| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 81 | Aircraft nose structure with landing gear compartment | US13710577 | 2012-12-11 | US08905352B2 | 2014-12-09 | Philippe Bernadet; Patrick Lieven; Marc Dugerie; Christophe Mialhe; Romain Delahaye |
| An aircraft nose structure includes a fuselage and a pressuretight bulkhead fixed at its periphery to the fuselage and transversely dividing the fuselage into a pressurized upper zone and an unpressurized lower zone for accommodating retractable nose landing gear. The pressuretight bulkhead includes a floor of the pressurized upper zone, and a substantially flat rear panel extending between a rear edge of the floor and the fuselage. The floor and the rear panel are fixed laterally to the fuselage. The fuselage includes an exterior wall and reinforcing transverse frames to which the exterior wall is fixed. In line with the pressuretight bulkhead, at least some of the transverse reinforcing frames extend along the outline of the pressurized upper zone and constitute members that reinforce the pressuretight bulkhead. | ||||||
| 82 | Sensor pod mount for an aircraft | US13372230 | 2012-02-13 | US08882046B2 | 2014-11-11 | Eric Edsall; Alejandro Pita; Jeff Turney |
| Embodiments related to mounting a sensor pod mount to an aircraft fuselage are disclosed. In one example embodiment, a sensor pod mount comprises a sensor pod mounting body where the sensor pod mounting body includes a mounting region for removably mounting the sensor pod mount to the fuselage using a coupling that joins a strut to the fuselage. | ||||||
| 83 | Radome and device for attaching said radome to an aircraft | US13395241 | 2010-09-10 | US08816916B2 | 2014-08-26 | Francis Dazet |
| The invention relates to a radome (1) for an aircraft, and more specifically to a device for connecting said radome to the structure of said aircraft. The radome that is the subject of the invention comprises a plurality of locking units able to bring together the opposing surfaces of the aircraft's fuselage (10) and the radome (1), each unit comprising: locking means (20) able to exercise a traction force on the surface of the fuselage, substantially normal to the surface, via attachment means; centering means able to withstand the shear forces substantially tangential to the opposing surfaces of the fuselage and radome; the locking means (20) are placed such that they are located inside the cone of resulting forces on the centering means so as to minimize the bending stresses generated by the assembly in the radome (1). | ||||||
| 84 | Thermal barrier coated RF radomes and method | US12629044 | 2009-12-01 | US08765230B1 | 2014-07-01 | John C. Waldrop, III; Daniel E. Driemeyer; Laura S. Riegel; Stanley A. Lawton |
| Thermal barrier coated RF radomes and a method for making the same are provided. In an embodiment of the disclosure, there is provided a method for making a thermal barrier coated radio frequency (RF) radome. The method comprises providing a radio frequency (RF) radome. The method further comprises applying a thermal barrier coating having a dielectric constant less than about 2.0 onto a surface of the radome to form a thermal barrier coated RF radome. The thermal barrier coating reduces a structure temperature of the radome by greater than 300 degrees Fahrenheit to enhance thermo-mechanical properties and performance of the RF radome. | ||||||
| 85 | AIRCRAFT COMPRISING AN ONBOARD WEATHER RADAR ANTENNA PROVIDED WITH INCLINED PANELS | US14099531 | 2013-12-06 | US20140159949A1 | 2014-06-12 | Christophe Mialhe |
| An aircraft comprising a fuselage and a radome fixed to the fuselage. The radome defines a housing and the fuselage comprises a sealed bulkhead closing the housing. A weather radar antenna comprises a main panel. A plurality of peripheral panels are arranged around the main panel, inclined from a planar surface of the main panel and located on the same side of the planar surface. The housing contains the antenna which is mounted on the fuselage through a mechanical support fixed to the fuselage and to the weather radar antenna on the same side of the planar surface as the peripheral panels. A bird strike shield is located between the antenna and the sealed bulkhead. The shield comprises a dome with a top and a base, the base being fixed to the aircraft fuselage. An opening is formed at the top of the dome through which the mechanical support passes. | ||||||
| 86 | ASSEMBLIES FOR EXTERNAL ATTACHMENT OF AIRBORNE SENSOR PODS TO AN AIRCRAFT FUSELAGE | US13655347 | 2012-10-18 | US20140110526A1 | 2014-04-24 | Romero Maia Soares DE AZEVEDO; Lafayete Faria SIQUEIRA; Sergio Cunha MONTESI |
| Sensor pod attachment assemblies are provided for attaching a sensor pod containing airborne sensor equipment to an aircraft fuselage. The sensor pod assemblies may include fore and aft pairs of attachment pylon assemblies each having a lower end attached to the aircraft fuselage and an upper end attached to the sensor pod. The fore pair of attachment pylon assemblies can include port and starboard pylon structures, and a cross-support base connected to upper ends of the port and starboard pylon structures. The aft pair of attachment pylon assemblies may include a lengthwise adjustable spar assembly. | ||||||
