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1. 发明申请

WO2009036465A9 NON-PLANAR ADAPTIVE WING SOLAR AIRCRAFT 审中-公开
标题翻译：非平面自适应翼式太阳能飞机
公开(公告)号：WO2009036465A9
公开(公告)日：2009-05-07
申请号：PCT/US2008076462
申请日：2008-09-15
申请人： AURORA FLIGHT SCIENCES CORP , PARKS ROBERT
发明人： PARKS ROBERT
IPC分类号： B64D27/00
CPC分类号： B64C3/16 , B64D27/24 , Y02T50/12 , Y02T50/44 , Y02T50/62
摘要： A system and method for assembling and operating a solar powered aircraft, composed of one or more modular constituent wing panels. Each wing panel includes at least one hinge interface that is configured to rotationally interface with a complementary hinge interface on another wing panel. When a first and second wing panel are coupled together via the rotational interface, they can rotate with respect to each other within a predetermined angular range. The aircraft further comprises a control system that is configured to acquire aircraft operating information and atmospheric information and use the same alter the angle between the wing panels, even if there are multiple wing panels. One or more of the wing panels can include photovoltaic cells and/or solar thermal cells to convert sol radiation energy or solar heat energy into electricity, that can be used to power electric motors.
摘要翻译：一种用于组装和操作太阳能飞机的系统和方法，由一个或多个模块化构成的翼板组成。每个翼板包括至少一个铰链接口，该铰链接口构造成与另一翼板上的互补铰链接口旋转地对接。当第一和第二翼片经由旋转界面联接在一起时，它们可以在预定角度范围内相对于彼此旋转。该飞机还包括控制系统，该控制系统被配置为获取飞机运行信息和大气信息，并且使用该控制系统改变翼板之间的角度，即使存在多个翼板。一个或多个翼板可以包括光伏电池和/或太阳能热电池以将溶胶辐射能或太阳能热能转换成电力，其可以用于为电动机供电。

2. 发明申请

WO2006069291A2 SYSTEM AND METHOD FOR UTILIZING STORED ELECTRICAL ENERGY FOR VTOL AIRCRAFT THRUST ENHANCEMENT AND ATTITUDE CONTROL 审中-公开
标题翻译：用于垂直起降飞机的存储电力的系统和方法提升和姿态控制
公开(公告)号：WO2006069291A2
公开(公告)日：2006-06-29
申请号：PCT/US2005046728
申请日：2005-12-22
申请人： AURORA FLIGHT SCIENCES CORP , PARKS ROBERT
发明人： PARKS ROBERT
IPC分类号： B64C1/00
CPC分类号： B64C15/00 , B64C29/0025 , B64C29/0033 , B64C29/0041 , B64C29/0083
摘要： A system and method are provided for a short take-off and landing/vertical take-off and landing aircraft that stores required take-off power in the form of primarily an electric fan engine, and secondarily in the form of an internal combustion engine, wherein the combined power of the electric fan and internal combustion engines can cause the STOL/VTOL A/C to take-off in substantially less amount of time and space than other STOL/VTOL A/C, and further wherein the transition from vertical to horizontal thrust is carefully executed to rapidly rise from the take-off position to a forward flight position, thereby minimizing the necessity for a larger electric fan engine.
摘要翻译：提供了一种用于以主要电动风扇发动机的形式存储所需起飞功率的短起飞和着陆/垂直起飞和着陆飞机的系统和方法，其次以内燃机的形式，其中电风扇和内燃机的组合功率可以使得STOL / VTOL A / C以比其它STOL / VTOL A / C大大减少的时间和空间来起飞，而且其中从垂直转向小心执行水平推力以从起飞位置快速上升到前进飞行位置，从而最小化对较大型电动风扇发动机的必要性。

