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序号	专利名	申请号	申请日	公开（公告）号	公开（公告）日	发明人
241	Temperature-Controlled UAV Storage System	US15882116	2018-01-29	US20180236840A1	2018-08-23	Robert Cantrell; David Winkle
Described in detail herein is an temperature-controlled UAV delivery system. One or more physical objects can be stored inside a temperature-controlled storage unit of a UAV. A temperature controlling device can control the temperature of the interior volume of the temperature-controlled storage unit. Sensors can detect a temperature of the interior volume of the temperature-controlled storage unit. The computing system can control the temperature controlling device to adjust the temperature of the interior volume of the temperature-controlled storage unit to an ideal temperature for storing the one or more physical objects based on the attributes associated with the one or more physical objects.
242	Sandwich panel with recessed channel network	US15865357	2018-01-09	US20180194096A1	2018-07-12	Nabankele Martial Somda; Inge Sanders; Bastian Schaefer
A composite sandwich panel comprises a top layer, a bottom layer, and a honeycomb core layer sandwiched between the top layer and the bottom layer. The honeycomb core layer includes an array of hollow cells formed between vertical walls. This array of hollow cells is recessed in the form of a channel network running from a first side face of the sandwich panel through the honeycomb core layer to a second side face, opposite to the first side face of the sandwich panel.
243	Thermal management systems and methods	US15202661	2016-07-06	US10017032B2	2018-07-10	William Webster Behrens; Andrew Richard Tucker
A thermal management system includes at least one vapor compression system (VCS) that is configured to cool portions of the vehicle. The VCS circulates a fluid therethrough to cool the portions of the vehicle through heat exchange. At least one reverse air cycle machine (RACM) couples to VCS through a first heat exchanger. The RACM is configured to receive ram air. The RACM expands the ram air. Heat from the fluid circulating through the VCS is transferred to the expanded ram air through the first heat exchanger.
244	Orbital cable holder systems and methods	US15453520	2017-03-08	US10012330B1	2018-07-03	Daniel S. Thomas; Jeffrey R. Dempsey
Systems and methods are provided for cable routing, such as within vehicles or structures. In certain examples, a cable holder is disclosed that includes one or more loop members with an interior groove and a rotatable cable holding member disposed within the interior groove. The rotatable cable holding member can be configured to rotate to decrease bends and/or stresses within the cable that the rotatable cable holding member is holding. Additionally, the rotatable cable holding member can be configured so that the cable held is perpendicular to the support for the cable.
245	Conformal body capacitors suitable for vehicles	US14457662	2014-08-12	US09966790B2	2018-05-08	Raj Bridgelall; Michael Corcoran
A vehicle system includes a plurality of capacitors each forming a portion of a vehicle structure, and a parallel electrical link between a pair of the plurality of capacitors, such that the pair of capacitors act as an aggregate capacitor.
246	Monocoque helicopter fuselage with integral tail boom	US14124247	2012-06-07	US09932123B2	2018-04-03	Peter Maloney; Nina Heatley
A composite structure forming a load bearing composite shell for a helicopter, with a shell which defines the exterior of a fuselage and includes a central fuselage section and tail boom, a fuselage which is adapted house an engine or drive train, a layered composite crashworthy seat and support structure and a fastening and a method of fastening by providing an adhesive between two layers which is allowed to flow through opposing holes in the layers to provide a chemical and mechanical attachment between the layers.
247	VIBRATION DAMPING SYSTEM	US15217824	2016-07-22	US20180022056A1	2018-01-25	Hongbin Shen; Phu Nguyen
A reduced vibration structure comprises honeycomb and a vibration damping coating on at least a portion of the internal surface of at least a portion of the cells of the honeycomb. The vibration damping coating is formed by curing a coating composition comprising acrylic polymer or copolymer emulsion and a vibration damping filler. The structure can include an adhesive coupled to both the upper surface and the lower surface of the honeycomb and two pieces of sheathing coupled to the adhesive, one on the upper surface and one on the lower surface of the honeycomb.
