WOODWARD MPC, INC. Patent applications |
Patent application number | Title | Published |
20150203188 | Line Replaceable, Fly-By-Wire Control Column and Control Wheel Assemblies with a Centrally Connected Line Replaceable Disconnect and Autopilot Assembly - A yoke for controlling the attitude of an aircraft is provided. The yoke includes a chassis, a pitch hub, a roll hub, a support column, a control wheel and a connection arrangement. The pitch hub rotatably mounts to the chassis. The roll hub rotatably mounts to the chassis for motion being generally parallel to the pitch hub. The support column attaches to the pitch hub for rotational motion with the pitch hub relative to the chassis. The control wheel pivotally attaches to the support column for rotational motion about a control wheel pivot axis being generally perpendicular to the pitch and roll hubs. The connection arrangement couples the control wheel to the roll hub and is configured to rotate the roll hub about the roll axis when the control wheel is rotated about the control wheel pivot axis. A system including interconnected yokes is also provided. | 07-23-2015 |
20130162418 | MOTOR GENERATED DETENT FEEL - A control stick system for simulating a detent mechanism in an aircraft is provided. The detent mechanism is simulated by a motor operably coupled to a lever and configured to bias the lever such that the user experiences the feel of a traditional detent mechanism. A controller operates the motor that provides the simulated detent by receiving data from multiple sensors regarding the position and the speed of the lever and the position and the speed of a rotor assembly of the motor. Using the position and the speed measurements, the controller is able to detect when the lever is entering a specific zone of a simulated detent range. Depending on what zone the lever is in, within the simulated detent range, the controller is configured to provide a different drive current to the motor. | 06-27-2013 |
20130105634 | COMPACT TWO AXIS GIMBAL FOR CONTROL STICK | 05-02-2013 |
20120176124 | Method and Apparatus for a Half-Bridge Variable Differential Transformer Position Sensing System - A half-bridge variable differential transformer position sensing system that includes a transducer having a stator with an inductive coil having a center tap configured to provide an output signal. The transducer also has an armature with a magnetically permeable core configured to move within the inductive coil, such that movement of the magnetically permeable core causes a change in the output signal. The position sensing system includes a first circuit configured to provide an excitation signal at one terminal of the inductive coil. The system includes no more than three electrical interface wires, and a microcontroller configured to calculate the degree of change in the position of the magnetically permeable core, and is configured to correct for variations in the voltage of the output signal due to the temperature of the transducer and due to non-linear effects on the output signal caused by movement of the magnetically permeable core. | 07-12-2012 |
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 |
20120097800 | LINE REPLACEABLE, FLY-BY-WIRE CONTROL COLUMNS WITH PUSH-PULL INTERCONNECT RODS - A control input system is provided. The system includes a pair of control columns that are selectively interconnected such that manipulation of one of the control columns is translated to the other one of the control columns. The system includes a disconnect arrangement for each of the degrees of freedom (pitch and roll) of the system that operably disconnects the two control columns such that the two control columns can operate independently such as in the event of failure of one of the control columns. The system may also include a discontinuous force profile for a restoring force mechanism that provides tactile feedback to the pilots simulating resistance provided by control surfaces of the aircraft. The system may also include an autopilot lockout mechanism that increases the force profile experienced by the pilots when autopilot mode is entered. | 04-26-2012 |
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 |
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 |
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 |