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公开(公告)号：US20240336366A1
公开(公告)日：2024-10-10
申请号：US18749764
申请日：2024-06-21
Applicant: Textron Innovations Inc.
Inventor： Kip Gregory Campbell , Kristen Stuart , Steven G. Hagerott
CPC classification number: B64D31/00 , B64C27/635 , B64C27/68 , B64C39/024 , B64D27/24 , B64U30/20 , B64U50/19 , B64U2201/00
Abstract: A system can include a flight controller for an aircraft that includes an electric motor that drives blades with a variable pitch, where the flight controller receives a command to change a flight characteristic of the aircraft and creates a torque command and a revolutions per minute (RPM) command. The system can also include a propulsion assembly, where the propulsion assembly creates a current command based at least in part on the torque command and the RPM command, creates a blade pitch command based at least in part on the torque command and the RPM command, communicates the current command to the electric motor to change a mechanical output of the electric motor, and communicates the blade pitch command to blade actuators to control the pitch of the blades. The current command and the blade pitch command cause the blades of the aircraft to rotate at a predetermined RPM.
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公开(公告)号：US10006928B1
公开(公告)日：2018-06-26
申请号：US15087026
申请日：2016-03-31
Applicant: Textron Innovations Inc.
Inventor： Steven G. Hagerott , Stephen M. Eddy , Russell Peters
IPC: G01P5/16
CPC classification number: G01P5/16 , G01P13/025
Abstract: Embodiments of a method to determine airspeed for aircraft include determining critical air data parameters without the use of pitot-static systems. Airspeed may be determined by iteratively repeating the method until converging on a stable airspeed value that differs from a previous airspeed value by less than a predetermined threshold. Airspeed may be determined by modeling aircraft lift and repeatedly updating dynamic pressure to converge on an airspeed based on the balance between aircraft lift and weight. Airspeed may be determined based on predetermined relationships between a horizontal control surface position and dynamic pressure. A voting logic method validates or invalidates airspeeds from dissimilar sources, including airspeeds determined using the methods described herein and conventional pitot-static systems.
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Patent Agency Ranking
公开(公告)号：US09340278B2
公开(公告)日：2016-05-17
申请号：US14275102
申请日：2014-05-12
Applicant: Textron Innovations Inc.
Inventor： Steven G. Hagerott , James L. Hammer , Phillippe A. Ciholas , Mark W. Palmer
Abstract: A system and method for a controlling an aircraft with flight control surfaces that are controlled both manually and by a computing device is disclosed. The present invention improves overall flight control operation by reducing the mechanical flight control surface components while providing sufficient back-up control capability in the event of either a mechanical or power-related failure. Through the present invention, natural feedback is provided to the operator from the mechanical flight control surface which operates independent of computer-aided flight control surfaces. Further, through the present invention, force input signals received from the pilot are filtered to improve the operation of the computer-aided flight control surfaces.
Abstract translation: 公开了一种用于控制具有由手动控制的飞行控制表面和由计算装置控制的飞行器的系统和方法。 本发明通过减少机械飞行控制表面部件同时在机械或电力相关故障的情况下提供足够的后备控制能力来改进总体飞行控制操作。 通过本发明，自动反馈从机械飞行控制表面提供给操作者，该机械飞行控制表面独立于计算机辅助飞行控制表面操作。 此外，通过本发明，对从飞行员接收的力输入信号进行滤波，以改善计算机辅助飞行控制表面的操作。
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公开(公告)号：US08874286B2
公开(公告)日：2014-10-28
申请号：US14085540
申请日：2013-11-20
Applicant: Textron Innovations Inc.
Inventor： Steven G. Hagerott , Steven Klausmeyer , Gonzalo E. Mendoza
CPC classification number: B64C19/00 , G05D1/0841
Abstract: An alternative system for damping the dutch roll mode in an aircraft is provided using roll control surfaces. Classical yaw dampers for the dutch roll mode utilize the yaw control surfaces such as a rudder to dampen the dutch roll mode oscillations. An alternative damper is described that utilizes roll control surfaces such as spoilers or ailerons to dampen the dutch roll mode.
