| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244234000 | Controller | 36 |
| 20090050748 | AIRCRAFT FLIGHT CONTROL SYSTEMS AND METHODS - An aircraft flight control system advantageously is provided with a control rod which is spline-connected to a bearing assembly so as to permit simultaneous independent longitudinal and rotational movements of the control rod while isolating such movements from one another (e.g., so as to allow operative interconnection to an aircraft's aileron and elevator control surfaces). Thus, the control rod is moveable in longitudinal and rotational directions relative to a longitudinal axis of the control rod in response to pitch and roll command inputs, respectively. The rotatable bearing assembly is adapted for connection to aileron control surfaces of the aircraft. The control rod is splined operatively to the bearing assembly so as to allow for independent simultaneous longitudinal and rotational movements of the control rod relative to the longitudinal axis thereof. As such, longitudinal movements of the control rod are isolated from the bearing member but rotational movements of the control rod are transferred to the bearing member to cause rotation thereof and thereby allow operation of the aileron control surfaces. Longitudinal movements of the control rod may however be transferred to a torque tube assembly via an articulated linkage to allow for operation of an aircraft's elevator control surface. | 02-26-2009 |
| 20090090816 | MECHANISMS AND METHODS FOR PROVIDING RUDDER CONTROL ASSIST DURING SYMMETRICAL AND ASYMMETRICAL THRUST CONDITIONS - Rudder assist mechanisms and methods are capable of being operably connected to an aircraft's rudder control system. The rudder assist mechanisms most preferably have over-the-center spring biasing functions so as to cause either substantially no spring force (i.e., when the linkage is over the spring-bias center) or substantially all spring force (i.e., when the linkage is left or right of the spring-bias center) to be exerted on the rudder control system. The rudder assist mechanism may include a control spring assembly, and a linkage assembly which operably connects the control spring assembly to the rudder control assembly. The linkage assembly is moveable operably between a null position wherein substantially no spring force of the control spring assembly is transferred to the rudder control system by the linkage assembly, and right and left spring-biased positions wherein right and left spring forces of the control spring assembly are transferred to the rudder control system, respectively. The null position may therefore establish a dead zone of rudder deflection within a selected range of right and left rudder control surface deflection angles. Thus, right and left spring forces may be transferred to the rudder control system when the rudder control surface is deflected at an angle which exceeds the selected range of deflection angles. Some embodiments include an actuator unit which is operably capable of moving the spring assembly and the linkage assembly connected thereto between a thrust symmetrical mode (TSM) condition and a thrust asymmetrical mode (TAM) condition so as to cause different spring forces to be exerted on the rudder control system in such different thrust conditions. | 04-09-2009 |
| 20090230252 | AIRCRAFT FLIGHT CONTROL - An aircraft flight control ( | 09-17-2009 |
| 20090321583 | Panel-Mounted Aircraft Control Stick - A panel-mounted control stick for aircraft providing for roll and pitch input that emulates the response of a traditional floor-mounted control stick. The panel-mounted control stick incorporates a pitch beam input assembly and a roll input assembly for translating the movements of the control stick into movements of aircraft control surfaces. | 12-31-2009 |
| 20090321584 | Panel-Mounted Aircraft Control Stick - A panel-mounted control stick for aircraft providing for roll and pitch input that emulates the response of a traditional floor-mounted control stick. The panel-mounted control stick incorporates a pitch beam input assembly and a roll input assembly for translating the movements of the control stick into movements of aircraft control surfaces. | 12-31-2009 |
| 20100072323 | ARTICULATING YOKE MOUNT - An articulating yoke mount includes a support plate, a first bracket assembly mounted to the support plate, and a second bracket assembly spaced from the first bracket assembly. A positioning of the support plate is selectively adjustable relative to the first bracket assembly and the second bracket assembly to position the support plate at a desired viewing angle. | 03-25-2010 |
| 20100301174 | SYSTEM FOR CONTROLLING AT LEAST ONE AIRCRAFT ENGINE AND AN AIRCRAFT COMPRISING SUCH A CONTROL SYSTEM - A system for controlling at least one aircraft engine and an aircraft comprising such a control system. The system ( | 12-02-2010 |
| 20110163206 | HELICOPTER CONTROL STICK SUPPORT ASSEMBLY - A support assembly for helicopter control sticks has a supporting structure; an instrument panel fixed to the supporting structure; and a connecting device for connecting the sticks to the supporting structure. The connecting device has a longitudinally elongated arm fitted on one end with the sticks; and the arm slides to move the sticks to/from the supporting structure, and rotates about a horizontal axis to adjust the height of the sticks. | 07-07-2011 |
| 20120085870 | VEHICLE ARMREST - An armrest for use by a pilot whilst operating a side stick inceptor has on its underside a number of secondary controls which can be operated when the side stick is not being used, the armrest then acting as a handgrip enabling the pilot to operate the secondary controls with a steady hand. | 04-12-2012 |
