| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 161 | Boundary layer flow sensor | US14261594 | 2014-04-25 | US09592920B2 | 2017-03-14 | Jeffrey D. Crouch |
| Apparatus and methods described herein provide for boundary layer flow sensor and corresponding determination of the flow characteristics of an ambient airflow over an aerodynamic surface. According to one aspect of the disclosure provided herein, the boundary layer flow sensor includes a body configured for mounting within or below the aerodynamic surface, a pressure port configurable between an open state for taking pressure measurements within the boundary layer of the ambient airflow and a closed state that protects the pressure port from contaminants when not in use. | ||||||
| 162 | Method of mounting pressure ports in the skin of an aircraft | US14492307 | 2014-09-22 | US09546006B2 | 2017-01-17 | Michel Bacou; Christophe Arruti |
| A method of mounting at least one pressure port in a skin of an aircraft, where the port is made with a hollow tube implanted in the skin, optimizes conditions whereby each of the tubes is made flush with the skin so that static or dynamic pressure measurements are accurate and reliable. The method includes a step of leveling each of the tubes and a step of painting the skin. To achieve satisfactory leveling conditions for the tubes on each occasion, the leveling step is independent of the layer of paint deposited on the skin. | ||||||
| 163 | METHOD AND DEVICE FOR DETERMINING THE VELOCITY OF A MEDIUM | US15034243 | 2014-11-04 | US20160273946A1 | 2016-09-22 | Christoph BAER; Thomas MUSCH; Stephan NEUBURGER; Michael VOGT; Timo JAESCHKE |
| A method and device for determining a velocity of a flowing medium that allows an as high as possible measuring accuracy without requiring a complicated measuring construction is achieved in that a vortex is generated in the medium and an electromagnetic signal is emitted into the medium. Then, the permittivity of the medium is determined and the velocity of the medium is determined using the permittivity measurement. | ||||||
| 164 | System and Method for a Wind Speed Meter | US14610933 | 2015-01-30 | US20160223579A1 | 2016-08-04 | Andreas Froemel; Marsetz Waldemar |
| According to an embodiment, a method of measuring wind speed includes measuring atmospheric pressure at a first pressure sensor arranged inside a case and shielded from wind, measuring air pressure at a second pressure sensor arranged at an opening in the case, and determining wind speed at the opening in the case based on measuring the atmospheric pressure and the air pressure. | ||||||
| 165 | Load distribution estimation | US13837418 | 2013-03-15 | US09335229B2 | 2016-05-10 | Jonathon P. Baker; Edward A. Mayda |
| A system and method for pressure based load measurement are provided. The system and method measure at least one pressure differential on an airfoil and determine at least one aerodynamic load associated with the at least one pressure differential. The determined at least one load is used to modify characteristics of the airfoil to increase efficiency and/or avoid damage. The determined at least one aerodynamic load may be further utilized to balance and/or optimize loads at the airfoil, estimate a load distribution along the airfoil used to derive other metrics about the airfoil, and/or used in a distributed control system to increase efficiency and/or reduce damage to, e.g., one or more wind turbines. | ||||||
| 166 | Method and apparatus for improved accuracy of static pressure measurement using pressure taps | US14220811 | 2014-03-20 | US09329197B2 | 2016-05-03 | Sho Sato |
| A method and apparatus for measuring static pressure. A tube is positioned within a hole in a structure. The hole has a hole diameter that is larger than a tube diameter of the tube such that a gap is formed between the tube and the hole. A first portion of deflected fluid that is deflected from a flow of fluid passing over the hole enters the gap and a second portion of the deflected fluid enters the tube. The static pressure of the fluid is measured at a location of the hole with the tube positioned within the hole. | ||||||
| 167 | METHOD AND DEVICE FOR AUTOMATICALLY ESTIMATING AT LEAST ONE SPEED OF AN AIRCRAFT | US14886727 | 2015-10-19 | US20160107762A1 | 2016-04-21 | Philippe Goupil; Nicola Mimmo; Pierre Chevalier; Daniel Lopez Fernandez; Rémy Dayre |
| A device including a first data generating unit for determining at least one aerodynamic hinge moment of at least one control surface of the aircraft, a second data generating unit for determining a plurality of data and at least one external static pressure and a model of hinge moment coefficient, a computation unit for computing with the aid of these data at least one speed of the aircraft, namely a Mach number and/or a conventional speed, and a data transmission unit for providing this speed to a user system. | ||||||
| 168 | Method and System of Measurement of Mach and Dynamic Pressure Using Internal Sensors | US14818432 | 2015-08-05 | US20160041196A1 | 2016-02-11 | Robert D. Frey, JR.; David J. Schorr |
