Class / Patent application number | Description | Number of patent applications / Date published |
244221000 | Control system | 72 |
20080197239 | Method and Device for Driving an Aircraft During the Ground Run Thereof - The inventive method consists in forming a difference (D | 08-21-2008 |
20080258014 | AIRCRAFT KINETIC LANDING ENERGY CONVERSION SYSTEM - A kinetic energy system which transfers the kinetic landing into recoverable electric energy for an aircraft. The system incorporates at least one wheel supporting the aircraft for landing and takeoff coupled with a dynamic functioning motor/generator mounted to and operated by rotation of the wheel to create electrical energy from kinetic energy. An induction shoe structurally connected to the aircraft and electrically connected to the motor/generator, which shoe draws the converted energy from the generator which supplies the load created by the inductively coupled induction shoe to the an ancillary load provided by the resistive heat sink on by the capacitor storage bank. This provides the generator circuit for conversion of the rotational energy of the wheel to electrical energy and creates braking drag. In exemplary embodiments, the system employs an energy storage system acting as the load to store electrical potential energy created by the generator. Additionally, the generator is employable as a motor, receiving energy from the storage system for traction power to the associated aircraft wheel. An induction grid or a surface mounted conductive layer mounted into or onto a runway is employed for transferring energy to and from the motor/generator. | 10-23-2008 |
20080272243 | Control apparatus for an aircraft - The present invention relates to a control apparatus for an aircraft comprising a multiaxially tiltable joystick for the actuation of at least two control transducers for the pitch and roll control of the aircraft, with the control transducers being associated with two control shafts which are connected to the joystick via a Cardan-like joint with two pivot axes aligned transversely to one another, with a pitch movement of the joystick being able to be converted via said joint into a rotation of the one control shaft and a roll movement of the joystick being able to be converted into a rotation of the other control shaft. In accordance with the invention, the control apparatus is characterized in that the two control shafts are rotatably journaled in a fixed manner at a common rack and in that the joint in each case has a freewheel with respect to the control shafts for tilt movements of the joystick in a plane parallel to the respective control shaft. | 11-06-2008 |
20090146018 | Control device - The invention relates to a control device, in particular for an aircraft, having a multiaxially tiltable joystick for the actuation of signal transducers, in particular for the pitch control and roll control of an aircraft, as well as having a cardan-like joint by means of which the joystick is tiltable about different pivot axes, said joint furthermore having at least one freewheel for a tilt movement of the joystick about one of the pivot axes. In accordance with the invention, the freewheel is formed by a lever mechanism or by an elastic component. | 06-11-2009 |
20090189024 | Device for Remotely Controlling Aircraft Control Surfaces - A device for remotely controlling the control surfaces of an aircraft, the device comprising: an actuator member pivotable about an axis and entraining a rotary shaft; a stationary finger parallel to the shaft and supported at a radial distance from the shaft; a moving finger secured to the shaft and supported at a radial distance therefrom, both fingers being parallel to the shaft; a first slab supported at a radial distance from the shaft beside the two fingers on one side thereof and suitable for turning about the axis of the shaft; a second slab supported at a radial distance from the shaft beside the two fingers on their side opposite from the first slab, and suitable for turning about the axis of the shaft; a third slab supported at a radial distance from the shaft beside the second slab at an angular distance therefrom and suitable for turning about the axis of the shaft; a first spring between the first and second slabs; and a second spring between the first and third slabs. | 07-30-2009 |
20090302170 | ROTATIONAL AIRCRAFT THROTTLE INTERFACE - An aircraft control input apparatus is configured to accept and provide to the aircraft control inputs from a user regarding the magnitude and direction of the aircraft's thrust vector. The present invention enables a user to continually provide control inputs to an aircraft in which both the magnitude and the direction of thrust vary. A rotational throttle interface is configured to alter its orientation within the aircraft based on the directional component of the aircraft's thrust vector. The rotational throttle interface enables the user to provide continual control inputs to command both the directional component of the thrust as well as the magnitude component. Accordingly the user can provide inputs regarding direction and magnitude throughout the operating envelope of the aircraft's thrust vector while maintaining continuous physical contact with the throttle. | 12-10-2009 |
