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公开(公告)号：US20190161182A1
公开(公告)日：2019-05-30
申请号：US15962889
申请日：2018-04-25
摘要： A rotorcraft including a control element, a control sensor connected to the control element, where the control sensor is operable to generate trim data indicating a displacement of the control element in relation to a trim position of the control element, and a flight control computer (FCC) operable to monitor the trim data and determine an active detent state of the control element. The active detent state is one of an in-detent state, an out-of-detent state, and an in-transition state. The FCC is operable to buffer a transition of the active detent state from the in-detent state to the out-of-detent state using the in-transition state. The FCC provides a first flight management function when the active detent state is the in-detent state or the in-transition state, and provides a second flight management function when the active detent state is the out-of-detent state.
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公开(公告)号：US20190161181A1
公开(公告)日：2019-05-30
申请号：US15940184
申请日：2018-03-29
摘要： A rotorcraft having a plurality of wheels, each wheel configured to receive weight of the rotorcraft when in contact with a landing surface, a plurality of wheel sensors, each wheel sensor associated with a respective wheel and having circuitry configured to generate a wheel on ground (WOG) signal indicating that the respective wheel is in contact with the landing surface, and a flight control computer (FCC) in signal communication with the plurality of wheel sensors, the FCC operable to execute a first hold loop having a first integrator and providing first control augmentation of a rotorcraft flight system, the FCC further operable to freeze the first integrator according to a number of WOG signals received from the plurality of wheel sensors, the FCC further operable to generate a first control signal according to a first value provided by the first integrator while the first integrator is frozen.
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公开(公告)号：US20190056734A1
公开(公告)日：2019-02-21
申请号：US16032928
申请日：2018-07-11
发明人： Robert Earl Worsham, II , Luke Dafydd Gillett , Troy Sheldon Caudill , Bradley Paul Regnier , Joshua Robert O'Neil , Brandon Jeffrey Thomas
摘要： In an embodiment, a rotorcraft includes a rotor system including a plurality of blades; two or more engines operable to rotate the plurality of blades; a control assembly operable to receive commands from a pilot; a flight control computer (FCC) in signal communication with the two or more engines, the FCC being operable to generate engine data indicating whether the two or more engines are functional; and a flight management system (FMS) in signal communication with the control assembly and the FCC, the FMS being operable to receive a takeoff type and a plurality of takeoff parameters input into the FMS by the pilot; generate a guidance profile for a Category A (Cat-A) takeoff procedure based on the takeoff type and the plurality of takeoff parameters, the Cat-A takeoff procedure including one or more decision points for performing a takeoff procedure based on whether all engines are operable or one engine is inoperable; receive a command to engage in a takeoff procedure from the control assembly; in response to the command to engage in the takeoff procedure, provide guidance cues to a pilot of the rotorcraft; receive the engine data from the FCC during operation of the rotorcraft; and update the guidance profile based on the engine data during operation of the rotorcraft.
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公开(公告)号：US20200023941A1
公开(公告)日：2020-01-23
申请号：US16416508
申请日：2019-05-20
摘要： In an embodiment, a rotorcraft includes: a flight control computer configured to: receive a first sensor signal from a first aircraft sensor of the rotorcraft; receive a second sensor signal from a second aircraft sensor of the rotorcraft, the second aircraft sensor being different from the first aircraft sensor; combine the first sensor signal and the second sensor signal with a complementary filter to determine an estimated vertical speed of the rotorcraft; adjust flight control devices of the rotorcraft according to the estimated vertical speed of the rotorcraft, thereby changing flight characteristics of the rotorcraft; and reset the complementary filter in response to detecting the rotorcraft is grounded.
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公开(公告)号：US20200003908A1
公开(公告)日：2020-01-02
申请号：US16022455
申请日：2018-06-28
摘要： A rotorcraft includes a flight control computer (FCC), a GPS receiver configured to calculate a groundspeed based on a first carrier signal, and an attitude and heading reference system (AHRS) configured to determine an acceleration of the rotorcraft. The AHRS is operable to receive an indication of the groundspeed from the GPS receiver and to calculate a velocity of the rotorcraft based on the indication of the groundspeed and the acceleration. The FCC is operable to receive an indication of the velocity from the AHRS, to generate the flight control device control signal according to the indication of velocity, and to send a flight control device control signal to one or more flight control devices.
