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公开(公告)号：US10684190B2
公开(公告)日：2020-06-16
申请号：US15313408
申请日：2015-05-22
发明人： Dominique Placko , Alain Rivollet , Thierry Bore
IPC分类号： G01M9/06
摘要： A device measures at least a first physical quantity of fluid flow in a three-dimensional space having at least one predetermined interface, between at least two media. The device comprises a computer prescribing first and second conditions at the different boundaries concerning the first physical quantity, associated respectively with a first source and a second source, different to one another, the first and second sources being point sources of mass flow of fluid and/or of force. The computer calculates, by distributed point source calculation, a first value of the first physical quantity from the first condition and from the first source and a second value of the first physical quantity from the second condition and from the second source, at at least one second point, different from the first test point, then combines the values to calculate for the first physical quantity respectively from the different boundary conditions and sources.
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公开(公告)号：US10605279B2
公开(公告)日：2020-03-31
申请号：US14601742
申请日：2015-01-21
申请人： Kevin Kremeyer
发明人： Kevin Kremeyer
摘要： Systems, equipment, and methods to deposit energy to modify and control shock waves and hypersonic or supersonic fluid flow, including systems for controlling, mitigating, and/or effecting air flow in relation to air vehicles, wind tunnels, or other assets, or the like, as well as systems, equipment, and methods for disrupting the shock structure at the inlet for the engine of an air vehicle traveling at supersonic or hypersonic speed; mitigating blast effects on vehicles; mitigating heating of throats in supersonic and hypersonic wind tunnels, as well as control the flow parameters and Mach number in their test sections.
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公开(公告)号：US20200026275A1
公开(公告)日：2020-01-23
申请号：US16121226
申请日：2018-09-04
发明人： Bernard Barriety , Robin Vernay , Fabio Vetrano , Davide Cantiani
摘要： A method for alleviating and protecting loads of a lifting surface of an aircraft based on control of structural distortions of the lifting surface. The lifting surface includes a control surface, a maneuvering system for displacing the control surface and sensors which measure a dimensional characteristic linked to the distortion of the lifting surface. The method acquires characteristic data linked to the distortion of the lifting surface, determines a set of values of the shape, analyzes the value of the strain attribute and compares the set of values characterizing the shape to the values of the tolerance interval associated with the lifting surface. If the set of values characterizing the shape is outside of the interval, the process triggers an activation of the maneuvering system to displace the control surface from an initial position in order to alleviate the loads on the lifting surface.
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公开(公告)号：US10519801B2
公开(公告)日：2019-12-31
申请号：US15363684
申请日：2016-11-29
发明人： Jérémy Giordan , Valentine Lucette Bader , André Pierre Jean Xavier Leroux , Stéphane Rousselin
摘要： An annular air flow passage, particularly for a turbine engine, comprising two radially internal and external annular walls. A measuring element is elongated in a direction between the internal and external annular walls, and a first of the internal or external ends of the element is fixed rigidly to a first of the internal or external walls. The element includes at least one tubular cavity extending along the element and supplied with pressurized fluid.
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公开(公告)号：US20190301969A1
公开(公告)日：2019-10-03
申请号：US16302768
申请日：2017-05-18
申请人： 1323079 Alberta Ltd.
发明人： Chris Morton , Kelly Zwarych
摘要： Methods and apparatus for monitoring fluid-dynamic drag on an object, such as a bicycle, ground vehicle, watercraft, aircraft, or portion of a wind turbine are provided. An array of sensors obtain sensor readings for example indicating: power input for propelling the object; air speed and direction relative to motion of the object; and ground speed of the object. Sensor readings may also indicate: temperature; elevation and humidity for providing a measurement of air density. Sensor readings may also indicate inclination angle and forward acceleration. Processing circuitry determines a coefficient of drag area based on the sensor readings and optionally one or more stored parameters, according to a predetermined relationship. A pitot tube based apparatus for measuring fluid speed and direction is also provided. Methods for dynamic in situ calibration of the pitot tube apparatus, and of adjusting correction factors applied to correct measurement errors of this apparatus are also provided.