20100327122 | Air-vehicle augmented kinesthetic control system - An augmented kinesthetic control system for use with a lift platform, the lift platform comprising first and second longitudinally-spaced thrust generating means, is provided. The first and second lift planes defined by the first and second thrust generating means are positioned below the lift platform center of gravity. The kinesthetic control means are coupled to means for aerodynamically altering the air flow from the first and second thrust generating means such that the intuitive and balancing movements of the pilot are magnified to allow kinesthetic control of a vehicle of greater size and utility. | 12-30-2010 |
20120032031 | CONTROL SYSTEM - The invention relates to a control system and to a method of operating such a control system, particularly to a control system for pilot command inputs for a helicopter, with a mechanical input signal ( | 02-09-2012 |
20120032032 | Air-Vehicle Integrated Kinesthetic Control System - A lift platform with a kinesthetic control system that is coupled to means for altering air flow through the first and second longitudinally-spaced ducts comprising the lift platform is provided. The control system includes a control handle bar with left and right hand grips, and first and second control roll bars located on either side of the lift platform's central cowling. Forward/rearward movement of the control handle bar from a neutral position generates nose-down/nose-up pitching moments, respectively; counterclockwise/clockwise movement of the control handle bar from the neutral position generates counterclockwise rotation/clockwise rotation of the lift platform about a lift platform vertical centerline; and left movement/right movement of the control roll bars generates left roll/right roll moments about the lift platform roll axis. | 02-09-2012 |
20130256462 | Unknown - A piloting device ( | 10-03-2013 |
20140001313 | MECHANICAL CONTROL MIXER AND METHOD THEREFOR | 01-02-2014 |
20150076288 | METHOD AND DEVICE FOR AIDING THE CONTROL OF AN AIRCRAFT DURING A PARABOLIC FLIGHT IN ORDER TO GENERATE WEIGHTLESSNESS IN THE AIRCRAFT - Method and device for aiding the control of an aircraft during a parabolic flight in order to generate weightlessness in the aircraft. | 03-19-2015 |
244223000 | With feel | 21 |
20090266939 | ACTIVE PILOT INCEPTOR WITH SELF WARM-UP - An active pilot inceptor system includes a pilot inceptor, a multi-phase motor, and a motor control. The pilot inceptor is configured to receive user input and is operable, in response to the user input, to move to a control position. The multi-phase motor is coupled to the pilot inceptor to selectively supply haptic feedback thereto. The motor control is operable to selectively energize the multi-phase motor in a manner that causes the multi-phase motor to generate torque and supply the haptic feedback to the inceptor, and to selectively energize the multi-phase motor in a manner that the multi-phase motor does not generate torque. | 10-29-2009 |
20090266940 | PRECISION ADJUST SPLIT DETENT FOR A VEHICLE - A method and apparatus for a split detent tactile cueing control system comprising an inceptor, a position sensor, vehicle sensors, and a flight control computer. The inceptor can be moved into different positions measured by a position sensor. The vehicle sensors generate signals in response to detecting parameters about a vehicle during a flight. The flight control computer is coupled to the inceptor and the vehicle sensors. The flight control computer is capable of generating actuation signals used to generate tactile cues to generate a flight path hold detent and an altitude hold detent within the plurality of positions using a force feel profile and the parameters. An extension of a latch force from the flight path hold detent to the altitude hold detent is present during changes in vehicle direction. Series actuator compensation allows increased split detent separation with insignificant command overshoot. | 10-29-2009 |
20090302171 | RATE LIMITED ACTIVE PILOT INCEPTOR SYSTEM AND METHOD - A variable rate limit is implemented in an active inceptor haptic feedback control system. The rate limit is modulated based on a rate error between an aircraft rate command supplied from the active inceptor, and actual aircraft rate. As the rate error increases, the rate limit is reduced, which limits inceptor movement and provides haptic feedback to a user when the rate error is exceeded. | 12-10-2009 |
20100025539 | ACTIVE CONTROL STICK ASSEMBLY INCLUDING TRACTION DRIVE - An active control stick assembly is provided. In one embodiment, the active control stick assembly includes a housing assembly, a control stick coupled to the assembly housing for rotation about at least a first rotational axis, a first artificial force feel (AFF) motor disposed in the housing assembly, and a first traction drive mechanically coupling the first AFF motor to the control stick. A controller is operatively coupled to the first AFF motor. The controller is configured to selectively activate the first AFF motor to supply a torque through the first traction drive and acting on the control stick about the first rotational axis. | 02-04-2010 |
20110168851 | AUTOMATIC TRIM SYSTEM FOR FLY-BY-WIRE AIRCRAFT WITH UNIQUE TRIM CONTROLLERS - A flight control system includes a controller which defines a controller displacement and a control surface which defines a control surface authority. A module operable to provide a displacement feel to the controller in response to a remaining portion of the controller displacement being greater than a remaining portion of the control surface authority and the module operable to re-reference a center of the controller displacement to equate the remaining portion of the controller displacement with the remaining portion of the control surface authority in response to the remaining portion of the controller displacement being less than the remaining portion of the control surface authority. | 07-14-2011 |
