An aircraft operation method of providing weight and center of gravity information is used to dispatch the aircraft. The aircraft has telescoping landing gear struts and strut seals that interfere with the free movement of the strut. An event trigger generated manually or automatically by an activation device triggers measurement and recording of internal strut pressure for a period of time. The recorded pressure measurements are transmitted to a first off-aircraft computer, which determines the total weight and center of gravity of the aircraft and provides the information to an operator of the aircraft.

An apparatus for sensing an elastic deformation of a hollow element, wherein the apparatus comprises at least one sensor that is arranged in a watertight capsule which is connected in a watertight manner to a connector device comprising at least one watertight electrical connector that is electrically connected to the at least one sensor, the at least one watertight electrical connector forming a first waterproof barrier of the connector device between an outside of the watertight capsule and the at least one sensor, and wherein the connector device comprises at least one further waterproof barrier that is formed between the first waterproof barrier and the at least one sensor.

An aircraft (10) is described as including a reference axis extending along at least a portion of the aircraft, and a propulsion system having a thrust vector feature (43) defining generally a direction of thrust of the turbofan engine (18), the thrust vector feature (43) extending relative to a thrust vector axis, where the turbofan engine (18) is disposed on the aircraft with the thrust vector feature (43) oriented with respect to the reference axis of the aircraft.

The invention relates to a payload monitoring system of an aircraft, wherein the system comprises at least one storage area (26, 28, 30, 32, 36, 38, 42) for a payload and at least one pressure sensor (10), wherein the at least one sensor (10) is configured to detect a weight force and its center of gravity of payload resting on the storage area (26, 28, 30, 32, 36, 38, 42). Furthermore, the invention relates to an aircraft and a method for operating an aircraft.

The present invention provides a large-scale high-speed rotary equipment measuring and intelligent learning assembly method and device based on vector minimization geometry center, mass center, the center of gravity and the center of inertia, belonging to the technical field of mechanical assembly. The method includes the steps of establishing a four-parameter circular profile measuring model for a single stage of rotor, simplifying the established four-parameter circular profile measuring model for the single stage of rotor, and establishing a four-target optimization model of the geometry center, mass center, the center of gravity and the center of inertia of multiple stages of rotors based on the angular orientation mounting position of each stage of rotor. The device include a base, an air flotation shaft system, an aligning and tilt regulating workbench, precise force sensors, a static balance measuring platform, an upright column, a lower transverse measuring rod, a lower telescopic inductive sensor, an upper transverse measuring rod and an upper lever type inductive sensor.

A method for loading an Unmanned Aerial Vehicle with multiple items is disclosed. The method includes determining a weight, size, and Center of Gravity of each of the multiple items. The method also includes positioning the multiple items relative to one another such that a combined Center of Gravity of the multiple items will be positioned within a predetermined region. The method further includes loading the multiple items onto the Unmanned Aerial Vehicle with the combined Center of Gravity of the multiple items positioned within the predetermined region.

The methods and systems provide for increasing the accuracy of aircraft weight and center of gravity determination through the use of filtered strut pressure measurements. Aircraft vertical and horizontal accelerations are determined as the aircraft is taxiing, and used to identify and reduce the number of significantly distorted pressure measurements, to allow the lesser distorted pressure measurements to be averaged, and a lesser number of distorted pressure measurements to be averaged; further identifying the aircraft in near-neutral acceleration and strut pressure values near-neutral of strut seal friction distortions. Pressure sensors, accelerometers, and an inclinometer are mounted in relation to landing gear struts to monitor, measure and record strut pressure as related to strut telescopic movement, rates of strut telescopic movement and aircraft vertical and horizontal accelerations; experienced by landing gear struts, as the aircraft proceeds through typical ground and taxi operations.

A method for loading an Unmanned Aerial Vehicle with one or more items is disclosed. The method includes determining a Center of Gravity of each of the one or more items. The method also includes matching a combined Center of Gravity of the one or more items with a Center of Gravity of the Unmanned Aerial Vehicle.

A device for weighing aircraft includes a weighing platform configured to receive a undercarriage leg of the aircraft and to generate weighing signals, a first calculation unit configured to calculate weighing information from the weighing signals generated by the weighing platform, a communication unit configured to transmit to a central device and to receive signals including at least one signal representing the weighing information calculated by the calculation unit, and a ground rolling unit configured to move the weighing platform over a surface.

A system for determining load distribution of pieces of cargo in a cargo hold of a vehicle may include a plurality of tags, each of the plurality of tags mounted on a different piece of the pieces of cargo in the cargo hold and carrying information indicative of a weight of the different piece of cargo on which it is mounted; a plurality of sensors mounted in a spaced array along a length of the cargo hold, each of the sensors capable of reading from the tags the information indicative of the weights of the pieces of cargo; and a computer connected to receive from the plurality of sensors the information indicative of the weights and information indicative of the locations of the pieces of cargo in the cargo hold, the computer programmed to calculate therefrom a weight and/or center of gravity of the plurality of the pieces of cargo.