| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 141 | HIGH ALTITUDE AIRCRAFT WING GEOMETRY | US15554755 | 2016-03-02 | US20180053991A1 | 2018-02-22 | Peter DAVIDSON; Reiner KICKERT |
| An unmanned high altitude aircraft operating above 15 km with transmitting and/or receiving antennas, enclosed or more than half enclosed on a projected area basis normal to the plane of the antenna(s), in a wing structure where the chord length of the wing section enclosing the phased arrays or horn antennas is at least 30 percent greater than the mean wing chord length, and the wing surface adjacent to the antenna(s) in the path of the electromagnetic radiation being received or transmitted by the antenna(s) is substantially composed of material relatively transparent to this radiation. | ||||||
| 142 | Aerial vehicle and a signal line protection assembly thereof | US15388439 | 2016-12-22 | US09896195B2 | 2018-02-20 | Di Ou |
| A signal line protection assembly for an aerial vehicle includes a foot stand and a protection sleeve configured to receive a signal line. The foot stand includes a foot stand sleeve. At least a portion of the protection sleeve is received in the foot stand sleeve. | ||||||
| 143 | GROUND MOVEMENT SYSTEM PLUGIN FOR VTOL UAVS | US15555533 | 2016-04-06 | US20180044000A1 | 2018-02-15 | Davide VENTURELLI; Francesca LORENZONI; Roberto NAVCNI |
| A ground movement plug-in (GMP) apparatus for providing ground propulsion to an unmanned aircraft vehicle (UAV). In an embodiment, the GMP apparatus includes a frame configured to mechanically couple with the UAV, a plurality of wheels, at least one of which is actuatable by a motor, and a controller operably coupled to the motor to control propulsion of the GMP apparatus. | ||||||
| 144 | AERIAL VEHICLE WITH DEPLOYABLE COMPONENTS | US15388478 | 2016-12-22 | US20170291684A1 | 2017-10-12 | Nicholas Robert Alley; Joshua Lemming Steele; Jesse Owen Williams; Daniel Kuehme; Jonathan Caleb Phillips |
| An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement. | ||||||
| 145 | Polyurea perimeter seal for an aircraft antenna or other aircraft part | US14799144 | 2015-07-14 | US09765888B2 | 2017-09-19 | Jeff Busby; Chad Knight; Kent Boomer; Mike Dry; Matt Boyd |
| A sealant is provided for use on an aircraft or other vehicle. The sealant may be used with a gasket. The sealant is a perimeter seal that comprises a polyurea member. The polyurea member is a self-curing, two-component mix. It may cure to a hardness in the range of about 40 to 100 (Shore A). It may maintain an adequate peel strength to withstand multiple thermal and pressure cycling, and may have a working life, wherein it may be shaped, of less than about eleven minutes. | ||||||
| 146 | STRUCTURAL ASSEMBLY FOR AN AIRCRAFT FUSELAGE WITH DOUBLE CURVATURE INCLUDING FRAMES WITH AN OPTIMIZED ORIENTATION | US15353319 | 2016-11-16 | US20170137106A1 | 2017-05-18 | Daniel BELLET; Philippe BERNADET |
| In order to allow an aircraft fuselage structure to provide optimum resistance to pressurization loads in a fuselage region with a double curvature, the fuselage structure includes a circumferential frame oriented so that the web of the circumferential frame has an orientation close to the local normal to the skin of the fuselage. | ||||||
| 147 | Low profile pass-through electrical connector | US13909061 | 2013-06-03 | US09623975B2 | 2017-04-18 | Brett Burton; Andrew Cox; Darren Wolfe |
| A low profile pass-through electrical connector is designed for aerospace applications. The connector allows voltage and current to pass-thru a conductive wing surface, while maintaining a low profile height for aerodynamic performance considerations. Examples of applications of the electrical connector include power for thin film heaters and communication antennae applications. | ||||||
| 148 | Method of opening a protective dome, in particular a radome, and radome equipped with a pantograph for implementation thereof | US14129500 | 2012-06-26 | US09608320B2 | 2017-03-28 | Jacques Fournie; Christophe Bernus; Thony Dupas; Jerome Phalippou; Gilles Mercadier; Nicolas Toureille; Frederic Milin; Jean Redon |
| A method for opening a dome for the protection of a device to be protected, fitted in a part described as fixed, in which, in the initial position before opening, a generally plane interface separates the dome from the fixed part, is provided. The method includes connecting the dome to the fixed part by at least two independent double-link connections that are movable in rotation between the dome and the fixed part. The links in a single connection being fitted in common to the dome and to the fixed part to form overall a pantograph in the shape of an isosceles trapezium which, during opening, opens out by pivoting until maximum opening is achieved, so that the dome moves away from the fixed part via a combination of movements in translation and in rotation. | ||||||
| 149 | Aerial vehicle with depolyable components | US15092219 | 2016-04-06 | US09580165B1 | 2017-02-28 | Nicholas Robert Alley; Joshua Lemming Steele; Jesse Owen Williams; Daniel Kuehme; Jonathan Caleb Phillips |
| An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement. | ||||||
| 150 | 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. | ||||||
| 151 | HOUSING FOR AIRCRAFT MOUNTED COMPONENTS | US15234614 | 2016-08-11 | US20160349366A1 | 2016-12-01 | John Leslie Paul Hill |
