| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 161 | Methods and Systems of Constructing a Multi Rotor Aircraft Fuselage | US14045646 | 2013-10-03 | US20140231582A1 | 2014-08-21 | Sean Headrick |
| A lower hull 403 and an upper hull 402 may form a multi rotor aircraft fuselage system comprising a comprising a thermoformed thin shell monocoque fuselage 500, center console assembly 200, the center console assembly comprising a center console cover 210, an auto pilot housing cover 220 and an auto pilot housing 225. A center fuselage area 300 contains the center console assembly 200. The center fuselage area is part of a plurality of arm assemblies 400. Each arm assembly may comprise a distal end 440 and a proximal end 410, an access panel cover 420 which may expose a access panel opening 419. An access panel opening 419 may lead to an arm void area 430, with the arm void area 430 further defined by the interior sections of the thin shell fuselage 500. | ||||||
| 162 | Low Profile Pass-Through Electrical Connector | US13909061 | 2013-06-03 | US20140151352A1 | 2014-06-05 | 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. | ||||||
| 163 | Thermal Management For Aircraft Composites | US13451904 | 2012-04-20 | US20130280470A1 | 2013-10-24 | Julian Norly |
| A composite article including a fiber-reinforced resin composite having an internal portion, and an internal surface and an external surface; and a thermal article formed of an anisotropic graphite sheet having a thermo-mechanical design constant of at least 10 mm-W/m*K, the thermal article positioned in the internal portion of the fiber-reinforced resin composite, wherein the thermo-mechanical design constant of a material is defined by thermal conductivity of the material multiplied by its average thickness. | ||||||
| 164 | HOUSING FOR AIRCRAFT MOUNTED COMPONENTS | US13600497 | 2012-08-31 | US20120326915A1 | 2012-12-27 | 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. | ||||||
| 165 | RADOME AND DEVICE FOR ATTACHING SAID RADOME TO AN AIRCRAFT | US13395241 | 2010-09-10 | US20120212391A1 | 2012-08-23 | 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). | ||||||
| 166 | Antenna fairing and method | US12033356 | 2008-02-19 | US07967253B2 | 2011-06-28 | 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. | ||||||
| 167 | COMPLIANT CROWN PANEL FOR AN AIRCRAFT | US12965451 | 2010-12-10 | US20110101164A1 | 2011-05-05 | William J. Koch; Donald P. Matheson |
| An aircraft forward pressure bulkhead and an aircraft crown panel are described herein. The forward pressure bulkhead includes a malleable and deformable dome that is configured to “catch” foreign objects, such as birds. The dome is intentionally designed to deform in response to a foreign object strike that imparts at least a threshold amount of impact energy to the bulkhead. The dome is free of rigid stiffeners and non-deformable reinforcement members that would otherwise hinder the flexible characteristic of the dome. Practical embodiments of the bulkhead utilize fewer parts, are less heavy, and are less expensive than traditional bulkheads that utilize rigid stiffeners. The crown panel has similar compliant characteristics. The crown panel is designed to simultaneously deform and deflect in response to foreign object impacts such as birds and hail. The crown panel is formed from a monolithic one-piece material, such as aluminum, and various reinforcing features are integrally formed in the material. | ||||||
| 168 | IN-FLIGHT TESTING KITS AND METHODS FOR EVALUATING PROPOSED AERODYNAMIC STRUCTURES FOR AIRCRAFT | US12178486 | 2008-07-23 | US20100018301A1 | 2010-01-28 | 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. | ||||||
| 169 | COLLAPSIBLE SHAPE MEMORY ALLOY (SMA) NOSE CONES FOR AIR VEHICLES, METHOD OF MANUFACTURE AND USE | US12141426 | 2008-06-18 | US20090314890A1 | 2009-12-24 | Frederick B. Koehler; Ward D. Lyman; Terry M. Sanderson |
| A nose cone formed from a shape memory alloy (SMA) having a recoverable strain of at least 2% collapses about the dome for storage, deploys at launch to protect the sensor dome and reduce drag during atmospheric flight and is shed to allow sensing for terminal maneuvers. The SMA is shape-set at elevated temperatures in its Austenite phase with a memorized shape having a radius of curvature greater than that of the sensor dome to reduce aerodynamic drag. The temperature is reduced and the SMA collapsed to conform to the curvature of the sensor dome within the recoverable strain for storage. A first mechanism is configured to return the collapsed SMA to its memorized shape at launch or prior to going supersonic. In one embodiment, the SMA is stored below its Martensite finish temperature in a temperature-induced Martensite phase in which case the mechanism heats the SMA above the Austenite finish temperature to return the material to its memorized shape. In another embodiment, the SMA is stored above its Austenite finish temperature in which case collapsing the SMA places the material in a strain-induced Martensite phase. The mechanism holds the collapsed SMA in place and the releases the stored energy allowing the SMA to return to the memorized shape. | ||||||
| 170 | Sealant template for use in sealing joints and method of sealing joints | US11705670 | 2007-02-13 | US20080191423A1 | 2008-08-14 | Binyamin Cohen |
