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公开(公告)号：US10884017B2
公开(公告)日：2021-01-05
申请号：US15934584
申请日：2018-03-23
Applicant: Rosemount Aerospace Inc.
Inventor： Todd Anthony Ell
Abstract: An angle-of-attack sensor includes at least one acoustic transmitter is configured to provide an acoustic pulse. The first acoustic receiver is positioned at a radial distance from the at least one acoustic transmitter. The first acoustic receiver is configured to receive the acoustic pulse at a first time and provide a first receiver signal. The second acoustic receiver is positioned at the radial distance from the at least one acoustic transmitter aligned with an axis that extends through the at least one acoustic transmitter and the first acoustic receiver. The second acoustic receiver is configured to receive the acoustic pulse at a second time and provide a second receiver signal. The angle-of-attack circuitry is configured to determine a delay difference between the first and second receiver signals representative of a difference between the first time and the second time and determine an angle-of-attack based upon the delay difference.
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公开(公告)号：US10861665B1
公开(公告)日：2020-12-08
申请号：US16593714
申请日：2019-10-04
Applicant: Rosemount Aerospace Inc.
Inventor： Roger Alan Backman , David P. Potasek
IPC: H01H85/041 , H01H85/00 , H01H69/02 , H01H85/175
Abstract: A micro-fuse assembly includes a substrate, a number of thin-film micro-fuses on the substrate, and a topping wafer configured to sealingly engage to at least one of the substrate or the thin-film micro-fuses to define a cavity therebetween. The cavity is configured to encapsulate the thin-film micro-fuses within an inert environment sealed within the cavity. A method of encapsulating a micro-fuse assembly within an inert environment using a topping wafer is also disclosed.
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公开(公告)号：US20200373042A1
公开(公告)日：2020-11-26
申请号：US16416541
申请日：2019-05-20
Applicant: Rosemount Aerospace Inc.
Inventor： David P. Potasek
IPC: H01C1/16
Abstract: Provided are embodiments for a resistor array. The resistor array includes a plurality of resistor elements, where the plurality of resistor elements includes a redundancy region for a most significant bit of an expected value. The resistor array also includes one or more switches coupled to the plurality of resistor elements, and a first terminal and a second terminal coupled to the plurality of resistor elements. Also provided are embodiments for trimming the resistor array where the resistor array includes a redundancy region for a most significant bit for an expected value.
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公开(公告)号：US10823631B2
公开(公告)日：2020-11-03
申请号：US15956657
申请日：2018-04-18
Applicant: Rosemount Aerospace Inc.
Inventor： Jun Zheng
Abstract: A MEMS pressure sensor includes a first plate with a hole on a diaphragm bonded to the first plate around its rim with the diaphragm positioned over the hole. An isolation frame is bonded to the diaphragm and a second plate with a pillar is bonded to the isolation frame around its rim to form a cavity such that the end of the pillar in the cavity is proximate a surface of the diaphragm. The diaphragm and second plate form a capacitive sensor which changes output upon deflection of the diaphragm relative to the second plate.
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公开(公告)号：US20200333206A1
公开(公告)日：2020-10-22
申请号：US16918224
申请日：2020-07-01
Applicant: Rosemount Aerospace Inc.
Inventor： Timothy Thomas Golly , Paul Robert Johnson , Greg Seidel
Abstract: A corrosion resistant apparatus for an air data probe with a sleeve being cylindrical in shape with a first end and a second end, at least one circumferentially extending groove on an outside of the sleeve configured to accommodate coils of a heater, and a bore at a center of the sleeve and extending between the first end and the second end configured to provide a pneumatic pathway that allows atmospheric conditions to reach measurement equipment of the air data probe.
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Patent Agency Ranking
公开(公告)号：US10782315B2
公开(公告)日：2020-09-22
申请号：US15489166
申请日：2017-04-17
Applicant: Rosemount Aerospace Inc.
Inventor： Jim Golden , David P. Potasek , Marcus Allen Childress
Abstract: A method of testing sensors includes providing a test sheet that includes a plurality of sensor assemblies, a plurality of test pads, and traces extending from the sensor assemblies to the plurality of test pads. A sensor is positioned on each sensor assembly. Each sensor is connected to the sensor assembly with wire bonds. An enclosure is formed over the plurality of sensor assemblies. An electrical signal is detected from each of the plurality of sensor assemblies at the test pads.
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公开(公告)号：US20200257001A1
公开(公告)日：2020-08-13
申请号：US16275152
申请日：2019-02-13
Applicant: Rosemount Aerospace Inc.
Inventor： Cuong Tho Huynh , Kaare Josef Anderson
IPC: G01S17/95
Abstract: Apparatus and associated methods relate to determining metrics of a cloud atmosphere using time difference measurements. A light projector projects a pulse of light into a cloud atmosphere, and a light sensor detects a portion of the projected pulse of light backscattered by the cloud atmosphere. A backscatter coefficient is calculated based on peak amplitude of the detected portion. An optical extinction coefficient is calculated based on a time difference between a peak time and a post-peak time, which correspond to times at which the peak amplitude of the detected portion occurs and at which the detected portion equals or crosses a sub-peak threshold, respectively. In some embodiments, a logarithm amplifier is used to facilitate processing of signals of widely varying amplitudes. In some embodiments, the sub-peak threshold is calculated as a fraction of the peak amplitude of the detected portion.
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公开(公告)号：US20200256888A1
公开(公告)日：2020-08-13
申请号：US16271021
申请日：2019-02-08
Applicant: Rosemount Aerospace Inc.
Inventor： Todd Anthony Ell , Richard Hull
Abstract: An acoustic air data sensing system includes an acoustic transmitter and a plurality of acoustic receivers. The acoustic transmitter is located to transmit an acoustic signal into airflow about an exterior of a vehicle. Each of the acoustic receivers is located at a respective angle from a wind angle reference line and a respective distance from the acoustic transmitter. Planar components of a velocity of the airflow are determined based on signal velocities of the acoustic signal to each of the plurality of acoustic receivers and the respective angles of the acoustic receivers from the wind angle reference line. Based on the planar components, the acoustic transmitter determines one or more of true airspeed and relative wind angle of the airflow about the exterior of the vehicle. The acoustic transmitter outputs the one or more of the true airspeed and the relative wind angle for operational control of the vehicle.
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公开(公告)号：US10726616B2
公开(公告)日：2020-07-28
申请号：US16680775
申请日：2019-11-12
Applicant: Rosemount Aerospace Inc.
Inventor： Julian C. Ryde , Xuchu Ding
Abstract: An image processing system configured to process perceived images of an environment includes a central processing unit (CPU) including a memory storage device having stored thereon a computer model of the environment, at least one sensor configured and disposed to capture a perceived environment including at least one of visual images of the environment and range data to objects in the environment, and a rendering unit (RU) configured and disposed to render the computer model of the environment forming a rendered model of the environment. The image processing system compares the rendered model of the environment to the perceived environment to update the computer model of the environment.
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公开(公告)号：US10718787B2
公开(公告)日：2020-07-21
申请号：US16138493
申请日：2018-09-21
Applicant: Rosemount Aerospace Inc.
Inventor： Brian Brent Naslund , Ronald Fritz Liffrig , Jaime Sly , Benjamin John Langemo
Abstract: A system for an aircraft includes a pneumatic sensor, an optical sensor, and a computer system. The pneumatic sensor is configured to sense a value external to the aircraft. The optical sensor is configured to emit an optical signal external to the aircraft and receive an optical response. The computer system is configured to receive the value and the optical response. The pneumatic sensor and the optical sensor do not extend beyond a boundary layer of the aircraft.
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