20110266396 | CONTACT DETECTION - The invention relates to a method for detecting a contact state between at least one driver/operator of a vehicle and a control input device designed to control the vehicle were a frequency spectrum is calculated from sensors detected movement signals based on which the contact state between the control input device and the driver/operator is determined. | 11-03-2011 |
20110284696 | Control column system - The present invention relates to an active control column system for controlling an aircraft, comprising a control member architecture and a control architecture, wherein the control member architecture has at least one mechanically movable control column, at least one actuator for controlling the control column and at least one detection means for detecting at least one state variable of the control column, and the control architecture includes at least one movement regulator for controlling at least one actuator, a feeling generation means for generating at least one desired movement parameter, wherein the feeling generation means is indirectly/directly connected to at least one movement regulator and the generated desired parameter can be supplied to the movement regulator, and wherein at least one detection means is indirectly or directly connected to the feeling generation means for the supply of at least one state variable. | 11-24-2011 |
20120025029 | Position Control System for Cross Coupled Operation of Fly-By-Wire Control Columns - A aircraft control system is provided. that provides tactile feedback between control columns of the aircraft relating to discrepancies in the control inputs to the sticks of the respective control columns. In one implementation, the sticks each have an associated feedback assembly that is adjustable relative to mechanical ground to adjust the feedback profile applied to the corresponding stick. The position of each feedback assembly is adjusted based on a relative displacement between the other feedback assembly and its corresponding stick to provide active feedback relating to the control of the other control column. | 02-02-2012 |
20120025030 | Indirect Drive Active Control Column - An indirect drive active control column for an aircraft control system is provided. The indirect drive active control column provides both active and passive feedback to the control stick. The passive feedback relates to adjustments of the control stick relative to a feedback neutral position. The active feedback actively adjusts the position of the feedback neutral position to adjust a feedback profile of the passive feedback. | 02-02-2012 |
20120025031 | Active Control Column With Manually Activated Reversion to Passive Control Column - An active control column transitionable to a fully passive state for an aircraft and methods of use are provided. The control column includes a passive feedback arrangement, a stick and a ground lock mechanism is provided. The passive feedback arrangement is moveable relative to a mechanical ground to adjust a feedback profile provided to the stick. The stick is movable relative to the mechanical ground and the passive feedback arrangement. The ground lock mechanism has a locked state in which the passive feedback arrangement is maintained in a fixed position relative to the mechanical ground. This places the control column in a fully passive state. The ground lock mechanism also has a normal state in which the passive feedback arrangement is permitted to move relative to the mechanical ground such that active feedback can be provided to the stick. | 02-02-2012 |
20120160967 | FAIL-PASSIVE VARIABLE GRADIENT CONTROL STICK DRIVE SYSTEM - A control system for an aircraft including a passive feedback arrangement, a stick and a positioning arrangement is provided that provides for user adjustability of the resistance applied to the stick, such as in a fly-by-wire system. The passive feedback arrangement is movable relative to a mechanical ground. The stick is moveable relative to the mechanical ground and the passive feedback arrangement. The passive feedback arrangement acts on the stick to resist movement of the stick relative to the passive feedback arrangement. This resistance provides passive feedback to the pilot for the fly-by-wire system. The positioning arrangement is coupled to the passive feedback arrangement for adjusting the position of the passive feedback arrangement relative to the mechanical ground in response to movement of the stick relative to the mechanical ground. | 06-28-2012 |
20120205494 | TACTILE CUEING APPARATUS - A tactile cueing apparatus for incorporation in an aircraft flight control system comprising a flight control surface, and a pilots inceptor ( | 08-16-2012 |
20130099064 | Methods And Systems For Providing Constant-Feel, Multi-Axis Tactile Cues - A system for adjusting tactile cues includes a controller having an axis and a cross-axis; an axis tactile cue generated in response to the position of the controller along the axis; a position scaling unit scaling a cross-axis controller position to generate a scaled cross-axis controller position; a force scaling unit scaling a cross-axis controller force to generate a scaled cross-axis controller force; a combiner combining the scaled cross-axis controller position and the scaled cross-axis controller force to generate an adjustment factor; and an adjuster adjusting the axis tactile cue in response to the adjustment factor to generate an adjusted axis tactile cue. | 04-25-2013 |
