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公开(公告)号：US12043370B2
公开(公告)日：2024-07-23
申请号：US17818863
申请日：2022-08-10
CPC分类号： B64C13/503 , B64C27/04 , B64C27/57 , B64C2027/8209
摘要： There is disclosed in one example a flight control computer for a rotary aircraft, including: a first interface to communicatively couple to a flight control input; a second interface to communicatively couple to flight geometry actuators; a data source; a multi-dimensional lookup table including a data structure to correlate flight control inputs to flight geometry actuator outputs according to a third-factor; and circuitry and logic instructions to: receive an input via the first interface; query the data source for the third-factor; query the multi-dimensional lookup table for a control input modifier according to the flight control input and the third-factor; and compute and send via a third interface a flight geometry output according to the control input modifier.
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公开(公告)号：US11952107B2
公开(公告)日：2024-04-09
申请号：US17469560
申请日：2021-09-08
发明人： Meng Wang , Ryan Madson , Jalpa Shah
CPC分类号： B64C13/503 , B64C9/28 , B64C13/16
摘要： An actuator control system can include a plurality of electro-mechanical actuators for operating one or more end effectors, a plurality of position sensors associated with the plurality of electro-mechanical actuators, each of the plurality of positions sensors providing an output indicating an actual position value, and a control system. The control system can be configured to receive an activation command signal and the position sensor outputs, and send a speed command for each of the plurality of electro-mechanical actuators and adjust the speed command of each of the plurality of electro-mechanical actuators using a common reference parameter to synchronize movement of the plurality of electro-mechanical actuators together.
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公开(公告)号：US11939042B2
公开(公告)日：2024-03-26
申请号：US17469611
申请日：2021-09-08
发明人： Meng Wang , Ryan Madson , Jalpa Shah
CPC分类号： B64C13/503 , B64C9/28 , B64C13/16
摘要： An actuator control system can include a plurality of electro-mechanical actuators for operating one or more end effectors, a plurality of position sensors associated with the plurality of electro-mechanical actuators, each of the plurality of positions sensors providing an output indicating an actual position value, and a control system. The control system can be configured to receive an activation command signal and the position sensor outputs, and send a speed command for each of the plurality of electro-mechanical actuators and adjust the speed command of each of the plurality of electro-mechanical actuators using a mean position value based on the actual position values to synchronize movement of the plurality of electro-mechanical actuators together.
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公开(公告)号：US11702191B1
公开(公告)日：2023-07-18
申请号：US18147640
申请日：2022-12-28
CPC分类号： B64C13/0421 , B64C13/503 , G05D1/0858
摘要： Disclosed are systems and methods for controlling an electric vertical take-off and landing (eVTOL) aircraft. In one embodiment, a system comprises a processor, a first inceptor, communicatively coupled to the processor, the first inceptor configured to accept longitudinal and lateral linear movements as manual input and provide corresponding signals to the processor, and a second inceptor, communicatively coupled to the processor, the second inceptor configured to accept longitudinal and lateral linear movements as manual input and provide corresponding signals to the processor, wherein the processor is configured to control a heading of an aircraft using a signal received from the second inceptor corresponding to lateral linear movement of the second inceptor. Some embodiments may additionally include at least one sensor and a thumb stick for each inceptor.
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公开(公告)号：US11526636B2
公开(公告)日：2022-12-13
申请号：US16471879
申请日：2017-12-18
申请人： BOMBARDIER INC.
发明人： Claude Tessier , Gabriel Meunier
IPC分类号： G06F30/15 , B64F5/60 , G06F30/20 , G06F113/28 , B64C13/00
摘要： Methods and systems relating to the design and testing of systems that include hinged flight control surfaces of aircraft are disclosed. The systems and methods disclosed herein make use of a structural model representing a structural environment of the system in a relatively simple manner. In various embodiments, the structural model comprises one or more actuation branches having a common linear actuation direction, a load mass, and a massless connector representative of a hinge line of the flight control surface. The massless connector is connected to and disposed between the one or more actuation branches and the load mass and is movable along the common linear actuation direction so that linear movement of the massless connector is correlated to rotational movement of the hinged flight control surface.
