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21. 发明申请

US20180362176A1 METHOD FOR DYNAMIC COMMAND LIMITING IN A DISTRIBUTED CONTROL SYSTEM 审中-公开
公开(公告)号：US20180362176A1
公开(公告)日：2018-12-20
申请号：US15780665
申请日：2016-12-01
申请人： HONDA PATENTS & TECHNOLOGIES NORTH AMERICA, LLC
发明人： Jukka Matti Hirvonen
IPC分类号： B64D31/08 , B64D31/12
摘要： According to one or more aspects, a control system for managing operational limits associated with two or more actuators includes a controller. The controller may continually monitor a first operational limit associated with a first actuator and a first operational limit associated with a second actuator. The controller may determine a first overall distributed control system operating limit based on the first operational limit associated with the first actuator, the first operational limit associated with the second actuator, and a type of operational limit associated with both operational limits.

22. 发明授权

US09849997B2 Method for synchronising the engines of an airplane with dual intermediate state 有权
公开(公告)号：US09849997B2
公开(公告)日：2017-12-26
申请号：US15304008
申请日：2015-04-15
申请人： Safran Aircraft Engines
发明人： Florent Nobelen
IPC分类号： B64D31/12 , F02C9/42 , F01D21/14 , F02C9/16
CPC分类号： B64D31/12 , F01D21/14 , F02C9/16 , F02C9/42 , F05D2220/323 , F05D2270/023 , F05D2270/13 , F05D2270/301 , F05D2270/304 , F05D2270/306
摘要： A method for synchronizing the engines of an airplane according to one activation logic having a deactivated state (20), an armed state (22), and one activated state (16), in which: the switching (36) of the synchronization from the armed state to the activated state is carried out via a first and then a second successive intermediate state (38, 39) of the activation logic, every instance of the activation logic switching from the second intermediate state (39) to the activated state involves the following: taking into consideration, on each engine, the activation state of the synchronization, and exchanging said data between the engines, the switching of the activation logic of one of the engines to the activated state requires that the safety and activation conditions of the other engine are all met. if one of the engines enters the deactivated state, the other engine does so as well; and for each engine, the switching (36, 42) of the synchronization from the armed state to the first and then to the second intermediate state takes place automatically when a first portion and then a second portion of the safety and/or activation conditions are met.

23. 发明授权

US09415877B2 Method of synchronizing the engines of an aircraft 有权
标题翻译：同步飞机发动机的方法
公开(公告)号：US09415877B2
公开(公告)日：2016-08-16
申请号：US14200130
申请日：2014-03-07
申请人： SNECMA
发明人： Florent Nobelen , Cedrik Djelassi
IPC分类号： B64D31/12 , F02C9/42
CPC分类号： B64D31/12 , F02C9/42
摘要： A method of synchronizing engines of an airplane in accordance with at least one activation logic (10, 10′) defining a deactivated state (20), a primed state (22), and at least one activated state (16, 18), and comprising: passing (32) synchronization from the deactivated state to the primed state when a pilot of the airplane issues an activation order; passing (36) synchronization from the primed state to the activated state when at least certain safety and/or activation conditions are satisfied; and passing (24, 34) synchronization from the activated or primed state to the deactivated state when the pilot issues a deactivation order or whenever at least some of the safety conditions are not satisfied.
摘要翻译：根据限定停用状态（20），起始状态（22）和至少一个激活状态（16,18）的至少一个激活逻辑（10,10'）来同步飞机引擎的方法，以及包括：当飞机的飞行员发出激活命令时，将（32）同步从停用状态传递到起动状态; 当满足至少某些安全和/或激活条件时，将（36）同步从引发状态传递到激活状态; 以及当所述飞行员发出停用命令时或者当至少一些所述安全条件不满足时，将（24,34）同步从所述激活或引发状态传递到所述停用状态。

24. 发明授权

US4772180A Aircraft thrust control 失效
公开(公告)号：US4772180A
公开(公告)日：1988-09-20
申请号：US902231
申请日：1986-08-29
申请人： Neil Walker , Stanley G. Day , Paul D. Collopy , George W. Bennett
发明人： Neil Walker , Stanley G. Day , Paul D. Collopy , George W. Bennett
IPC分类号： B64D31/12 , B64C11/30 , B64C11/50 , F02C9/58 , F02K3/072 , B64C11/48
CPC分类号： F02C9/58 , B64C11/306 , B64C11/50 , F02K3/072 , B64D2027/005 , Y02T50/66
摘要： An integrated control system for coaxial counterrotating aircraft propulsors driven by a common gas turbine engine. The system establishes an engine pressure ratio by control of fuel flow and uses the established pressure ratio to set propulsor speed. Propulsor speed is set by adjustment of blade pitch.

25. 发明授权

US3206640A Synchronizing arrangement for airplane engines or the like 失效
标题翻译：飞机发动机等的同步装置
公开(公告)号：US3206640A
公开(公告)日：1965-09-14
申请号：US7940460
申请日：1960-12-29
申请人： WOODWARD GOVERNOR CO
发明人： LEESON JR JAMES L
IPC分类号： B64C11/50 , B64D31/12 , H02P5/52
CPC分类号： B64D31/12 , B64C11/50 , H02P5/56

26. 发明授权

US11970282B2 Aircraft thrust management with a fuel cell 有权
公开(公告)号：US11970282B2
公开(公告)日：2024-04-30
申请号：US17568892
申请日：2022-01-05
申请人： General Electric Company
发明人： Honggang Wang , Kum Kang Huh , Michael Anthony Benjamin , Koji Asari
IPC分类号： B64D27/24 , B64D27/10 , B64D31/12 , B64D27/02 , B64D41/00
CPC分类号： B64D31/12 , B64D27/10 , B64D27/24 , B64D2027/026 , B64D2041/005 , B64D2221/00
摘要： Systems and methods of aircraft thrust management are provided. For example, a propulsion system for an aircraft comprises a fuel cell assembly comprising a fuel cell, a turbomachine, and a controller comprising memory and one or more processors. The memory stores instructions that, when executed by the one or more processors, cause the propulsion system to perform operations including receiving data indicative of a propulsion system thrust discrepancy and modifying an output of the fuel cell in response to receiving data indicative of the propulsion system thrust discrepancy. Modifying the fuel cell output may include modifying output products, an electrical power output, or both of the fuel cell to balance the thrust provided by the propulsion system.