| 87 | Low Profile Pass-Through Electrical Connector | US13908885 | 2013-06-03 | US20140015733A1 | 2014-01-16 | 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. | ||||||
| 88 | Sensor Pod Mount for an Aircraft | US13372230 | 2012-02-13 | US20130206914A1 | 2013-08-15 | Eric Edsall; Alejandro Pita; Jeff Turney |
| Embodiments related to mounting a sensor pod mount to an aircraft fuselage are disclosed. In one example embodiment, a sensor pod mount comprises a sensor pod mounting body where the sensor pod mounting body includes a mounting region for removably mounting the sensor pod mount to the fuselage using a coupling that joins a strut to the fuselage. | ||||||
| 89 | AIRCRAFT NOSE STRUCTURE WITH LANDING GEAR COMPARTMENT | US13710577 | 2012-12-11 | US20130146710A1 | 2013-06-13 | Philippe Bernadet; Patrick Lieven; Marc Dugerie; Christophe Mialhe; Romain Delahaye |
| An aircraft nose structure includes a fuselage and a pressuretight bulkhead fixed at its periphery to the fuselage and transversely dividing the fuselage into a pressurized upper zone and an unpressurized lower zone for accommodating retractable nose landing gear. The pressuretight bulkhead includes a floor of the pressurized upper zone, and a substantially flat rear panel extending between a rear edge of the floor and the fuselage. The floor and the rear panel are fixed laterally to the fuselage. The fuselage includes an exterior wall and reinforcing transverse frames to which the exterior wall is fixed. In line with the pressuretight bulkhead, at least some of the transverse reinforcing frames extend along the outline of the pressurized upper zone and constitute members that reinforce the pressuretight bulkhead. | ||||||
| 90 | Aircraft front portion including a concave bulkhead separating a non-pressurized radome area and a pressurized area | US12686761 | 2010-01-13 | US08434717B2 | 2013-05-07 | Cédric Meyer; Bernard Guering |
| An aircraft front portion includes a sealed bulkhead separating a non pressurized radome area from a pressurized area. The sealed bulkhead is delimited by two surfaces opposite to each other, one being substantially concave when seen from the radome area and the other being substantially convex when seen from the pressurized area. | ||||||
| 91 | In-flight testing kits and methods for evaluating proposed aerodynamic structures for aircraft | US12178486 | 2008-07-23 | US07966872B2 | 2011-06-28 | Kevin R. Lutke; Blaine K. Rawdon |
| In-flight testing methods and kits for in-flight testing of proposed aerodynamic structures are disclosed. The methods and kits involve a testing station carried on a pre-existing fully engineered and tested host aircraft. Interchangeable but differently configured aerodynamic structures may be carried upon the host aircraft, and existing systems of the host aircraft may be utilized to conduct the testing, avoiding time and cost associated with constructing fully operational demonstrator aircraft for testing purposes. | ||||||
| 92 | Closure system for a support structure | US12340141 | 2008-12-19 | US07909289B2 | 2011-03-22 | Juan Perez-Sanchez |
| System for opening and closing a structural part arranged on a support structure. The system includes at least one hinged joint device for flexibly connecting the structural part to the support structure. The at least one hinged joint device is arranged inside the support structure and has an axis of rotation about which the structural part can be pivoted relative to the support structure during opening and closing. A locking arrangement is structured and arranged to connect the structural part to the support structure in a form-locking manner when the structural part is in a closed position. In the closed position, the locking arrangement is arranged to relieve the at least one hinged joint device. This Abstract is not intended to define the invention disclosed in the specification, nor intended to limit the scope of the invention in any way. | ||||||
| 93 | Ducted Fan Unmanned Aerial Vehicle Conformal Antenna | US12267246 | 2008-11-07 | US20100328169A1 | 2010-12-30 | Daniel Ross Collette; Joseph Scott Helsing, JR. |
| A conformal antenna for an unmanned aerial vehicle is provided that may be applied to a surface of the vehicle. The conformal antenna may be integrated with a surface on the vehicle, and is used to effectively transmit and receive video, command and/or control signals. The conformal antenna allows for the transmission and reception of signals from any direction, and may work with signals greater than a quarter wavelength. A protective layer may be placed over the conformal antenna. | ||||||
| 94 | ANTENNA FAIRING AND METHOD | US12033356 | 2008-02-19 | US20100038488A1 | 2010-02-18 | Stanley D. Ferguson; William W. Herling; David A. Treiber |
