A camera with a field of view toward an external environment of an aircraft is disposed within an aircraft door such that a ground surface is within the field of view of the camera during taxiing of the aircraft. A display device is disposed within an interior of the aircraft. A processor is operatively coupled to the camera and to the display device. The processor analyzes image data captured by the camera for docking guidance by identifying, within the captured image data, a region on the ground surface corresponding to an alignment fiducial indicating a parking location for the aircraft, determining, based on the region of the captured image data corresponding to the alignment fiducial indicating the parking location, a relative location of the aircraft with respect to the alignment fiducial, and outputting an indication of the relative location of the aircraft to the alignment fiducial.

Systems and vehicle are provided. A vehicle system for a vehicle includes: a trajectory selection module configured to select a potential vehicle path relative to a current vehicle movement condition; a trajectory movement condition module configured to estimate a modeled movement condition of the vehicle along the potential vehicle path; a limit comparison module configured to determine whether the modeled movement condition violates vehicle limits; and a violation indicator module configured to generate an indication of impending violation.

A method may comprise: receiving, via a controller and through a camera, visual data corresponding to a row of latch assemblies in a cargo handling system; and determining, via the controller, whether each latch assembly in the row of latch assemblies is in a properly securing state.

An imaging system for an aircraft is disclosed. A plurality of image sensors are attached, affixed, or secured to the aircraft. Each image sensor is configured to generate sensor-generated pixels based on an environment surrounding the aircraft. Each of the sensor-generated pixels is associated with respective pixel data including, position data, intensity data, time-of-acquisition data, sensor-type data, pointing angle data, latitude data, and longitude data. A controller generates a buffer image including synthetic-layer pixels, maps the sensor-generated pixels to the synthetic-layer pixels in the buffer image, fills a plurality of regions of the buffer image with the sensor-generated pixels, and presents the buffer image on a head-mounted display (HMD) to a user of the aircraft.

Provided is an abnormality detection device for a rotary wing unit. The rotary wing unit includes a plurality of rotary wings that is coaxially disposed. The abnormality detection device includes a controller configured to acquire at least one of a correlation at the time of normal operation between operation parameters related to the rotary wings and a correlation at the time of abnormal operation between the operation parameters and detect abnormality of the rotary wing unit, based on a correlation at the time of actual operation between the operation parameters and at least one of the correlation at the time of normal operation and the correlation at the time of abnormal operation.

A monitoring system for monitoring a kinematic coupling between an actuator and an element controlled by the latter includes a first sensor to detect the operative movement of the actuator. A second sensor is designed to detect the actual movement of the controlled element. A computer unit, based on the operative movement of the actuator, determines an anticipated movement of the controlled element and compares this anticipated movement with the actual movement of the controlled element. An error message is emitted when a value of the deviation between the anticipated movement and the actual movement exceeds a predefined threshold value.

An aircraft control system (100) including an input interface (102), an output interface (114) and a processing engine (108) having a classifier (110) that applies input data (104) generated by the input interface (102) to generate output control data (112). The classifier (110) has a plurality of parameters which represent a control policy for operating the aircraft (800). The output interface (114) generates control outputs to control the aircraft (800) based on the output control data (112). A machine learning system (900) for training the classifier (110) including an environment (902), a pathway evaluation engine (904), storage (906), and a training engine (908). The machine learning system (900) generates training data (912) by selecting a pathway representing an operating procedure using the pathway evaluation engine (904). The training engine (908) trains the classifier (110) using the training data (912).

An uplock for use with an aircraft landing gear is disclosed having a hook configured to engage a capture pin mounted on the landing gear. The hook is mounted for movement between a closed and locked position and an open and unlocked position. A proximity detector directly detects whether the pin is “up”. An uplock hook sensor detects when the hook is in the closed and locked position. The outputs of the proximity detector and the uplock hook sensor may be used to indicate the “up and locked” condition, i.e., landing gear up, and/or to indicate a fault. Such outputs may be provided by an associated device of an avionics system.

An apparatus for loading and unloading cargo, capable of loading cargo while distributing the weight of the cargo and unloading the cargo regardless of the loading order of the cargo, is provided. The apparatus for loading and unloading cargo may include: a base portion; a rail installed on the base portion; a plurality of movable plates disposed on the rail, supporting the cargo, and moving along the rail; and a raising-lowering portion connected between the base portion and a body so that the base portion can be raised and lowered.

An aircraft system for an aircraft is disclosed having a controller that is configured to receive at least one signal during a landing procedure of the aircraft and to determine that the aircraft is at a predetermined stage in the landing procedure, on the basis of the at least one signal. The predetermined stage in the landing procedure is before a command to extend at least one landing gear of the aircraft is issued during the landing procedure. The controller is configured to cause initiation of at least a part of a procedure to interrogate an aircraft braking system, on the basis of the determination.