A tip gap monitoring system for a ducted aircraft having a proprotor system including a duct and a plurality of proprotor blades includes sensors coupled to the proprotor system. The sensors are configured to detect one or more parameters of the proprotor system to form a plurality of sensor measurements. The tip gap monitoring system also includes a flight control computer in data communication with the sensors. The flight control computer includes a tip gap measurement module configured to determine a tip gap distance between the duct and the proprotor blades based on the sensor measurements.

A tip gap control system for a ducted aircraft includes a flight control computer including an inner duct surface control module configured to generate an inner duct surface actuator command and a proprotor system in data communication with the flight control computer. The proprotor system includes a duct having active inner duct surfaces movable into various positions including a retracted position and an extended position. The proprotor system also includes proprotor blades surrounded by the duct and one or more actuators coupled to the active inner duct surfaces. The one or more actuators move the active inner duct surfaces between the various positions based on the inner duct surface actuator command, thereby controlling a tip gap between the proprotor blades and the duct.

A tip gap control system for a ducted aircraft includes a flight control computer including a blade length control module configured to generate a blade tip actuator command and a proprotor system in data communication with the flight control computer. The proprotor system includes a duct and proprotor blades surrounded by the duct. Each of the proprotor blades includes an active blade tip movable into various positions including a retracted position and an extended position. The tip gap control system also includes one or more actuators coupled to the active blade tips. The one or more actuators move the active blade tips between the various positions based on the blade tip actuator command, thereby controlling a tip gap between the proprotor blades and the duct.

Methods, apparatus, and articles of manufacture to control and monitor a folding wingtip actuation system are disclosed. An example apparatus includes a sequence and control module to determine whether to control a movement of a folding wingtip assembly coupled to a wing of an aircraft, the sequence and control module is to determine actions during a first stage and a second stage to complete in sequence to move the folding wingtip assembly, determine a status of a first component of the folding wingtip assembly based on a sensor measurement, in response to the status being a non-responsive status, replace a first input from the first component with a second input from a second component, and control the movement of the folding wingtip assembly based on the actions and the second input.

Disclosed herein is a flight control cable sensor for detecting actuation of a flight control cable of an aircraft. The flight control cable sensor comprises a draw wire encoder, comprising an extendable-retractable wire. The flight control cable sensor further comprises a first connector, co-movably fixed to the extendable-retractable wire, and a second connector, co-movably fixable to the flight control cable and configured to removably co-movably engage the first connector up to a predetermined pull-off force.

An attachment assembly for connecting an actuator to a frame, a method for manufacturing this attachment assembly and a method for reducing backlash in an attachment assembly. The attachment assembly comprises: an outer yoke having a first end and an opposite second end and defining an internal cavity at said second end. The outer yoke has an aperture provided at its second end connected to the cavity; and an inner yoke located within the cavity. A tie bar having a ball shaped end extends through said aperture such that the ball shaped end is positioned within the cavity and cannot pass through the aperture. A spring is provided at said first end of said outer yoke that is configured to bias the inner yoke in the direction of the aperture. The attachment also includes shearable means for holding the inner yoke.

A seat configuration verification system and method for an internal cabin of a vehicle include a verification control unit that receives position data regarding positions of seat assemblies within the internal cabin. The verification control unit compares the position data with seat configuration data representative of the seat configuration to determine if the positions of the seat assemblies within the internal cabin conform to the seat configuration.

A tip gap control system for a ducted aircraft includes a flight control computer including a blade length control module configured to generate a blade tip actuator command and a proprotor system in data communication with the flight control computer. The proprotor system includes a duct and proprotor blades surrounded by the duct. Each of the proprotor blades includes an active blade tip movable into various positions including a retracted position and an extended position. The tip gap control system also includes one or more actuators coupled to the active blade tips. The one or more actuators move the active blade tips between the various positions based on the blade tip actuator command, thereby controlling a tip gap between the proprotor blades and the duct.

An integrated asymmetric brake system for an aircraft includes a housing and a control surface actuator arranged in the housing. The control surface actuator includes a torque limiter output member and is operable to selectively deploy and retract a control surface. An asymmetry brake system is arranged in the housing and is operably connected to the control surface actuator and the torque limiter output member. The asymmetry brake system is selectively operable to prevent deployment of the control surface by activating the torque limiter output member upon detecting an asymmetry event. An asymmetry brake test monitor switch is mounted in the housing and operably coupled to the asymmetry brake system. The asymmetry brake test monitor switch is monitored to confirm functionality of the asymmetry brake system prior to flight.

A system and method for detecting fixed pitch operation of a variable pitch propeller of an engine are provided. A command signal for maintaining a rotational speed of the propeller at a reference speed is output. An actual value of at least one of the rotational speed and a blade angle of the propeller is obtained. From the actual value, it is assessed whether an expected change in the at least one of the rotational speed and the blade angle of the propeller has occurred in response to the command signal. Responsive to determining that the expected change in the at least one of the rotational speed and the blade angle of the propeller has not occurred in response to the command signal, operation of the propeller at fixed pitch is detected and an alert output accordingly.