| 20120205495 | Method And Device For Yaw Controlling Of An Aircraft - According to the invention, the pilot having beforehand moved a commanding system in such a manner that the movement of said system ( | 08-16-2012 |
| 20120217349 | Panel-Mounted Aircraft Control Stick - A panel-mounted control stick for aircraft providing for roll and pitch input that emulates the response of a traditional floor-mounted control stick. The panel-mounted control stick incorporates a pitch beam input assembly and a roll input assembly for translating the movements of the control stick into movements of aircraft control surfaces. | 08-30-2012 |
| 20120234985 | CYCLIC STICK FOR MECHANICALLY TRANSMITTING COMMANDS FOR CONTROLLING A ROTORCRAFT, THE STICK HAVING A LEVER ARM THAT IS AMPLIFIED SELECTIVELY IN THE EVENT OF AN EMERGENCY - The invention provides a control mechanism for controlling flight of an aircraft, the control mechanism comprising a cyclic control stick ( | 09-20-2012 |
| 20120261520 | ARTICULATING YOKE MOUNT - An articulating yolk mount includes a first support plate and a second support plate connected relative to the first support plate. The second support plate is rotatable relative to the first support plate. | 10-18-2012 |
| 20120273623 | 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. | 11-01-2012 |
| 20130037659 | Control Quadrant - An aircraft with a control system having joint control for a throttle and a propeller of an aircraft may be modified to decouple the joint control of a throttle and a propeller. Control of the throttle and propeller may be independent of the other. Exemplary modification of a control system may use new structures, existing structures, repurpose existing structures, or use a combination thereof. Additionally or alternatively, modification of a control system may provide controls with tactile distinction to a user. | 02-14-2013 |
| 20130256463 | Piloting device for piloting an aircraft having a protected force sensor - A piloting device for piloting an aircraft includes a piloting member ( | 10-03-2013 |
| 20140014781 | AIRCRAFT CONTROL STICK OPERATIONAL IN ACTIVE AND PASSIVE MODES - An apparatus and method is provided for operating an aircraft control stick in an active mode and a passive mode. The method comprises subjecting the control stick to an a resilient restoring force in the passive mode, and neutralizing the restoring force in the active mode. A spring assembly is provided for exerting and neutralizing the restoring force, which may be varied between minimum and maximum values. | 01-16-2014 |
| 20140263850 | CONTROL MEMBER PROVIDED WITH A BLADE COLLECTIVE PITCH LEVER AND YAW CONTROL MEANS, AND AN AIRCRAFT - A control member ( | 09-18-2014 |
| 20140353433 | ROTORCRAFT FLIGHT CONTROL STICK TILTABLY MOUNTED ON A SUPPORT BY A FLEXIBLE ROD WITH A FIXED END - A fly-by-wire control mechanism for a rotorcraft, the mechanism comprising a stick ( | 12-04-2014 |
| 20150108283 | Wingtip Control System - A method and apparatus for a wingtip control system. The wingtip control system comprises a switch system for a flight deck of an aircraft and a controller. The switch system is configured to be placed into an armed state and generate an armed signal. The controller is in communication with the switch system. The controller is configured to receive the armed signal from the switch system, visually indicate a desired position for a wingtip of the aircraft in the switch system in response to an event occurring during operation of the aircraft, and generate a movement command to move the wingtip. | 04-23-2015 |
| 20160009375 | HIGH LIFT CONTROL METHOD AND SYSTEM FOR AIRCRAFT | 01-14-2016 |
| 20160107657 | UNIVERSAL MULTI-ROLE AIRCRAFT PROTOCOL - The Curtis Protocol, an aircraft control interface, is provided. The Curtis Protocol standardizes the division and selection of aircraft flight regimes and flight modes within the selected flight regime. | 04-21-2016 |
| 20160252926 | FLIGHT CONTROL DEVICE FOR AN AIRCRAFT | 09-01-2016 |
| 244235000 | Rudder bar and pedal | 7 |
| 20100078524 | 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. | 04-01-2010 |
| 20110108674 | Cockpit Rudder Control Mechanism For An Aircraft - A cockpit rudder control mechanism is described for accepting aircraft control input utilizing rudder pedals depending from a movable carriage to rotate a shaft. The mechanism may be removed from the aircraft for maintenance and the position of the mechanism within the aircraft may be adjusted for a particular user. Movement of the rudder pedals is conveyed by linkages to a collar which rotates a shaft. The rotation of the shaft is measured for control input to the aircraft or is transferred to the mechanical control systems for the aircraft. | 05-12-2011 |
| 20130175403 | BRAKE ASSEMBLY INCLUDING INDEPENDENTLY ACTIVATABLE BRAKE ACTUATORS - A braking system may include a plurality of independently activatable groups of brake actuators, which may allow the braking force applied to a brake disc stack to be modified, e.g., in response a type of braking event. In some examples, a braking system comprises a brake assembly that includes a brake stack and a plurality of brake actuators. Each brake actuator may be configured to compress the brake stack when the brake actuator is activated. The braking system may further comprise a processor configured to detect a first type of braking event and, in response, activate a first number of brake actuators to compress the brake stack. The processor may further be configured to detect a second type of braking event and, in response, activate a second number of brake actuators to compress the brake stack, the first number being less than the second number. | 07-11-2013 |