3. 发明申请

WO2006069304A3 VARIABLE ENGINE INLET FOR SHORT TAKE-OFF AND LANDING AND VERTICAL TAKE-OFF AND LANDING AIRCRAFT 审中-公开
标题翻译：变速引擎适用于短时起飞和着陆以及垂直起飞和着陆飞机
公开(公告)号：WO2006069304A3
公开(公告)日：2006-09-14
申请号：PCT/US2005046755
申请日：2005-12-22
申请人： AURORA FLIGHT SCIENCES CORP , PARKS ROBERT
发明人： PARKS ROBERT
IPC分类号： B64C15/12
CPC分类号： F01D9/065 , B64C29/0075 , B64C29/0083 , B64C2201/028 , B64C2201/048 , B64C2201/088 , B64C2201/167 , B64D27/18 , B64D29/04 , B64D33/02 , F02C6/12 , F02C7/042 , F02K3/00 , F05D2220/90
摘要： A system and method for tilting an engine in a vertical take-off and landing/short take-off and landing aircraft (VTOL/STOL A/C) is provided comprising a main control system, an engine tilting mechanism, and an air flow volume detector, which is located in the engine. The system and method tilt the engine to maximize engine performance based on a variety of parameters including the air flow volume so that forward and horizontal speeds are maximized at the appropriate times, and also to reduce radar cross section and infra-red visibility.
摘要翻译：提供了一种用于使发动机在垂直起飞和着陆/短距起飞和降落飞机（VTOL / STOL A / C）中倾斜的系统和方法，其包括主控制系统，发动机倾斜机构和空气流量探测器，位于发动机中。该系统和方法倾斜发动机以基于包括空气流量在内的各种参数使发动机性能最大化，从而使前进和水平速度在适当的时间最大化，并且还减小雷达横截面和红外可见度。

4. 发明申请

WO2006137869A3 SYSTEM AND METHOD FOR CONTROLLING A ROLL RATE OF A TORSIONALLY-DISCONNECTED FREEWING AIRCRAFT 审中-公开
标题翻译：用于控制扭转断开自由飞行器的滚动速率的系统和方法
公开(公告)号：WO2006137869A3
公开(公告)日：2007-03-08
申请号：PCT/US2005033233
申请日：2005-09-19
申请人： AURORA FLIGHT SCIENCES , PARKS ROBERT
发明人： PARKS ROBERT
IPC分类号： G05D1/00 , B64C3/38
CPC分类号： B64C3/385 , G05D1/0808 , G05D1/0816
摘要： An aircraft includes a fuselage, and first and second freewings. Each of the first and second freewings is separately mounted to the fuselage and independently freely pivotable about respective pivot axes. The aircraft includes an angular rate sensor configured to measure a roll rate of the fuselage and to output a first roll rate signal. The aircraft includes a controller in communication with the angular rate sensor and configured to receive a second roll rate signal from the pilot and to compare the first and second roll rate signals to generate first and second control surface control signals. The aircraft includes at least one control actuator in communication with the controller and configured to actuate a first control surface of the first freewing and a second control surface of the second freewing in response to the first and second control surface control signals, respectively, to control the roll rate of the aircraft.
摘要翻译：一架飞机包括一个机身，第一和第二个飞行员。第一和第二自由度中的每一个分别安装到机身并且可以围绕相应的枢转轴线独立地自由地枢转。该飞行器包括角速度传感器，其被配置为测量机身的滚动速率并输出第一滚动速率信号。飞机包括与角速度传感器通信的控制器，并被配置为从飞行员接收第二滚动速率信号，并比较第一和第二滚动速率信号以产生第一和第二控制面控制信号。该飞行器包括至少一个与控制器连通的控制致动器，其被配置为分别响应于第一和第二控制面控制信号致动第一自由摆动的第一控制面和第二自由摆动的第二控制面，以控制飞机的滚动率。