248	INTERCHANGEABLE INTERNAL MODULAR AVIONICS PLATFORM ASSEMBLY	US15688737	2017-08-28	US20180014432A1	2018-01-11	Kenneth Alan Szarek
Internal interchangeable modular avionics platform assemblies and methods for removably mounting and interchanging modular avionics platforms within an aircraft. In some embodiments, modular avionics platform assemblies may include a modular avionics platform configured to support various avionics equipment, suitable for removable mounting within a forward fuselage, and interchangeable with a number of alternate platforms. A platform may include a frame structure, and mounting pins and a connector assembly disposed on the frame structure. The mounting pins may project outwardly from the frame structure to align with and detachably secure to corresponding airframe members of an aircraft when the frame structure is in a mounted position. The connector assembly may be disposed on the frame structure and have a plurality of connectors, including connectors for alternating current, direct current, and data. In some embodiments, the platform may also include an environmental cooling system disposed on the frame structure.
249	WINGLESS AIRCRAFT	US14999667	2016-06-10	US20170355435A1	2017-12-14	Francis Joseph Clark
Wings do not produce lift. It is the thrust provided by an engine (or engines) that enable an aircraft to rise off the ground.
250	Support bracket	US14993506	2016-01-12	US09835287B2	2017-12-05	Seth E. Rosen; Kenneth Crawford
A support bracket includes a body, an arm, a first mount, a boss, and a second mount. The arm extends laterally from the body and a first fastener opening passes through the arm. The first mount extends from a first side of the body, and a first fillet is disposed at the interface of the first mount and the body. A boss extends from a second side of the body and a second fastener opening passes through the boss. A second fillet is disposed at the interface of the boss and the body. The second mount extends into the body opposite the boss. A third fillet is disposed at the interface of the second mount and the first side and a fourth fillet is disposed at the interface of the second mount and the second side.
251	Symmetrical continuous multidirectional ultra-light ultra-strong structure	US15165838	2016-05-26	US09834325B2	2017-12-05	Mindaugas Ramaska
A multidimensional structures that is formed of thirty six interconnecting members in such a manner as to form eight (8) tetrahedrons and six (6) octahedrons thereby providing a structure that is both light weight and strong, the interconnecting members variously intersecting at a central point that may be formed of a single unified structure having fillets in the middle of the multidimensional structure and at twelve (12) external connecting points.
252	GASKET HAVING A PLIABLE RESILIENT BODY WITH A PERIMETER HAVING CHARACTERISTICS DIFFERENT THAN THE BODY	US15646888	2017-07-11	US20170305523A1	2017-10-26	Jeff Busby; Kent Boomer; Matt Boyd; Michael Dry; Douglas Smith
A single piece gasket is disclosed having a skeletal member, typically metallic, and a pliable body. The pliable body includes a first portion having a first firmness and a second perimeter portion have a firmer consistency. When such a composite body is placed under compression, the perimeter will tend to limit the flow of the softer inner material past the firmer perimeter region or portion of the gasket. In this manner, creep or overrun of the less firm portion material will be reduced.
253	HAND-LAUNCHED UNMANNED AERIAL VEHICLE	US15338802	2016-10-31	US20170297706A1	2017-10-19	Guocheng ZHAO; Wei LUO
The invention discloses a hand-launched unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles. The hand-launched unmanned aerial vehicle comprises a body, a tail, at least one power source and a lens bin, wherein the body comprises a middle section, a first side section and a second side section; two sides of the middle section are respectively detachably connected with the first side section and the second side section correspondingly; the tail is fixed to the middle section; the power source is fixed to the middle section; and the lens bin is fixed to the middle section and provided with a flexible cushion. The invention overcomes the technical defects in the prior art that the body maintenance cost of the hand-launched unmanned aerial vehicle is high and the lens bin is very likely to be damaged due to collision between the lens bin of the hand-launched unmanned aerial vehicle and the ground.
254	CONTROL SYSTEM, CONTROL METHOD, AND STORAGE MEDIUM	US15515653	2015-08-04	US20170297201A1	2017-10-19	Atsushi SHIONOZAKI; Satoshi IKEDA; Tetsuo TAWARA; Yasushi MIYAJIMA
[Object] To provide a control system, a control method, and a storage medium through which a moving object can change a surrounding environment of a user depending on an emotion of the user.[Solution] Provided is a control system including: an estimation unit that estimates an emotion of a user; and a moving object controller that controls a moving object to change a surrounding environment of the user depending on the estimated emotion.
255	Aircraft comprising a cockpit delocalized outside an upper part of the nose	US14138406	2013-12-23	US09789961B2	2017-10-17	Jason Zaneboni; Bruno Saint-Jalmes
An aircraft including a fuselage, a cockpit and a cabin, wherein the cockpit is situated below the cabin and outside the nose, such as a lancet-shaped nose, of the aircraft and may extend to a front end of the aircraft, and the viewing surfaces in the cockpit may be entirely formed of digital display screens.
