公开(公告)号：US20240326988A1

公开(公告)日：2024-10-03

申请号：US18703188

申请日：2022-10-09

申请人： PENTAXI LTD

发明人： Eran GROSS ,  Yair DUBESTER ,  Jacques CHEMLA

IPC分类号： B64C17/02 ,  B64C27/28 ,  B64C39/12 ,  B64D27/357 ,  B64D31/09 ,  B64D45/00 ,  H01M50/249

CPC分类号： B64C17/02 ,  B64C27/28 ,  B64C39/12 ,  B64D27/357 ,  B64D31/09 ,  B64D45/00 ,  H01M50/249 ,  H01M2220/20

摘要： Systems and methods for an aircraft comprising: wings in tandem configuration wherein each wing having one tilting motor; an additional tilting motor located at the rear part of said aircraft; wherein all said tilting motors can tilt in the range between full horizontal and full vertical positions; at least two arrays of batteries, said arrays capable of moving forward and backward; sensing means; a computing device configured for: receiving said sensed information; controlling said motors; calculating the compensation required in case of a single motor failure and controlling the active motors accordingly; based on said sensed information and flight/movement instructions calculating continuously the optimal center of gravity location in the range possible given the movement range of said batteries arrays and controlling the movement of said batteries arrays accordingly.

公开(公告)号：US20240175409A1

公开(公告)日：2024-05-30

申请号：US18071141

申请日：2022-11-29

申请人： Raytheon Technologies Corporation

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

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

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

摘要： 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：US20240353867A1

公开(公告)日：2024-10-24

申请号：US18635198

申请日：2024-04-15

申请人： Textron eAviation Inc.

发明人： William Alexander Dean ,  Steven G. Hagerott

IPC分类号： G05D1/85 ,  B64D31/09

CPC分类号： G05D1/854 ,  B64D31/09

摘要： An aircraft emergency descent method includes setting a pre-set maximum collective blade pitch and a pre-set altitude as part of a failure procedure; monitoring rotor assemblies through an aircraft control system and a failure detection module; determining when a rotor assembly has failed; and activating the failure procedure. The failure procedure includes commanding a maximum torque to a motor of each rotor assembly such that the rotational velocity of functioning rotors increases; detecting the increase in rotational velocity; adjusting either motor torque or a collective blade pitch to regulate rotational velocity; monitoring altitude of the aircraft; and upon determining when the aircraft reaches the pre-set altitude, adjusting the collective blade pitch to the pre-set maximum collective blade pitch via the at least one governor such that momentum is conserved, causing a descent rate of the aircraft to decrease as the aircraft approaches a ground surface.

公开(公告)号：US12055100B2

公开(公告)日：2024-08-06

申请号：US17841175

申请日：2022-06-15

申请人： Airbus Operations SAS

发明人： Claudia Conte ,  Quentin-Alexandre Flamant-Bati ,  Xavier Collas ,  Marie-Claire Pineri

IPC分类号： F02C7/262 ,  B64D31/06 ,  B64D31/09 ,  F02C6/00 ,  F02C9/42 ,  F02C9/46

CPC分类号： F02C7/262 ,  B64D31/06 ,  B64D31/09 ,  F02C6/00 ,  F02C9/42 ,  F02C9/46 ,  F05D2220/323 ,  F05D2260/85 ,  F05D2270/092 ,  F05D2270/093 ,  F05D2270/13 ,  F05D2270/303 ,  F05D2270/334

摘要： A system for automated management of in-flight restarting of engines of an aircraft includes controllers, each engine of the aircraft being managed by one of the controllers. A controller that detects an engine that has stopped: cuts off the energy supply of the engine and performs a windmill engine start. If at least one other engine has stopped, prioritization of engine restarting includes: collecting information concerning a state of health of each engine; determining from the information collected information representing a probability of restarting each stopped engine; determining a sequential order of restarting the stopped engines as a function of information representing the probability of restarting each stopped engine. Each stopped engine continues to be windmill started until selection of the engine in question in the sequential order of restarting the stopped engines. Thus, the operational status of the aircraft is improved as quickly as possible.