| A system for calculating airspeed and dynamic pressure comprises a system body, an internal accelerometer, located within the system body, an internal pressure sensor, located in the system body, the internal pressure sensor being not hermetically sealed within the system body and capable of measuring the static pressure of the ambient atmosphere, and a processor in reception of the internal accelerometer, and the internal pressure sensor, capable of calculating Mach number via an axial acceleration, and capable of calculating a dynamic pressure and a true airspeed via the Mach number. | ||||||
| 169 | MEMS-Based Conformal Air Speed Sensor | US14318955 | 2014-06-30 | US20150377662A1 | 2015-12-31 | Gary A. Ray |
| Systems and methods for measuring air speed which solve the problem of icing or blockage by creating an exterior surface on an aircraft that channels air and measures the pressure difference of the pressure through the airflow and the static pressure. This exterior surface cannot be blocked easily because air is always flowing when the aircraft is in motion, any external matter that could be on the exterior surface is readily visible, and the exterior surface can be heated to prevent icing. In addition, the exterior surface is made of a flexible material that is able to conform closely to the exterior shape of the aircraft. The preferred embodiments comprise microelectromechanical system pressure sensors placed under the air channels for measuring the pressure difference in each channel and an air speed processor for transforming the pressure differences into an air speed estimate. | ||||||
| 170 | MEASUREMENT SYSTEM FOR MEASURING THE VELOCITY OF AN AIRCRAFT | US14710319 | 2015-05-12 | US20150329216A1 | 2015-11-19 | Pascal Laurens |
| The disclosure herein relates to a measurement system to measure characteristics of the velocity vector of an aircraft in relation to a surrounding air mass, the measurement system comprising—a frontal surface of the aircraft, two primary sensors, each being fixed to the frontal surface of the aircraft and able to deliver an output value relating to the deformation experienced by the sensor, and a processing unit able to receive the output values and able to calculate the angle of attack and/or the velocity of the aircraft on the basis of these output values. | ||||||
| 171 | THREE-DIMENSIONAL FLOW VELOCITY VECTOR, ENERGY AND MASS GAUGE | US14403031 | 2013-06-25 | US20150160091A1 | 2015-06-11 | Guoping Du; Jiajia Du; Xiaofeng Song; Guanglin Du |
| A three-dimensional flow velocity vector, energy and mass gauge is provided, wherein it comprises an elastic leather cover, both ends of which are mounted with a rigid sealing plug, separately, the elastic leather cover and the rigid sealing plug forming a cylindrical sealing cavity, in which a cable connecting line hole is installed on the upper rigid sealing plug, while an injection hole for injecting liquid into the cylindrical sealing cavity, on which a sealing plug is provided, is installed on the lower rigid sealing plug; and a measuring device for measuring the flow velocity vector and energy and a device for measuring the mass are installed in the cylindrical sealing cavity. The gauge has the advantages of a simple structure, convenient manufacturing and comprehensive detection. | ||||||
| 172 | MICROELECTRONIC ENVIRONMENTAL SENSING MODULE | US13853801 | 2013-03-29 | US20140294046A1 | 2014-10-02 | Olivier Le Neel; Ravi Shankar; Suman Cherian |
| Sensors for air flow, temperature, pressure, and humidity are integrated onto a single semiconductor die within a miniaturized Venturi chamber to provide a microelectronic semiconductor-based environmental multi-sensor module that includes an air flow meter. One or more such multi-sensor modules can be used as building blocks in dedicated application-specific integrated circuits (ASICs) for use in environmental control appliances that rely on measurements of air flow. Furthermore, the sensor module can be built on top of existing circuitry that can be used to process signals from the sensors. By integrating the Venturi chamber with accompanying environmental sensors, correction factors can be obtained and applied to compensate for temporal humidity fluctuations and spatial temperature variation using the Venturi apparatus. | ||||||
| 173 | WATER FLOW MEASUREMENT DEVICE | US13086441 | 2011-04-14 | US20120260692A1 | 2012-10-18 | Gary R. Lange; William B. Fox |
| A chiller system including an evaporator for evaporating a refrigerant and a water pipe in fluid communication with the evaporator. The water pipe is configured to allow water to pass through at a flow rate and to circulate the water with the evaporator to exchange heat with the refrigerant in the evaporator. The chiller system includes a flow restrictor tube within the water pipe that is configured to allow the water to flow through the flow restrictor tube at a reduced flow rate relative to the flow rate. The chiller system also includes a measuring probe that passes through walls of the water pipe and the flow restrictor tube and includes an accuracy range of flow rates less than the flow rate. The measuring probe is configured to measure the reduced flow rate within the flow restrictor tube where the reduced flow rate is within the accuracy range. | ||||||