5. 发明申请

WO2007005040A3 ADAPTIVE LANDING GEAR 审中-公开
标题翻译：自适应接地齿轮
公开(公告)号：WO2007005040A3
公开(公告)日：2009-04-09
申请号：PCT/US2005033234
申请日：2005-09-19
申请人： AURORA FLIGHT SCIENCES , PARKS ROBERT , MINELLI ROBERT , HAASE STEPHEN , BOERTLEIN NEIL
发明人： PARKS ROBERT , MINELLI ROBERT , HAASE STEPHEN , BOERTLEIN NEIL
IPC分类号： B64C25/10 , B64C25/22 , G06Q30/00
CPC分类号： G06Q30/08
摘要： An adaptive landing gear system for use in an aircraft includes a plurality of leveling struts. Each leveling strut includes an adaptive portion and landing pad. Each adaptive portion includes a fluid reservoir. A change in the volume of fluid in the fluid reservoir is configured to cause a change in extension of the corresponding landing pad. The adaptive portion of each leveling strut is in fluidic connection with the adaptive portion of at least one other leveling strut. The system includes a plurality of valves between the adaptive portions. Compression of the leveling strut forces fluid from the adaptive portion into the adaptive portion of at least one other leveling strut to extend the landing pad of the at least one other leveling strut. The valves prevent fluid from flowing back into the adaptive portion after compression.
摘要翻译：一种用于飞行器的自适应起落架系统包括多个调平支柱。每个调平支柱包括自适应部分和着陆垫。每个自适应部分包括流体储存器。流体储存器中的流体体积的变化被配置成引起对应着陆垫的延伸的改变。每个调平支柱的自适应部分与至少一个其他调平支柱的自适应部分流体连接。该系统包括在自适应部分之间的多个阀。平整支柱的压缩将流体从自适应部分强制进入至少一个其他调平支柱的自适应部分，以延伸至少一个其他调平支柱的着陆垫。压缩后阀门可防止流体回流到自适应部位。

6. 发明申请

WO2007056247A3 DELIVERY OF AGENTS SUCH AS CELLS TO TISSUE 审中-公开
标题翻译：递送代理作为细胞组织
公开(公告)号：WO2007056247A3
公开(公告)日：2009-05-07
申请号：PCT/US2006043133
申请日：2006-11-06
申请人： MEDRAD INC , UBER ARTHUR E III , HIRSCHMAN ALAN D , FACHER EVAN , GELBLUM EUGENE A , GRIFFITHS DAVID M , RHINEHART EDWARD J , REILLY DAVID M , COWAN KEVIN P , CEDARHOLM PAGE , TUCKER BARRY L , TROCKI MARK , MISHLER DAVID , BARTONY HENRY E JR , PARKS ROBERT
发明人： UBER ARTHUR E III , HIRSCHMAN ALAN D , FACHER EVAN , GELBLUM EUGENE A , GRIFFITHS DAVID M , RHINEHART EDWARD J , REILLY DAVID M , COWAN KEVIN P , CEDARHOLM PAGE , TUCKER BARRY L , TROCKI MARK , MISHLER DAVID , BARTONY HENRY E JR , PARKS ROBERT
IPC分类号： A61M31/00 , B65D25/04
CPC分类号： A61J1/1443 , A61J1/1456 , A61J1/1475 , A61M5/142 , A61M5/1723 , A61M5/3145 , A61M31/005 , B01L3/502 , B01L2300/044 , B01L2300/0681 , G06F19/3468
摘要： A system for delivering a fluid comprising cells to tissue of a patient, includes: a least a first container for holding an injection fluid in which the agent is carried; a first powered drive in operative connection with the container, the first powered drive being operable to pressurize contents of the container; a control system in operative connection with the first powered drive and operative to control the first powered drive; a fluid path in fluid connection with the container, the fluid path including a patient interface adapted to deposit the cells within tissue of the patient; a sensor system; and a communication system in connection with at least the control system and the sensor system. The communication system is adapted to provide information to the control system. The control system in adapted to transmit a control signal to at least the first powered drive based at least in part on information provided to the control system. The cells can for example be progenitor cells or stem cells.
摘要翻译：一种用于将包含细胞的流体输送到患者的组织的系统，包括：用于保持其中携带有药剂的注射液体的至少第一容器; 与容器操作性连接的第一动力驱动器，第一动力驱动器可操作以对容器的内容物进行加压; 控制系统，其与第一动力驱动器操作连接并且可操作以控制第一动力驱动; 与容器流体连接的流体路径，流体路径包括适于将细胞沉积在患者组织内的患者界面; 传感器系统; 以及至少与控制系统和传感器系统相关的通信系统。通信系统适于向控制系统提供信息。控制系统适于至少部分地基于提供给控制系统的信息将控制信号发送到至少第一动力驱动器。细胞可以例如是祖细胞或干细胞。

