| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 181 | Multifunctional pod for an aircraft | US15082219 | 2016-03-28 | US10086941B2 | 2018-10-02 | Horst Christof |
| A multifunctional pod for an aircraft has at least two separate regions. At least one first region of the pod is provided for receiving fuel. A second region of the pod includes at least one receiving device for releasably attaching at least one additional load. The additional load can be releasably attached to the receiving device via a loading opening on the side of the pod facing away from the aircraft. | ||||||
| 182 | MODULAR CONTAINER TRANSPORT SYSTEMS | US15884288 | 2018-01-30 | US20180194548A1 | 2018-07-12 | Elie Helou, JR. |
| Disclosed are apparatus, systems, and methods, including a cargo transport system comprising a spine assembly, a container assembly, and an outer fairing. The spine assembly comprises a rigid spine and a plurality of mounts arranged on the rigid spine in a plurality of mount rows. The container assembly comprises a plurality of containers secured to the spine assembly using at least a subset of the plurality of mounts. The outer fairing at least partially encloses the container assembly. Each container of the plurality of containers comprises a plurality of fittings for securing the container to the spine assembly and/or another container of the container assembly. The container assembly is enclosed within a pressurization space for pressurizing the container assembly. | ||||||
| 183 | DEVICE AND METHOD FOR CONTROLLING FLUID FLOW OVER AN OPTICAL INSTRUMENT | US15381166 | 2016-12-16 | US20180172040A1 | 2018-06-21 | Kirk A. Miller; Mauricio A. Salinas; Dustin Hamill |
| A device is provided for controlling fluid flow over a window of a movable optical instrument housing. The device includes a generally annular body having an inner peripheral edge configured to correspond to a peripheral edge of the window of the housing and an outer peripheral edge, an arcuate outer surface disposed between the inner peripheral edge and the outer peripheral edge, and a reduced width portion between the inner peripheral edge and the outer peripheral edge. The reduced width portion is configured to lower elevation torque. Other embodiments of the device and methods for controlling fluid flow are further disclosed. | ||||||
| 184 | Modular Payload Systems for Aircraft | US15270053 | 2016-09-20 | US20180079482A1 | 2018-03-22 | Steven Ray Ivans; Brent Chadwick Ross |
| A modular payload system for an aircraft includes a modular bay recessed within the aircraft. The modular bay includes a modular bay interface. The modular payload system includes a plurality of payload modules each having a respective function and a payload interface adapted to connect to at least a portion of the modular bay interface. The plurality of payload modules are interchangeably insertable into the modular bay to enable the modular bay to support the functions of the plurality of payload modules. | ||||||
| 185 | INTEGRATED DETACHABLE BALLISTIC SHIELD | US15704114 | 2017-09-14 | US20180072423A1 | 2018-03-15 | Iker VÉLEZ DE MENDIZÁBAL ALONSO; Esteban MARTINO GONZÁLEZ; Carlos GARCÍA NIETO; Edouard MENARD; Enrique GUINALDO FERNÁNDEZ; Soledad CRESPO PEÑA; Jesús Javier VÁZQUEZ CASTRO |
| A lightweight shield for aircraft protection against threat of high energy impacts, which comprises, a structural layer that has a first side and a second side, the first side being intended for receiving the impact, and a ballistic material layer for absorbing high energy impacts, having a first side and a second side. The first side of the ballistic material layer is faced to the second side of structural layer and joined to the structural layer via a progressively detachable interface and, the second side of the ballistic material layer is a free surface. | ||||||
| 186 | UNMANNED AERIAL VEHICLE WITH DEPLOYABLE TRANSMIT/RECEIVE MODULE APPARATUS WITH RAMJET | US15165663 | 2016-05-26 | US20170343645A1 | 2017-11-30 | Inyoung Daniel Kim; Ryan S. Wilson |
