专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明申请

WO2019009940A1 INVERTIBLE DRONE FOR SELECTIVE POWER CAPTURE 审中-公开
公开(公告)号：WO2019009940A1
公开(公告)日：2019-01-10
申请号：PCT/US2018/029014
申请日：2018-04-24
申请人： QUALCOMM INCORPORATED
发明人： VON NOVAK, William Henry
IPC分类号： B64C39/02 , B64D27/24 , G05D1/00
CPC分类号： G05D1/0808 , B64C39/024 , B64C2201/021 , B64C2201/042 , B64C2201/066 , B64D27/24 , B64D2211/00 , G05D1/0005 , H02S50/00 , H02S99/00 , H04B10/807 , H04L67/125 , Y02T50/44 , Y02T50/55 , Y02T50/62
摘要： Various embodiments include methods for operating a photovoltaic-powered drone (101) having a photovoltaic surface (110) on one side of at least one of wing or fuselage body of the drone (101). The method may include determining a flight attitude for the drone based on a first drone attitude for optimizing light energy harvesting by the photovoltaic surface (110) and a second drone attitude for minimizing power expenditure by an onboard propulsion system of the drone (101) to reach a designated destination. The method may include flying the drone in the determined flight attitude while converting light into electricity en route to the designated destination.

2. 发明申请

WO2017146579A1 AIRPLANE WITH AN AFT-FUSELAGE MOUNTED PROPULSIVE EMPENNAGE WITH INTEGRATED CONTROL SURFACES 审中-公开
标题翻译：带有集成控制表面的AFT-FUSELAGE安装式推进力仪的飞机
公开(公告)号：WO2017146579A1
公开(公告)日：2017-08-31
申请号：PCT/NL2017/050116
申请日：2017-02-24
申请人： TECHNISCHE UNIVERSITEIT DELFT
发明人： VELDHUIS, Leonardus , VAN ARNHEM, Nando
IPC分类号： B64C11/00 , B64D27/02
CPC分类号： B64C11/001 , B64C5/02 , B64C9/02 , B64C9/38 , B64C39/062 , B64C2003/445 , B64D27/02 , Y02T50/14 , Y02T50/44 , Y02T50/66
摘要： Airplane comprising a fuselage with an empennage, wherein the fuselage is provided with wings and comprises a propulsion system (6) with propellers, wherein the propulsion system is integrated with the aft-fuselage mounted empennage forming a propulsive empennage. The 'propulsive empennage' preferably comprises two ring wings (7), each forming a duct wherein each duct is provided with at least one propeller mounted in the duct. The two ring wings are mounted symmetrically on sides of the fuselage.
摘要翻译：包括具有尾翼的机身的飞机，其中机身设置有机翼并且包括具有螺旋桨的推进系统（6），其中推进系统与安装在机身后部的尾翼集成，形成推进器尾翼。 “推进尾翼”优选包括两个环形翼（7），每个形成一个管道，其中每个管道设有至少一个安装在管道中的螺旋桨。两个环翼对称安装在机身两侧。

