公开(公告)号：US20240327005A1

公开(公告)日：2024-10-03

申请号：US18383539

申请日：2023-10-25

Applicant: Rosemount Aerospace Inc.

Inventor： Sathish Thangavel ,  Paul R. Johnson ,  Shivanshu Bajpai

IPC: B64D15/12 ,  B64D15/20 ,  G01P5/165

CPC classification number: B64D15/12 ,  B64D15/20 ,  G01P5/165

Abstract: A method of ice protection includes performing anti-icing on a forward portion of an air data sensor for a first duration while maintaining de-icing on an aft portion of the air data probe in a deactivated state. The method includes activating de-icing on the aft portion of the air data probe for a second duration while also performing anti-icing on the forward portion of the air data sensor.

公开(公告)号：US11939996B2

公开(公告)日：2024-03-26

申请号：US17154276

申请日：2021-01-21

Applicant: Goodrich Actuation Systems Limited

Inventor： Graham James Burgess ,  Paul Smith

IPC: B64D15/16 ,  B64D15/20 ,  F15B15/26

CPC classification number: F15B15/261 ,  B64D15/16 ,  B64D15/20

Abstract: A locking system includes a locking element which is movable between a first, locking position and a second unlocking position and an unlocking actuator for moving the locking element (from the first position to the second position over an unlocking stroke length (Su). The system further comprises a control unit configured to command the unlocking actuator to move the locking element from the first position to a third position over an anti-icing stroke length (Sa) which is shorter than the unlocking stroke length (Su).

公开(公告)号：US11931978B2

公开(公告)日：2024-03-19

申请号：US18020808

申请日：2020-12-22

Applicant: INDUSTRY-ACADEMIC COOPERATION FOUNDATION GYEONGSANG NATIONAL UNIVERSITY

Inventor： Young Woo Nam ,  Hyeon Seok Choe ,  Jin Hwe Kweon ,  Rho Shin Myong ,  Won Ho Choi

IPC: B29D24/00 ,  B29B15/10 ,  B29C70/06 ,  B29C70/88 ,  B29L31/30 ,  B64C1/00 ,  B64D15/20 ,  C08J5/08 ,  C08L63/00

CPC classification number: B29D24/005 ,  B29B15/10 ,  B29C70/06 ,  B29C70/882 ,  B64D15/20 ,  C08J5/08 ,  C08L63/00 ,  B29L2031/30 ,  B29L2031/3005 ,  B29L2031/3076 ,  B64C2001/0072

Abstract: An anti-icing honeycomb core composite manufactured by forming an electromagnetic wave absorption layer by using dielectric fiber, molding the electromagnetic wave absorption layer into a honeycomb core structure by using a molded part including a first base, a second base, and an inner block, hardening the honeycomb core structure, and removing the molded part. The molding step includes first stacking, on the first base including a plurality of grooves in which the inner blocks each having a hexagonal column shape are able to be seated, a plurality of the inner blocks and a plurality of the electromagnetic wave absorption layers as the honeycomb core structure so that the electromagnetic wave absorption layer is disposed between the plurality of inner blocks, and second stacking covering the inner blocks and the electromagnetic wave absorption layers stacked on the first base with the second base having the same shape as the first base.

公开(公告)号：US11772801B2

公开(公告)日：2023-10-03

申请号：US17195065

申请日：2021-03-08

Applicant: Instrumar Limited

Inventor： Stuart Inkpen ,  Chris Nolan ,  Bill Conway ,  Dana Linfield ,  David Bonnell ,  Joshua Swamidas ,  Ruth Abraham

IPC: B64D15/20 ,  B64D15/12 ,  B64D45/00 ,  G08B19/02

CPC classification number: B64D15/20 ,  B64D15/12 ,  B64D45/00 ,  G08B19/02

Abstract: An electric field sensor includes an insulating substrate, a plurality of electrodes, an insulator, a plurality vias, and a ground ring. The electrodes are disposed on the substrate. The insulator is disposed over the electrodes. The vias are coupled to the electrodes and extend through the substrate at a right angle to the electrodes. The ground ring is disposed around the electrodes and the vias and is configured to attenuate a sensitivity of the sensor to electric fields outwards of the ground ring.

公开(公告)号：US20230202660A1

公开(公告)日：2023-06-29

申请号：US17646060

申请日：2021-12-27

Applicant: THE BOEING COMPANY

Inventor： John Alexander Ziebart ,  Douglas James Silva ,  Hosam E. El-Gabalawy ,  Luis Antonio Laracuente-Colon ,  Camron Ravell Call

IPC: B64D15/12 ,  B64D15/20

CPC classification number: B64D15/12 ,  B64D15/20

Abstract: An ice protection system for an aircraft includes one or more heaters configured to be coupled to a surface of a wing of the aircraft. The ice protection system also includes a controller configured to, in response to a first determination indicating presence of an icing condition, determine a setpoint temperature for a first location of an outer surface of the wing configured to be heated by a heater of the one or more heaters. The controller is also configured to control power provided to the heater based on the setpoint temperature. The setpoint temperature for the first location is determined to cause a second location of the outer surface of the wing, which is heated by the heater and is located at a particular distance from the first location, to remain above a threshold temperature based on a projected temperature profile of the outer surface heated by the heater.

