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公开(公告)号：US20220267014A1
公开(公告)日：2022-08-25
申请号：US17181964
申请日：2021-02-22
发明人： Haifeng Wang , Jing Song
摘要： In some examples, a system includes a receiver configured to receive temperature data for a region of airspace from a data source external to the vehicle. The system also includes processing circuitry configured to determine one or more moisture values for the region of airspace based on radar returns received by a weather radar onboard the vehicle. The processing circuitry is further configured to determine a potential for icing at a location within the region of airspace based on the one or more moisture values and further based on the temperature data received from the data source. The processing circuitry is also configured to generate an output based on the determined potential for icing at the location.
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公开(公告)号：US20220161933A1
公开(公告)日：2022-05-26
申请号：US16953807
申请日：2020-11-20
摘要： An optical ice detector and airspeed probe includes an ice detection module and an airspeed module. The ice detection module detects the presence or absence of ice, water, or ice and water particles, and the airspeed module determines a line-of-sight speed along a directional vector, each based on backscatter light returns emitted from a common collimated light source. An electronics module determines an airspeed of an aircraft based on the line-of-sight speed determined by the airspeed module and at least one aircraft parameter received from the air data system.
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公开(公告)号：US20220155332A1
公开(公告)日：2022-05-19
申请号：US17589332
申请日：2022-01-31
摘要： A probe head for an air data probe includes a ceramic body and a heater embedded within the ceramic body.
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公开(公告)号：US11325713B2
公开(公告)日：2022-05-10
申请号：US16618663
申请日：2018-06-04
申请人： SHORT BROTHERS PLC
发明人： Robert Samuel Wilson
摘要： Ice protection systems of aircraft and related methods are disclosed. In one embodiment of the present invention, the system includes a gas-discharge lamp and an electric power source. The gas-discharge lamp is configured to emit infrared radiation toward an inner surface of an aircraft skin. The electric power source is operatively connected to the gas-discharge lamp.
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5.发明申请公开(公告)号：US20220135237A1
公开(公告)日：2022-05-05
申请号：US17509214
申请日：2021-10-25
发明人： David Jamison
摘要： Ice detection test apparatuses, systems, and methods are disclosed. In some cases, ice detection and precautionary system shut-down event reduction systems and related methods are provided. The system utilizes a turbine engine ice detection apparatus that includes and engine pressure simulation device, an air moving device, and a first air pressure sensor associated with the engine pressure simulation device. The embodiment further includes an ice monitor controller that receives inputs from the first air pressure sensor and at least one second sensor located adjacent a turbine engine intake. The ice monitor controller performs comparisons of inputs from these sensors against each other and stored values to determine actual icing conditions then generate warnings on a display to an operator. The exemplary control section has multiple modes including manual, semi-manual and automatic.
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公开(公告)号：US20210327290A1
公开(公告)日：2021-10-21
申请号：US16850779
申请日：2020-04-16
申请人： THE BOEING COMPANY
发明人： Markus Florian PEUKERT , Samantha A. Schwartz , Mitchell G. Woolever , Jason W. Clark , Katie M. Reid , Joshua T. Glazer
摘要： The present disclosure provides for informed de-icing by identifying a travel time range for an aircraft from a de-icing station to a runway; identifying a holdover window based on predicted weather conditions during the travel time range; estimating a takeoff time for the aircraft based on a takeoff queue for the runway and the travel time range; and in response to the holdover window expiring before the estimated takeoff time, delaying the aircraft from de-icing. In some aspects, informed de-icing includes, in response to identifying an aircraft scheduled for de-icing within a caution threshold of a scheduled takeoff time and to determining that a push time cannot be delayed: evaluating an effect of repeating a de-icing operation for the aircraft on flight operations; and in response to the effect exceeding an impact threshold: rescheduling the de-icing operation for the aircraft based on a new takeoff time.
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公开(公告)号：US11148787B2
公开(公告)日：2021-10-19
申请号：US16096496
申请日：2017-04-24
申请人： SAFRAN
IPC分类号： B64C23/00 , F01D25/02 , F01D5/14 , F01D9/02 , B64D15/22 , B64D15/16 , B64D15/00 , B64D15/20 , B64D15/12 , F02C7/047 , F02K3/06
摘要： The invention concerns an aircraft propulsion system comprising at least one member (1, 3, 4, 8) in contact with a turbulent flow of a stream (F), characterised in that said member is covered, at least partially, by a piezoelectric structure (S) such as a piezoelectric film, said structure (S) comprising a grooved structure (5, 6, 7, 9) comprising a series of grooves, in contact with the flow of the stream, the grooves extending in the direction of flow of the stream, the grooved structure comprising at least one geometric parameter (h, s, w) configured to adapt depending on at least one parameter of the flow of the stream and/or an operating point of the propulsion system and/or an engine speed of the propulsion system.
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公开(公告)号：US20210171205A1
公开(公告)日：2021-06-10
申请号：US17112249
申请日：2020-12-04
申请人： ROLLS-ROYCE plc
发明人： Salvatore IPPEDICO
摘要： Disclosed is a blower controller for controlling a blower that supplies a pressurised airflow to an air conditioning pack of an aircraft. The blower controller comprises a pack flow demand adjustment module configured to receive a pack flow demand signal representative of a desired mass flow rate of an airflow supplied by the air conditioning pack, and a blower condition signal indicative of a condition of an intake airflow received by the blower, and determine an corrected pack flow demand based on the pack flow demand and the blower condition signal. The controller also includes a first control signal generator configured to receive the corrected pack flow demand and generate a first control signal to control a first operating parameter of the blower in response to the corrected pack flow demand. Also disclosed is an environmental control system for an aircraft, including the blower controller.
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公开(公告)号：US10940952B2
公开(公告)日：2021-03-09
申请号：US15571588
申请日：2016-05-05
申请人： INSTRUMAR LIMITED
发明人： Stuart Inkpen , Chris Nolan , Bill Conway , Dana Linfield , David Bonnell , Joshua Swamidas , Ruth Abraham
摘要： A method of monitoring for the in-flight accretion of matter involves an electric field sensor applying a time-varying electric field to an engine surface of an aircraft while the aircraft is in flight. The electric field sensor is thermally-coupled and thermally-matched to the engine surface. A sensor monitor receives, in substantially real-time from the electric field sensor, at least one measurement set that includes a measurement of a phase and a magnitude of a current detected by the electric field sensor and resulting from the time-varying electric field. The sensor monitor generates an assessment, in substantially real-time, of an instantaneous accumulation of matter on the engine surface from the at least one measurement set. The sensor monitor activates an alarm upon the assessment indicating an accumulation of matter on the engine surface.
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公开(公告)号：US10794835B2
公开(公告)日：2020-10-06
申请号：US15903411
申请日：2018-02-23
IPC分类号： G01N21/85 , B64D45/00 , G01S17/02 , G01S7/481 , B64D47/06 , G01S17/87 , G01S17/95 , B64D15/20 , F21W107/30 , G01S7/499
摘要： A sensor assembly comprises a device mounted on a surface of a vehicle and extending through at least one passage in the surface of the vehicle, and a sensor comprising a short range particulate (SRP) sensor, or a light detection and ranging (LiDAR) air data sensor. The sensor is co-located and integrated with the device mounted on the surface of the vehicle. No additional passages through the surface of the vehicle are needed to integrate the sensor with the device.
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