A system for providing visual feedback in an aircraft having an actuatable component includes a controller providing automatic control of the actuatable component in an automatic mode and permitting manual control of the actuatable component in a manual mode. A handle assembly is in communication with the actuatable component to provide manual control of the actuatable component in the manual mode. The system also includes a light panel integrated with the handle assembly, in communication with said controller, and configured to selectively illuminate to inform a user of the mode of the actuatable component.

A flap slat control lever and a method for operating the lever are disclosed. The lever includes: a first displacement sensor to detect a displacement of the flap slat control lever and generate a first displacement detection signal; a second displacement sensor to detect the displacement of the flap slat control lever and generate a second displacement detection signal; a first control command module to receive the first displacement detection signal; and a second control command module to receive the second displacement detection signal, wherein the first control command module is in a standby state and the second control command module is in a working state.

An aircraft flap deployment system has a track, a carriage supported by the track; an actuator operatively connected to the carriage for moving the carriage along the track between various carriage positions; a flap pivotally connected to the carriage and to a link such that each position of the carriage has a corresponding flap position; and a flap controller communicating with the actuator for controlling actuation of the actuator. In at least one carriage position, the flap is in an intermediate flap position at a negative flap angle and the actuator maintains the carriage and the flap in position. An aircraft wing assembly having the flap deployment system, an aircraft having the aircraft wing assembly, and a method for controlling a position of a flap of an aircraft are also disclosed.

A wing for an aircraft. The wing includes a main wing and a trailing edge high lift assembly movably arranged at a trailing edge of the main wing. The trailing edge high lift assembly includes a flap and a connection assembly movably mounting the flap to the main wing, such that the flap is movable between a retracted position and at least one extended position, wherein the connection assembly is configured such that the flap is movable relative to the main wing in a linear and/or rotational manner. The connection assembly is configured such that the flap is movable relative to the main wing in a decoupled linear and rotational manner.

A method for controlling a position of a flap of an aircraft includes: receiving, by an actuator, a signal indicative of a desired flap position; when the desired flap position is a retracted flap position: moving the carriage along a track to a first carriage position thereby pivoting the flap to the retracted flap position where the flap is at a neutral flap angle; when the desired flap position is an intermediate flap position: moving the carriage along the track to a second carriage position thereby pivoting the flap to the intermediate flap position where the flap is at a negative flap angle; when the desired flap position is an extended flap position: moving the carriage along the track to a third carriage position thereby pivoting the flap to the extended flap position where the flap is at a positive flap angle. An aircraft flap deployment system is also disclosed.

This document details a series of inventions relating to the design and optimization of hybrid-to-electric aircraft. In particular, a system and method is presented to improve the effectiveness of mixed aerodynamic control surfaces which are actuated by a novel electromechanical actuator which allows the system to be tolerant to actuator faults and jams. In addition, innovations relating to integration and quick swap of large energy storage units such as batteries are disclosed, and further, an algorithm which may be used to optimize numerous aspects of the regional hybrid-to-electric aircraft known as Total Cost Door to Door or TCD2D.

An aircraft flap lever is disclosed. The lever is included in a housing, and is supported on an axle. The lever also has a protruding pin that is biased upwards towards four optional radially-spaced notches. Each notch results in a different lever setting, and thus different flap position. The system includes a rocker mechanism that is pivotally mounted on the axle, and prevents skipping over notches when the lever is activated.

Systems, methods, and apparatus to control aircraft roll operations are disclosed herein. An example system includes a control wheel position determiner to determine a control wheel position based on an input from a control wheel of the aircraft, a control wheel force determiner to determine a first control wheel force based on a sensor measurement, and a spoiler controller to map the control wheel position to a second control wheel force, the second control wheel force based on nominal characteristics of the aircraft, determine a first difference between the first control wheel force and the second control wheel force, and in response to determining that the first difference does not satisfy a threshold, move a flight control surface based on a third control wheel force, the third control wheel force based on a second difference between the first difference and the threshold.

A method for controlling a position of a flap of an aircraft includes: receiving, by an actuator, a signal indicative of a desired flap position; when the desired flap position is a retracted flap position: moving the carriage along a track to a first carriage position thereby pivoting the flap to the retracted flap position where the flap is at a neutral flap angle; when the desired flap position is an intermediate flap position: moving the carriage along the track to a second carriage position thereby pivoting the flap to the intermediate flap position where the flap is at a negative flap angle; when the desired flap position is an extended flap position: moving the carriage along the track to a third carriage position thereby pivoting the flap to the extended flap position where the flap is at a positive flap angle. An aircraft flap deployment system is also disclosed.

Systems, methods, and apparatus to control aircraft roll operations are disclosed herein. An example system includes a control wheel position determiner to determine a control wheel position based on an input from a control wheel of the aircraft, a control wheel force determiner to determine a first control wheel force based on a sensor measurement, and a spoiler controller to map the control wheel position to a second control wheel force, the second control wheel force based on nominal characteristics of the aircraft, determine a first difference between the first control wheel force and the second control wheel force, and in response to determining that the first difference does not satisfy a threshold, move a flight control surface based on a third control wheel force, the third control wheel force based on a second difference between the first difference and the threshold.