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1.发明申请MULTIPLE POWER ASSURANCE CHECK PROCEDURE FOR AIRCRAFT WITH AN ENGINE INLET BARRIER FILTER INSTALLED 审中-公开安装发动机入口过滤器的飞机多功能保修检查程序公开(公告)号：US20160347479A1
公开(公告)日：2016-12-01
申请号：US15167886
申请日：2016-05-27
Applicant: Bell Helicopter Textron Inc.
Inventor： Joshua Robert O'Neil , Martin Peryea , Andrew Jordan Birkenheuer
CPC classification number: B64D43/00 , B64D2033/0246 , B64D2045/0085 , B64F5/60
Abstract: A method of conducting an engine power assurance check includes performing a first engine power assurance check wherein the first engine power assurance check is judged as passing or failing based on power performance values calculated assuming the presence of a substantially clogged or blocked inlet barrier filter and in response to a fail result of the first engine power assurance check, performing a second engine power assurance check wherein the second power assurance check is judged as passing or failing based on power performance values calculated assuming at least one of no inlet barrier filter being installed and an open bypass of an installed inlet barrier filter.
Abstract translation: 执行发动机功率保证检查的方法包括执行第一发动机功率保证检查，其中基于基本上堵塞或阻塞的入口阻挡过滤器的存在而计算的功率性能值，将第一发动机功率保证检查判断为通过或失败，并且 响应于所述第一发动机功率保证检查的故障结果，执行第二发动机功率保证检查，其中所述第二功率保证检查基于假定安装无入口阻挡滤波器的至少一个而计算的功率性能值被判断为通过或失败; 安装的入口挡板过滤器的开路旁路。
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2.发明授权公开(公告)号：US10766631B2
公开(公告)日：2020-09-08
申请号：US15167886
申请日：2016-05-27
Applicant: Bell Helicopter Textron Inc.
Inventor： Joshua Robert O'Neil , Martin Peryea , Andrew Jordan Birkenheuer
Abstract: A method of conducting an engine power assurance check includes performing a first engine power assurance check wherein the first engine power assurance check is judged as passing or failing based on power performance values calculated assuming the presence of a substantially clogged or blocked inlet barrier filter and in response to a fail result of the first engine power assurance check, performing a second engine power assurance check wherein the second power assurance check is judged as passing or failing based on power performance values calculated assuming at least one of no inlet barrier filter being installed and an open bypass of an installed inlet barrier filter.
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公开(公告)号：US20190056734A1
公开(公告)日：2019-02-21
申请号：US16032928
申请日：2018-07-11
Applicant: Bell Helicopter Textron Inc.
Inventor： Robert Earl Worsham, II , Luke Dafydd Gillett , Troy Sheldon Caudill , Bradley Paul Regnier , Joshua Robert O'Neil , Brandon Jeffrey Thomas
Abstract: In an embodiment, a rotorcraft includes a rotor system including a plurality of blades; two or more engines operable to rotate the plurality of blades; a control assembly operable to receive commands from a pilot; a flight control computer (FCC) in signal communication with the two or more engines, the FCC being operable to generate engine data indicating whether the two or more engines are functional; and a flight management system (FMS) in signal communication with the control assembly and the FCC, the FMS being operable to receive a takeoff type and a plurality of takeoff parameters input into the FMS by the pilot; generate a guidance profile for a Category A (Cat-A) takeoff procedure based on the takeoff type and the plurality of takeoff parameters, the Cat-A takeoff procedure including one or more decision points for performing a takeoff procedure based on whether all engines are operable or one engine is inoperable; receive a command to engage in a takeoff procedure from the control assembly; in response to the command to engage in the takeoff procedure, provide guidance cues to a pilot of the rotorcraft; receive the engine data from the FCC during operation of the rotorcraft; and update the guidance profile based on the engine data during operation of the rotorcraft.
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