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121. 发明授权

US10351231B2 Rotorcraft autopilot and methods 有权
公开(公告)号：US10351231B2
公开(公告)日：2019-07-16
申请号：US15687454
申请日：2017-08-26
申请人： Merlin Technology, Inc.
发明人： John E. Mercer , Nicholas Albion , Mark Bartel , Marc Feifel , Mark Marvin
IPC分类号： B64C27/57 , B64C13/18 , B64C13/42 , B64C27/56 , B64C27/59 , B64C27/64 , B64C27/68 , G05D1/00 , G05D1/08 , G05D1/10
摘要： A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

122. 发明授权

US10329025B2 Invertible aircraft 有权
公开(公告)号：US10329025B2
公开(公告)日：2019-06-25
申请号：US15594342
申请日：2017-05-12
申请人： AeroVironment, Inc.
发明人： Matthew Todd Keennon , Karl Robert Klingebiel
IPC分类号： B64D31/06 , B64C27/12 , B64C27/59 , B64C39/02 , B64C11/20 , B64C11/32 , B64C27/04 , B64C29/00 , B64C27/08 , B64C27/473 , B64D31/00 , B64C27/06 , G05D1/00
摘要： A rotorcraft including a fuselage, one or more motor-driven rotors for vertical flight, and a control system. The motors drive the one or more rotors in either of two directions of rotation to provide for flight in either an upright or an inverted orientation. An orientation sensor is used to control the primary direction of thrust, and operational instructions and gathered information are automatically adapted based on the orientation of the fuselage with respect to gravity. The rotors are configured with blades that invert to conform to the direction of rotation.

123. 发明授权

US10279898B2 Rocket or ballistic launch rotary wing vehicle 有权
公开(公告)号：US10279898B2
公开(公告)日：2019-05-07
申请号：US14122045
申请日：2012-05-23
申请人： John Green , Philip Geoghegan , Michael Alexander Snook
发明人： John Green , Philip Geoghegan , Michael Alexander Snook
IPC分类号： B64C27/59 , B64C27/605 , B64C27/32 , B64C27/58 , B64C39/02 , B64C27/00 , B64C27/08 , B64C27/50 , B64D27/02 , B64D27/24 , B64F1/04
摘要： A rocket or ballistic launch rotary wing air vehicle may include a rocket or ballistic launch propulsion system for launching the vehicle, a rotary wing flight system for providing powered flight comprising dual counter rotating coaxial rotors, and a control system programmed to adjust the pitch of a rotor to anyh determined degree of pitch independently of a flap angle of the flap hinge during a transition of the dual counter rotating coaxial rotors from a stowed position to a deployed position.

124. 发明授权

US10099781B2 Emergency collective actuator and method for a helicopter 有权
公开(公告)号：US10099781B2
公开(公告)日：2018-10-16
申请号：US15723594
申请日：2017-10-03
申请人： Merlin Technology Inc.
发明人： John E. Mercer , Mark H. Marvin
IPC分类号： B64C27/59 , B64C27/57 , B64C27/04 , B64C27/00
摘要： A helicopter includes a rotor system having a rotor with an adjustable pitch that is controlled at least in part by a pilot using a collective control and which helicopter generates a Low RPM signal that is indicative of a threshold low rotational speed of the rotor. An actuator arrangement can move the collective control by exerting a force on the collective control such that the pilot is able to overcome the actuator force but which otherwise can move the collective control from a current operational position toward a minimum pitch position. A clutch can co-rotate with a motor to serve in transferring the actuation force to reduce the adjustable pitch and can slip relative to the actuator shaft assembly responsive to an application of a counterforce applied by the pilot to the collective control such that the counterforce overcomes the actuation force.

125. 发明申请

US20180194462A1 Teetering Rotor Hub System 审中-公开
公开(公告)号：US20180194462A1
公开(公告)日：2018-07-12
申请号：US15401233
申请日：2017-01-09
申请人： Bell Helicopter Textron Inc.
发明人： Drew Alan Sutton , Frank Brad Stamps
IPC分类号： B64C27/72 , B64C27/78 , B64C27/48 , B64C27/82 , B64C27/59
CPC分类号： B64C27/72 , B64C27/43 , B64C27/48 , B64C27/59 , B64C27/78 , B64C27/82 , B64C2027/8227
摘要： The present invention includes a rotor hub system, comprising: a teetering rotor hub disposed about a mast, the teetering rotor hub comprising: a first and a second yoke; each connected to a set of rotor blades, wherein the second set of rotor blades and the first set of rotor blades are disposed in a common plane, but the first and the second yoke do not come in contact.