| 174 | STATIC PORT APPARATUS | US12946192 | 2010-11-15 | US20120118075A1 | 2012-05-17 | Timothy T. Golly |
| A static port apparatus for an aircraft having a static plate having inner and outer surfaces for fixture on the aircraft. The static plate including a first set of a plurality of port apertures and at least a second set of a plurality of port apertures. Each port aperture of the second set of port apertures is coaxially positioned with respect to each port aperture of the first set of port apertures. | ||||||
| 175 | Sensor unit having a measuring probe and a housing part with sensors and a computing unit integrated in the housing part | US11995548 | 2006-07-13 | US08065925B2 | 2011-11-29 | Oliver Betz |
| The static pressure, the differential pressure, and the temperature must be known in order to be able to determine the mass flow rate, the volumetric flow under standard conditions, or the enthalpy flow of a fluid. Desired variables are detected by individual sensors located in an integrated sensor unit, and the values detected by the individual sensors are then processed in a computing unit that is also integrated in the sensor unit. The sensor unit outputs a value, which also takes other parameters and/or physical constants into account, to a control unit that is connected downstream. Some of the computing is advantageously done in the sensor unit so that some load is relieved from the control unit. | ||||||
| 176 | AIRCRAFT DYNAMIC PRESSURE ESTIMATION SYSTEM AND METHOD | US12705007 | 2010-02-12 | US20110202291A1 | 2011-08-18 | Alan Bruce Hickman |
| Methods and apparatus are provided for estimating aircraft dynamic pressure. The load on the flight control surface actuator that is coupled to a flight control surface is measured. An estimate of the aircraft dynamic pressure is calculated from the measured load. | ||||||
| 177 | FLUID FLOW MONITORING | US12377467 | 2008-09-10 | US20100275684A1 | 2010-11-04 | David William Gough; Graham Andrew Johnsson; Clyde Warsop; Martyn John Hucker |
| To provide an indication of whether airflow is separated, as opposed to other states of flow, over a surface, two or more adjacent sensors at a location on the surface each produce an analogue signal representative of airflow. The analogue signals are correlated with each other, and the degree of correlation indicates whether the airflow is in a separated state. The correlation may be carried out by comparing processed values of the analogue signals, and thresholding the comparison result. | ||||||
| 178 | MULTIFUNCTIONAL ELECTRONIC DEVICE AND METHOD FOR USING THE SAME | US12616322 | 2009-11-11 | US20100275683A1 | 2010-11-04 | LI-JIN JIA |
| A portable electronic device includes a housing, a processor unit received in the housing, and an anemometer unit mounted on the housing and electrically connected to the processor unit. The anemometer unit transforms pressure of wind blowing thereon into electronic signals, and the processor unit receives and processes the electronic signals to obtain wind pressures and velocities. | ||||||
| 179 | SENSOR | US12441451 | 2007-11-09 | US20090266163A1 | 2009-10-29 | Satoshi Ohuchi; Toshiyuki Nozoe; Hiroyuki Aizawa |
| A sensor includes detecting element (28) with an acceleration sensor, which is formed of weight (18) coupled to rigid section (14) via flexible section (16), substrate (10) confronting weight (18), and an electrode section including opposed electrodes (20, 22, 24, 26) placed on respective opposed faces of weight (18) and substrate (10). This structure prevents weight (18) from moving along Z-axis, so that a detection accuracy of acceleration occurring along X-axis or Y-axis can be improved. | ||||||
| 180 | Method and Device for Detecting, on the Ground, the Obstruction of a Pressure Tap of a Static Pressure Sensor of an Aircraft | US11816078 | 2006-02-02 | US20080150763A1 | 2008-06-26 | Laurent Fontova; Sebastien Freissinet |
| The invention relates to a method and device for detecting, on the ground, the obstruction of a pressure tap of a static pressure sensor of an aircraft. The device (1) comprises a pressure sensor (2) provided for measuring the pressure inside a probe (4), which has a heating system (9) for heating the probe (4) and which, when the heating system (9) is activated, carries out a first measurement of at least one parameter dependent on the pressure inside the probe (4), and a predetermined duration after the activation of the heating system (9), carries out a second measurement of said parameter. The inventive device also comprises at least one central processing unit (11) for calculating the difference between the first and second measurements and for comparing this difference to a predetermined value, and comprises warning means (13) for emitting a warning signal indicating the detection of an obstruction if the difference is greater than said predetermined value. | ||||||
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