公开(公告)号：US20240175409A1

公开(公告)日：2024-05-30

申请号：US18071141

申请日：2022-11-29

Applicant: Raytheon Technologies Corporation

Inventor： David Wasselin ,  Nancy Poisson ,  Brian V. Winebrenner ,  Bradley C. Schafer ,  Ramesh Rajagopalan

IPC: F02K1/76 ,  B64D31/09 ,  B64D45/00 ,  B64D45/04 ,  B64F5/60 ,  G05D1/617 ,  G05D1/654 ,  G05D109/22

CPC classification number: F02K1/76 ,  B64D31/09 ,  B64D45/04 ,  B64F5/60 ,  G05D1/617 ,  G05D1/654 ,  B64D2045/0085 ,  G05D2109/22

Abstract: A system of an aircraft includes a thrust reverser control configured to control deployment of one or more thrust reversers of the aircraft, a brake control configured to control operation of one or more brakes of the aircraft, and a controller. The controller is configured to detect a landing condition of the aircraft, determine one or more thrust reverser deployment and brake control parameters for one or more current conditions at a target location of the aircraft, and control the one or more thrust reversers and the one or more brakes upon landing at the target location based on the one or more thrust reverser deployment and brake control parameters. The controller can modify one or more control parameters of the aircraft based on detecting a change in the one or more current conditions at the target location or a fault condition of the aircraft.

公开(公告)号：US20240011869A1

公开(公告)日：2024-01-11

申请号：US17860814

申请日：2022-07-08

Applicant: Raytheon Technologies Corporation

Inventor： David Wasselin ,  Rose A. Wasselin

IPC: G01M15/14 ,  F01D21/00

CPC classification number: G01M15/14 ,  F01D21/003 ,  F05D2260/83 ,  F05D2220/32

Abstract: Examples described herein provide a method for aircraft engine maintenance testing for an engine of an aircraft. The method includes causing, by an aircraft maintenance computer, a full authority digital engine control to enter a test mode. The method further includes loading, via the aircraft maintenance computer, a script to the full authority digital engine control, the script defining a specific maintenance test sequence. The method further includes performing, by the full authority digital engine control, the specific maintenance test sequence. The method further includes implementing a corrective action to correct a defect detected by the specific maintenance test sequence.

公开(公告)号：US20230166857A1

公开(公告)日：2023-06-01

申请号：US18071138

申请日：2022-11-29

Applicant: Raytheon Technologies Corporation

Inventor： David Wasselin ,  Nancy Poisson ,  Brian V. Winebrenner ,  Bradley C. Schafer ,  Ramesh Rajagopalan

IPC: B64D31/06 ,  B64D45/00

CPC classification number: B64D31/06 ,  B64D45/00

Abstract: A system of an aircraft includes one or more gas turbine engines and a controller. The controller is configured to detect a pre-takeoff condition of the aircraft and determine one or more control parameters for one or more current conditions at a target location of the aircraft. The controller is further configured to determine a final takeoff speed of the one or more gas turbine engines based on the one or more control parameters. At least one of the one or more gas turbine engines is controlled to accelerate to the final takeoff speed after transitioning from the pre-takeoff condition to a takeoff condition.