A flight pushback state monitoring method based on multi-modal data fusion comprises: 1, constructing a control intention recognition rule, and recognizing a pushback intention from a control instruction sent by a controller; 2, constructing a flight intention recognition model, extracting an aircraft action from a real-time monitoring video, and capturing a flight intention; and 3, constructing an intention alignment fusion rule, and judging whether control intention information conflicts with flight intention information; by fusing the control intention and the flight intention, the method can realize the following auxiliary functions: timely judging whether the aircraft follows the pushback instruction sent by the controller, if a captain does not act according to the control instruction or acts arbitrarily without a control instruction, giving an inconsistent alarm, and a function of monitoring the flight pushback state is implemented.

A method 300 for deploying an aircraft landing gear including: receiving an aircraft landing gear deployment signal 310, receiving an aircraft position signal indicative of a distance of the aircraft from an aircraft landing site 320, receiving one or more flight signals indicating one or more dynamic conditions or parameters relating to the flight of the aircraft 330, determining, based at least on the one or more flight signals, a first aircraft position, relative to the aircraft landing site, at which the landing gear deployment should commence 340, and deploying the landing gear (a) when the aircraft reaches the first aircraft position, in the event that the deployment signal is received before the aircraft reaches the first aircraft position, or (b) immediately, in the event that the deployment signal is received when the aircraft has passed the first aircraft position 350.

Disclosed is a method of operating a Portable Cargo Panel (PCP) for an aircraft, including: detecting a gesture on a display of the PCP; determining that the gesture is a command to view on the display a first cargo compartment; securing a wireless connection with the first control panel therein; receiving, from the first control panel, a health state of each of a plurality of Cargo Handling Units (CHUs) therein; displaying, on the display, the first cargo compartment with the plurality of CHUs and the operational state of the plurality of CHUs; controlling one or more of the CHUs in the first cargo compartment by transmitting, to the first control panel, a command to: run a diagnostic test against the one or more of the plurality of CHUs; or control the plurality of CHUs to move a Unit Load Device (ULD) into, within or out of the first cargo compartment.

A propulsion assembly for an unmanned aerial vehicle (UAV), includes a motor, a propeller seat configured to be driven by the motor and to receive a propeller, and a sensor configured to collect sensing data useful for determining a type of the propeller disposed on the propeller seat and controlling the motor based on the type of the propeller.

An aircraft having a fuselage with one or more wings coupled to the fuselage. A pair of booms are attached to the one or more wings. Each boom has a front end coupled with a front propulsion system and a rear end coupled with a rear propulsion system. Each front propulsion system includes a front motor coupled with a foldable front propeller in a tractor configuration. Each rear propulsion system includes a rear motor coupled with a foldable rear propeller in a pusher configuration.

An uplock is disclosed including a hook configured to engage a capture pin mounted on an aircraft component. The hook is mounted for movement between a closed position and an open position. The uplock further includes an indicator system configured to detect whether a pin is engaged with the hook when the hook is in the closed position.

A system for displaying the state of an aircraft cargo door. The cargo door is configured pivot between a closed position and an open position, the closed and open positions defining a pivoting range. The cargo door is lockable both in the closed position and in the open position. The cargo door is in a regular state when locked in the closed position or the open position. The cargo door is in a warning state when in the pivoting range between the closed position and open position. The cargo door is in a faulty state when unlocked in the closed position or unlocked in the open position or when there is an obstacle in the pivoting range. The cargo door comprises at least one indicator configured to display the respective state of the cargo door, the indicator being detectable from a distance of at least 7.5 m.

A method of determining the position of one or more components of a landing gear assembly of an aircraft is disclosed including scanning the one or more components with a lidar system to generate a set of position data points, each position data point comprising a set of three orthogonal position values. The position data points are partitioned into one or more clusters using a distance metric. Each cluster is determined to represent a component of the landing gear assembly. The position of the components are then determined from the position data points in the clusters. The value of the distance metric for a first position data point and a second position data point is representative of the difference between a first position value of the three orthogonal position values of the first position data point and the corresponding first position value of the three orthogonal position values of the second position data point.

A method of determining the steering angle of a landing gear assembly of an aircraft is disclosed including scanning the landing gear assembly with a lidar system to generate a set of three-dimensional position data points, each position data point including a set of three orthogonal position values. A two-dimensional image from the set of three-dimensional position data points, by converting a position value of each of the three-dimensional position data points to an image property value of a set of image property values. A boundary of an area of the two-dimensional image of which each position data point has the same image property value is identified, where the area corresponds to a component of the landing gear assembly. The steering angle of the landing gear assembly is then determined from the shape and/or orientation of the identified boundary.

A propulsion assembly for an unmanned aerial vehicle (UAV) includes a motor configured to rotate in a first direction, a propeller seat configured to be driven by the motor to rotate in the first direction and to receive a propeller, and a sensor configured to collect sensing data useful for determining whether the propeller is locked to the propeller seat, without requiring operation of the motor.