20130105634 | COMPACT TWO AXIS GIMBAL FOR CONTROL STICK | 05-02-2013 |
20130299644 | Throttle Interface for Variable Thrust Vector Aircraft - An aircraft control input apparatus is configured to accept and provide to the aircraft control inputs from a user regarding the magnitude and direction of the aircraft's thrust vector. The present invention enables a user to continually provide control inputs to an aircraft in which both the magnitude and the direction of thrust vary. A rotational throttle interface is configured to alter its orientation within the aircraft based on the directional component of the aircraft's thrust vector. The rotational throttle interface enables the user to provide continual control inputs to command both the directional component of the thrust as well as the magnitude component. Accordingly the user can provide inputs regarding direction and magnitude throughout the operating envelope of the aircraft's thrust vector while maintaining continuous physical contact with the throttle. | 11-14-2013 |
20140091181 | CONTROLLER - A controller includes a first body portion, adapted to be grasped by a person's middle finger, ring finger, and pinky finger, a second body portion adapted to be grasped by a person's index finger, and a third body portion that defines a first surface adapted to receive a person's thumb. A finger switch is positioned on a front surface of the second body portion. The finger switch is positioned such that it may be actuated by the person's index finger. The second body portion is disposed between the first body portion and the third body portion. The second body portion defines an offset with respect to the first body portion. The third body portion defines a second surface above the finger switch, which may receive the person's index finger. | 04-03-2014 |
20140263848 | REVERSIBLE FLIGHT CONTROL SYSTEMS - An improved flight control system is described, providing for increased or reduced pilot input forces necessary to cause desired control surface deflections. | 09-18-2014 |
20150108281 | Method for monitoring the operation of an aircraft piloting device and an aircraft piloting device thus monitored - A method for monitoring an aircraft piloting device including at least one piloting member ( | 04-23-2015 |
20150314857 | CREW SEAT INTEGRAL INCEPTOR SYSTEM FOR AIRCRAFT - A system and method for controlling a trajectory of a vehicle includes a crew seat with first and second inceptors mounted to a portion of the crew seat; a processor with memory having instructions stored thereon that cause the system to: receive signals indicative of a trajectory for the vehicle; receive signals indicative of a deviation in a trajectory of the vehicle; and transmit signals for controlling a flight path of the vehicle. A second inceptor is configured for selecting one or more menus on a user display and being configured to interact with a fly-by-wire control system for transmitting signals indicative of movement of flight surface of the vehicle. The crew seat is configured to be located on the vehicle, in a control station remotely located from the vehicle, or in a second vehicle remotely located from the vehicle. | 11-05-2015 |
20150344128 | DEVICE FOR WARNING A ROTORCRAFT PILOT BY MEANS OF TACTILE SIGNALS AND MAKING USE OF A TRIM ACTUATOR CONNECTED TO A FLIGHT CONTROL MEMBER - A method of using a tactile signal warning device forming part of a human-operated flight control member of a rotorcraft. The warning device makes use of an anchorable motorized trim actuator for generating a resisting force against movement of the flight control member. The warning device comprises a warning unit that, as a function of a power margin (MP | 12-03-2015 |
20160122001 | ELECTRONIC FLIGHT CONTROLS WITH PARALLEL PROCESSED TORQUE & POSITIONING FOR PILOT OR ASTRONAUT TOUCH FEEDBACK - Cockpit controls designed for a at least two pilots and automation. Duplications of controls: sticks and control columns move along the same position path in unison with other sets of controls electronically based on a plurality of parallel processed parameters allowing two pilots to assist each other effectively with the ability of one pilot to override the other for effective monitoring and control in normal and emergency situations. | 05-05-2016 |
244224000 | With locking means | 7 |
20080203234 | Trim Actuator Actuating System for a Hydraulically Actuatable Trimmable Horizontal Stabilizer Actuator - The present invention relates to a trim actuator actuating system having two separate hydraulic power supply systems, through which it is possible for the first time to use a hydraulic linear actuator as a trimmable horizontal stabilizer actuator in an aircraft. The at least one hydraulic linear actuator is coupled to the first power supply system in such a way that it applies hydraulic power to the linear actuator during normal operation. In order to ensure the application of pressure to the hydraulic linear actuator in case of breakdown, in such a case, the pressure application to the hydraulic linear actuator is maintained with the aid of the second hydraulic power supply system. | 08-28-2008 |
20080258015 | DEVICE AND METHOD FOR TWISTING AND CLAMPING MOVEABLE FLAPS - The invention relates to a device for twisting and clamping a second flap moveable about a rotational axis with respect to a first flap. A device includes a twisting device arranged on the first flap including a drivable shaft rotatable about the rotational axis and a catch connected to the second flap. The device also includes a clamping device including a clamping sleeve arranged along the rotational axis. | 10-23-2008 |