公开(公告)号：US11685534B2

公开(公告)日：2023-06-27

申请号：US16989475

申请日：2020-08-10

Applicant: Lockheed Martin Corporation

Inventor： William Betush ,  Russell Guy Torti

IPC: B64D15/00 ,  B64D15/20 ,  B64C3/38 ,  B64D43/02

CPC classification number: B64D15/20 ,  B64C3/38 ,  B64D43/02

Abstract: A system includes a plurality of sensors along a surface of an airfoil operable to measure a first set of ice thickness values at a first time and a second set of ice thickness values at a second time. The system further includes a processor configured to determine a first plurality of lift calculation variables and a second plurality of lift calculation variables. The processor also generates a threshold angle of attack value and updates the threshold angle of attack value at the second time, based on one or more differences between the first and second sets of ice thickness values and the first and second plurality of lift calculation variables. The processor is further configured to send, to a display, based on the updated threshold angle of attack, one or more changes to flight data to adjust the actual angle of attack of the airfoil.

公开(公告)号：US10082573B2

公开(公告)日：2018-09-25

申请号：US14883149

申请日：2015-10-14

Applicant: Honeywell International Inc.

Inventor： Brian P. Bunch ,  Paul E. Christianson

IPC: G01S13/95 ,  G01S7/06 ,  G01W1/08 ,  G01W1/00 ,  B64D15/20

CPC classification number: G01S13/953 ,  B64D15/20 ,  G01S7/062 ,  G01W1/00 ,  G01W1/08 ,  G01W2001/003 ,  G01W2203/00 ,  Y02A90/18

Abstract: Systems and methods of detecting type I ice crystals using an aircraft's onboard weather radar system are disclosed. An exemplary embodiment identifies radar returns having a return level signal strength less than a radar return sensitivity threshold level, determines if at least one of a weather condition and a flight condition concurrently exists with the identified radar returns having the return level signal strength less than the radar return sensitivity threshold level, and identifies a region of airspace potentially having type I ice crystals when the at least one of the weather condition and the flight condition concurrently exists with the identified radar returns having the return level signal strength less than the radar return sensitivity threshold level.

公开(公告)号：US10071808B1

公开(公告)日：2018-09-11

申请号：US15598412

申请日：2017-05-18

Applicant: THE BOEING COMPANY

Inventor： Cris K. Bosetti ,  Hosam E. El-Gabalawy

IPC: B64D15/22 ,  B64D15/12 ,  B64D43/02

CPC classification number: B64D15/20

Abstract: An icing conditions detection system is configured to detect icing conditions with respect to an aircraft. The icing conditions detection system includes an icing conditions detector secured to a surface of the aircraft and that is configured to detect liquid water within an air stream through which the aircraft flies. A free stream of atmospheric air passes over the icing conditions detector during flight. An icing conditions determination control unit is communicatively coupled to the icing conditions detector, and is configured to detect a first icing condition and a second icing condition based on at least one icing conditions signal received from the icing conditions detector. The first icing condition differs from the second icing condition.

公开(公告)号：US20180209887A1

公开(公告)日：2018-07-26

申请号：US15411520

申请日：2017-01-20

Applicant: Rosemount Aerospace Inc.

Inventor： Mark Ray ,  Kaare Josef Anderson

IPC: G01N15/02 ,  G01N15/06 ,  G01W1/00

CPC classification number: G01N15/0211 ,  B64D15/20 ,  G01N21/49 ,  G01N2015/0026 ,  G01S7/4811 ,  G01S7/4815 ,  G01S7/4818 ,  G01S17/95 ,  G01W1/00

Abstract: Apparatus and associated methods relate to determining a size and/or density of Super-cooled Large Droplets (SLDs) in a cloud atmosphere by comparing detected optical signals reflected from small and large sampling volumes of a cloud atmosphere. In some embodiments, an optical pulse is generated and divergently projected from a first optical fiber. A collimating lens is aligned within the divergently projected optical pulse collimating a portion thereof. The collimated and uncollimated portions of the optical pulse are projected into the small and large sampling volumes of the cloud atmosphere, respectively. The ratio of the collimated to the uncollimated portions can be optically controlled. Signals corresponding to optical pulses having different collimated/uncollimated ratios are backscattered by the cloud atmosphere, detected and compared to one another. A processor is configured to calculate, based on scintillation spike differences between the optical pulses of different collimated/uncollimated ratios, a size and/or density of SLDs.

公开(公告)号：US09994327B1

公开(公告)日：2018-06-12

申请号：US15377287

申请日：2016-12-13

Applicant: United Technologies Corporation

Inventor： Zhijun Zheng ,  James H Anderson ,  Scott David Sanicki

IPC: B64D15/20 ,  B64D15/02 ,  B64D29/00 ,  B64D33/02

CPC classification number: B64D15/20 ,  B64D15/00 ,  B64D15/02 ,  B64D15/22 ,  B64D29/00 ,  B64D2033/0233 ,  F02C7/047

Abstract: A method for anti-ice performance analysis may comprise cycling a flow of heating air through an aircraft structure, measuring a temperature of the aircraft structure to generating an oscillatory signal, measuring a minimum temperature value of the oscillatory signal, and calculating anti-ice conditions of the aircraft structure based on the minimum temperature value.