27. 发明授权

US11905004B2 Air mobility vehicle 有权
公开(公告)号：US11905004B2
公开(公告)日：2024-02-20
申请号：US17190081
申请日：2021-03-02
申请人： Hyundai Motor Company , Kia Motors Corporation
发明人： Woo Suk Jung , Hee Kwang Lee , Hyun Seok Hong , Hyun Woo Jun
IPC分类号： B64D27/24 , B64D35/02 , B64D31/12 , B64D31/10 , B64D33/02 , B64D31/00 , B64D27/02 , B64C29/00 , B64C27/82 , B64C27/32 , B60L58/12 , B60L53/00
CPC分类号： B64C27/82 , B60L53/00 , B60L58/12 , B64C27/32 , B64C29/0025 , B64D27/02 , B64D27/24 , B64D31/00 , B64D31/10 , B64D31/12 , B64D33/02 , B64D35/02 , B60L2200/10 , B64C2027/8227 , B64D2027/026 , B64D2033/0213
摘要： In an air mobility vehicle, an engine operates as required to provide mechanical driving force or electric energy. A battery is charged with the electric energy from the engine. Main rotors operate using the electric energy of the battery and electric power generated by the engine to perform takeoff, landing, and cruising. Auxiliary rotors are disposed at or adjacent to the center of gravity of a vehicle body and mechanically connected to the engine via a clutch. The auxiliary rotors perform the takeoff, the landing, or the cruising by receiving the mechanical driving force from the engine when the clutch is in an engaged position. A controller monitors the states of the battery and the main rotors and controls the operations of the engine and the clutch.

28. 发明公开

US20240051670A1 AIRCRAFT EQUIPPED WITH A DISTRIBUTED PROPULSION SYSTEM HAVING SUCTION AND PRESSURE FANS 审中-公开
公开(公告)号：US20240051670A1
公开(公告)日：2024-02-15
申请号：US18495871
申请日：2023-10-27
申请人： General Electric Company
发明人： Brendan Michael Freely , Kurt David Murrow , Michael James McMahon , Andrew Breeze-Stringfellow
IPC分类号： B64D27/02 , B64C23/00 , B64D27/24 , B64D31/12 , F04D25/16
CPC分类号： B64D27/02 , B64C23/00 , B64D27/24 , B64D31/12 , F04D25/166
摘要： An aircraft equipped with a distributed fan propulsion system and methods of operating such aircraft are provided. In one aspect, an aircraft includes a wing having a top surface and a bottom surface. The aircraft also has a distributed propulsion system that includes a suction fan array having one or more fans mounted to the wing and a pressure fan array having one or more fans mounted to the wing. The fans of the suction fan array are each positioned primarily above the top surface of the wing and the fans of the pressure fan array are each positioned primarily below the bottom surface of the wing. The fans of the suction fan array are controllable independent of the fans of the pressure fan array so that the air pressure above and/or below the wing can be locally controlled, allowing for adjustment of lift on the wing.

29. 发明授权

US11827372B2 Engine characteristics matching 有权
公开(公告)号：US11827372B2
公开(公告)日：2023-11-28
申请号：US16875196
申请日：2020-05-15
申请人： Pratt & Whitney Canada Corp.
发明人： Leonid Guerchkovitch , Aaron J. Kaufman , Boris Karpman , Manuj Dhingra
IPC分类号： B64D31/12 , B64D27/02 , B64D31/06 , B64F5/60 , B64D27/24
CPC分类号： B64D31/12 , B64D27/02 , B64D27/24 , B64D31/06 , B64F5/60 , B64D2027/026
摘要： A method of controlling a multi-engine aircraft includes receiving input for commanded thrust and modifying the commanded thrust using a model of an incumbent powerplant to generate a modified commanded thrust for matching aircraft performance with a new powerplant to the aircraft performance with the incumbent powerplant. The method includes applying the modified commanded thrust to the new powerplant.

30. 发明授权

US11807378B2 Alternating starter use during multi-engine motoring 有权
公开(公告)号：US11807378B2
公开(公告)日：2023-11-07
申请号：US16829172
申请日：2020-03-25
申请人： RTX CORPORATION
发明人： David Gelwan , Jesse W. Clauson , Frederick M. Schwarz
IPC分类号： F01D19/02 , B64D31/12 , F02C9/00 , F02C7/27 , F02C7/277 , F02C9/18 , F02C7/26 , F02C7/268 , F02C7/275
CPC分类号： B64D31/12 , F01D19/02 , F02C7/27 , F02C7/277 , F02C9/00 , F02C9/18 , F02C7/26 , F02C7/268 , F02C7/275 , F05D2220/323 , F05D2220/50 , F05D2240/40 , F05D2260/85 , F05D2270/304
摘要： A system is provided for alternating starter use during multi-engine motoring in an aircraft. The system includes a first engine starting system of a first engine. A first controller is in communication with a second controller that controls a second engine starting system of a second engine, the first controller being configured to intermittently direct power to the first engine starting system to alternately accelerate and decelerate the first engine during motoring with respect to the second engine.

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