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公开(公告)号：US20240182152A1
公开(公告)日：2024-06-06
申请号：US18285402
申请日：2022-04-28
CPC分类号： B64C1/0683 , H04R1/028 , H04R1/04 , H04R1/086 , H04R1/2876 , B64C2001/0054 , B64C2220/00 , H04R2410/07 , H04R2499/13
摘要： A nosecone of an aircraft sensor probe may include a first portion defining a tip of the nosecone that is formed from a first material. The nosecone further includes a second portion aft of the first portion and formed from a second material. The second portion may define an internal volume. The second material may have a greater porosity than the first material. The nosecone may further include a third portion aft of the second portion. The third portion may be configured to arrange a microphone assembly relative to the internal volume. The nosecone may a component or subassembly or a sensor probe for the aircraft. For example, the sensor probe may include the nosecone and the microphone assembly. The nosecone may be configured to block the audio signals at the tip and reduce turbulent noise of the audio signals associated with non-parallel local flow angles of the airflow.
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公开(公告)号：US11840323B2
公开(公告)日：2023-12-12
申请号：US18103992
申请日：2023-01-31
发明人： John F. Gundlach , Jacob S. Allen
CPC分类号： B64C1/061 , B33Y80/00 , B64C3/24 , B64C2001/0054
摘要： Additive manufactured airframe structure having a plurality of additive manufactured airframe segments operable to be linked together in an assembled direction. Each of the plurality of additive manufactured airframe segments are separate from one another in an unassembled configuration. Plurality of reinforcement elements operable to be received in a receiving portion of the plurality of airframe segments and extending through the plurality of airframe segments in a normal direction. Receiving portion is located on the interior of a respective one of the plurality of airframe segments.
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公开(公告)号：US20180134365A1
公开(公告)日：2018-05-17
申请号：US15791833
申请日：2017-10-24
发明人： Christian KNIPPRATH
CPC分类号： B64C1/062 , B32B3/12 , B32B2605/18 , B64C1/08 , B64C1/22 , B64C3/187 , B64C2001/0054 , B64D11/0619
摘要： An aircraft protective component for an aircraft module, the aircraft protective component includes: a plurality of cells connected together to form a lattice, each cell having a chiral structure, wherein the lattice of the cells is configured to at least partially surround the aircraft module to provide an energy absorption barrier for the aircraft module. The aircraft protective component enables the energy generated by an impact to the aircraft to be dissipated throughout the lattice of the protective component. The protective component thus acts as a ‘crumple zone’ to minimize the transfer of such impact energy to the aircraft module.
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公开(公告)号：US20180086454A1
公开(公告)日：2018-03-29
申请号：US15567586
申请日：2016-04-20
CPC分类号： B64C13/30 , B64C1/061 , B64C3/56 , B64C13/28 , B64C31/02 , B64C39/024 , B64C2001/0054 , B64C2201/021 , B64C2201/102 , B64C2201/128 , B64C2201/141 , B64C2211/00
摘要： An aerial delivery assembly for autonomously delivering a load to a target location, the assembly comprising an airframe which comprises a main body, at least one deployable lift providing structure, the lift providing structure being moveable between a stowed position and a deployed position; and at least one deployable and adjustable control structure for controlling the flight of the assembly and moveable between a stowed position and a deployed position. The main body comprises a compartment for receiving a load to be delivered. The assembly further comprises a control unit comprising an actuation module for use in adjusting the control structure, wherein the control unit is releaseably connected to the airframe such that it is reusable in an aerial delivery assembly having a different airframe.
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公开(公告)号：US20170335872A1
公开(公告)日：2017-11-23
申请号：US15599548
申请日：2017-05-19
发明人： Bradley D. Belcher
CPC分类号： F16B5/02 , B64C2001/0054 , C23C18/1653 , C25D5/18 , C25D5/56 , C25D7/00
摘要： In one example, an article including a soft substrate defining at least one of a first outer perimeter of the substrate or an aperture extending through the soft substrate defining a second outer perimeter of the aperture; a hard coating on the outer surface of the soft substrate; and at least one reinforcement member extending through the soft substrate at a location adjacent to at least one of the first outer perimeter or the second outer perimeter, wherein the at least one reinforcement member increases resistance to compression of the soft substrate at the location of the at least one reinforcement member.
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公开(公告)号：US20140224933A1
公开(公告)日：2014-08-14
申请号：US14175490
申请日：2014-02-07
发明人： Carsten Paul
IPC分类号： B64C1/06
CPC分类号： B64C1/06 , B64C1/062 , B64C1/1461 , B64C2001/0054 , B64C2001/0072 , Y02T50/43
摘要： The present invention relates to a vehicle with a skin, which has a hole with a circumferential edge, and with a structure formed from a plurality of support elements, on which structure the skin is arranged, which vehicle is characterized in that a first support element of the plurality of support elements has a first bearing surface with a first and a second section, wherein the skin is arranged flat against the first section of the first bearing surface and wherein the circumferential edge runs at least in sections in the area of the first bearing surface, and that an integrally formed frame element is arranged against the second section of the first bearing surface and, in the area of the first bearing surface, is arranged against the skin.