3. 发明申请

WO2017123699A1 HYBRID PROPULSION VERTICAL TAKE-OFF AND LANDING AIRCRAFT 审中-公开
标题翻译：混合推进垂直起飞和着陆飞机
公开(公告)号：WO2017123699A1
公开(公告)日：2017-07-20
申请号：PCT/US2017/013105
申请日：2017-01-12
申请人： AURORA FLIGHT SCIENCES CORPORATION
发明人： GIANNINI, Francesco , GOMEZ, Martin , COTTRELL, Dan , LEDE, Jean-Charles , ROBERTS, Tom , SCHAEFER, Carl, Jr. , COLAS, Dorian , WHIPPLE, Brian , NUHFER, Tim , HUNTER, Herb , GROHS, Jonathon , PETULLO, Steve
IPC分类号： B64C3/38 , B64C5/04 , B64C5/16 , B64C29/00 , B64C39/12 , B64D27/02 , B64D27/24
CPC分类号： B64C29/0033 , B64C3/385 , B64C5/04 , B64C5/16 , B64C39/024 , B64C39/12 , B64C2201/021 , B64C2201/042 , B64C2201/048 , B64D27/24 , B64D29/02 , B64D2027/026 , Y02T50/14 , Y02T50/44 , Y02T50/64
摘要： A hybrid propulsion aircraft (100) is described having a distributed electric propulsion system. The distributed electric propulsion system includes a turbo shaft engine (112) that drives one or more generators (116) through a gearbox (132). The generator (116) provides AC power to a plurality of ducted fans (108, 110), each being driven by an electric motor (506). The ducted fans (108, 110) may be integrated with the hybrid propulsion aircraft's wings (104, 106). The wings (104, 106) can be pivotally attached to the fuselage (102), thereby allowing for vertical take-off and landing. The design of the hybrid propulsion aircraft (100) mitigates undesirable transient behavior traditionally encountered during a transition from vertical flight to horizontal flight. Moreover, the hybrid propulsion aircraft (100) offers a fast, constant-altitude transition, without requiring a climb or dive to transition. It also offers increased efficiency in both hover and forward flight versus other VTOL aircraft and a higher forward max speed than traditional rotorcraft.
摘要翻译：描述了具有分布式电力推进系统的混合动力推进飞行器（100）。分布式电力推进系统包括通过齿轮箱（132）驱动一个或多个发电机（116）的涡轮轴发动机（112）。发电机（116）向多个管道式风机（108,110）提供AC电力，每个管道式风机由电动机（506）驱动。管道风扇（108,110）可以与混合动力推进飞机的机翼（104,106）集成。机翼（104,106）可枢转地附接到机身（102），从而允许垂直起飞和着陆。混合动力推进飞行器（100）的设计减轻了从垂直飞行向水平飞行过渡期间传统上遇到的不期望的瞬态行为。此外，混合动力推进飞机（100）提供快速，恒定高度的过渡，而不需要爬升或俯冲转换。与其他垂直起降飞机相比，它还提高了悬停和前进飞行的效率，并且比传统的旋翼飞行器具有更高的前进最大速度。

4. 发明申请

WO2017065858A3 EJECTOR AND AIRFOIL CONFIGURATIONS 审中-公开
标题翻译：喷射器和机翼配置
公开(公告)号：WO2017065858A3
公开(公告)日：2017-07-13
申请号：PCT/US2016044326
申请日：2016-07-27
申请人： JETOPTERA INC , EVULET ANDREI
发明人： EVULET ANDREI
IPC分类号： B64C15/14 , F02K1/36
CPC分类号： B64D29/02 , B64C9/38 , B64C15/00 , B64C21/00 , B64C39/024 , B64C2201/10 , B64C2201/104 , B64D27/10 , B64D27/18 , B64D33/02 , B64D33/04 , B64D2033/0273 , Y02T50/166 , Y02T50/32 , Y02T50/44
摘要： A propulsion system coupled to a vehicle. The system includes an ejector having an outlet structure out of which propulsive fluid flows at a predetermined adjustable velocity. A control surface having a leading edge is located directly downstream of the outlet structure such that propulsive fluid from the ejector flows over the control surface.
摘要翻译：与车辆连接的推进系统。该系统包括具有出口结构的喷射器，推进流体在该出口结构中以预定的可调节速度流动。具有前缘的控制表面直接位于出口结构的下游，使得来自喷射器的推进流体流过控制表面。

5. 发明申请

WO2017065859A2 FLUIDIC PROPULSIVE SYSTEM 审中-公开
公开(公告)号：WO2017065859A2
公开(公告)日：2017-04-20
申请号：PCT/US2016/044327
申请日：2016-07-27
申请人： JETOPTERA, INC. , EVULET, Andrei
发明人： EVULET, Andrei
IPC分类号： B64D27/18 , B64D29/02
CPC分类号： B64D29/02 , B64C9/38 , B64C15/00 , B64C21/00 , B64C21/04 , B64C39/024 , B64C2201/10 , B64C2201/104 , B64D27/10 , B64D27/18 , B64D33/02 , B64D33/04 , B64D2033/0273 , Y02T50/166 , Y02T50/32 , Y02T50/44
摘要： A propulsion system coupled to a vehicle. The system includes a convex surface, a diffusing structure coupled to the convex surface, and at least one conduit coupled to the convex surface. The conduit is configured to introduce to the convex surface a primary fluid produced by the vehicle. The system further includes an intake structure coupled to the convex surface and configured to introduce to the diffusing structure a secondary fluid accessible to the vehicle. The diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid and secondary fluid.

