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公开(公告)号：US11255923B2
公开(公告)日：2022-02-22
申请号：US16533139
申请日：2019-08-06
发明人： Gary Froman
摘要： An electrical bonding test device, including a test system circuit configured to generate a current pulse for ground bonding testing of subject units, a first test system connector configured to provide an electrical connection between a first unit connector shell of a first unit of the subject units and the test system circuit and to pass the current pulse to the first unit connector shell during the ground bonding testing, and a second test system connector configured to provide an electrical connection between a second unit connector shell of a second unit of the subject units and a first node of the test system circuit. The test system circuit is further configured to provide an indication indicating whether a bonding path through the subject units is a conductive path having a resistance below a resistance threshold.
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公开(公告)号：US20220024573A1
公开(公告)日：2022-01-27
申请号：US17333745
申请日：2021-05-28
摘要： A method and system to control a rotor system includes automatically changing a rotor speed of the rotor system of the tiltrotor aircraft while moving the rotor system from a first position and a first rotor speed to a second position and a second rotor speed over a time period in accordance with an acceleration-rate profile that varies over the time period using a controller communicably coupled to the rotor system of the tiltrotor aircraft.
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公开(公告)号：US20210387717A1
公开(公告)日：2021-12-16
申请号：US17462546
申请日：2021-08-31
摘要： A rotor assembly has a rotor hub having a unitary structure. The rotor assembly further includes a unitary crosshead having a first upper tab and a first lower tab located vertically below the first upper tab. The first upper tab and the first lower tab define a slot therebetween to accept a first pin of the first rotor blade. A second upper tab and a second lower tab located vertically below the second upper tab define a slot therebetween to accept a second pin of the second rotor blade. A first recess is provided between the first lower tab and the second lower tab so that the crosshead comprises no material directly between at least a portion of the first lower tab and the second lower tab along at least one straight path.
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公开(公告)号：US11198504B2
公开(公告)日：2021-12-14
申请号：US16400002
申请日：2019-04-30
发明人： Guy Bernard
摘要： An energy absorbing landing system for an aircraft having a fuselage includes landing legs rotatably coupled to the fuselage configured to outwardly rotate when receiving a landing load having a magnitude. The energy absorbing landing system also includes an energy absorption unit coupled to the fuselage and cables coupling the energy absorption unit to the landing legs. The energy absorption unit is configured to selectively apply a resistance to the outward rotation of the landing legs via the cables based on the magnitude of the landing load, thereby absorbing the landing load when the aircraft lands.
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公开(公告)号：US20210362852A1
公开(公告)日：2021-11-25
申请号：US16879129
申请日：2020-05-20
摘要： A propulsion assembly for an aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The propulsion assembly includes a housing coupled to the fuselage of the aircraft. A coaxial rotor system includes a first rotor assembly and a second rotor assembly that are rotatable about a common axis of rotation. The first rotor assembly counter-rotates relative to the second rotor assembly. A motor assembly is operably associated with the coaxial rotor system. The motor assembly provides torque and rotational energy to the first rotor assembly and the second rotor assembly. A gimbal assembly couples the coaxial rotor system to the housing such that the coaxial rotor system is tiltable relative to the fuselage to generate a thrust vector.
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公开(公告)号：US20210362851A1
公开(公告)日：2021-11-25
申请号：US16879070
申请日：2020-05-20
发明人： John Richard McCullough , Andrew Thomas Carter , Sung Kyun Kim , Matthew John Hill , Lynn Francis Eschete
摘要： An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft has an airframe including first and second wings with a fuselage extending therebetween. A propulsion assembly is coupled to the fuselage and includes a counter-rotating coaxial rotor system that is tiltable relative to the fuselage to generate a thrust vector. A flight control system is configured to direct the thrust vector. In the VTOL orientation, the first wing is forward of the fuselage, the second wing is aft of the fuselage and the coaxial rotor system is configured to provide thrust in line with a yaw axis of the aircraft. In the biplane orientation, the first wing is below the fuselage, the second wing is above the fuselage and the coaxial rotor system is configured to provide thrust in line with a roll axis of the aircraft.
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公开(公告)号：US11174018B2
公开(公告)日：2021-11-16
申请号：US16886000
申请日：2020-05-28
摘要： The present invention includes an a plurality of first variable speed motors mounted on a tail boom of the helicopter; one or more fixed pitch blades attached to each of the plurality of first variable speed motors; and wherein a speed of one or more of the plurality of first variable speed motors is varied to provide an anti-torque thrust.
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公开(公告)号：US11174013B2
公开(公告)日：2021-11-16
申请号：US17037476
申请日：2020-09-29
IPC分类号： B64C27/12 , B64D27/10 , B64D27/24 , B64D35/02 , F16D41/08 , F16D48/02 , F16D28/00 , B64C27/06 , F16D25/061
摘要： A failsafe multimode clutch assembly is positioned in a powertrain of a rotorcraft. The clutch assembly includes a freewheeling unit having input and output races. The freewheeling unit has a driving mode in which torque applied to the input race is transferred to the output race and an overrunning mode in which torque applied to the output race is not transferred to the input race. A bypass assembly has an engaged position that couples the input and output races of the freewheeling unit. An actuator assembly must be energized to shift the bypass assembly from the engaged position to a disengaged position. In the disengaged position, the overrunning mode of the freewheeling unit is enabled such that the clutch assembly is configured for unidirectional torque transfer. In the engaged position, the overrunning mode of the freewheeling unit is disabled such that the clutch assembly is configured for bidirectional torque transfer.
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公开(公告)号：US20210343178A1
公开(公告)日：2021-11-04
申请号：US17354999
申请日：2021-06-22
摘要： Systems and methods include providing a virtual reality (“VR”) flight emulator system that simulates control, operation, and response of a vehicle. The flight emulator includes a control interface and a head-mounted display worn by a user. Motion, orientation, and/or forces experienced by the simulated vehicle are imparted to a user through a motion-control seat. Multiple flight emulators can be connected to a communication network, and a master flight emulator may teleport into a slave flight emulator in order to observe, overtake, override, and/or assume control of the slave flight emulator. Inputs made via the control interface of the master flight emulator or during playback of a pre-recorded training exercise or flight mission are translated into the control interface, head-mounted display, and motion-control seat of the slave flight emulator to provide real-time feedback to the user of the slave flight emulator.
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公开(公告)号：US20210341947A1
公开(公告)日：2021-11-04
申请号：US17373682
申请日：2021-07-12
发明人： Kip Gregory Campbell
摘要： According to one implementation of the present disclosure, a method for determining angle-of-attack for an unpowered vehicle is disclosed. The method includes: determining a monotonic portion of a look-up curve of an angle-of-attack operating plot; during flight, determining, by an accelerometer disposed on the unpowered vehicle, first and second accelerometer outputs, where the first and second accelerometer outputs correspond to first and second body-fixed load factor measurements, respectively; determining an operating point on the monotonic portion by applying a quotient of the first and second accelerometer outputs to the angle-of-attack operating plot; and determining an angle-of-attack parameter corresponding to the determined operating point.
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