An active inceptor apparatus and method for operating a machine. The apparatus comprises a stick member having a grip portion, the stick member being pivotably mounted relative to a housing. It further comprises a position sensor responsive to, and for generating signals indicative of, stick member position. A force sensor is provided on the stick member responsive to, and for generating signals indicative of, force applied to the stick by a user. The apparatus also includes a control unit operable to receive the position and force signals from the position and force sensors respectively. The control unit is operable to process the signals according to a predetermined relationship to determine a value FD indicative of force applied to the stick member relative to displacement of the stick member. The control unit is also operable to generate machine control signals as a function of position signals and force signals in dependence upon the value FD, for communication to the machine.

An active inceptor apparatus and method for operating a machine. The apparatus comprises a stick member having a grip portion, the stick member being pivotably mounted relative to a housing. It further comprises a position sensor responsive to, and for generating signals indicative of, stick member position. A force sensor is provided on the stick member responsive to, and for generating signals indicative of, force applied to the stick by a user. The apparatus also includes a control unit operable to receive the position and force signals from the position and force sensors respectively. The control unit is operable to process the signals according to a predetermined relationship to determine a value FD indicative of force applied to the stick member relative to displacement of the stick member. The control unit is also operable to generate machine control signals as a function of position signals and force signals in dependence upon the value FD, for communication to the machine.

Systems and methods are provided for a lockout device. The lockout device may prevent movement of aircraft control devices. The lockout device may include one or more portions and may include features that are designed to couple to or clasp a yoke of an aircraft as well as interface or couple to a pedal housing of the aircraft. Features of the lockout device may prevent movement of the aircraft control devices. The lockout device may include features to lock the device and may be multiple separate pieces or may be a hinged device.

An aircraft may include a control lever movable along a lever path and configured to control a system of the aircraft, and a selectively engageable detent feature configured to inhibit travel of the control lever and operable in a disengaged configuration in which the control lever is movable along the lever path without restriction by the selectively engageable detent feature, and an engaged configuration in which the selectively engageable detent feature inhibits travel of the control lever at a particular location along the lever path.

An aircraft may include a control lever movable along a lever path and configured to control a system of the aircraft, and a selectively engageable detent feature configured to inhibit travel of the control lever and operable in a disengaged configuration in which the control lever is movable along the lever path without restriction by the selectively engageable detent feature, and an engaged configuration in which the selectively engageable detent feature inhibits travel of the control lever at a particular location along the lever path.

Systems and methods for locking a control lever are provided. One system includes a locking device having a body configured to couple to a control lever within an aircraft to prevent the control lever from moving. The locking device also includes at least one hole defined through the body. The one hole is configured to receive one of a lock or a tag therein.

Systems and methods for locking a control lever are provided. One system includes a locking device having a body configured to couple to a control lever within an aircraft to prevent the control lever from moving. The locking device also includes at least one hole defined through the body. The one hole is configured to receive one of a lock or a tag therein.

A resistive and locking system for locking rotation of a shaft. The system includes a housing defining an axis AX therethrough. The housing includes a drive shaft mounted in the housing and extending axially from a bottom end of the housing and a first stage comprising a resistive mechanism provided in the housing. The housing also includes a second stage comprising a locking mechanism arranged in the housing above the first stage. The locking mechanism is biased axially to frictionally engage with and lock the first stage mechanism to prevent rotation of the drive shaft, the locking mechanism including a magnetic unlocking mechanism configured to remove the frictional engagement with the first stage on application of power to the locking mechanism.

A resistive and locking system for locking rotation of a shaft. The system includes a housing defining an axis AX therethrough. The housing includes a drive shaft mounted in the housing and extending axially from a bottom end of the housing and a first stage comprising a resistive mechanism provided in the housing. The housing also includes a second stage comprising a locking mechanism arranged in the housing above the first stage. The locking mechanism is biased axially to frictionally engage with and lock the first stage mechanism to prevent rotation of the drive shaft, the locking mechanism including a magnetic unlocking mechanism configured to remove the frictional engagement with the first stage on application of power to the locking mechanism.

An inceptor apparatus for an aircraft having a primary inceptor member provided in the form of a stick member having a grip portion, at which the stick member can be gripped by a pilot's hand, and a secondary inceptor member provided at an upper portion of the primary inceptor member and having an actuating portion, at which the secondary inceptor member can be manually actuated by a pilot's thumb. Both inceptor members have associated a respective sensor assembly which is provided to generate electronic flight control signals or commands in response to at least one of i) pivoting movements of the respective inceptor member around each of two independent maneuvering axes associated to the inceptor member, ii) forces acting on or via the respective inceptor member in pivoting directions with respect to each of the maneuvering axes, and iii) lateral flexing or bending of the respective inceptor member.