| A system for bistatic radar target detection employs an unmanned aerial vehicle (UAV) having a ramjet providing supersonic cruise of the UAV. Deployable antenna arms support a passive radar receiver for bistatic reception of reflected radar pulses. The UAV operates with a UAV flight profile in airspace beyond a radar range limit. The deployable antenna arms have a first retracted position for supersonic cruise and are adapted for deployment to a second extended position acting as an airbrake and providing boresight alignment of the radar receiver. A mothership aircraft has a radar transmitter for transmitting radar pulses and operates with an aircraft flight profile outside the radar range limit. A communications data link operably interconnects the UAV and the tactical mothership aircraft, transmitting data produced by the bistatic reception of reflected radar pulses in the UAV radar antenna to the mothership aircraft. | ||||||
| 187 | AIRCRAFT FORCE MULTIPLICATION | US15057574 | 2016-03-01 | US20170254622A1 | 2017-09-07 | David W. Evans; Gregory L. Larson; Jeffrey M. Yang |
| A manned aircraft and unmanned aerial vehicles (UAVs) fly on a mission as a team. The UAVs carry additional weapons and/or munitions that can be controlled by the manned aircraft. The pilot of the manned aircraft selects weapons or munitions carried by either the manned aircraft or one of the UAVs. A display in the manned aircraft illustrates weapons available on both the manned aircraft and UAVs. The pilot of the manned aircraft picks a weapon from the display and then targets and fires the weapon. The targeting and guidance of the weapon can be carried out using computers on the manned aircraft and/or computers on the UAV. | ||||||
| 188 | Armor system | US14428999 | 2013-09-23 | US09709363B2 | 2017-07-18 | Hananya Cohen; Edwin Cohen |
| An armor system pellet is provided. The pellet includes a pellet body attached to four projections for interlocking adjacent pellets when arranged in an array. The pellet is configured such that the width of a first pair of co-linear projections is less than a width of a second pair of co-linear projections. | ||||||
| 189 | Rotating window and radome for surveillance pod | US14173008 | 2014-02-05 | US09575169B2 | 2017-02-21 | Peter Colantonio |
| A pod has a rotatable housing and a motor for driving the rotatable housing to rotate. The rotatable housing includes an image capture device for capturing an electromagnetic image and a radar transmitting and capturing device for capturing a radar image. The motor is operable to change an orientation of the rotatable housing relative to a pod housing, such that a desired one of the electromagnetic image capture device and the radar transmission and reception system faces an area that is to be studied. A method is also disclosed. | ||||||
| 190 | Weapon interface system and delivery platform employing the same | US13975609 | 2013-08-26 | US09550568B2 | 2017-01-24 | 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. | ||||||
| 191 | Coating composition for coated substrates and methods of making the same | US13843213 | 2013-03-15 | US09546300B2 | 2017-01-17 | Alexander Bimanand; Krishna K. Uprety; Khushroo H. Lakdawala |
| A coating composition including a hydrophobic first aliphatic polyisocyanate, a second aliphatic polyisocyanate including a hydrophilic portion, a polyester polyol, a hydrophilic polyol, and a fluorinated polyol compound is disclosed. A coated substrate including a topcoat including the composition is also disclosed. Methods of forming the topcoat on a substrate are also disclosed. | ||||||
| 192 | DUAL-MODE FORMATION-LIGHT SYSTEM | US14746270 | 2015-06-22 | US20160368620A1 | 2016-12-22 | Philippe Lapujade |
| A dual-mode aviation formation-light system has an array of paired visible-light and infrared-light elements. Each pair can be commonly orientated such that, in a non-covert mode, a hemispherical light pattern is emitted by each visible-light element, while in a covert mode, a body of each visible-light element obstructs a solid-angle portion of infrared-light emitted from its paired infrared-light element and prevents transmission therethrough. In some embodiments, the body is substantially opaque to the infrared light. When affixed to a lateral-facing side of an aircraft body, the infrared-light obstruction can be directional. Directional obstruction can prevent an observer on a ground surface from detecting infrared-light emission from an aircraft in the sky above. An exemplary dual-mode aviation-formation lighting system can provide both covert and non-covert lighting signals to adjacent aircraft, while advantageously obscuring ground directed infrared-light emission in a covert mode. | ||||||
| 193 | Bilaterally asymmetric design for minimizing wave drag | US14628218 | 2015-02-21 | US09522727B2 | 2016-12-20 | William Pflug; Brian J. Tillotson |
