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公开(公告)号：US20220106051A1
公开(公告)日：2022-04-07
申请号：US17063118
申请日：2020-10-05
发明人： Boris Novosad , Jan Tomas
摘要： An actuation system for an aircraft piston engine includes a controller and an actuator. The controller selectively supplies motor control signals to a motor. The actuator includes a housing, a motor, a main rod, a control handle, and an inner rod. The main rod receives a drive torque from the motor and translates in either a first axial direction or a second axial direction. The main rod is responsive to an axial drive force to translate in either the first axial direction or the second axial direction. The inner rod is disposed within the main rod and is movable between a first position, in which main rod rotation causes the main rod to translate, and a second position, in which main rod rotation does not cause the main rod to translate, but application of the axial force to the control handle causes the main rod to translate.
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公开(公告)号：US20210354843A1
公开(公告)日：2021-11-18
申请号：US16874912
申请日：2020-05-15
摘要： A method of controlling a hybrid-electric aircraft powerplant includes running a first control loop for command of a thermal engine based on error between total response commanded for a hybrid-electric powerplant and total response from the hybrid-electric powerplant. A second control loop runs in parallel with the first control loop for commanding the thermal engine based on error between maximum thermal engine output and total response commanded. A third control loop runs in parallel with the first and second control loops for commanding engine/propeller speed, wherein the third control loop outputs a speed control enable or disable status. A fourth control loop runs in parallel with the first, second, and third control loops for commanding the electric motor with non-zero demand when the second control loop is above control to add response from the electric motor to response from the thermal engine to achieve the response commanded.
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公开(公告)号：US20210323425A1
公开(公告)日：2021-10-21
申请号：US16851353
申请日：2020-04-17
摘要： An engine system for an aircraft comprising a propulsor configured to drive the aircraft, a thermal combustion engine configured to drive the propulsor, an electric motor connected to the thermal combustion engine and configured to drive the propulsor, a power converter configured to apply a torque to the electric motor and generate electric energy from the torque applied to the electric motor, and an engine controller, the engine controller being configured to determine a current power output of the thermal combustion engine, determine an optimum power output of the thermal combustion engine based on current operating conditions, and vary the torque applied to the electric motor so as to vary a load on the thermal combustion engine, wherein the torque may be varied by an amount required to vary the power output of the thermal combustion engine to the determined optimum power output.
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公开(公告)号：US20210317787A1
公开(公告)日：2021-10-14
申请号：US17220425
申请日：2021-04-01
发明人： Hannes WUESTENBERG
IPC分类号： F02C7/36 , F02C6/20 , F16H57/02 , F16H57/08 , F16H57/032 , B64D35/02 , B64D31/14 , B64D27/10
摘要： The invention relates to a planetary gear box in a gas turbine engine, characterized by at least one protective device in the interior of a casing of the planetary gear box, wherein the protective device is designed and configured to divert at least one particle which is moving in the casing, in particular in an event of damage, and/or to extract kinetic energy from the moving at least one particle, in particular by deformation of the protective device, wherein the protective device is coupled to the casing of the planetary gear box, to a planet gear and/or to a planet carrier. The invention also relates to a gas turbine engine.
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公开(公告)号：US11121557B2
公开(公告)日：2021-09-14
申请号：US15946947
申请日：2018-04-06
摘要： A power distribution system is disclosed for conducting electrical power through a combination of hollow tube conductors and flexible cabling. Each hollow tube conductor includes an end formed into flat pads. The flexible cabling comprises litz wire, and includes ends crimped to integral lugs. An end of the flexible cabling is coupled to an end of the hollow tube conductor. The other end of the flexible cabling is coupled to an electric device. The other end of the hollow tube conductor is coupled to another flexible cable, which is in turn coupled to another electric device. By connecting the hollow tube conductors, flexible cabling, and electrical devices in this way, an electrically conductive pathway may be established between the electrical devices. The power distribution system conducts alternating current (AC) power, and addresses the skin effect phenomenon that occurs when conducting AC power. The power distribution system can be utilized in the highly-constrained environment of electric aircraft, where weight and space is at a premium.