20090194641 | Exterior Mechanical Interlock for a Linear Actuator - A locking mechanism, which permits fixation to a piston rod of a linear actuator relatively to a cylinder of the actuator, as well as a linear actuator equipped with such a locking mechanism as well as to an aircraft with at least one linear activator that is equipped with the locking mechanism. The locking mechanism includes a plurality of first positive locking elements which are arranged lengthwise with the outside circumference of the cylinder and in certain distances to one another and at least one second positive locking element, which is moved together with the piston rod upon activation of the linear actuator and thus passes a segment of the cylinder. The at least one second positive locking element is positively engageable with one of the plurality of first locking elements at discrete positions of the cylinder lengthwise, by which the piston rod is fixed relatively to the cylinder. | 08-06-2009 |
20100019097 | Aircraft Control Surface Gust Lock - Embodiments of the present disclosure generally provide a device for securing the external control surfaces of an aircraft. A gust lock is described for securing the control surfaces of an aircraft that includes an elongated top plate having a rotably associated strap lock, an elongated bottom plate having a rotably mounted capture piece, and a strap running from the capture piece through the strap lock to a tail section. | 01-28-2010 |
20100038493 | High gain asymmetry brake - An asymmetry brake includes a housing, a shaft, a pilot brake, a primary brake, and a ball ramp assembly. The shaft of the asymmetry brake is rotatable relative to the housing about an axis of rotation. The primary brake is movably connected with the shaft. The pilot brake is configured to selectively engage the housing to generate a triggering torque. The triggering torque is transferred through the ball ramp assembly to the primary brake, which in response engages the housing to generate a braking torque on the shaft. The disposition of the ball ramp assembly between the pilot brake and the primary brake allows the ball ramp assembly to return to an operative non-separated condition when the pilot brake is disengaged from the housing. The return of the ball ramp assembly to the operative non-separated condition allows the primary brake to disengage from the housing which releases the shaft to rotate. | 02-18-2010 |
20140061388 | HELICOPTER CONTROL STICK SUPPORT ASSEMBLY - A support assembly for a helicopter control stick is provided. The support assembly includes a supporting structure and an instrument panel fixed to each other; and a connecting assembly for connecting the stick to the supporting structure. The connecting assembly includes an arm elongated in a longitudinal direction and having one end supporting the stick; a guide for connecting the arm in longitudinally sliding manner to the supporting structure, to move the end to and from the supporting structure; and a rotary assembly for connecting the arm to the supporting structure in rotary manner about a horizontal axis, to adjust the height of the end. The rotary assembly has a first releasable retainer, wherein the first releasable retainer operates to lock rotation of the arm with respect to the supporting structure in a desired angular position. | 03-06-2014 |
20140061389 | AIRCRAFT THROTTLE CONTROL DEVICE INCLUDING A CAM COUPLING - An aeroengine control device including a mount and having pivotally mounted thereon a code wheel together with a main lever and a secondary lever, both for turning the code wheel. Each lever is movable between a rest position and a maximum actuation position. The secondary lever is mounted to pivot on the main lever. Cam paths are mounted on the code wheel and on the mount in such a manner that the main lever can move the code wheel when the main lever is moved while the secondary lever is in the rest position. The secondary lever can move the code wheel when the secondary lever is moved while the main lever is in the rest position, with movement of either lever being prevented when the other lever is clearly away from its rest position. | 03-06-2014 |
244226000 | Fluid | 13 |
20090039205 | AIRCRAFT FLIGHT CONTROL USER INTERFACE LINKAGE SYSTEM - A user interface linkage system includes first and second user interfaces that are linked by a single hydraulic circuit. The system is configured to provide compensation for relatively slow changes in hydraulic fluid pressure due, for example, to temperature variations. The system is also configured to allow the user interfaces to be selectively unlinked from each other. | 02-12-2009 |
20090159756 | AIRCRAFT FLIGHT CONTROL USER INTERFACE FLUID LINKAGE SYSTEM - A user interface fluid linkage system includes first and second user interfaces that are linked by a single, constant volume fluid line. The system includes identically configured, but oppositely mounted hydraulic fluid chambers to link motion between the first and second user interfaces. | 06-25-2009 |
