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公开(公告)号：US20240017840A1
公开(公告)日：2024-01-18
申请号：US17865999
申请日：2022-07-15
Applicant: Rosemount Aerospace Inc.
Inventor： Vincent R. LoPresto
CPC classification number: B64D15/20 , B64D45/00 , G01K1/024 , B64D2045/0085
Abstract: An ice protection system for an aircraft includes an ice detector disposed in an external aircraft surface, a temperature sensor, and a controller. The ice detector includes an ice sensor. The controller includes an icing threshold module which receives a temperature measurement from the temperature sensor, receives an ice accretion signal from the ice sensor, compares the temperature measurement to an icing threshold temperature, and determines whether the temperature measurement is above the icing threshold temperature. The controller suppresses an icing conditions alert if the temperature measurement exceeds the icing threshold temperature.
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公开(公告)号：US20240329212A1
公开(公告)日：2024-10-03
申请号：US18126612
申请日：2023-03-27
Applicant: Rosemount Aerospace Inc.
Inventor： Vincent R. LoPresto , Mark D. Ray , Kaare Josef Anderson
IPC: G01S7/4861 , G01S7/481 , G01S17/04 , G01S17/88 , G01S7/497
CPC classification number: G01S7/4861 , G01S7/4811 , G01S17/04 , G01S17/88 , G01S2007/4975
Abstract: A method includes checking an optical detector with a field of view for degradation by: directing the optical detector to a surface of an object in the field of view, wherein the surface is positioned at a given distance from the optical detector, and wherein the surface has a known reflectance; detecting an optical return from the surface with the optical detector to generate a return signal; and determining whether the return signal is representative of a degraded signal. The method includes outputting an alert for maintenance action if the return signal is indicative of a degraded signal.
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公开(公告)号：US20240151832A1
公开(公告)日：2024-05-09
申请号：US17982197
申请日：2022-11-07
Applicant: Rosemount Aerospace Inc.
Inventor： Vincent R. LoPresto , Kaare Josef Anderson , Mark D. Ray
CPC classification number: G01S7/497 , B64D15/20 , B64D45/00 , G01S17/95 , B64D2045/0085
Abstract: In accordance with at least one aspect of this disclosure, a method of detecting a fault in a plurality of optical detectors includes receiving a first return beam from a first optical detector interrogation beam to generate a first optical signal indicative of an atmospheric condition from a first location on board the aircraft and receiving a second return beam from a second optical detector interrogation beam to generate a second optical signal indicative of the atmospheric condition from a second location on board the aircraft. The method includes, comparing each of the first and second optical signals with a baseline value to determine whether there is a fault in at least one optical detector of the plurality of optical detectors.
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4.发明授权公开(公告)号：US10124900B2
公开(公告)日：2018-11-13
申请号：US15195811
申请日：2016-06-28
Applicant: Rosemount Aerospace Inc.
Inventor： Vincent R. LoPresto
Abstract: Apparatus and associated methods relate to determining, based on a spatial extent of ice accretion, a maximum size of super-cooled droplets contained in an atmosphere and/or if an atmosphere contains super-cooled water droplets that equal and/or exceed a predetermined size. A testing region on an exterior surface of an aircraft is monitored for ice accretion by an ice detector. A boundary calculator determines a specific location to be tested within the testing region. The determined specific location corresponds to a calculated boundary that separates an ice-accretion region from an ice-free region if the atmosphere contains super-cooled water droplets of no larger than the predetermined size. If the ice detector detects ice accretion at the determined specific location, an alert is generated. The alert can advantageously inform a pilot of the aircraft that the atmosphere contains super-cooled water droplets that equal or exceed the predetermined size.
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公开(公告)号：US11459112B2
公开(公告)日：2022-10-04
申请号：US16517237
申请日：2019-07-19
Applicant: Rosemount Aerospace Inc.
Inventor： Vincent R. LoPresto , Weston D. C. Heuer
Abstract: A method including providing power to an aircraft probe anti-ice system, monitoring an actual power demand of the aircraft probe anti-ice system, monitoring an air data parameter and atmospheric conditions surrounding an aircraft and calculating an expected power demand of the aircraft probe anti-ice system based on the air data parameters and the atmospheric conditions, comparing the actual power demand of the aircraft probe anti-ice system to the expected power demand, and performing a corrective action if the actual power demand and the expected power demand are different by more than an acceptable amount.