| A traffic collision avoidance system (TCAS) device is provided. The device includes a radome having an antenna. A chassis is bonded to said radome about a periphery by a skirt layer. A housing is adhesively bonded to the radome, the skirt layer and the chassis. The housing has a substantially flat bottom portion with a wall extended about a periphery, the wall forming a lap joint with the chassis and radome. | ||||||
| 152 | COMPOSITES FOR PROTECTING SIGNAL TRANSMITTERS/RECEIVERS | US14588080 | 2014-12-31 | US20160297941A1 | 2016-10-13 | Choung Lai; Ajay Padwal; Marie J. Demers; David W. Stresing; John E. Langlois |
| Embodiments of the present disclosure are directed to a composition and composite for protecting a transmission/reception device. The composite can include a reinforcing material and a cured epoxy composition impregnating the reinforcing material. The cured epoxy composition can contain reaction constituents including less than 50% stoichiometric amount of an anhydride curing agent to an epoxy resin. The composite can exhibit synergistic improvements in mechanical strength, weatherability, and signal transmission properties. | ||||||
| 153 | 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. | ||||||
| 154 | METHOD OF OPENING A PROTECTIVE DOME, IN PARTICULAR A RADOME, AND RADOME EQUIPPED WITH A PANTOGRAPH FOR IMPLEMENTATION THEREOF | US14129500 | 2012-06-26 | US20160190679A1 | 2016-06-30 | Jacques FOURNIE; Christophe BERNUS; Thony DUPAS; Jerome Phalippou; Gilles Mercadier; Nicolas Toureille; Frederic Milan; Jean Roden |
| A method for opening a dome for the protection of a device to be protected, fitted in a part described as fixed, in which, in the initial position before opening, a generally plane interface separates the dome from the fixed part, is provided. The method includes connecting the dome to the fixed part by at least two independent double-link connections that are movable in rotation between the dome and the fixed part. The links in a single connection being fitted in common to the dome and to the fixed part to form overall a pantograph in the shape of an isosceles trapezium which, during opening, opens out by pivoting until maximum opening is achieved, so that the dome moves away from the fixed part via a combination of movements in translation and in rotation. | ||||||
| 155 | UNIVERSAL ADAPTER PLATE ASSEMBLY | US14760764 | 2014-01-09 | US20160190675A1 | 2016-06-30 | Vipula DASANAYAKA |
| An improved universal zero-moment support and adapter plate assembly is shown and described. In one embodiment, the assembly comprises an adjustable zero-moment support configured together with an off-axis adjustment. In other embodiments, an adapter and support assembly includes an external fitting, an adapter plate and an adjustable zero-moment support. | ||||||
| 156 | AIRCRAFT ANTENNA COVER, AIRCRAFT MEMBER COVER, AIRCRAFT, AND RAIN EROSION BOOT FOR AIRCRAFT | US14670629 | 2015-03-27 | US20160031568A1 | 2016-02-04 | Takashi YOKOI |
| An antenna cover of an aircraft including: a cover that protects an antenna mounted in the aircraft; a conductive layer having conductivity that is provided on an outer side of the cover; and a rain erosion boot that covers one region of the conductive layer, wherein the rain erosion boot includes a main material having an insulating property, is given conductivity, and is grounded to an airframe via the conductive layer, or the rain erosion boot includes a main material having an insulating property, and is given hydrophilicity. | ||||||
| 157 | POLYUREA PERIMETER SEAL FOR AN AIRCRAFT ANTENNA OR OTHER AIRCRAFT PART | US14799144 | 2015-07-14 | US20160018000A1 | 2016-01-21 | Jeff Busby; Chad Knight; Kent Boomer; Mike Dry; Matt Boyd |
| A sealant is provided for use on an aircraft or other vehicle. The sealant may be used with a gasket. The sealant is a perimeter seal that comprises a polyurea member. The polyurea member is a self-curing, two-component mix. It may cure to a hardness in the range of about 40 to 100 (Shore A). It may maintain an adequate peel strength to withstand multiple thermal and pressure cycling, and may have a working life, wherein it may be shaped, of less than about eleven minutes. | ||||||
| 158 | OBJECT DEFLECTION DEVICE AND PROTECTION UNIT | US14593497 | 2015-01-09 | US20150197345A1 | 2015-07-16 | Rob Abbinante |
| An object deflection unit comprising a deflection unit having an adapting plate and a top surface, a plurality of doubler units affixed to an aircraft frame, where the deflection unit is secured to the aircraft frame via the securing flange and doubler units. | ||||||
| 159 | Antenna support bracket | US12899111 | 2010-10-06 | US09065171B2 | 2015-06-23 | Eric John Lundeen |
| A method and apparatus comprising a planar member and a number of support members. The planar member may be configured to be attached to an airframe of an aircraft. The number of support members may be configured to connect the number of antennas to the planar member. | ||||||
| 160 | Front landing-gear well | US14348093 | 2012-09-27 | US20140246542A1 | 2014-09-04 | Bernard Guering; Yves Durand |
| A forward part of an aircraft comprising a fuselage and a landing gear well housing a forward landing gear comprising a breaker strut designed to adopt an extended configuration when the landing gear is extended, configuration in which said breaker strut lies in a strut plane parallel to the transverse direction of the forward part. The forward part comprises a transverse beam resisting strut reactions located above the landing gear well and mounted on the fuselage at its two ends, the beam having a globally rectangular cross-section, in which the median plane parallel to the length of the rectangle is coincident with said strut plane. | ||||||
QQ群二维码
意见反馈
意见反馈