6. 发明申请

WO2017042712A1 APPARATUS AND METHODS FOR DISTRIBUTING ELECTRIC POWER ON AN AIRCRAFT DURING A LIMITED POWER AVAILABILITY CONDITION 审中-公开
标题翻译：用于在有限的动力可用性条件下分配飞机上的电力的装置和方法
公开(公告)号：WO2017042712A1
公开(公告)日：2017-03-16
申请号：PCT/IB2016/055362
申请日：2016-09-08
申请人： BOMBARDIER INC. , SHORT BROTHERS PLC
发明人： NFONGUEM, Gustave , ILIESCU, Vlad
IPC分类号： B64D41/00
CPC分类号： B64D41/00 , B64D41/007 , B64D2221/00 , Y02T50/44
摘要： Methods and apparatus for distributing electric power from a power source of an aircraft to a plurality of electrical loads of the aircraft during a limited power availability condition are disclosed. An exemplary method comprises: distributing electric power from the power source of the aircraft to the plurality of electrical loads; receiving one or more signals indicative of a demand for electric power by one or more of the plurality of electrical loads; and adjusting the power distribution to the plurality of electrical loads based on the demand for electric power by the one or more plurality of electrical loads. The power distribution is also adjusted to maintain an overall power consumption of the plurality of electrical loads at or below a threshold.
摘要翻译：公开了在有限的功率可用性条件期间将电力从飞行器的电源分配到飞行器的多个电负载的方法和装置。一种示例性方法包括：将电力从飞机的电源分配到多个电负载; 通过所述多个电负载中的一个或多个接收指示电力需求的一个或多个信号; 以及基于所述一个或多个多个电负载对电力的需求来调整对所述多个电负载的功率分配。还调整功率分布以维持等于或低于阈值的多个电负载的总功耗。

7. 发明申请

WO2017041018A1 FLUIDIC PROPULSIVE SYSTEM AND THRUST AND LIFT GENERATOR FOR AERIAL VEHICLES 审中-公开
标题翻译：流体推进系统和用于空中客车的起升和起跳发电机
公开(公告)号：WO2017041018A1
公开(公告)日：2017-03-09
申请号：PCT/US2016/050236
申请日：2016-09-02
申请人： JETOPTERA, INC.
发明人： EVULET, Andrei
IPC分类号： B64C21/04 , B64C23/00 , B64C39/12 , B64D27/02 , B64D33/04 , F02K1/28 , F02C3/32
CPC分类号： B64D29/02 , B64C9/38 , B64C15/00 , B64C21/00 , B64C21/04 , B64C39/024 , B64C2201/10 , B64C2201/104 , B64D27/10 , B64D27/18 , B64D33/02 , B64D33/04 , B64D2033/0273 , Y02T50/166 , Y02T50/32 , Y02T50/44
摘要： A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at least one tail conduit. The fore ejectors respectively include an outlet structure out of which gas from the at least one fore conduit flows. The at least one tail ejector includes an outlet structure out of which gas from the at least one tail conduit flows. First and second primary airfoil elements have leading edges respectively located directly downstream of the first and second fore ejectors. At least one secondary airfoil element has a leading edge located directly downstream of the outlet structure of the at least one tail ejector.
摘要翻译：车辆包括产生气流的主体和气体发生器。至少一个前导管和尾管与流体耦合到发生器。第一和第二前喷射器流体地联接到至少一个前导管。至少一个尾喷射器流体地联接到所述至少一个尾管。前喷射器分别包括出口结构，来自至少一个前导管的气体流出。至少一个尾喷射器包括出口结构，来自至少一个尾管的气体从该出口结构流出。第一和第二主翼元件具有分别位于第一和第二前部喷射器的下游的前缘。至少一个副翼元件具有位于至少一个尾喷射器的出口结构的下游的前缘。