7. 发明申请

WO2007001373A3 INBOUND TRANSITION CONTROL FOR A TRAIL-SITTING VERTICAL TAKE OFF AND LANDING AIRCRAFT 审中-公开
标题翻译：用于垂直起落架和起落架的起落架过渡控制
公开(公告)号：WO2007001373A3
公开(公告)日：2008-01-17
申请号：PCT/US2005033235
申请日：2005-09-19
申请人： AURORA FLIGHT SCIENCES , PARKS ROBERT
发明人： PARKS ROBERT
IPC分类号： B64C29/02
CPC分类号： B64C3/385 , B64C29/02 , G05D1/0669 , Y02T50/145
摘要： A system for controlling inbound transition of an aircraft includes a fuselage and first and second freewings pivotably mounted on opposing sides thereof. The system includes an airspeed sensor that outputs an airspeed indication signal. The system includes a controller for increasing aircraft engine thrust to substantially maximum for inbound transition, and for generating pitch and freewing control signals. The system includes actuators for actuating aircraft control surfaces in response to the pitch control signal to rapidly increase pitch of the fuselage to decelerate the aircraft, and for actuating freewing control surfaces in response to the freewing control signal to adjust lift produced by the freewings to oppose climbing of the aircraft due to the increase in engine thrust and the increase in the fuselage pitch. The controller is configured to decrease the engine thrust as the aircraft decelerates until the aircraft is in a hover mode.
摘要翻译：一种用于控制飞行器入境过渡的系统包括机身以及可枢转地安装在其相对侧上的第一和第二快门。该系统包括输出空速指示信号的空速传感器。该系统包括一个控制器，用于将飞机发动机推力增加到进入过渡的基本最大值，并产生俯仰和自由控制信号。该系统包括用于响应于俯仰控制信号来致动飞行器控制表面的致动器，以快速增加机身的俯仰以使飞行器减速，并且响应于释放控制信号来起动释放控制表面，以调节由空档产生的升力以反对由于发动机推力的增加和机身间距的增加，飞机上升。控制器配置成当飞机减速直到飞机处于悬停模式时，减小发动机推力。

8. 发明申请

WO2007001372A9 DUCTED SPINNER FOR ENGINE COOLING 审中-公开
标题翻译：用于发动机冷却的导向螺丝
公开(公告)号：WO2007001372A9
公开(公告)日：2007-05-03
申请号：PCT/US2005033232
申请日：2005-09-19
申请人： AURORA FLIGHT SCIENCES , PARKS ROBERT
发明人： PARKS ROBERT
IPC分类号： B64D33/02
CPC分类号： B64C11/001 , B64C11/14 , B64D33/08
摘要： A system for cooling a ducted fan aircraft engine includes a first nacelle surrounding the engine and a second nacelle substantially concentrically surrounding the first nacelle. The system includes a first spinner coupled around a base of a rotor of the ducted fan and a second spinner substantially concentrically surrounding the first spinner and forming a duct between first and second spinners. The second spinner includes an opening to allow air to flow into the duct. The rotor includes a plurality of airfoils penetrating through the first and second spinners. Each of the airfoils includes a first portion located in the duct, and a second portion located between the second spinner and a fuselage of the ducted fan. The first portions of the airfoils provide cooling airflow over the engine and structural support for the second portions. The second portions of the airfoils provide thrust for the aircraft.
摘要翻译：用于冷却管道风扇飞机发动机的系统包括围绕发动机的第一机舱和基本上同心地围绕第一机舱的第二机舱。该系统包括耦合在管道风扇的转子的基部周围的第一旋转器和基本上同心地围绕第一旋转器并在第一和第二旋转器之间形成管道的第二旋转器。第二旋转器包括允许空气流入管道的开口。转子包括穿过第一和第二旋转器的多个翼型件。每个翼型件包括位于管道中的第一部分和位于第二旋转器和管道风扇的机身之间的第二部分。翼型件的第一部分在发动机上提供冷却气流，并为第二部分提供结构支撑。翼型件的第二部分为飞机提供推力。

