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1. 发明授权

US11843347B2 Solar tracker system 有权
公开(公告)号：US11843347B2
公开(公告)日：2023-12-12
申请号：US17648545
申请日：2022-01-20
申请人： FCX Solar LLC
发明人： Christopher Thomas Needham , Frank Carl Oudheusden
IPC分类号： H02S20/32 , H01L31/0475 , H02S30/00 , H02S30/10 , G01M9/04 , G01M9/06 , F16M11/18 , F16M11/10
CPC分类号： H02S20/32 , H01L31/0475 , H02S30/00 , H02S30/10 , F16M11/10 , F16M11/18 , F16M2200/021 , G01M9/04 , G01M9/06
摘要： A photovoltaic system includes a collection of photovoltaic modules, a base supporting the collection of photovoltaic modules, and a damper coupled between the collection of photovoltaic modules and the base. The damper resists movement of the photovoltaic modules relative to the base. The damper has a first damping ratio when the collection of photovoltaic modules moves at a first rate relative to the base and a second damping ratio when the collection of photovoltaic modules moves at a second rate relative to the base, and the damper passively transitions from the first damping ratio to the second damping ratio.

2. 发明授权

US09950751B2 Aerodynamic system and method for diagnosing the aerodynamic system and verify downforce estimation based on electric motor current 有权
公开(公告)号：US09950751B2
公开(公告)日：2018-04-24
申请号：US15229762
申请日：2016-08-05
申请人： GM GLOBAL TECHNOLOGY OPERATIONS LLC
发明人： Edward T. Heil , Joshua R. Auden
IPC分类号： B60J9/00 , B62D35/00 , G01M9/06 , B62D37/02 , G01M9/08
CPC分类号： B62D35/00 , B62D35/005 , B62D35/007 , B62D37/02 , G01M9/06 , G01M9/08
摘要： A method can be executed to diagnose an aerodynamic system and includes the following steps: (a) determining, via a controller, a first expected downforce acting on an aerodynamic element of a vehicle based, at least in part, on a current position of the aerodynamic element relative to a vehicle body of the vehicle, wherein an electric motor is operatively coupled to the aerodynamic element; (b) determining, via the controller, a second expected downforce acting on the aerodynamic element of the vehicle based, at least in part, on an electrical current used to move the electric motor in order to move the aerodynamic element from the current position to another position; (c) determining a deviation, via the controller, based on the first expected downforce and the second expected downforce; and (d) controlling, via the controller, the aerodynamic element based, at least in part, on the deviation.

3. 发明申请

US20170254723A1 FLUTTER DETECTION SENSOR 审中-公开
公开(公告)号：US20170254723A1
公开(公告)日：2017-09-07
申请号：US15060297
申请日：2016-03-03
申请人： United Technologies Corporation
发明人： Troy Shannon Prince
IPC分类号： G01M9/06 , G01M15/14
CPC分类号： G01M9/06 , F01D17/08 , F01D25/04 , F04D29/665 , F05D2220/36 , F05D2260/96 , F05D2270/10 , F05D2270/3013 , F05D2270/334 , F05D2270/336 , G01M15/14
摘要： Systems and methods for monitoring aerostructures are provided. In various embodiments, a method for monitoring an aerostructure may include: receiving a signal from a pressure sensor, the pressure sensor located downstream from the aerostructure; performing a time frequency analysis on the signal to calculate a power level over a range of frequencies; monitoring the power level over the range of frequencies; and determining a susceptibility to a flutter condition based on the monitoring the power level.

4. 发明授权

US09637243B2 Aircraft lift transducer 有权
公开(公告)号：US09637243B2
公开(公告)日：2017-05-02
申请号：US14139566
申请日：2013-12-23
申请人： Safe Flight Instrument Corporation
发明人： Joseph S. Tiseo , Randall A. Greene
IPC分类号： B64D45/00 , B64C15/02 , B64C11/00 , B64C13/50 , G01M9/06 , G01L1/14 , G01D5/20
CPC分类号： B64D45/00 , B64C11/001 , B64C13/50 , B64C15/02 , G01D5/2006 , G01L1/14 , G01M9/06
摘要： An aircraft lift transducer may include a vane, actuator, an LC circuit, and a processor. The vane may be positioned on the leading edge of a wing of the aircraft, where the angle defined by the chord of the wing and the vane changes when the aircraft angle of attack changes. The actuator may be associated with the vane and change position when the angle defined by the vane and the chord changes. The LC circuit may include an induction coil spaced from the actuator and an oscillator. The oscillation frequency of the LC circuit may change when the position of the actuator changes. The processor may receive the change in the oscillation frequency and may determine a corresponding change in an available lift of the aircraft.