| 20130327896 | ROTORCRAFT YAW PILOTING SYSTEM MAKING USE OF A MEMBER OF THE HUMAN-OPERATED TYPE AND OF A FLIGHT CONTROL GENERATOR FO THE OBJECTIVE TYPE - A system and a method for controlling a rotorcraft ( | 12-12-2013 |
| 20140131523 | ABOVE-THE-FLOOR RUDDER AND BRAKE CONTROL SYSTEM - A modular brake and rudder control system usable in an aircraft. The modular system mounts atop the flight deck floor without penetrating through the floor when the system is operatively connected to the aircraft's fly-by-wire brake and rudder systems. Pedal assemblies extending from the housing are rotatable and longitudinally moveable relative to the housing. A brake control system fully contained in the housing is connected to the pedal assemblies and provides a signal via an electrical connector to the fly-by-wire brake system upon rotation of the pedals. A rudder control system is fully contained in the housing and is operable independent of the brake control system. The rudder control system detects longitudinal motion of the pedal assemblies and provides a signal via an electrical connector to the fly-by-wire rudder system. The housing, the electrical connectors, the pedal assemblies, the brake control system and the rudder control system define a modular component installable and removable from the cockpit as a unit. | 05-15-2014 |
| 20150144743 | Control Device of Aircraft Steering Apparatus - A control device | 05-28-2015 |
| 20160159457 | RUDDER BAR FOR AN AIRCRAFT - A rudder bar for an aircraft comprising a floor, a steering connecting rod and a braking connecting rod. The rudder bar comprises a base fixed above the floor, a pedal arm mounted rotatably on the base about a first axis of rotation and having a lower end and an upper end, a pedal mounted rotatably on the lower end about a second axis of rotation, a first transmission assembly configured to transmit a movement to the steering connecting rod when the pedal arm pivots about the first axis of rotation, and a second transmission assembly configured to transmit a movement to the braking connecting rod when the pedal pivots about the second axis of rotation. | 06-09-2016 |
| 244236000 | Electrical pickup | 6 |
| 20090302172 | INPUT/STEERING MECHANISMS AND AIRCRAFT CONTROL SYSTEMS FOR USE ON AIRCRAFT - Input/steering mechanisms and aircraft control systems are provided. In an embodiment, by way of example only, an input/steering mechanism is provided for use with an aircraft control system. The input/steering mechanism includes a yoke that includes a hub, an alphanumeric keyboard, and a first grip surface. The alphanumeric keyboard is disposed on a face of the hub and is adapted to receive a manual input from a user and to transmit an output signal to the aircraft control system in response to the manual input. The first grip surface is formed on an outer periphery of the hub and is contoured to correspond with one or more fingers of the user, the first grip surface is formed such that a thumb of the user is positioned to rest in proximity to at least a portion of the alphanumeric keyboard when the one or more fingers grip the first grip surface. | 12-10-2009 |
| 20100078525 | INPUT SYSTEM FOR A LANDING FLAP CONTROL OF AN AIRCRAFT - An input system ( | 04-01-2010 |
| 20100308179 | ELECTRIC POWER ACTUATOR AND CONTROL METHOD FOR SUCH AN ACTUATOR - An electric power actuator and a method of controlling such an actuator are disclosed. The actuator ( | 12-09-2010 |
| 20110101176 | CONTROL STATION - Control station which comprises: a seat ( | 05-05-2011 |
| 20110155861 | DEVICE FOR PILOTING A CRAFT HAVING AN ELECTROMAGNETIC ACTUATOR - A device for piloting includes a piloting member connected to at least one member for driving the craft, an electromechanical support box including, for each pivot connection, at least one actuating motor of the piloting member constituted of an electromagnetic actuator including a movable armature integrally formed with the piloting member and equipped with at least one permanent magnet having a magnetic moment parallel to the axis of the pivot connection, and an electromagnetic circuit including a fixed armature, arranged to allow the movable armature to move in the air gap zone, the magnetic moment of the movable armature sweeping each radial surface portion, and at least one coil winding which is dependent in position on the fixed armature and is capable of generating electromagnetic torque on the movable armature. | 06-30-2011 |
| 20140374541 | AIRCRAFT CONTROL APPARATUS, CONTROL SYSTEM AND CONTROL METHOD - An aircraft control apparatus, control system, and control method are disclosed. A control apparatus includes: a first control rod configured to have a movement in a first movement direction controlling a motion of an aircraft in a first motion direction, wherein after an external force on the first control rod in the first movement direction is removed, the first control rod automatically returns to a preset position in the first movement direction; wherein the preset position which the first control rod automatically returns to corresponds to the aircraft in the first motion direction maintaining a state of flight; wherein the maintaining state of flight depends on control signals received by the aircraft generated resulting from changes in the external force applied to the control rod in the first movement direction and state signals measured by state measurement sensors carried by the aircraft. | 12-25-2014 |