| A sealant template for use in sealing a joint between a component and a vessel to which the component is attached comprises a support member on which are adhesively adhered inner and outer template sections. The inner template section has a ring-shape having an outer profile similar to but smaller than the periphery of the base of the component, and the outer template section has a ring-shape having an inner profile similar to but larger than the periphery of the base of the component. When the inner template section is adhesively adhered to the base of the component and the outer template section is adhesively adhered to the vessel surface, a ring-shaped gap exists between the inner and outer template sections at the joint between the component and the vessel to facilitate application of sealant to the joint. The inner and outer template sections may be provided with tabs to facilitate removal of the template sections from the backing member and adherence thereof to the component and the vessel. The inner and outer template sections may be provided with weakened regions to enable separation of the template sections into plural template section pieces to simplify adhering the template sections to the component and the vessel. The weakened regions may be formed by perforated lines or score lines. | ||||||
| 171 | Aircraft fuselage element and method of taking a number of pictures | US11025087 | 2004-12-29 | US07324747B2 | 2008-01-29 | Hagen Kempas |
| An aircraft fuselage element (26) with a fuselage body (30) which forms an internal cavity (40) and which includes a viewing window (32, 34). To provide for taking substantially distortion-free high-resolution pictures in the infrared wavelength range and from a large angular range the fuselage body (30) is mounted for rotation about an axis of rotation (36). | ||||||
| 172 | Closure system for a support structure | US10943251 | 2004-09-17 | US20050116106A1 | 2005-06-02 | 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. | ||||||
| 173 | Aircraft sensor pod assembly | US10373459 | 2003-02-25 | US06745981B1 | 2004-06-08 | Stanley Irvin Rainer; Vito Richard Simone; Paul Arthur Fraser |
| The invention is a sensor pod for mounting on the top surface of the fuselage of an aircraft. The pod it supported by right and left front supports and right and left rear supports that attach to the fuselage on either side of the longitudinal axis of the aircraft. A fifth structural support, aligned with the longitudinal axis of the aircraft, has a first end attached to the fuselage of the aircraft a second end attached to the sensor pod the aircraft. | ||||||
| 174 | Aircraft fore structure | US09245842 | 1999-02-08 | US06213428B1 | 2001-04-10 | Pascal Chaumel; Francis Dazet |
| An aircraft fore-structure for wide- and very-wide body freight aircraft that is characterized by the presence of a unpressurized landing gear compartment in the lower fore end section. The landing gear compartment is formed by a ceiling at the top, that is preferably domed, and by a partition towards the rear. A door that is provided in the partition provides access through the landing gear compartment to the pressurized compartment located behind said partition. An opening in the fore of the landing gear compartment also provides access to the radar chamber without requiring the radome to be dismantled. The original layout of the landing gear compartment enables fore landing gear to be installed that is larger than that in existing aircraft. | ||||||
| 175 | Connecting device for the dome of a missile | US136205 | 1993-10-15 | US5404814A | 1995-04-11 | Peter Fisch; Hans Kordulla |
| A connecting assembly serves for connecting a dome covering a seeker head with the structure of a missile. A holding ring extends over the rim of said dome, positively holding this dome and connected with the structure of the missile. An annular recess is provided underneath the holding ring along the rim of the dome. This recess contains a flexible sealing substance for establishing a seal between the holding ring and the dome. It is important, that no additional material bonding such as cementing or soldering is provided between the dome and the holding ring. | ||||||
| 176 | Swinging pod antenna mount | US467707 | 1983-02-18 | US4509709A | 1985-04-09 | Charles G. Utton; Bill D. Stratman |
| Antenna pods are located outboard of each wheel fairing on a C-130 aircraft, which pods are supported by truss members attached to the aircraft and pivotally affixed to an upper row of antenna lugs and two travelling nut jack screw units affixed to the aircraft and pivotally attached to two lower antenna lugs. When the jack screws are longitudinally extended the antenna pod is pivoted out of an operating position and into a maintenance position. | ||||||
| 177 | Rotatable radome for aircraft | US69998957 | 1957-12-02 | US3026516A | 1962-03-20 | DAVIS EDWARD M |
| 178 | Arrangement of aircraft propulsion and radio viewing components | US74487447 | 1947-04-30 | US2494368A | 1950-01-10 | STEELE FREDERICK I; WILLIS ADDISON O |
| 179 | Airplane structure | US24347738 | 1938-12-01 | US2242200A | 1941-05-13 | WOODS ROBERT J |
| 180 | SEALED BOTTOM OF A FRONT END OF AN AIRCRAFT | US16225519 | 2018-12-19 | US20190185135A1 | 2019-06-20 | Bernard GUERING; Laurent SAINT-MARC |
| A sealed bottom in the frame of a cockpit with centered pilot is disclosed for increasing the bulk inside the radome and making it possible to improve the optimization of the volumes. The sealed bottom includes a semi-cylindrical central part having four edges that are parallel in pairs, two curved edges, and two straight edges and a planar peripheral part extending at least partially around the central part. The peripheral part (22) is located in the plane of the straight edges of the central part and linked thereto. This configuration will allow to free up space to increase the number of passengers or reduce the size of the aircraft. | ||||||
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