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Patent Agency Ranking
公开(公告)号：US20210016886A1
公开(公告)日：2021-01-21
申请号：US16517237
申请日：2019-07-19
Applicant: Rosemount Aerospace Inc.
Inventor： Vincent R. LoPresto , Weston D. C. Heuer
Abstract: A method including providing power to an aircraft probe anti-ice system, monitoring an actual power demand of the aircraft probe anti-ice system, monitoring an air data parameter and atmospheric conditions surrounding an aircraft and calculating an expected power demand of the aircraft probe anti-ice system based on the air data parameters and the atmospheric conditions, comparing the actual power demand of the aircraft probe anti-ice system to the expected power demand, and performing a corrective action if the actual power demand and the expected power demand are different by more than an acceptable amount.
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公开(公告)号：US20180319506A1
公开(公告)日：2018-11-08
申请号：US15588308
申请日：2017-05-05
Applicant: Rosemount Aerospace Inc.
Inventor： Vincent R. LoPresto , Mark Sherwood Miller
CPC classification number: B64D15/20 , B64C1/1484 , B64D47/02 , B64D47/08
Abstract: Apparatus and associated methods relate to projecting a light beam onto an interior surface of an aircraft window so as to indicate a testing location to test for ice accretion. The testing location is determined, by a boundary locator, based on aircraft flight conditions, aircraft exterior shape, and a predetermined size of super-cooled droplets, which could present a hazard to the aircraft. The determined test location corresponds to a calculated boundary that separates locations where super-cooled water droplets of the predetermined size cause ice-accretion from locations where such particles do not cause ice accretion, for such aircraft flight conditions. The light beam is then projected onto the interior surface of the aircraft window at the determined test location. The projected beam of light can indicate, to an observer and/or a detector, a location to monitor for ice accretion caused by super-cooled water droplets of the predetermined size.
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公开(公告)号：US10093426B2
公开(公告)日：2018-10-09
申请号：US15332843
申请日：2016-10-24
Applicant: Rosemount Aerospace Inc.
Inventor： Vincent R. LoPresto
Abstract: Apparatus and associated devices relate to a system for measuring a maximum size of super-cooled water droplets in a cloud atmosphere. The system includes a housing having a convex exterior surface on a forward end and having stabilizers projecting from an aft end. The system includes a gimballed mounting mechanism configured to attach the housing to an aircraft while permitting the housing to freely pitch and yaw with respect to the aircraft. When an airstream engages the stabilizers, the housing aligns with a direction of the engaging airstream. The system includes a sequence of indices on a corresponding sequence of ice-accretion regions of the convex exterior surface, each of the sequence of indices visible in the absence of ice accretion. The forward-most ice-free one of the sequence of indices is indicative of a maximum size of super-cooled water droplets.
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公开(公告)号：US20180111694A1
公开(公告)日：2018-04-26
申请号：US15332843
申请日：2016-10-24
Applicant: Rosemount Aerospace Inc.
Inventor： Vincent R. LoPresto
Abstract: Apparatus and associated devices relate to a system for measuring a maximum size of super-cooled water droplets in a cloud atmosphere. The system includes a housing having a convex exterior surface on a forward end and having stabilizers projecting from an aft end. The system includes a gimballed mounting mechanism configured to attach the housing to an aircraft while permitting the housing to freely pitch and yaw with respect to the aircraft. When an airstream engages the stabilizers, the housing aligns with a direction of the engaging airstream. The system includes a sequence of indices on a corresponding sequence of ice-accretion regions of the convex exterior surface, each of the sequence of indices visible in the absence of ice accretion. The forward-most ice-free one of the sequence of indices is indicative of a maximum size of super-cooled water droplets.
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公开(公告)号：US20240077260A1
公开(公告)日：2024-03-07
申请号：US18201051
申请日：2023-05-23
Applicant: Rosemount Aerospace Inc.
Inventor： Vincent R. LoPresto , Brian Daniel Matheis
Abstract: An aerodynamic friction energy deicing system can include a heat energy device configured to be operatively connected to an aircraft structure and to convert heat energy due to aerodynamic friction on the aircraft structure into another form or to store heat energy due to aerodynamic friction on the aircraft structure. The converted or stored energy can be used for any suitable purpose, e.g., for use in ice prevention and/or deicing and/or powering one or more aircraft systems.
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