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公开(公告)号：US20210247419A1
公开(公告)日：2021-08-12
申请号：US17057019
申请日：2020-05-28
发明人： Dazhi WANG , Xiaoyan GUO , Yuanda CI , Feng CAI , Xiao WANG , Shaoyan ZUO
摘要： The present invention belongs to the field of ship engineering, and provides a ship real wind measuring device calibration method. In this method a ship sway simulator is build using a 2-axis ganged platform, natural wind is simulating generated using a wind tunnel flow field. Then the ship sway simulator is controlled to simulate the ship spatial motion under the disturbance of stormy waves. Furthermore, the data of the wind speed and direction is obtained under different sway angles and speeds. So that the database of wind direction and speed measurement, attitude measurement, actual wind direction and speed measurement is formed. Subsequently, a calibration model based on BP neural network is constructed using this database, a ship real wind direction and speed calibration algorithm is formed, which can calibrate a ship real wind measuring device.
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公开(公告)号：US10994866B1
公开(公告)日：2021-05-04
申请号：US17118637
申请日：2020-12-11
发明人： Wei He , Xinxing Mu , Shufen Tian , Qiang Fu , Yao Zou , Haifeng Huang , Xiuyu He
摘要： A flight test system for a flapping-wing aerial vehicle includes a host computer platform, a measurement mechanism, and a wind tunnel. The measurement mechanism is configured to mount a to-be-tested flapping-wing aerial vehicle prototype. The measurement mechanism includes an Euler angle controller, a flow angle controller, and a tripod. The flow angle controller is mounted on the tripod. The Euler angle controller is in transmission connection with the flow angle controller. The flapping-wing aerial vehicle prototype is detachably connected to the Euler angle controller by using a first connecting member. The host computer platform is in communication connection with the measurement mechanism and the wind tunnel, and is configured to control a wind speed of the wind tunnel and display a flight status of the flapping-wing aerial vehicle prototype in real time during test.
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公开(公告)号：US10890509B2
公开(公告)日：2021-01-12
申请号：US15555948
申请日：2016-03-04
发明人： Christian Hartmann , Anton Knestel
摘要： The device described herein and the associated method relate, in particular, to a holding device for a wind tunnel test stand 1, in particular for a wind tunnel balance. The device may comprise a holding base 5a, 6a, which may be arranged outside of a conveyor belt 3 of the wind tunnel test stand 1, and a support element 7 having at least two ends 7a, 7b. Via a connection element 13, one end of the support element 7 may be connected to a wheel 22 of a test object 4. Furthermore, a support device 8 may be provided, which may be connected to the support element 7 in such a way that a change in a rotational orientation of the support element 7 can cause a lifting or lowering movement of the support device 8.
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4.发明申请公开(公告)号：US20200217749A1
公开(公告)日：2020-07-09
申请号：US16647432
申请日：2019-03-21
发明人： Dechuan SUN , Ming LU
摘要： A parameter similarity method for test simulation conditions of an aerodynamic heating environment is disclosed. With respect to the requirement that the adiabatic wall enthalpy and the cold-wall heat flux are equal in the simulation test of the aerodynamic heating environment, a method that can ensure the similarity of ground test parameters and flight parameters without the equal adiabatic wall enthalpy is proposed, and solves the problems of relying on the equal adiabatic wall enthalpy and making it difficult to accurately simulate the real aerodynamic heating environment in the current test simulation method, and provides guarantee for heat transfer and ablation test research of thermal protection/insulation material under the high temperature aerodynamic heating environment. The test conditions are not affected by the value of the adiabatic wall enthalpy. According to the method, most test devices can simulate the aerodynamic heating environment with high enthalpy.
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公开(公告)号：US10086298B2
公开(公告)日：2018-10-02
申请号：US15789234
申请日：2017-10-20
发明人： Ruslan Romanenko , Alexandr Parmanin , Aledsandr Ivoninskii , Svjatoslav Lisin , Ivan Savchenko , Eugeny Sharov
摘要： A vertical wind tunnel skydiving simulator including a flight chamber entrance that has a curved air deflector that extends into a waiting chamber, in which a convex surface of the curved air deflector faces across or towards the flight chamber entrance or into the flight chamber, and extends into the waiting chamber a sufficient distance to substantially reduce the flow of turbulent air into the waiting chamber. The curved surface is at the top of the entrance and can also be at the sides. The shape the curved surface takes is sufficient to minimize the flow of turbulent air into the waiting chamber; the effect is to make it more comfortable and less noisy for people in the waiting area. This also helps to preserves the laminar, non-turbulent flow of air in the flying chamber, even across the flight chamber entrance. This makes flying more comfortable and predictable.