126. 发明申请

US20180156285A1 MAGNETORHEOLOGICAL FLUID CLUTCH APPARATUS WITH CYLINDRICAL FLUID GAP 审中-公开
公开(公告)号：US20180156285A1
公开(公告)日：2018-06-07
申请号：US15785916
申请日：2016-04-21
申请人： EXONETIK INC.
发明人： Jean-Sebastien PLANTE , Marc DENNINGER , Guifre JULIO , Patrick CHOUINARD , Pascal LAROSE
IPC分类号： F16D37/02 , B64C27/59 , F16D29/00 , F16D37/00
摘要： A magnetorheological fluid clutch apparatus comprises a stator having at least an annular wall; a first rotor rotatably mounted to the stator, the first rotor having at least one first shear surface; a second rotor rotatably mounted to the stator for rotating about a common axis with the first rotor, the second rotor having at least one second shear surface opposite the at least one first shear surface, the shear surfaces separated by at least one annular space. A magnetorheological (MR) fluid is in an MR fluid chamber including the at least one annular space, the MR fluid configured to generate a variable amount of torque transmission between the rotors when subjected to a magnetic field. An inner magnetic core and an outer magnetic core with an annular cavity therebetween receive the annular wall of the stator, the inner magnetic core and the outer magnetic core connected to at least one of the rotors to rotate therewith so as to be rotatably mounted to the stator. Outer and inner fluid gaps are between the inner magnetic core and the annular wall, and between the outer magnetic core and the annular wall, the outer and inner fluid gaps filled with at least one fluid. At least one coil is supported by the annular wall and actuatable to deliver a magnetic field through the MR fluid, the magnetic field following a path comprising the annular wall, the outer fluid gap, the outer magnetic core, the at least one first shear surface and the at least one second shear surface,the inner magnetic core and the inner fluid gap, wherein one of the rotors is adapted to be coupled to a power input and the other of the rotors is adapted to be connected to an output whereby actuation of the at least one coil results in a variation of torque transmission between the rotors.

127. 发明申请

US20180093763A1 ROTORCRAFT AUTOPILOT AND METHODS 审中-公开
公开(公告)号：US20180093763A1
公开(公告)日：2018-04-05
申请号：US15687454
申请日：2017-08-26
申请人： Merlin Technology, Inc.
发明人： John E. Mercer , Nicolas Albion , Mark Bartel , Marc Feifel , Mark Marvin
IPC分类号： B64C27/57 , G05D1/00 , G05D1/08 , B64C27/68 , B64C27/64 , B64C27/59 , B64C13/42 , B64C13/18 , G05D1/10 , B64C27/56
CPC分类号： B64C27/57 , B64C13/18 , B64C13/42 , B64C27/56 , B64C27/59 , B64C27/64 , B64C27/68 , G05D1/0077 , G05D1/0816 , G05D1/0858 , G05D1/102 , Y02T50/44
摘要： A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

128. 发明申请

US20170050728A1 EMERGENCY COLLECTIVE ACTUATOR AND METHOD FOR A HELICOPTER 有权
标题翻译：紧急收集执行机构和直升机方法
公开(公告)号：US20170050728A1
公开(公告)日：2017-02-23
申请号：US15345273
申请日：2016-11-07
申请人： Merlin Technology Inc.
发明人： John E. Mercer , Mark H. Marvin
IPC分类号： B64C27/57 , B64C27/04 , B64C27/59 , B64C27/00
CPC分类号： B64C27/57 , B64C27/006 , B64C27/04 , B64C27/59
摘要： A helicopter includes a rotor system having a rotor with an adjustable pitch that is controlled at least in part by a pilot using a collective control and which helicopter generates a Low RPM signal that is indicative of a threshold low rotational speed of the rotor. An actuator arrangement can move the collective control by exerting a force on the collective control such that the pilot is able to overcome the actuator force but which otherwise can move the collective control from a current operational position toward a minimum pitch position. A clutch can co-rotate with a motor to serve in transferring the actuation force to reduce the adjustable pitch and can slip relative to the actuator shaft assembly responsive to an application of a counterforce applied by the pilot to the collective control such that the counterforce overcomes the actuation force.
摘要翻译：直升机包括具有可调间距的转子的转子系统，其至少部分地由飞行员使用集体控制来控制，并且哪个直升机产生指示转子的阈值低转速的低RPM信号。致动器装置可以通过在集体控制上施加力来移动集体控制，使得飞行员能够克服致动器力，但是否则可以将集体控制从当前操作位置向最小桨距位置移动。离合器可以与电动机共同旋转以用于传递致动力以减小可调节节距并且响应于由飞行员施加到集体控制的反作用力的应用而相对于致动器轴组件滑动，使得反作用力克服致动力。