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公开(公告)号：US10345191B2
公开(公告)日：2019-07-09
申请号：US15415687
申请日：2017-01-25
申请人： Joel A. Walter , Edward G. Duell , Paul A. Nagle
发明人： Joel A. Walter , Edward G. Duell , Paul A. Nagle
IPC分类号： G01M9/04 , G01M9/06 , G01M17/007
摘要： A transportable wind tunnel testing automobiles, motorcycles, bicycles, scale-model aircraft, building structures, and other products requiring high-quality and low noise directed air flow. The wind tunnel comprises one or more containers which can be separately transported on trailers. Each wind tunnel container comprises one or more fans, conditioning screens, acoustic baffles, and a reduction or contraction section. Wind tunnels may be connected end-to-end or side-to-side, with joined outflow. The wind tunnel containers can be used on the trailers, or can be removed and temporarily installed at a location.
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公开(公告)号：US10309868B2
公开(公告)日：2019-06-04
申请号：US15193389
申请日：2016-06-27
申请人： The Boeing Company
摘要： An apparatus is provided for providing simulated smoke. The apparatus comprises a reservoir including a reservoir port, and a bladder disposed in the reservoir. The bladder can be deflated to cause a fluid substance to flow through the reservoir port into the reservoir to fill the reservoir with the fluid substance to generate smoke. The bladder can be inflated to cause smoke to flow out of the reservoir through the reservoir port to provide simulated smoke.
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公开(公告)号：US20190094094A1
公开(公告)日：2019-03-28
申请号：US16138515
申请日：2018-09-21
CPC分类号： G01L19/0092 , B64D43/00 , G01L19/086 , G01L19/141 , G01L19/147 , G01L19/148 , G01M9/065 , H01L29/84
摘要： A sensor is configured to attach to a main body and includes a sensor body, a transducer, a transmitter, and a power source. The sensor body is configured to provide a smooth transition with a surface of the main body. The transducer is positioned within the sensor body and is configured to provide a sensed output. The transmitter is positioned within the sensor body and is configured to transmit the sensed output. The power source is positioned within the sensor body and is configured to provide electrical power to the transducer and the transmitter.
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公开(公告)号：US20190003912A1
公开(公告)日：2019-01-03
申请号：US15641148
申请日：2017-07-03
申请人： The Boeing Company
发明人： Sho Sato , Chen Chuck
摘要： Various techniques are provided for correcting error in static pressure data. In one example, a system includes an aircraft component. The aircraft component can include a port disposed within the aircraft component. A static pressure sensor is disposed within the port. The static pressure sensor is configured to provide primary pressure data in response to environmental air pressure. The data provided can include error due to acoustic disturbance. The system can also include an acoustic sensor configured to provide acoustic data in response to the acoustic disturbance. Data from the static pressure sensor and the acoustic sensor can be provided to a processor communicatively coupled to the static pressure sensor and the acoustic sensor. The processor can be configured to determine corrected static pressure data using the provided primary pressure data and the provided acoustic data. Additional systems and similar methods are also provided.
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100.发明授权公开(公告)号：US10138754B2
公开(公告)日：2018-11-27
申请号：US15348824
申请日：2016-11-10
IPC分类号： F01D21/00 , G01D11/24 , G01M15/14 , F01D5/14 , G01L15/00 , G01L19/14 , G01P5/165 , G01M9/06 , G01F1/46 , G01P5/10 , G01P5/14
摘要： The present invention relates to a device for measuring aerodynamic magnitudes (1) intended to be placed transversally in a flow passage (12, 13) of a turbine engine comprising: an upstream body (2) having a profile of general cylindrical shape defining a leading edge (5) a plurality of sensors (4), the instrumentation lines (45) of the sensors being placed in the body (2), the sensitive elements (41) of the sensors extending at the leading edge (5); a downstream fairing (3) mounted on the upstream body (2) and defining a trailing edge (6); the downstream fairing (3) comprising, in the longitudinal direction of the upstream body (2), several sections (35) fixed independently of each other to the body (2), two successive sections (35) being connected by a flexible junction (37).
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