摘要翻译： 本发明涉及一种具有皮肤的车辆，其具有周向边缘的孔，并且具有由多个支撑元件形成的结构，其上布置有皮肤，其特征在于，第一支撑元件 所述多个支撑元件具有带有第一和第二部分的第一支承表面，其中所述皮肤平坦地布置在所述第一支承表面的所述第一部分上，并且其中所述周边边缘至少在所述第一 并且整体形成的框架元件抵靠第一支承表面的第二部分布置，并且在第一支承表面的区域中被布置成抵靠着皮肤。
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公开(公告)号：US20240294244A1
公开(公告)日：2024-09-05
申请号：US18117145
申请日：2023-03-03
申请人： JETZERO, INC.
发明人： Mark Allan Page
CPC分类号： B64C1/12 , B32B7/09 , B64C39/00 , B64F5/10 , B32B5/024 , B32B5/12 , B32B5/263 , B32B2250/20 , B32B2260/023 , B32B2260/046 , B32B2262/106 , B32B2605/18 , B64C2001/0054
摘要： An aircraft with carbon fiber material comprising a blended wing body having a main body and wings with no clear demarcation between the wings and the main body along a leading edge of the aircraft, wherein the blended wing body comprises, at least an outer skin surface comprising a carbon fiber material, at least a structural element comprising the carbon fiber material, and at least a portion of the main body comprising the carbon fiber material and configured to contain a pressure vessel and at least a propulsor, the at least a propulsor attached to the blended wing body and configured to propel the aircraft.
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8.发明申请公开(公告)号：US20190185129A1
公开(公告)日：2019-06-20
申请号：US16193109
申请日：2018-11-16
发明人： Zhenggui Wang , Muhsin Öcal
CPC分类号： B64C1/10 , B32B5/18 , B32B15/08 , B32B15/20 , B32B2262/106 , B32B2605/18 , B64C2001/0054
摘要： A pressure bulkhead for a pressurized cabin of an aerospace craft includes: a pressure wall and a frame for connecting the pressure wall to the aerospace craft; wherein the frame is connected to the pressure wall; wherein the pressure wall has: a core layer; and a first covering layer and a second covering layer; wherein the core layer is arranged between the first covering layer and the second covering layer; and wherein the core layer comprises an auxetic foam. Such a pressure bulkhead has increased stiffness, thus ensuring that smaller bending deformations and lower stresses occur. Hence costs can be saved, and the volume of the pressurized cabin which can be made available to the crew and passengers is maximized.
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公开(公告)号：US20180086434A1
公开(公告)日：2018-03-29
申请号：US15567585
申请日：2016-04-20
申请人： George Michael Cook
CPC分类号： B64C13/30 , B64C1/061 , B64C3/56 , B64C13/28 , B64C31/02 , B64C39/024 , B64C2001/0054 , B64C2201/021 , B64C2201/102 , B64C2201/128 , B64C2201/141 , B64C2211/00
摘要： An aircraft for the autonomous aerial delivery of a load to a target location, the aircraft comprising an airframe having at least one adjustable control structure for controlling the flight of the aircraft and a main body adapted to receive a load a self-contained control module releaseably connected to the airframe, the control module containing an actuator for adjusting the control structure and a controller for producing an electrical drive signal for controlling the actuator; and at least one linkage extending from the control module to the at least one adjustable control structure so as to operably connect the control module to the at least one adjustable control structure, wherein the actuator of the control module is adapted to adjust the at least one adjustable control structure using the at least one linkage so as to control the flight of the aircraft and to steer the aircraft to the target location.
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10.发明申请公开(公告)号：US20160194069A1
公开(公告)日：2016-07-07
申请号：US14881117
申请日：2015-10-12
发明人： Alan TAYLOR
CPC分类号： B64C1/38 , B64C27/08 , B64C39/024 , B64C2001/0054 , B64C2001/0072 , B64C2201/027 , B64C2201/042 , B64F5/10 , Y02T50/43
摘要： An unmanned aerial vehicle includes a body and a heat source disposed in the body. The heat source includes at least one of an electronic controller system and a motor. The unmanned aerial vehicle further includes a plurality of rotor blades. At least a portion of the body is constructed of crystalline carbon fibers.
摘要翻译： 无人驾驶飞行器包括设置在车体中的主体和热源。 热源包括电子控制器系统和电动机中的至少一个。 无人飞行器还包括多个转子叶片。 身体的至少一部分由结晶碳纤维构成。
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