| An air vehicle may include a body having forwardly-swept fixed wings or unswept fixed wings. The body may have a longitudinal axis continuously oriented parallel to a forward flight direction when the air vehicle is in flight. The air vehicle may include at least one of the following components being mounted on opposite sides of the body: longitudinally offset engine nacelles, asymmetrically lengthened engine nacelles, and longitudinally offset protruding aerodynamic surfaces comprising at least one of stabilizers, canards, empennage control surfaces, external stores, and high aspect ratio wings. | ||||||
| 194 | MULTIFUNCTIONAL POD FOR AN AIRCRAFT | US15082219 | 2016-03-28 | US20160288906A1 | 2016-10-06 | Horst Christof |
| A multifunctional pod for an aircraft has at least two separate regions. At least one first region of the pod is provided for receiving fuel. A second region of the pod includes at least one receiving device for releasably attaching at least one additional load. The additional load can be releasably attached to the receiving device via a loading opening on the side of the pod facing away from the aircraft. | ||||||
| 195 | ROTATING WINDOW AND RADOME FOR SURVEILLANCE POD | US14173008 | 2014-02-05 | US20160223664A1 | 2016-08-04 | Peter Colantonio |
| A pod has a rotatable housing and a motor for driving the rotatable housing to rotate. The rotatable housing includes an image capture device for capturing an electromagnetic image and a radar transmitting and capturing device for capturing a radar image. The motor is operable to change an orientation of the rotatable housing relative to a pod housing, such that a desired one of the electromagnetic image capture device and the radar transmission and reception system faces an area that is to be studied. A method is also disclosed. | ||||||
| 196 | DOME COATING FOR COUNTERMEASURE ANTI-ICING FUNCTIONALITY | US14942199 | 2015-11-16 | US20160223392A1 | 2016-08-04 | Michael J. Powers; Donald K. Smith |
| An infrared countermeasure system comprises a transparent infrared camera dome with an anti-icing surface coating. | ||||||
| 197 | Stealth aerial vehicle | US13490593 | 2012-06-07 | US09387930B2 | 2016-07-12 | Jochen Dornwald; Bartholomaeus Bichler |
| An aerial vehicle having a low radar signature includes a first side on which turbine openings, and payload bays or landing gear bays are disposed. A second side of the aerial vehicle is designed to have a smaller radar signature than the first side. | ||||||
| 198 | Aircraft with improved aerodynamic performance | US13985522 | 2011-05-30 | US09284046B2 | 2016-03-15 | Massimo Lucchesini; Emanuele Merlo |
| An aircraft (10) with improved aerodynamic performances is adapted to keep the directional stability and a very good aerodynamic behavior at medium-high incidence. The aircraft (10) includes a fuselage (12) to which shaped wings (18, 20) are associated, and a nose (52). The aircraft (10) also includes a vortex control device (72) of the extension of the leading edge of the wing at the root (LERX), shaped in order to symmetrize the bursting of the vortices generated by such LERX with a medium-high incidence. Said aircraft comprises removable equipment with at least one dissipation device of incident radar waves, on at least one hot portion of the aircraft. | ||||||
| 199 | Stealth Aerial Vehicle | US13490593 | 2012-06-07 | US20150375862A1 | 2015-12-31 | Jochen DORNWALD; Bartholomaeus Bichler |
| An aerial vehicle having a low radar signature includes a first side on which turbine openings, and payload bays or landing gear bays are disposed. A second side of the aerial vehicle is designed to have a smaller radar signature than the first side. | ||||||
| 200 | On-board passive protection device | US13919535 | 2013-06-17 | US09188411B2 | 2015-11-17 | Soenke Jacobsen |
| In order to provide additional safety measurements for protection on-board a vehicle, a mobile on-board passive protection device for use on-board of a vehicle is provided. The mobile passive protection device comprises side panels and a top and a bottom panel, which panels are enclosing at least one stowage compartment, a plurality of castors for providing movability on-board a vehicle, and a support structure for connecting the castors and the panels. At least one of the side panels is provided with a bullet-protection layer. | ||||||
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