129. 发明授权

US09511856B2 Emergency collective actuator and method for a helicopter 有权
标题翻译：紧急集体执行器和直升机方法
公开(公告)号：US09511856B2
公开(公告)日：2016-12-06
申请号：US14562479
申请日：2014-12-05
申请人： Merlin Technology Inc.
发明人： John E. Mercer , Mark H. Marvin
IPC分类号： B64C27/57 , B64C27/00 , B64C27/04 , B64C27/59
CPC分类号： B64C27/57 , B64C27/006 , B64C27/04 , B64C27/59
摘要： A helicopter includes a rotor system having a rotor with an adjustable pitch that is controlled at least in part by a pilot using a collective control and which helicopter generates a Low RPM signal that is indicative of a threshold low rotational speed of the rotor. An actuator arrangement can move the collective control by exerting a force on the collective control such that the pilot is able to overcome the actuator force but which otherwise can move the collective control from a current operational position toward a minimum pitch position. A clutch can co-rotate with a motor to serve in transferring the actuation force to reduce the adjustable pitch and can slip relative to the actuator shaft assembly responsive to an application of a counterforce applied by the pilot to the collective control such that the counterforce overcomes the actuation force.
摘要翻译：直升机包括具有可调间距的转子的转子系统，其至少部分地由飞行员使用集体控制来控制，并且哪个直升机产生指示转子的阈值低转速的低RPM信号。致动器装置可以通过在集体控制上施加力来移动集体控制，使得飞行员能够克服致动器力，但是否则可以将集体控制从当前操作位置向最小桨距位置移动。离合器可以与电动机共同旋转以用于传递致动力以减小可调节节距并且响应于由飞行员施加到集体控制的反作用力的应用而相对于致动器轴组件滑动，使得反作用力克服致动力。

130. 发明申请

US20160122013A1 SCISSORING FOLD ARRANGEMENT FOR DUAL PLANE FOUR BLADED ROTOR HUBS 有权
标题翻译：双平面四叶轮转向器的分解折叠装置
公开(公告)号：US20160122013A1
公开(公告)日：2016-05-05
申请号：US14533276
申请日：2014-11-05
申请人： BELL HELICOPTER TEXTRON INC.
发明人： Terry Thompson , Frank B. Stamps
IPC分类号： B64C27/59 , B64C27/10
CPC分类号： B64C27/10 , B64C27/50
摘要： A rotor blade system includes a first hub assembly having a first set of rotor blades and rotatably attached to a rotor mast, a second hub assembly having a second set of rotor blades and rotatably attached to the rotor mast, the second hub assembly being positioned at a space relative to the first hub assembly, a torque splitter device engaged with both the first hub assembly and the second hub assembly, and a locking device operably associated with the torque splitter device. The method includes rotating the first hub relative to the second hub via the torque splitter until the first set of rotor blades align with the second set of rotor blade about a common horizontal axis.
摘要翻译：转子叶片系统包括具有第一组转子叶片并可旋转地连接到转子柱的第一轮毂组件，第二轮毂组件，其具有第二组转子叶片并可旋转地附接到转子杆，第二轮毂组件定位在相对于第一轮毂组件的空间，与第一轮毂组件和第二轮毂组件两者接合的扭矩分配器装置，以及可操作地与转矩分配器装置相关联的锁定装置。该方法包括经由转矩分配器使第一毂相对于第二轮毂旋转，直到第一组转子叶片围绕公共水平轴线与第二组转子叶片对准。

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