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公开(公告)号：US20210270147A1
公开(公告)日：2021-09-02
申请号：US17181100
申请日：2021-02-22
发明人： Tomasz GRUBBA , Jos RAVEN
IPC分类号： F01D21/04 , F16H57/025 , B64D27/10 , B64D31/06 , B64D31/14 , F02C7/32 , F01D25/16 , F01D21/06
摘要： The invention relates to a torque limiting device in a torque bearing connecting structure between a gearbox and a stationary structure in a gas turbine engine, wherein the torque limiting device comprises a mechanical fuse in the connection structure comprising an at least partially circumferential weakening of the material. The invention also relates to a gas turbine engine.
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公开(公告)号：US11106205B2
公开(公告)日：2021-08-31
申请号：US16135399
申请日：2018-09-19
发明人： Paul A. Adamski
摘要： A control assembly for an aircraft system according to an example of the present disclosure includes a multi-core processor that has a plurality of cores coupled to a communications module and to an arbitration module. The communications module is operable to communicate information between the plurality of cores and one or more aircraft modules. The plurality of cores include first and second cores operable to concurrently execute a first discrete set of software instructions to generate respective instances of an output. The arbitration module is operable to communicate each and every one of the respective instances to control the one or more aircraft modules. A method of operating an aircraft system is also disclosed.
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98.发明申请公开(公告)号：US20210188452A1
公开(公告)日：2021-06-24
申请号：US16755526
申请日：2018-10-08
发明人： Lizhi SHANG , Monika IVANTYSYNOVA
IPC分类号： B64D27/02 , B64D27/24 , B64D27/10 , B64C29/00 , B64D31/04 , B64D31/06 , B64D31/14 , B64D33/08
摘要： A hydraulic propulsion system is disclosed. The system includes one or more input interfaces configured to receive mechanical power from a power source, four or more variable displacement pumps coupled to the one or more input interfaces adaptable to generate a controlled variable quantity of fluid to be pumped out of each of the variable displacement pumps in response to a control input from a corresponding control interface, and four or more positive displacement motors each fluidly coupled to a corresponding variable displacement pump and configured to receive the pumped fluid, wherein each motor is configured to be mechanically coupled to one or more aerodynamic rotors of a multi-rotor vertical take-off and landing aircraft to control thrust and attitude.
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公开(公告)号：US10759545B2
公开(公告)日：2020-09-01
申请号：US16012040
申请日：2018-06-19
IPC分类号： B64D31/06 , B64D27/02 , B64D27/12 , B64D27/24 , B64D31/14 , H02K7/18 , H02K11/00 , F02C6/20 , F02C6/14 , H02K7/20
摘要： A propulsion system for an aircraft includes at least one gas turbine engine, an electric auxiliary fan driving motor configured to selectively receive electric power input from one or more electric power sources, and at least one auxiliary propulsion fan configured to selectively receive a motive force from either or both of the at least one gas turbine engine and the electric auxiliary fan driving motor. The propulsion system also includes a controller configured to establish a plurality of takeoff thrust settings of the at least one gas turbine engine and the electric auxiliary fan driving motor such that a minimum total aircraft thrust required for takeoff of the aircraft is produced.
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公开(公告)号：US20190382123A1
公开(公告)日：2019-12-19
申请号：US16012040
申请日：2018-06-19
IPC分类号： B64D31/06 , B64D27/02 , B64D27/12 , B64D27/24 , B64D31/14 , H02K7/18 , H02K7/20 , H02K11/00 , F02C6/20 , F02C6/14
摘要： A propulsion system for an aircraft includes at least one gas turbine engine, an electric auxiliary fan driving motor configured to selectively receive electric power input from one or more electric power sources, and at least one auxiliary propulsion fan configured to selectively receive a motive force from either or both of the at least one gas turbine engine and the electric auxiliary fan driving motor. The propulsion system also includes a controller configured to establish a plurality of takeoff thrust settings of the at least one gas turbine engine and the electric auxiliary fan driving motor such that a minimum total aircraft thrust required for takeoff of the aircraft is produced.
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