Abstract translation: 使用滚动控制表面提供了一种用于阻尼飞行器中荷兰式滚筒模式的替代系统。 用于荷兰卷模式的古典偏航阻尼器利用诸如方向舵的偏航控制表面来抑制荷兰式摇摆模式振荡。 描述了一种替代的阻尼器，其使用诸如扰流板或副翼的滚动控制表面来抑制荷叶辊模式。
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公开(公告)号：US20140288731A1
公开(公告)日：2014-09-25
申请号：US14275102
申请日：2014-05-12
Applicant: Textron Innovations Inc.
Inventor： Steven G. Hagerott , James L. Hammer , Phillippe A. Ciholas , Mark W. Palmer
IPC: B64C19/00
Abstract: A system and method for a controlling an aircraft with flight control surfaces that are controlled both manually and by a computing device is disclosed. The present invention improves overall flight control operation by reducing the mechanical flight control surface components while providing sufficient back-up control capability in the event of either a mechanical or power-related failure. Through the present invention, natural feedback is provided to the operator from the mechanical flight control surface which operates independent of computer-aided flight control surfaces. Further, through the present invention, force input signals received from the pilot are filtered to improve the operation of the computer-aided flight control surfaces.
Abstract translation: 公开了一种用于控制具有由手动控制的飞行控制表面和由计算装置控制的飞行器的系统和方法。 本发明通过减少机械飞行控制表面部件同时在机械或电力相关故障的情况下提供足够的后备控制能力来改进总体飞行控制操作。 通过本发明，自动反馈从机械飞行控制表面提供给操作者，该机械飞行控制表面独立于计算机辅助飞行控制表面操作。 此外，通过本发明，对从飞行员接收的力输入信号进行滤波，以改善计算机辅助飞行控制表面的操作。
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公开(公告)号：US20140114505A1
公开(公告)日：2014-04-24
申请号：US14085540
申请日：2013-11-20
Applicant: Textron Innovations Inc.
Inventor： Steven G. Hagerott , Steven Klausmeyer , Gonzalo E. Mendoza
IPC: B64C19/00
CPC classification number: B64C19/00 , G05D1/0841
Abstract: An alternative system for damping the dutch roll mode in an aircraft is provided using roll control surfaces. Classical yaw dampers for the dutch roll mode utilize the yaw control surfaces such as a rudder to dampen the dutch roll mode oscillations. An alternative damper is described that utilizes roll control surfaces such as spoilers or ailerons to dampen the dutch roll mode.
Abstract translation: 使用滚动控制表面提供了一种用于阻尼飞行器中荷兰式滚筒模式的替代系统。 用于荷兰卷模式的古典偏航阻尼器利用诸如方向舵的偏航控制表面来抑制荷兰式摇摆模式振荡。 描述了一种替代的阻尼器，其使用诸如扰流板或副翼的滚动控制表面来抑制荷叶辊模式。
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公开(公告)号：US12139253B1
公开(公告)日：2024-11-12
申请号：US18463167
申请日：2023-09-07
Applicant: Textron Innovations Inc.
Inventor： Guy Bernard , Steven G. Hagerott
Abstract: Embodiments are directed to systems and methods for controlling a tiltrotor aircraft using a flight control system. A flight control computer is configured to control aircraft effectors in response to inputs from inceptors. The flight control computer stores instructions for controlling aircraft effectors. The instructions cause the flight control computer to perform the steps of converting a signal representing longitudinal motion of a first inceptor into a fore-and-aft translational rate command for the tiltrotor aircraft; converting a signal representing lateral motion of the first inceptor into a side-to-side translational rate command for the tiltrotor aircraft; converting a signal representing longitudinal motion of a second inceptor into a height rate command for the tiltrotor aircraft; and converting a signal representing lateral motion of the second inceptor to a yaw rate command for the tiltrotor aircraft.
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