20090242705 | HYDRAULIC SYSTEM PROTECTED FROM EXTERNAL IMPACTS - A hydraulic system includes at least one hydraulic circuit with at least one pump, one or more consumer equipment units, at least one HP discharge line comprising at least one bypass, the bypass being located between the pump and the units, at least one return line including at least one bypass, the bypass being located between a tank and the units. The hydraulic system further includes at least one closure element on the at least one HP line between the bypass and the units, and at least one nonreturn valve on the at least one return line between the bypass and the units. The closure element is placed automatically in the closed position when a break of the HP line is detected downstream of the closure element of the HP line. | 10-01-2009 |
20110139938 | AIRCRAFT REACTION LINK - An aircraft reaction link includes a pair of linear portions, a coupling portion that couples ends of the pair of linear portions on the same side to each other, a fulcrum shaft attachment portion, and a cylinder attachment portion. A metal frame that is made of a metallic material and that is provided so as to extend across the coupling portion and the pair of linear portions and a composite frame that is made of fiber-reinforced plastic and that is provided so as to extend at least in the pair of linear portions are bonded together, and thereby, the pair of linear portions and the coupling portion are formed. The metal frame is provided so as to extend from the fulcrum shaft attachment portion to the cylinder attachment portion. | 06-16-2011 |
20140110532 | Direct-Drive Control of Aircraft Stability Augmentation - According to one embodiment, a stability augmentation system includes a master linkage, a stability augmentation motor, and three linkages. A first linkage is coupled to the master linkage and operable to receive movements representative of pilot commands from a pilot command system. A second linkage is coupled between the stability augmentation motor and the master linkage and operable to receive movements representative of augmentation commands from the stability augmentation motor. A third linkage is coupled to the master linkage and operable to transmit movements representative of blade position commands to a blade control system in response to the movements representative of pilot commands and the movements representative of augmentation commands. | 04-24-2014 |
244227000 | With electric control | 8 |
20090308983 | AIRCRAFT CONTROL SURFACE DRIVE SYSTEM AND ASSOCIATED METHODS - A control surface drive system having a plurality of actuator assemblies are coupled to first and second supply lines and to a return line. The first and second supply lines are connected to a source of hydraulic fluid. At least one of the actuator assemblies has a hydraulic actuator movably connectable to an aircraft control surface. A flow control assembly is connected to the return line and to at least one of the first and second supply lines. A bypass line is in fluid communication with the first and second supply lines and positioned to recycle the hydraulic fluid from one of the first and second supply lines back into the other one of the first and second supply lines when the hydraulic actuator moves toward the first position. A computer controller operatively interconnects the plurality of actuator assemblies and the flow control assembly. It is emphasized that this abstract is provided to comply with the rules requiring an abstract. It is submitted with the understanding that it will not be used to interpret or limit the scope or meaning of the claims (37 C.F.R. §1.72(b)). | 12-17-2009 |
20100170999 | MORE ELECTRIC FLIGHT CONTROL SYSTEM ONBOARD AN AIRCRAFT - The invention relates to a more electric flight control system onboard an aircraft provided with flight control surfaces and means of controlling these surfaces, that comprises at least one local electro-hydraulic generator (HPP | 07-08-2010 |
20110186691 | AIRCRAFT - An aircraft having at least one in-flight attitude control system, in turn having at least one actuator; and a hydraulic circuit connected to the actuator and having at least one pump designed to deliver a first flow when the pressure of the hydraulic circuit is above a presettable threshold value. The pump is designed to deliver a second flow greater than the first flow, and the aircraft has a sensor for detecting a quantity associated with the pressure of the hydraulic circuit; and a programmable central control unit, which controls the pump to deliver the second flow when the quantity detected by the sensor corresponds to a pressure of the hydraulic circuit below the threshold value. | 08-04-2011 |
20130168501 | PRIMARY FLIGHT CONTROLS - Primary flight controls ( | 07-04-2013 |
20150083868 | Mechanical and Magnetic Control System for Magnetorheological Actuators - In some embodiments, a method of provided boosted actuation to an aircraft flight control device includes receiving an input from a pilot input device via a mechanical input member, providing mechanical energy to a driving member of a controlled-slippage actuator, and varying the strength of a magnetic field applied to a magnetorheological (MR) fluid disposed between the driving member and a driven member of the controlled-slippage actuator based on the relative positions of the mechanical input member and a mechanical output member that is in mechanical communication with the driven member and the aircraft flight control device. | 03-26-2015 |