9. 发明申请

WO2007001372A3 DUCTED SPINNER FOR ENGINE COOLING 审中-公开
标题翻译：用于发动机冷却的导向螺丝
公开(公告)号：WO2007001372A3
公开(公告)日：2009-04-23
申请号：PCT/US2005033232
申请日：2005-09-19
申请人： AURORA FLIGHT SCIENCES , PARKS ROBERT
发明人： PARKS ROBERT
IPC分类号： F02K3/04
CPC分类号： B64C11/001 , B64C11/14 , B64D33/08
摘要： A system for cooling a ducted fan aircraft engine includes a first nacelle surrounding the engine and a second nacelle substantially concentrically surrounding the first nacelle. The system includes a first spinner coupled around a base of a rotor of the ducted fan and a second spinner substantially concentrically surrounding the first spinner and forming a duct between first and second spinners. The second spinner includes an opening to allow air to flow into the duct. The rotor includes a plurality of airfoils penetrating through the first and second spinners. Each of the airfoils includes a first portion located in the duct, and a second portion located between the second spinner and a fuselage of the ducted fan. The first portions of the airfoils provide cooling airflow over the engine and structural support for the second portions. The second portions of the airfoils provide thrust for the aircraft.
摘要翻译：用于冷却管道风扇飞机发动机的系统包括围绕发动机的第一机舱和基本上同心地围绕第一机舱的第二机舱。该系统包括耦合在管道风扇的转子的基部周围的第一旋转器和基本上同心地围绕第一旋转器并在第一和第二旋转器之间形成管道的第二旋转器。第二旋转器包括允许空气流入管道的开口。转子包括穿过第一和第二旋转器的多个翼型件。每个翼型件包括位于管道中的第一部分和位于第二旋转器和管道风扇的机身之间的第二部分。翼型件的第一部分在发动机上提供冷却气流，并为第二部分提供结构支撑。翼型件的第二部分为飞机提供推力。

10. 发明申请

WO2007001371A3 VIBRATION ISOLATION ENGINE MOUNT SYSTEM AND METHOD FOR DUCTED FAN AIRCRAFT 审中-公开
标题翻译：振动隔离发动机安装系统和方法
公开(公告)号：WO2007001371A3
公开(公告)日：2007-10-04
申请号：PCT/US2005033231
申请日：2005-09-19
申请人： AURORA FLIGHT SCIENCES , PARKS ROBERT , LEDE JEAN-CHARLES
发明人： PARKS ROBERT , LEDE JEAN-CHARLES
IPC分类号： B64D27/00 , F02K99/00 , F16F7/00
CPC分类号： F02K5/02 , A63H27/12 , F02C7/20 , F02K5/00 , F05D2220/90 , F05D2250/241 , F05D2260/96 , Y02T50/672
摘要： A vibration isolation engine mount system and method for ducted fan aircraft, such as ducted fan vertical takeoff and landing (VTOL) aircraft, includes an engine for driving the ducted fan. The system includes an engine support structure for supporting the engine within the ducted fan. A rotor of the ducted fan is coupled to an engine shaft of the engine via a rotor hub. The system includes a plurality of vibration isolators configured to mount the engine to the engine support structure. Each of the plurality of vibration isolators is substantially concentrically oriented along a surface of a sphere. A center of the sphere is located at a center of the rotor hub.
摘要翻译：用于管道式风扇飞机的隔振发动机安装系统和方法，例如管道风扇垂直起降（VTOL）飞机，包括用于驱动管道风扇的发动机。该系统包括用于在发动机风扇内支撑发动机的发动机支撑结构。管道风扇的转子通过转子毂联接到发动机的发动机轴。该系统包括多个隔振器，其构造成将发动机安装到发动机支撑结构上。多个隔振器中的每一个基本上沿着球体的表面同心取向。球体的中心位于转子毂的中心。

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