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6.发明申请公开(公告)号：US20180094623A1
公开(公告)日：2018-04-05
申请号：US15832252
申请日：2017-12-05
申请人： The Boeing Company
摘要： Rotary actuator assemblies, wind tunnels including the same, and associated methods are disclosed. A rotary actuator assembly includes a rotary element and a rotary actuator with a shape memory alloy element. The rotary actuator is configured to generate a first torque and a second torque in opposing rotary directions to rotate the rotary element. A rotary actuator assembly further includes an assist magnetic element and a receiver magnetic element configured to generate a magnetic force therebetween. Wind tunnels include an aerodynamic model with a rotary actuator assembly to rotate a portion of the aerodynamic model with respect to an airstream in a chamber. A method of rotating a rotary element includes modulating a temperature of a shape memory alloy element and applying a supplemental torque to the rotary element with an assist magnetic element and a receiver magnetic element.
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公开(公告)号：US20180068551A1
公开(公告)日：2018-03-08
申请号：US15257332
申请日：2016-09-06
申请人： The Boeing Company
CPC分类号： G08B21/182 , G01M5/0016 , G01M5/0041 , G01M5/0066 , G01M9/02 , G06F17/50 , H04L67/12 , H04Q9/00 , H04Q2209/823
摘要： A system for monitoring a model in a wind tunnel is provided. The system includes a plurality of sensors attached to a model in a wind tunnel. Each sensor of the plurality of sensors is configured to measure an attribute of the model. The system also includes a computing device in communication with the plurality of sensors. The computing device is programmed to receive a plurality of signals from the plurality of sensors, store a first threshold and a second threshold based on normalized alarm limits associated with at least one of the plurality of sensors, analyze the plurality of signals based, at least in part, on the first threshold and the second threshold, determine that a potentially negative condition is occurring based on the analysis, and alert a user to the potentially negative condition.
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公开(公告)号：US09897078B2
公开(公告)日：2018-02-20
申请号：US15163011
申请日：2016-05-24
申请人： The Boeing Company
摘要： Rotary actuator assemblies, wind tunnels including the same, and associated methods are disclosed. A rotary actuator assembly includes a rotary element and a rotary actuator with a shape memory alloy element. The rotary actuator is configured to generate a first torque and a second torque in opposing rotary directions to rotate the rotary element. A rotary actuator assembly further includes an assist magnetic element and a receiver magnetic element configured to generate a magnetic force therebetween. Wind tunnels include an aerodynamic model with a rotary actuator assembly to rotate a portion of the aerodynamic model with respect to an airstream in a chamber. A method of rotating a rotary element includes modulating a temperature of a shape memory alloy element and applying a supplemental torque to the rotary element with an assist magnetic element and a receiver magnetic element.
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公开(公告)号：US09778122B2
公开(公告)日：2017-10-03
申请号：US14449849
申请日：2014-08-01
发明人： Richard A. Meyer , Robert L. Josephson , Jason A. Christopherson , Todd Robert Osmundson , Nicholas Devon LaMoore , Riley August Rogotzke
摘要： In one aspect, a transducer body includes a support having clevis halves. The sensor body includes a generally rigid peripheral member disposed about a spaced-apart central hub joined to each of the clevis halves. At least three flexure components couple the peripheral member to the hub. The flexure components are spaced-apart from each other at generally equal angle intervals about the hub; the sensor body further including a flexure assembly for some flexure components joining the flexure component to at least one of the hub and the peripheral member, the flexure assembly being compliant for forces in a radial direction from the hub to the peripheral member. Each flexure assembly is configured such that forces transferred concentrate strain at a midpoint along the length of each corresponding flexure component.
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公开(公告)号：US09654161B2
公开(公告)日：2017-05-16
申请号：US15200102
申请日：2016-07-01
IPC分类号： G01M15/14 , H04B1/16 , G01M17/007 , F02C6/16 , G01M9/02
CPC分类号： H04B1/1646 , B65D19/16 , F01D5/02 , F01D17/02 , F01D21/003 , F01D25/285 , F02C6/16 , F04D27/001 , F04D29/321 , F05B2220/302 , F05B2260/83 , F05D2220/323 , F05D2260/83 , F23R2900/00019 , G01M9/02 , G01M9/04 , G01M15/14 , G01M17/007 , Y02E60/15
摘要： A process for testing a turbine of a gas turbine engine at high altitudes, where a large volume of compressed air is stored in a large reservoir of at least 10,000 m3 such as an underground storage cavern, compressed air from the storage reservoir is passed through heat exchanger to preheat the compressed air to a temperature that would normally be discharged from a compressor, the preheated compressed air is burned with a fuel in the combustor, and additional compressed air from the reservoir is passed through an injector located downstream from the turbine to produce a decreased pressure such that a low atmospheric condition at the turbine exit is simulated.
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