Abstract: An airplane rudder and brake pedal assembly includes a rudder arm assembly having one rudder arm with first upper and lower arm portions, and another rudder arm with second upper and lower arm portions. The rudder arm assembly is assembled to a beam at an intersection of the first upper and lower arm portions, and an intersection of the second upper and lower arm portions. The first and second rudder arms are configured to rotate about the beam at the intersection. The rotation of the first and second rudder arms is configured to adjust control surfaces that control a yaw axis of the airplane. A brake pedal is attached to the first and second lower arm portions. Rotation of the brake pedal brakes the airplane. A rotary sensor is assembled to the brake pedal and the lower arm portion, and configured to determine an extent of the brake pedal rotation.

Abstract: An airplane rudder and brake pedal assembly includes a rudder arm assembly having one rudder arm with first upper and lower arm portions, and another rudder arm with second upper and lower arm portions. The rudder arm assembly is assembled to a beam at an intersection of the first upper and lower arm portions, and an intersection of the second upper and lower arm portions. The first and second rudder arms are configured to rotate about the beam at the intersection. The rotation of the first and second rudder arms is configured to adjust control surfaces that control a yaw axis of the airplane. A brake pedal is attached to the first and second lower arm portions. Rotation of the brake pedal brakes the airplane. A rotary sensor is assembled to the brake pedal and the lower arm portion, and configured to determine an extent of the brake pedal rotation.

Abstract: An airplane rudder and brake pedal assembly includes a rudder arm assembly having one rudder arm with first upper and lower arm portions, and another rudder arm with second upper and lower arm portions. The rudder arm assembly is assembled to a beam at an intersection of the first upper and lower arm portions, and an intersection of the second upper and lower arm portions. The first and second rudder arms are configured to rotate about the beam at the intersection. The rotation of the first and second rudder arms is configured to adjust control surfaces that control a yaw axis of the airplane. A brake pedal is attached to the first and second lower arm portions. Rotation of the brake pedal brakes the airplane. A rotary sensor is assembled to the brake pedal and the lower arm portion, and configured to determine an extent of the brake pedal rotation.

Abstract: An airplane rudder and brake pedal assembly includes a rudder arm assembly having one rudder arm with first upper and lower arm portions, and another rudder arm with second upper and lower arm portions. The rudder arm assembly is assembled to a beam at an intersection of the first upper and lower arm portions, and an intersection of the second upper and lower arm portions. The first and second rudder arms are configured to rotate about the beam at the intersection. The rotation of the first and second rudder arms is configured to adjust control surfaces that control a yaw axis of the airplane. A brake pedal is attached to the first and second lower arm portions. Rotation of the brake pedal brakes the airplane. A rotary sensor is assembled to the brake pedal and the lower arm portion, and configured to determine an extent of the brake pedal rotation.

Abstract: An actuator is provided. The actuator includes a housing and a ram linearly movable relative to the housing. The ram is selectively mechanically coupled to a drive screw of the actuator such that in one configuration, the ram is decoupled from the drive screw to allow it to linearly move independently from rotation of the drive screw.

Abstract: An actuator is provided. The actuator includes a housing and a ram linearly movable relative to the housing. The ram is selectively mechanically coupled to a drive screw of the actuator such that in one configuration, the ram is decoupled from the drive screw to allow it to linearly move independently from rotation of the drive screw.

Abstract: 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.

Abstract: A pedal system for an aircraft comprising a pedal and a pedal mounting mechanism is provided. The pedal is configured for manipulation through at least one operational degree of freedom by a pilot to provide control inputs to the aircraft. The pedal mounting mechanism is configured for supporting the pedal within a cockpit of the aircraft for manipulation by the pilot. The pedal mounting mechanism provides at least two adjustment degrees of freedom for adjusting the position of the pedal within the cockpit.

Abstract: 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.

Abstract: A pedal system for an aircraft comprising a pedal and a pedal mounting mechanism is provided. The pedal is configured for manipulation through at least one operational degree of freedom by a pilot to provide control inputs to the aircraft. The pedal mounting mechanism is configured for supporting the pedal within a cockpit of the aircraft for manipulation by the pilot. The pedal mounting mechanism provides at least two adjustment degrees of freedom for adjusting the position of the pedal within the cockpit.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A self centering, angularly displacable joystick allowing multiple compound torque profiles is provided. The self centering joystick includes a first mount and a base. The first mount located a fixed distance away from the base. The joystick extends from a restoring plate having an upper surface and a multi-faceted lower surface pivotally mounted to said first mount to partially rotate about a first axis. A linearly displaceable force plate having a substantially flat upper surface is disposed between said base and said multi-faceted surface, and a spring is provide between the base and the force plate, the spring biasing the force plate against the multi-faceted surface to provide a centering force there against. The multifaceted surface includes a center position facet oriented such that the centering force applied by the force plate is evenly distributed on each side of the first axis when said center position facet is aligned parallel with the upper surface of the force plate.