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公开(公告)号：US10386843B2
公开(公告)日：2019-08-20
申请号：US15477944
申请日：2017-04-03
IPC分类号： G05D1/02 , G05D1/00 , G01S19/40 , B64C13/50 , G01C21/16 , G01S19/49 , G05D1/10 , B64C27/06 , G01S19/15
摘要： In accordance with an embodiment, a method of operating a rotorcraft includes operating the rotorcraft in a position hold mode by determining whether GPS position data is usable, receiving a position of the rotorcraft from a GPS sensor, determining a position error based on received GPS position data and a held position when the GPS position data is usable, determining the position error based on a rotorcraft velocity when the GPS position data is not usable, and transmitting an actuator command based on the determined position error.
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公开(公告)号：US10261517B2
公开(公告)日：2019-04-16
申请号：US15484994
申请日：2017-04-11
发明人： Christopher Mike Bothwell , Sung Kyun Kim , Jillian Samantha Alfred , Robert Earl Worsham, II , Luke Dafydd Gillett , Morganne Cody Klein
摘要： A rotorcraft including a flight control computer (FCC) providing a vertical speed hold for the rotorcraft, a collective control, and a collective trim motor connected to the collective control. The collective trim motor moves the collective control according to a collective set command generated by the FCC according to a target vertical speed and when the FCC determines the collective control is in-detent. A collective position sensor is connected to the collective control. The collective position sensor generates, and sends to the FCC, a collective position signal indicating the position of the collective control. A flight control device controls a flight parameter of the rotorcraft in response to a flight control device control signal received from the FCC. The FCC generates the flight control device control signal according to the collective position signal, and sends the flight control device control signal to a flight control device.
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公开(公告)号：US20190056753A1
公开(公告)日：2019-02-21
申请号：US15961439
申请日：2018-04-24
摘要： An embodiment rotorcraft includes a rotor system including a plurality of blades; a control assembly operable to receive commands from a pilot; a flight control system (FCS), the flight control system operable to control flight of the rotorcraft by changing an operating condition of the rotor system; and a flight management system (FMS) in signal communication with the control assembly and the FCS. The FMS is operable to receive a target location and a plurality of approach parameters from the control assembly; generate a plurality waypoints between a current location of the rotorcraft and a missed approach point (MAP) based on the target location and the plurality of approach parameters; receive a command to engage in an approach maneuver from the control assembly; and in response to the command to engage in the approach maneuver, instruct the FCS to fly to the MAP.
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公开(公告)号：US20180244369A1
公开(公告)日：2018-08-30
申请号：US15443826
申请日：2017-02-27
CPC分类号： B64C13/503 , B64C13/18 , F02C9/44 , G05D1/0061 , G05D1/085 , G05D1/0858
摘要： A fly-by-wire system for a rotorcraft includes a computing device having control laws. The control laws are operable to engage a roll command or a yaw command in response to deflection of a beep switch of a pilot control assembly, wherein a roll angle for the roll command or a yaw rate for the yaw command is determined based on forward airspeed of the rotorcraft. The beep switch may be disposed on a collective control of the pilot control assembly. The control laws are further operable to disengage the roll command or the yaw command in response to the beep switch being returned from a deflected position to a neutral position. In representative aspects, the roll angle or the yaw rate may correspond to a standard rate turn (e.g., 3° per second).
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公开(公告)号：US20190161203A1
公开(公告)日：2019-05-30
申请号：US15978646
申请日：2018-05-14
发明人： Robert Earl Worsham, II , Morganne Cody Klein , Christopher M. Bothwell , Luke Dafydd Gillett , Jillian Samantha Alfred , Sung Kyun Kim , Stephanie Baynham , Troy Caudill
摘要： In an embodiment, a method of indicating flight modes of a rotorcraft includes: detecting a change in flight mode of the rotorcraft from a previous flight mode to an active flight mode, the active flight mode and the previous flight mode each being from one of a first subset or a second subset of a plurality of flight modes; determining whether the active flight mode and the previous flight mode are from different subsets of the plurality of flight modes; and updating one or more flight mode indicators on an instrument panel of the rotorcraft in response to the active flight mode and the previous flight mode being from different subsets of the plurality of flight modes.
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