256	System and method for interconnecting composite structures	US14199034	2014-03-06	US09758232B2	2017-09-12	Memis Tiryaki; Ulrich Bieling
A system for interconnecting components in a vehicle body structure, and especially for interconnecting fiber-reinforced composite components in a fuselage structure of an aircraft. The system includes a first adapter member, a second adapter member and a connector member. The first adapter member has a first mating portion configured to substantially conform with a profile of a first component of the structure in more than one plane. A first attachment portion is connected to the first mating portion. The second adapter member has a second mating portion configured to substantially conform with a profile of a second component of the structure in more than one plane. A second attachment portion is connected to the second mating portion. The connector member securely interconnects the first and second attachment portions of the first and second adapter members. A related method of interconnecting components in a vehicle body structure is also disclosed.
257	Conductive Radius Filler System and Method	US15061942	2016-03-04	US20170253346A1	2017-09-07	America O. Schaaf; Elise Rae E. Castorina; Gabriel Z. Forston; Patrice K. Ackerman
There is provided a conductive radius filler system and method. The system has a composite assembly with one or more composite structures having one or more radius filler regions. The system further has one or more conductive radius fillers filling the one or more radius filler regions. Each of the conductive radius fillers has a conductive element of electrically conductive material. The system further has one or more over-arching systems connected to the one or more conductive radius fillers, via one or more conductive radius filler connections, forming one or more current handling systems of the system. The one or more current handling systems include one or more of an edge glow handling system configured to handle edge glow, a static dissipation handling system configured to handle static dissipation, and a current return handling system configured to handle current return.
258	Aircraft Airfoil Having A Stitched Trailing Edge And Manufacturing Method Thereof	US15438896	2017-02-22	US20170246833A1	2017-08-31	Soledad Crespo Peña; Carlos García Nieto; Iker Vélez De Mendizabal Alonso; Enrique Guinaldo Fernández
A configuration and manufacturing method for a trailing edge of an aircraft airfoil, such as a control surface or a lifting surface is described. The trailing edge is formed and configured by upper and lower composite covers, which are stitched to each other with a metallic wire, such as the metallic wire is electrically in contact with upper and lower metallic meshes to provide electrical continuity between meshes. According to a method, upper and lower covers configuring the trailing edge, are stitched with the metallic wire before curing the covers, so that the metallic wire gets embedded within the composite material. A trailing edge for an aircraft airfoil, which is easy to manufacture and that at the same time fulfills aerodynamic, mechanical and electrical conductivity requirements is described.
259	Interchangeable internal modular avionics platform assembly	US14919663	2015-10-21	US09750162B2	2017-08-29	Kenneth Alan Szarek
Internal interchangeable modular avionics platform assemblies and methods for removably mounting and interchanging modular avionics platforms within an aircraft. In some embodiments, modular avionics platform assemblies may include a modular avionics platform configured to support various avionics equipment, suitable for removable mounting within a forward fuselage, and interchangeable with a number of alternate platforms. A platform may include a frame structure, and mounting pins and a connector assembly disposed on the frame structure. The mounting pins may project outwardly from the frame structure to align with and detachably secure to corresponding airframe members of an aircraft when the frame structure is in a mounted position. The connector assembly may be disposed on the frame structure and have a plurality of connectors, including connectors for alternating current, direct current, and data. In some embodiments, the platform may also include an environmental cooling system disposed on the frame structure.
260	Joints in fibre metal laminates	US14622056	2015-02-13	US09731807B2	2017-08-15	Thomas Beumler
An aircraft panel with a laminate structure is provided that comprises a stack of a plurality of metal sheet layers, at least one fiber reinforced adhesive layer, and at least one cover segment. At least one outer layer of the metal sheet layers comprises at least two separate metal sheets that overlap with each other along their respective commonly adjoining edges, providing an overlapping joint of the two separate metal sheets. The at least one fiber reinforced adhesive layer comprises fiber elements embedded in a matrix structure. One of the at least one fiber reinforced adhesive layers is arranged between two adjacent metal sheet layers. Further, the at least one cover segment is arranged on an outside surface of the laminate structure, the cover segment covering a region of the overlapping joint. Still further, the at least one cover segment comprises at least one layer of reinforcement fibers.

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