, operable to jet a high pressure jet onto the missile. | ||||||
| 114 | Predicting aerodynamic impacts for small appendages (IRCM installation) on large fixed wing aircraft using computational fluid dynamics | US12350601 | 2009-01-08 | US08249843B1 | 2012-08-21 | Peter Q. Gendron; Michael R. Mendenhall |
| A method for predicting aerodynamic impact for small appendages on aircraft, wherein the improvement comprises using an adaptable computational fluid dynamic model of airflow adjacent the appendage by isolating a patch surrounding the small appendage, measuring the load on the patch without the appendage in place and with the appendage in a place and subtracting the two for increasing computational accuracy of the load predictions for the small appendage to be able to measure the effect of the small appendage. | ||||||
| 115 | Wireless Precision Avionics Kit | US12966478 | 2010-12-13 | US20120150365A1 | 2012-06-14 | Barry A. Maxwell; James R. Adamek; James D. Walert; George Stern; George W. Pigg |
| A wireless precision avionics kit is provided for retrofitting aircraft to facilitate communication between the cockpit and modern military stores without hardware or software modifications to the aircraft. The store includes an electrical interface that requires data and possibly power from the aircraft and provides for communication via a message set. The kit may be used with any aircraft that provides a rack or pylon for mounting the store and the capability to release the store. The kit may be used with aircraft having no existing capability to communicate with smart stores, with aircraft having an incompatible interface for modern stores or even with aircraft that have a compatible hardware interface for which the software is outdated. | ||||||
| 116 | ARRANGEMENT FOR STORING AND LAUNCHING PAYLOADS | US13266062 | 2009-04-23 | US20120125183A1 | 2012-05-24 | Christer Zätterqvist |
| An arrangement for storing and launching payloads. An elongate body includes at least one launch opening. The elongate body is configured to store the payloads in compartments. The compartments include openings. The arrangement is configured to be mounted on a vehicle with a longitudinal direction of the elongate body essentially coinciding with a direction of motion of the vehicle. The elongate body includes deflectors configured to act on an air stream and to permanently create an air covering layer across and over the compartment openings during use. | ||||||
| 117 | ARRANGEMENT AT AN AIRCRAFT OF A DISPENSER UNIT FOR COUNTERMEASURES | US13144962 | 2009-01-16 | US20120018581A1 | 2012-01-26 | Robert Melin |
| An arrangement at an aircraft of a dispenser unit for countermeasures. The arrangement including a wall of an aircraft fuselage. A dispensing nozzle is arranged on the dispenser unit through which the countermeasures are dispensed. The dispenser unit is arranged within the aircraft fuselage. An aperture for dispensing the countermeasures is arranged in the wall of the aircraft fuselage. The aperture is arranged to substantially coincide with the dispensing nozzle. | ||||||
| 118 | JETTISONABLE ARMOR | US12682408 | 2007-10-11 | US20110252954A1 | 2011-10-20 | Martin Peryea; Jon Stewart Tatro |
| An aircraft has an armor releasably attached to the body of an aircraft, an actuator connecting the armor to the body of the aircraft, and a control that, upon operation, actuates the actuator to release the armor from the body. | ||||||
| 119 | ARRANGEMENT AND METHOD FOR LAUNCHING COUNTER-MEASURES | US12995294 | 2008-05-30 | US20110155856A1 | 2011-06-30 | Björn Zachrisson |
| A method for launching counter-measures from a launch opening of a dispenser mounted on an aeroplane. The counter-measures are launched in a direction obliquely forwards and downwards relative to the aeroplane. In order to facilitate launching of counter-measures, a low dynamic pressure is created permanently across the launch opening of the dispenser by a fixed element acting on the air stream. An arrangement for storing and launching counter-measures including an elongate body provided with at least one launch opening used for storing the counter-measures in compartments. The arrangement is designed to be mounted on an aeroplane with the longitudinal direction of the elongate body essentially coinciding with the flight direction of the aeroplane. The counter-measures are connected to a firing control unit for feeding firing signals to the counter-measures. The arrangement is designed to be mounted under the aeroplane. The compartments include openings and are intended for launching the counter-measures in a direction obliquely forwards and downwards relative to the aeroplane. | ||||||
| 120 | Energy absorbing impact band and method | US11790144 | 2007-04-24 | US07866605B2 | 2011-01-11 | Timothy J. Lee; Jason L. Firko; Jonathan W. Gabrys |
| An energy absorbing apparatus and system for leading edge structures includes an impact member, such as a “bird-band”, of a plastically deformable material of a predetermined configuration positioned with the structure in an area of the leading edge of the structure to absorb energy of an impact of a projectile with the leading edge of the structure, and to redistribute the energy of the impact to the structure, and can break up the projectile, and can increase the impact area. The structure can have one or more sheet members, such as a single sheet, or an inner face sheet and an outer face sheet with a core positioned between the inner face sheet and the outer face sheet. One or more impact members of the plastically deformable material can be positioned with one or more of the single sheet, the inner face sheet, the outer face sheet or the core. | ||||||
QQ群二维码
意见反馈
意见反馈