| A fairing suitable for enclosing a component mounted on an exterior surface of a mobile platform, and more particularly on an outer surface of a high speed mobile platform such as a jet aircraft or an aerospace vehicle. The fairing provides aggressive closure angles for optimum RF performance when used to house an antenna that is scanned to varying azimuth and elevation angles. The fairing further provides low aerodynamic drag, is scalable to enclose components having wide ranging dimensions, and provides attached flow with minimum separation of airflow thereover for airflows experienced by high speed jet aircraft, and reduces or eliminates RF reflections within the fairing from the RF beam of the antenna. | ||||||
| 95 | CLOSURE SYSTEM FOR A SUPPORT STRUCTURE | US12340141 | 2008-12-19 | US20090173824A1 | 2009-07-09 | Juan PEREZ-SANCHEZ |
| System for opening and closing a structural part arranged on a support structure. The system includes at least one hinged joint device for flexibly connecting the structural part to the support structure. The at least one hinged joint device is arranged inside the support structure and has an axis of rotation about which the structural part can be pivoted relative to the support structure during opening and closing. A locking arrangement is structured and arranged to connect the structural part to the support structure in a form-locking manner when the structural part is in a closed position. In the closed position, the locking arrangement is arranged to relieve the at least one hinged joint device. This Abstract is not intended to define the invention disclosed in the specification, nor intended to limit the scope of the invention in any way. | ||||||
| 96 | Closure system for a support structure | US10943251 | 2004-09-17 | US07503523B2 | 2009-03-17 | Juan Perez-Sanchez |
| System for opening and closing a structural part arranged on a support structure. The system includes at least one hinged joint device for flexibly connecting the structural part to the support structure. The at least one hinged joint device is arranged inside the support structure and has an axis of rotation about which the structural part can be pivoted relative to the support structure during opening and closing. A locking arrangement is structured and arranged to connect the structural part to the support structure in a form-locking manner when the structural part is in a closed position. In the closed position, the locking arrangement is arranged to relieve the at least one hinged joint device. | ||||||
| 97 | FRONT AIRCRAFT PART COMPRISING A FLAT PARTITION BETWEEN A PRESSURISED ZONE AND A NON-PRESSURISED ZONE HOUSING LANDING GEAR | US11964537 | 2007-12-26 | US20080210813A1 | 2008-09-04 | Bernard GUERING; Jonathan Guering |
| The present invention relates to a front aircraft part (1) comprising a non-pressurised landing gear housing zone (28) designed to house a front landing gear (30) in a retracted state, as well as a pressurised zone (2) adjacent to the non-pressurised landing gear housing zone. According to the invention, the pressurised zone is delimited by a set of walls among which only a substantially flat-shaped sealed partition wall (10) also participates in delimiting the non-pressurised landing gear housing zone (28). | ||||||
| 98 | Supersonic flight vehicle | US06252230 | 1981-03-31 | US07392963B1 | 2008-07-01 | Stanley Leek; Hugh R. Joiner; Brian R. Caro |
| A supersonic guided weapon has radiation sensitive apparatus carried behind a radiation transparent window the window being formed within an open recess in the weapon nose, the recess being such that at supersonic speeds it forms shock waves which trap air within the recess to provide a measure of kinetic heat insulation for the window and also a minimum of supersonic drag. An elongate nose region can be provided ahead of the recess to house further radiation sensitive or radiation emitting apparatus. | ||||||
| 99 | Aircraft radome and integral attaching structure | US533931 | 1995-09-26 | US5820077A | 1998-10-13 | Gary C. Sutliff; Matthew T. Cackett; Teresa A. Guy |
| A radome structure having an integrally attached attaching structure for attachment to an aircraft is disclosed, the attaching structure being affixed to a rearward portion of the radome. The attaching structure preferably comprises, at least in part, a core material which is capable of strengthening the attaching structure, thereby making it stronger than the material from which the radome shell is fabricated. | ||||||
| 100 | Antenna and mounting device and system | US316900 | 1994-10-03 | US5621421A | 1997-04-15 | Arvin L. Kolz; C. Edward Knittle |
| An antenna and mounting device assembly fits on opposite sides of an aircraft to handle radio signals during flight. The antenna has a boom and radiating elements extending normal to the boom. The mounting device includes a first clamping bracket that attaches to the exterior of the aircraft, a pair of spaced arms that are twisted relative to the longitudinal axis of the first clamping bracket to orient the antenna relative to the horizontal and a second clamping bracket that attaches to the antenna. | ||||||
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