5. 发明授权

US09606214B2 Aero-wave instrument for the measurement of the optical wave-front disturbances in the airflow around airborne systems 有权
公开(公告)号：US09606214B2
公开(公告)日：2017-03-28
申请号：US14502015
申请日：2014-09-30
申请人： THE BOEING COMPANY
发明人： Bryan Lee Kelchner , Kenneth Jerkatis , Richard Brooks Holmes , Nikolaus Mcnerney , Jed Donaldson
IPC分类号： G06F7/70 , G06F19/00 , G06G7/00 , G06G7/76 , G01S3/786 , G01M9/06 , G01J9/00 , G02B17/06 , B64C30/00 , G01C19/04 , G02B7/182 , G02B23/08 , G02B26/08 , H04N7/18 , G02B26/10 , G02B27/14
CPC分类号： G01S3/786 , B64C30/00 , G01C19/04 , G01J9/00 , G01M9/06 , G02B7/1821 , G02B17/061 , G02B17/0657 , G02B17/0663 , G02B23/08 , G02B26/0816 , G02B26/105 , G02B27/14 , H04N7/183
摘要： The aircraft includes a fuselage and at least one aerodynamic interface surface. It further includes a gimbaled mirror system which includes a mirror supported by a gimbal to receive a light beam from a light emitting source and reflect the light beam to a first periscope fold mirror. A wave front measuring system includes at least five reflective which reflects the light beam to a fast steering mirror. The fast steering mirror reflects the light beam directly to a beam splitter wherein the light beam is split into a transmitted portion and a reflected portion of the light beam.

6. 发明授权

US09389132B1 Methods and systems for estimating an orientation of a tethered aerial vehicle relative to wind 有权
公开(公告)号：US09389132B1
公开(公告)日：2016-07-12
申请号：US14141193
申请日：2013-12-26
申请人： Google Inc.
发明人： Kenny Jensen , Damon Vander Lind
IPC分类号： G01L1/22 , G01L5/16
CPC分类号： G01L5/16 , F03D5/00 , F05B2240/917 , F05B2240/921 , G01L1/22 , G01M9/06 , Y02E10/70 , Y02E10/728
摘要： A system may include a tether coupled to a ground station. The system may also include an aerial vehicle coupled to the tether and configured to fly in a given path relative to the ground station based on a length of the tether. The system may also include one or more load cells coupled to the tether and configured to provide information indicative of a tether force between the tether and the aerial vehicle. The one or more load cells may be arranged in a given arrangement indicative of a direction of the tether force. The system may also include a controller configured to determine an angle between a direction of wind incident on the aerial vehicle and a plane defined by a longitudinal axis and a lateral axis of the aerial vehicle based on the tether force.

7. 发明授权

US09187187B2 Method of calculating dynamic pressure at the level of an aircraft surface 有权
标题翻译：计算飞机表面水平的动态压力的方法
公开(公告)号：US09187187B2
公开(公告)日：2015-11-17
申请号：US13661958
申请日：2012-10-26
申请人： AIRBUS OPERATIONS (S.A.S)
发明人： Benoit Calmels
IPC分类号： B64F5/00 , G06F17/50 , G01M9/06
CPC分类号： B64F5/00 , G01M9/06 , G06F17/5009 , G06F17/5095
摘要： The invention is aimed at a method simulating the aerodynamic flow around an aircraft, so as to detect the aerodynamic loads exerted on a predetermined surface of the aircraft. The method includes a phase of determining a value denoted QA of global dynamic pressure at the level of the predetermined surface of the aircraft. The method includes steps of carrying out simulations of aerodynamic flow around the predetermined surface of the aircraft for given environmental conditions, on the basis of a mesh produced around the shape of the aircraft, determining a local dynamic pressure qA around the predetermined surface of the aircraft, and then calculating the global dynamic pressure QA.
摘要翻译：本发明的目的在于一种模拟飞机周围的空气动力学流动的方法，以便检测施加在飞行器的预定表面上的空气动力学载荷。该方法包括在飞行器的预定表面的水平处确定表示为总体动态压力的QA的值的相位。该方法包括以下步骤：基于围绕飞机形状产生的网格，在给定的环境条件下对飞机的预定表面周围的空气动力学流动进行模拟，确定飞行器预定表面周围的局部动态压力qA ，然后计算全局动态压力QA。