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公开(公告)号：US11329575B2
公开(公告)日：2022-05-10
申请号：US16081945
申请日：2017-03-01
申请人： NANOMOTION LTD
发明人： Nir Karasikov
摘要： A flap actuator for adjusting the orientation of a flap or the like, the actuator. The actuator includes: a static arcuate member having a radius of curvature; a piezoelectric motor biased to be in operable contact with the static arcuate member; a housing for housing the piezoelectric motor; and a flap orientation shaft operably connecting between the housing and the flap. The distance between the shaft and the static arcuate member is essentially equal to the radius of curvature of the static arcuate member.
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公开(公告)号：US11249491B2
公开(公告)日：2022-02-15
申请号：US16395875
申请日：2019-04-26
发明人： Hao Luo , Di Ou , Chaobing Chen , Dayang Zheng , Wentao Wang
摘要： An unmanned aerial vehicle (UAV) includes a central part, a frame assembly, and a propulsion assembly mounted to the frame assembly. The UAV also includes a servo mounted to the central part. The servo includes a driving apparatus, a control apparatus operably coupled with the driving apparatus, and a sensor configured to obtain operating parameters of the driving apparatus. The operating parameters include operating positions of the driving apparatus. The control apparatus is configured to control the driving apparatus to rotate to a predetermined position and stay at the predetermined position based on the operating positions of the driving apparatus obtained by the sensor.
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公开(公告)号：US11128251B1
公开(公告)日：2021-09-21
申请号：US16862212
申请日：2020-04-29
申请人： The Boeing Company
IPC分类号： H02P29/024 , H02P5/68 , H02P27/06 , B64C13/00
摘要： A fault-tolerant power system architecture for aircraft electric propulsion. The fault-tolerant systems continue to operate in the event of the failure of (or one or more faults within) some component. The fault-tolerant design enables the system to continue its intended operation, possibly at a reduced level, rather than failing completely, when some part of the system fails. When a turn-to-turn fault in an AC motor is detected, a motor controller will short three top or three bottom switches in the inverter together (effectively shorting the associated stator windings) to divert fault current from the motor windings to the motor controller, where cooling is available. Also, when a fault in or at the input to a motor controller is detected, the motor controller cuts off power to the motor by issuing a command that causes an upstream contactor with high-voltage DC bus input to open.
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公开(公告)号：US10745141B2
公开(公告)日：2020-08-18
申请号：US15780676
申请日：2016-12-01
摘要： A rudder bias system for an aircraft with a right engine and a left engine includes a component determining a left and right primary and secondary thrust estimates. The system includes a left engine thrust estimate selector determining a left selected estimate based on the left thrust estimates and a right engine thrust estimate selector determining a right selected estimate based on the right thrust estimates. The system includes an enable and mode component determining one or more corresponding validities for the thrust estimates. The system includes a control component generating an engage command based on a thrust differential between the right engine and the left engine, calculated from the left selected estimate and the right selected estimate and a torque command based on an equivalent pedal force assistance calculated as a difference between the thrust differential and an activation threshold.
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公开(公告)号：US20200239144A1
公开(公告)日：2020-07-30
申请号：US16845373
申请日：2020-04-10
申请人： THE BOEING COMPANY
发明人： Thomas Joseph Moran
摘要： A galley cart includes walls defining an interior cavity extending between a front and a rear of the galley cart and the interior cavity extending between a top end and a bottom end. A supply port is provided in flow communication with the interior cavity and a return port is provided in flow communication with the interior cavity. A barrier is positioned between the supply port and the return port within the interior cavity of the cart to define a supply chamber and a return chamber to control airflow through the interior cavity.
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