8. 发明申请

WO2017037435A1 ELECTRICAL POWER SUPPLY ON A VEHICLE 审中-公开
标题翻译：车上的电力供应
公开(公告)号：WO2017037435A1
公开(公告)日：2017-03-09
申请号：PCT/GB2016/052660
申请日：2016-08-26
申请人： BAE SYSTEMS PLC
发明人： WOODHOUSE, Gordon, Charles , BOSTON, Luke, Michael
IPC分类号： H02J1/10 , B64D41/00
CPC分类号： H02J1/10 , B64D41/00 , B64D2041/005 , H02J7/34 , H02J2001/004 , Y02T50/44 , Y02T50/54 , Y02T90/36
摘要： A vehicle (100) comprising: an engine (102); an engine driven electrical power generator (104) configured to be driven by the engine (102); a fuel cell (110); one or more vehicle subsystems (106); a memory (118) storing a plurality of different power sharing templates (126), each power sharing template (126) specifying different power supply sharing information; and a controller (116, 22) configured to: select a power sharing template (126) from the plurality of power sharing templates (126); and control the engine driven electrical power generator (104) and the fuel cell (110) to supply electrical power to the one or more vehicle subsystems (106) such that said supply of electrical power is proportioned between the engine driven electrical power generator (104) and the fuel cell (110) in accordance with the power supply sharing information specified in the selected power sharing template (126).
摘要翻译：一种车辆（100），包括：发动机（102）; 发动机驱动的发电机（104），被构造成由所述发动机（102）驱动; 燃料电池（110）; 一个或多个车辆子系统（106）存储多个不同功率共享模板（126）的存储器（118），指定不同电源共享信息的每个功率共享模板（126）以及控制器（116,22），被配置为：从所述多个功率共享模板（126）中选择功率共享模板（126）; 并且控制所述发动机驱动的发电机（104）和所述燃料电池（110）以向所述一个或多个车辆子系统（106）提供电力，使得所述发动机驱动的发电机（104））和燃料电池（110），根据在所选择的功率共享模板（126）中指定的电源共享信息。

9. 发明申请

WO2017014508A1 하이브리드 전기 추진시스템을 이용하는 수직이착륙 항공기 审中-公开
标题翻译：使用混合电动推进系统的垂直起落架和起落架飞机
公开(公告)号：WO2017014508A1
公开(公告)日：2017-01-26
申请号：PCT/KR2016/007760
申请日：2016-07-15
申请人： 주식회사 한국카본
发明人： 박정규 , 조진수 , 김보성 , 윤승현 , 원성홍 , 정태철 , 조수영 , 이근호 , 박규성 , 하주형 , 문창모 , 백선호 , 맹창준 , 이한기 , 김민준 , 이다인
IPC分类号： B64D31/06 , B64D27/24 , B64D35/04 , B64D35/02 , B64C29/00 , B64C27/12 , B64C27/32
CPC分类号： B64D27/24 , B64C29/0025 , B64C29/0033 , B64C2201/042 , B64D27/02 , B64D31/06 , B64D35/02 , B64D2027/026 , B64D2221/00 , Y02T50/44 , Y02T50/64
摘要： 하이브리드 전기 추진시스템을 이용하는 수직이착륙 항공기가 개시된다. 일 실시예에 따른 하이브리드 수직이착륙 항공기는 엔진, 상기 엔진에서 공급되는 동력을 이용하여 전력을 생산하는 발전기, 상기 발전기에서 생산된 전력을 저장하는 배터리, 상기 배터리에 저장된 전력 및 상기 발전기에서 생산되되 상기 배터리에 저장되지 않은 전력 중 적어도 하나를 공급받으며, 적어도 하나의 추력 발생 장치에 동력을 제공하는 모터 및 상기 배터리에 저장된 전력만을 상기 모터에 공급하고, 상기 모터의 출력을 조절하여 지속 가능 시간을 제어하는 사일런스(silence) 모드 또는 상기 배터리에 저장되지 않은 전력을 상기 모터에 공급하는 노멀(normal) 모드를 선택하고, 상기 선택된 모드에 기초하여, 상기 모터에 공급되는 전력에서, 상기 배터리에 저장된 전력의 양 및 상기 배터리에 저장되지 않은 전력의 양을 결정하는 제어부를 포함할 수 있다.
摘要翻译：公开了使用混合动力推进系统的垂直起降飞机。根据一个实施例的混合动力垂直起降飞机包括：发动机; 发电机，通过使用从发动机供给的动力产生电力; 存储由发电机产生的电力的电池; 提供存储在电池中的电力中的至少一个的电动机和由发电机产生但不存储在电池中的电力，并且向至少一个推进生成装置供电; 以及控制单元，其仅将存储在电池中的电力提供给电动机，通过调节电动机的输出或向电动机提供不是电动机的正常供电模式来选择控制寿命的静音模式存储在电池中，并且基于所选择的模式，确定存储在电池中的电力的量和未存储在电池中的电力量，供给到电动机的电力。