8. 发明授权

US09134196B2 Inlet icing protection simulation system 有权
标题翻译：进水结冰保护仿真系统
公开(公告)号：US09134196B2
公开(公告)日：2015-09-15
申请号：US13598223
申请日：2012-08-29
申请人： Charles Steven Meis , David Charles Hass
发明人： Charles Steven Meis , David Charles Hass
IPC分类号： G01M9/08 , G01M9/06 , B64D15/04 , G01M17/00
CPC分类号： G01M9/08 , B64D15/04 , G01M9/06 , G01M17/00
摘要： A method and apparatus for generating a flow of heated air in an airfoil model of an inlet of an aircraft engine. Heated air is sent into a duct system associated with the airfoil model of the inlet of the aircraft engine. The heated air is circulated within the airfoil model of the inlet of the aircraft engine using the duct system in a manner that simulates air flowing in the inlet of the aircraft engine.
摘要翻译：一种用于在飞行器发动机的入口的翼型模型中产生加热空气流的方法和装置。加热空气被送入与飞机发动机的入口的翼型模型相关联的管道系统中。加热的空气在飞行器发动机的入口的翼型模型内使用管道系统以模拟在飞行器发动机的入口中流动的空气的方式循环。

9. 发明申请

US20140130611A1 PRESSURE TRANSDUCER STRUCTURES SUITABLE FOR CURVED SURFACES 审中-公开
标题翻译：压力传感器结构适用于弯曲表面
公开(公告)号：US20140130611A1
公开(公告)日：2014-05-15
申请号：US14157933
申请日：2014-01-17
申请人： Nora Kurtz
发明人： Anthony D. Kurtz , Scott J. Goodman , Alexander A. Ned
IPC分类号： G01L1/18
CPC分类号： G01L1/18 , G01L19/003 , G01M9/06
摘要： A flexible transducer structure suitable for attaching to a curved surface such as the leading edge of an aircraft wing is provided. In one example embodiment, a method may include receiving, at a sensor disposed on a flexible sheet, a pressure, wherein the sensor is electrically coupled to a conductive trace disposed on the flexible sheet; measuring, by the sensor, the pressure to generate a pressure signal; outputting, by the sensor, to the conductive trace, the pressure signal, wherein the conductive trace extends away from the sensor on the flexible sheet; and wherein the flexible sheet is adaptable to conform to a contour of a curved surface.
摘要翻译：提供了适于附接到诸如飞机机翼的前缘的曲面的柔性换能器结构。在一个示例性实施例中，一种方法可以包括在设置在柔性片材上的传感器处接收压力，其中传感器电耦合到布置在柔性片材上的导电迹线; 通过传感器测量产生压力信号的压力; 由传感器输出导电迹线，压力信号，其中导电迹线远离柔性片上的传感器延伸; 并且其中所述柔性片适应于符合曲面的轮廓。

10. 发明申请

US20140067288A1 High Temperature, High Bandwidth Pressure Acquisition System 有权
标题翻译：高温，高带宽压力采集系统
公开(公告)号：US20140067288A1
公开(公告)日：2014-03-06
申请号：US14076835
申请日：2013-11-11
申请人： Nora Kurtz
发明人： Anthony D. Kurtz , Alexander A. Ned , Joseph R. VanDeWeert
IPC分类号： G01L9/00 , G01L9/06
CPC分类号： G01L9/00 , G01L9/065 , G01L15/00 , G01M9/06
摘要： A method, device and system are provided for measuring multiple pressures under severe conditions. In one embodiment, a method comprises receiving, by a processor, from a first sensor, a first pressure signal; receiving, by the processor, from a second sensor, a second pressure signal; receiving, by the processor, from a first memory, a first correction coefficient for the first sensor; receiving, by the processor, from a second memory, a second correction coefficient for the second sensor; modifying, by the processor, the first pressure signal using the first correction coefficient to generate a first corrected pressure signal; modifying, by the processor, the second pressure signal using the second correction coefficient to generate a second corrected pressure signal; and outputting, by the processor, the first corrected pressure signal and the second corrected pressure signal.
摘要翻译：提供了一种用于在恶劣条件下测量多种压力的方法，装置和系统。在一个实施例中，一种方法包括由处理器从第一传感器接收第一压力信号; 由处理器从第二传感器接收第二压力信号; 由处理器从第一存储器接收第一传感器的第一校正系数; 由所述处理器从第二存储器接收所述第二传感器的第二校正系数; 由所述处理器修改所述第一压力信号，使用所述第一校正系数来生成第一校正压力信号; 通过处理器修改第二压力信号，使用第二校正系数来产生第二校正压力信号; 并且由处理器输出第一校正压力信号和第二校正压力信号。

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