20160052620 | SYMMETRICALLY LOADED DUAL HYDRAULIC FLY-BY-WIRE ACTUATOR - An actuation system for resolving the effects of force-fight between multiple stages within an actuator coupled to an aircraft flight control member includes a yoke configured for connection to the flight control member, a first actuator operatively coupled to the yoke, and a second actuator and a third actuator operatively coupled to the yoke, the second and third actuators symmetrically arranged on opposite sides of the first actuator. A first control member is operatively coupled to the first actuator, and a second control member is operatively coupled to the second actuator and the third actuator. The second control member is configured to operate independent of the first control member to effect motion of the flight control member. | 02-25-2016 |
20180022443 | ELECTRIC ACTUATOR DRIVING AND CONTROLLING DEVICE, AND AIRCRAFT | 01-25-2018 |
20180022444 | ELECTRIC ACTUATOR DRIVING AND CONTROLLING DEVICE, AND AIRCRAFT | 01-25-2018 |
244228000 | Electric | 9 |
20090014595 | ELECTRICAL CONTROL SYSTEM FOR AN AIRCRAFT STEERING VANE - The invention concerns a system ( | 01-15-2009 |
20100072322 | FULL AUTHORITY FLY-BY-WIRE PEDAL SYSTEM - A pedal system particularly tailored to a Fly-By-Wire (FBW) flight control system includes a double gradient linkage assembly. The double gradient linkage assembly includes a damper system and a spring system that improves yaw axis (azimuth) control of the aircraft. Control is only required when a change in the yaw axis state is demanded. Since only minimal displacement inputs to such a FBW flight control system is required, the travel of the pedals are exceeding compact, such that pilot workload is significantly reduced through the reduction in the frequency and magnitude of aircraft control inputs. | 03-25-2010 |
20100084517 | ELECTROMECHANICAL ACTUATION SYSTEM AND METHOD - Electromechanical actuation systems and methods are provided. The electromechanical actuation system includes first, second, and third linear actuators having respective first, second, and third ranges of motion and an output member coupled to the first, second, and third linear actuators such that a position of a selected portion of the output member is based on actuation of the first, second, and third linear actuators. | 04-08-2010 |
20100200701 | FLY-BY-WIRE CONTROL SYSTEM FOR AN AIRCRAFT COMPRISING DETECTION OF PILOT INDUCED OSCILLATIONS AND A CONTROL FOR SUCH A SYSTEM - A fly-by-wire control system for an aircraft including detection of pilot induced oscillations and a mobile control unit for such a system, According to the invention, provision is made for the pivotings of the mobile control unit to be damped by a controllable damper controlled by a detector that detects oscillations corresponding to pilot induced oscillations. | 08-12-2010 |
20110108673 | ELECTRONIC OPERATIONAL CONTROL DEVICE FOR A PILOTING MEMBER WITH CROSS-MONITORING, PILOTING DEVICE AND AIRCRAFT - An electronic operational control device for an aircraft piloting device with two connected piloting members, includes electronic circuits for main monitoring from signals delivered by sensors associated with one of the piloting members, and at least one electronic circuit ( | 05-12-2011 |
20130082149 | POWER SUPPLY AND CONTROL DEVICE FOR ACTUATORS, CORRESPONDING ACTUATION ASSEMBLY, AND AIRCRAFT COMPRISING SUCH A DEVICE - A power supply and control device for a plurality of electric actuators, the device comprising a control circuit and a power circuit, the power circuit having an inverter module connected to a switch module provided with connection means for connection to the actuators, the control circuit being connected to the switch module to operate it so as to connect the actuators sequentially to the inverter module, wherein the control circuit is arranged to control the inverter module and the switch module sequentially, and wherein the control circuit includes a monitoring module arranged to detect a malfunction of the device. An actuator assembly comprising a plurality of actuators and such a power supply and control device, and an aircraft including a plurality of actuators and such a power supply and control device of the above-specified type. | 04-04-2013 |
20140138492 | INTEGRATED SEAT MOUNTED INCEPTOR - An inceptor is provided including a control stick mounted to a seat. The control stick is movable about at least a first axis. A fly-by-wire inceptor control system is housed within a portion of the seat. The inceptor control system is configured to provide input signal indicative of movement of the control stick to a flight control system. | 05-22-2014 |
20160046364 | SYSTEMS FOR INCEPTOR CONTROL IN FLY-BY-WIRE AIRCRAFT SYSTEMS - Aircraft, control-by-wire systems, and controllers are provided. The aircraft includes a flight control surface and a control-by-wire system. The control-by-wire system includes an input device and a controller. The input device is configured to control the flight control surface. The controller is communicatively coupled with the input device and configured to automatically offset a neutral force position of the input device based on a deviation of the aircraft from a reference condition while the aircraft is operated in a manual flight mode. | 02-18-2016 |
20160375996 | ELECTRO-RHEOLOGICAL ELASTOMERIC, VARIABLE-STIFFNESS FLIGHT CONTROL DEVICE - According to one embodiment, a flight control device includes a grip, a stick associated with the grip, and a gimbal. The stick defines a first axis. The gimbal includes a first platform, a second platform, a first electro-rheological elastomeric bearing, and a second electro-rheological elastomeric bearing. The first platform is coupled to the stick and configured to rotate on a second axis that is perpendicular to the first axis. The second platform is in mechanical communication with the first platform and configured to rotate on a third axis that is perpendicular to the second axis. The first electro-rheological elastomeric bearing defines the second axis, and the second electro-rheological elastomeric bearing defines the third axis. The first and second electro-rheological elastomeric bearing being configured to each have a variable stiffness. | 12-29-2016 |
