Systems, computer-implemented methods and/or computer program products that facilitate measuring weight and balance and optimizing center of gravity are provided. In one embodiment, a system 100 utilizes a processor 106 that executes computer implemented components stored in a memory 104. A compression component 108 calculates compression of landing gear struts based on height above ground of an aircraft. A gravity component 110 determines center of gravity based on differential compression of the landing gear struts. An optimization component 112 automatically optimizes the center of gravity to a rear limit of a center of gravity margin.

An unmanned aerial vehicle (UAV) control method includes obtaining target flight data and current flight data; determining a control state variable based on the target flight data and the current flight data; and calibrating a center of gravity of the UAV based on the control state variable.

There is provided a system for determining real-time parameters of an aircraft, the system comprising: at least two sensing apparatus, each of the at least two sensing apparatus including a plurality of in-ground sensors; and at least one processing apparatus to process data received from the at least two sensing apparatus. It is preferable that a positioning of the at least two sensing apparatus is determined by a type of the aircraft being measured.

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 device for controlling a balance of an urban air mobility, may include a receiver configured to receive occupant information related to the urban air mobility from a cloud server; and a controller configured to control the balance of the urban air mobility according to the received occupant information.

A system and method for moving an item using an unmanned aerial vehicle (UAV) are described herein. The system includes an unmanned aerial vehicle (UAV), and a mechanism attached to the UAV. The mechanism is configured to grab an item located substantially horizontally vis--vis the UAV or to a lateral side of the UAV. The mechanism is configured to maintain a balance of the UAV such that a center of gravity of the UAV including the mechanism is located substantially on a vertical line containing an original center of gravity of the UAV without the mechanism.

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 method for improving inflight fuel efficiency of an aircraft includes sensing aircraft fuel weight in the aircraft fuel tanks and reading the fuel weight by a flight management system during aircraft flight; calculating a current center of gravity position from the fuel weight; calculating an aircraft longitudinal trim drag factor from the current center of gravity; and adjusting a fuel burn prediction utilizing the longitudinal trim drag factor. A system for improving aircraft inflight fuel efficiency includes a flight management system programmed to calculate a current center of gravity position from a current aircraft fuel weight, calculate a longitudinal trim drag factor from the current center of gravity, adjust a fuel burn prediction, and display in the flight deck an adjusted fuel burn prediction for each leg of aircraft flight, which is used to adjust aircraft performance automatically by the flight control system or by the pilot.

Embodiments are directed to obtaining data from at least one sensor, the data pertaining to rotor loads and motion, processing, by a device comprising a processor, the data to obtain an estimate of at least one of gross weight (GW) and center of gravity (CG) for a rotorcraft, and outputting the estimate.

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.