A method, vehicle, and system for calculating the location of a center of mass of the vehicle and transferring fuel to move the location of the center of mass are provided. The location of the center of mass of the vehicle is determined by measuring or calculating forces acting on the vehicle that counteract the gravitational forces on the vehicle. The location of the center of mass is calculated by determining on a moment arm of the gravitational force that counteracts the moment arms of the other forces acting on the vehicle. Fuel can be transferred among differently-located fuel tanks in the vehicle to move the location of the center of mass to a position in which at least some of the other forces acting on the vehicle are reduced, which may increase the speed and/or efficiency of the vehicle.

The present application provides an unmanned aerial vehicle (UAV) for a long duration flight. An exemplary UAV may include a UAV body assembly. The UAV may also include a flight control system (FCS) coupled to the UAV body assembly. The UAV may further include a motor coupled to the UAV body assembly at one end and coupled to a propeller at the other end. The FCS is communicatively connected to the motor. A center of gravity (CG) of the UAV is at a point between 21% and 25% of a mean aerodynamic chord (MAC) of the UAV.

A system for monitoring the center of gravity of an aircraft includes receiving flight plan information regarding a flight plan of an aircraft indicative of planned events to occur during operation of the aircraft; predicting a center of gravity of the aircraft during operation of the aircraft based on the flight plan information; plotting a center of gravity curve based on the predicted center of gravity of the aircraft on a display, the center of gravity curve including a plurality of markers, each marker corresponding to one of the planned events, the location of each marker on the center of gravity curve indicating when during the operation of the aircraft the event is planned to occur, one of the events indicating an in-flight event; and updating the plotted center of gravity curve in real-time during operation of the aircraft based on an actual center of gravity of the aircraft.

An aircraft reconfigurator system reconfigures a predetermined aircraft configuration, in particular a cabin layout, for which a distance between a position of a center of gravity of the aircraft, the center of gravity being optimized with respect to aerodynamic characteristics, and the actual position of the center of gravity is determined and thereupon an element of the aircraft is selectively displaced such that the position of the center of gravity is approximated to the optimized position of the center of gravity. Afterwards, a new aircraft configuration, in which the selected element is arranged in the new position, is determined. By means of the reconfiguration of the aircraft it is possible to save fuel.

Systems and methods for managing a center of gravity of a vehicle on a display associated with the vehicle are provided. The method includes: determining an initial value of a center of gravity prior to a start of a journey, and receiving a value for a consumption of a fuel for the journey; determining, by a processor, a change in the center of gravity at each waypoint based on the initial value and the fuel consumed; generating a first user interface that illustrates the center of gravity at the waypoints over the journey and that illustrates that the change in the center of gravity exceeds a predefined threshold; based on the change in the center of gravity exceeding the predefined threshold, generating, a second user interface that provides a selection to bring the center of gravity below the predefined threshold; and updating the first user interface based on the selection.

A system and associated methodology determine navigation parameters of a vehicle under varying center of gravity position and varying unknown gravitational forces. The system uses high precision accelerometers arranged in a plurality of configurations.

This disclosure describes a system and method for determining the center of gravity of a payload engaged by an automated aerial vehicle and adjusting components of the automated aerial vehicle and/or the engagement location with the payload so that the center of gravity of the payload is within a defined position with respect to the center of gravity of the automated aerial vehicle. Adjusting the center of gravity to be within a defined position improves the efficiency, maneuverability and safety of the automated aerial vehicle. In some implementations, the stability of the payload may also be determined to ensure that the center of gravity does not change or shift during transport due to movement of an item of the payload.

Provided are computer-implemented methods for autonomously controlling an aircraft with vertical take-off and landing capabilities and folding wings that includes controlling a plurality of thrust producing components of an aircraft to cause the aircraft to rise vertically when wings of the aircraft are in a first folded configuration, where when the wings of the aircraft are in the first folded configuration, a leading edge of each wing is oriented in a vertical direction setting motor controller gains based on the wings of the aircraft being in the first folded configuration, and causing the aircraft to align with a direction of airflow when the wings of the aircraft are in the first folded configuration, and controlling thrust producing components and control surfaces and internal articulation mechanisms of the aircraft to cause the aircraft to transition from folded wing configuration to unfolded wing configuration. Systems and computer program products are also provided.