244229000 | Dual | 4 |
20080237402 | Aircraft trim safety system and backup controls - Methods and apparatuses that control trim of an aircraft even in the presence of conflicting trim inputs, for example by disabling the trim input switches on the aircraft when conflicting switch inputs are received. When conflicting switch inputs are received and certain time conditions are met, the controller can disable the switch inputs and provide a backup and independent means to control the trim circuitry. The pilot can be allowed to re-enable the disabled inputs. | 10-02-2008 |
20120056039 | CONTROL SYSTEM FOR AN AIRCRAFT - This invention relates to a control system for an aircraft consisting of at least two active inceptor units and at least one coupling means, wherein the coupling means generates or influences at least one setpoint for the control of at least one of the active inceptor units, wherein the generated setpoint corresponds to a movement setpoint for a movement controller. | 03-08-2012 |
20140097300 | ELECTRONIC FLIGHT CONTROLS WITH PARALLEL PROCESSED TORQUE & POSITIONING FOR PILOT OR ASTRONAUT TOUCH FEEDBACK - Cockpit controls designed for a multi pilot or multi astronaut crew and automation. All duplications of controls: yoke and control columns, or sticks, and pedals move in unison with the other sets of controls electronically based on a plurality of parallel processed parameters allowing feel or touch feedback for effective monitoring and control by the pilot or astronaut in normal and emergency situations. | 04-10-2014 |
20160176511 | ADJUSTABLE HEIGHT CYCLIC CONTROL ASSEMBLY AND METHOD | 06-23-2016 |
244230000 | With variable output | 4 |
20100308178 | VARIABLE RATIO CRANK FOR A MANUAL FLIGHT CONTROL LINKAGE OF A ROTARY WING AIRCRAFT - The present invention relates to a bellcrank ( | 12-09-2010 |
20140191087 | AIRCRAFT AND AIRCRAFT CONTROL METHOD - An aircraft is provided with a mechanical linkage that mechanically transmits an amount of manipulation of a control stick to a rudder controlling mechanism, an amount-of-manipulation sensor that detects the amount of manipulation, and an FBW control-law computing unit that calculates an FBW control-law command indicating an amount of control for a craft in accordance with the detected amount of manipulation. Also, with the aircraft, a high-pass filter outputs, among the control-stick manipulation amounts detected by the amount-of-manipulation sensor, an amount of change in the control-stick manipulation amounts; by subtracting the amount of change that has passed through the high-pass filter by means of the subtracting portion, the FBW control-law command serves as an SAS command; and the rudder controlling mechanism is driven by adding an amount of movement of an SAS actuator in accordance with the SAS command to the control-stick manipulation amount transmitted by the mechanical linkage. | 07-10-2014 |
20160122000 | SYSTEM AND METHOD FOR OPTIMIZING HORIZONTAL TAIL LOADS - A method of controlling an elevator of an aircraft may include identifying a current stabilizer angle of incidence of a stabilizer of the aircraft. The stabilizer may include an elevator pivotably coupled to the stabilizer. The method may further include comparing the current stabilizer angle of incidence with a threshold stabilizer angle of incidence, and selecting an elevator position limit that is more restrictive if the current stabilizer angle of incidence is greater than or equal to the threshold stabilizer angle of incidence. The method may additionally include moving the elevator to a commanded elevator position that is no greater than the elevator position limit. | 05-05-2016 |
20170233066 | PITCH CONTROL SYSTEM | 08-17-2017 |
244231000 | With interengaging gearing | 2 |
20100206993 | STEERING STRUCTURE OF TOY PLANE AND INFRARED FOUR-CHANNEL REMOTE-CONTROL ELECTRIC TOY PLANE - This invention discloses a steering structure of toy plane and an infrared four-channel remote-control electric toy plane. The steering structure of toy plane includes small internal guide, large external guide, elliptical shaft, and sector gear; the small internal guide has a rectangle hole with rounded angles and two arc-back bosses, and driven by the sector gear, the small internal guide contacts the elliptical shaft along the second and fourth quadrants; the large external guide has the elliptical hole, and driven by the sector gear, the large external guide contacts the elliptical shaft along first and third quadrants. The small infrared four-channel remote-control plane has adopted such steering structure, which allows the small internal guide or the large external guide to change the rotating direction of lower propeller by contacting the elliptical shaft, so as to realize the simple steering structure, also large reduction on product cost, and the functions of Forward/Backward and Left Turn/Right Turn of mini toy plane. | 08-19-2010 |
20140021303 | COMPLEX-DYNAMIC AIR AND GROUND VEHICLE CONTROL INCEPTOR - A complex-dynamic air and ground vehicle control inceptor assembly that provides active positional control with the capability of back drive (pilot over-ride) via a direct connection between the lever, a high gear-ratio gearbox, and the motor without the use of a clutch. | 01-23-2014 |