10. 发明申请

WO2016193372A1 COOLING SYSTEM FOR A GALLEY, AND METHOD OF OPERATING SUCH A COOLING SYSTEM 审中-公开
标题翻译：用于汽车的冷却系统，以及操作这种冷却系统的方法
公开(公告)号：WO2016193372A1
公开(公告)日：2016-12-08
申请号：PCT/EP2016/062497
申请日：2016-06-02
申请人： AIRBUS OPERATIONS GMBH
发明人： TRUEMPER, Torsten
IPC分类号： B64D13/08 , B64D13/06 , B64D11/04
CPC分类号： B64D11/04 , B64D13/08 , B64D2013/0629 , B64D2013/0655 , F25B2339/047 , F25B2600/112 , F25B2600/2511 , F25B2700/21173 , Y02T50/44 , Y02T50/46 , Y02T50/56
摘要： A cooling system (10) for a galley (100) for installation in a transportation means, in particular an aircraft, comprises a cooling device (11) which comprises a coolant circuit (12) adapted to be flown through with a coolant. The cooling system (10) further comprises a fluid line (18) which is adapted to be flown through with a fluid to be cooled and which is thermally coupled with the coolant circuit (12) of the cooling device (11) in order to transfer heat from the fluid to be cooled flowing through the fluid line (18) to the coolant circulating in the coolant circuit (12), and an air line (38) which is adapted to be flown through with air and which is thermally coupled to the coolant circuit (12) of the cooling device (11) in order to transfer heat from the coolant circulating in the coolant circuit (12) to the air line (38). The air line (38), downstream of the thermal coupling of the air line (38) with the coolant circuit (12) of the cooling device (11), is connectable to a cabin region (52) of the transportation means accommodating the galley (100) in order to supply the cabin region (52) with air warmed by heat transfer from the coolant circulating in the coolant circuit (12) of the cooling device (11).
摘要翻译：用于安装在运输装置，特别是飞行器中的用于厨房（100）的冷却系统（10）包括冷却装置（11），其包括适于通过冷却剂流动的冷却剂回路（12）。冷却系统（10）还包括流体管线（18），该流体管线（18）适于与要冷却的流体一起流动，并且与冷却装置（11）的冷却剂回路（12）热耦合以便传递来自待冷却的流体的热量流过流体管线（18）到在冷却剂回路（12）中循环的冷却剂，以及空气管线（38），其适于通过空气流动并且热耦合到冷却装置（11）的冷却剂回路（12），以将来自在冷却剂回路（12）中循环的冷却剂的热量传递到空气管路（38）。空气管线（38）与冷却装置（11）的冷却剂回路（12）的热耦合下游的空气管线（38）可连接到容纳厨房的运输装置的客舱区域（52）（100），以便从所述冷却装置（11）的冷却剂回路（12）中循环的冷却剂供应由热传递加热的空气的所述客舱区域（52）。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式