A method for directly determining a theoretical damage of at least one component of a device includes providing load-specific reference data in an evaluation unit, sensing actual load-specific data by a load sensing system, and transmitting the actual, load-specific data to the evaluation unit. The actual load-specific data includes classified load collectives comprising a dwell time of occurring damage variables at defined load levels, a number of load changes of occurring damage variables, and an event count of occurring damage variables. The method further includes scaling the load-specific reference data to the actual load-specific data for calculating the theoretical damage of the at least one component and determining a remaining service life.

A system to estimate the good distribution of loading onboard an aircraft capable of carrying out a target mission. The system includes at least one operability index determination module, a module for verifying whether the distribution of loading onboard the aircraft is considered to be a good distribution by comparing the operability index of the target mission with a predetermined operability index threshold. The determination of the operability index makes it possible to know whether the aircraft can carry out a target mission in good conditions.

A method for directly determining a theoretical damage of at least one component of a device includes providing load-specific reference data in an evaluation unit, sensing actual load-specific data by a load sensing system, and transmitting the actual, load-specific data to the evaluation unit. The actual load-specific data includes classified load collectives comprising a dwell time of occurring damage variables at defined load levels, a number of load changes of occurring damage variables, and an event count of occurring damage variables. The method further includes scaling the load-specific reference data to the actual load-specific data for calculating the theoretical damage of the at least one component and determining a remaining service life.

A method and system for determining the weight and at least a first coordinate of the center of gravity of a structure such as a vehicle, in particular, an aircraft.

A cargo restraint system and associated methods may include sensing assemblies associated with cargo latches in a cargo hold of an aircraft. In some embodiments, the sensing assemblies include sensors configured to sense information relating to the cargo latches, wireless communication circuits configured to transmit the sensed information to a central controller, and batteries powering the wireless communication circuits. A wireless power transmission system may be configured to wirelessly broadcast power to the sensor assemblies to charge the batteries. In some embodiments, the cargo latches are transitionable between an extended configuration for cargo restraint and a retracted configuration for cargo loading and unloading, and the sensors are configured to sense whether the cargo latches are in the extended configuration.

A system of hardware and software for determining the weight and center of gravity location of an airplane or other vehicles, like a forklift, truck, maritime vessel. The same system could be used to determine stresses or movement on stationary structures is disclosed. This system employs commercially available, off the shelf or existing, proven, and inexpensive technology and utilizes empirical data. Further, it is designed as a supplemental check on calculated results, which are subject to data errors and are circumvented by this invention's equipment. The system includes a set of pressure and load, strain, bending, and/or other sensors, a voltage source, a voltmeter, a computer, a display, an empirically derived database, a temperature sensor, a set of switches, wireless transmission, and a power source that allows the system to be used for determining the weight and center of gravity location of an airplane or other vehicle.

A system of hardware and software for determining the weight and center of gravity location of an airplane or other vehicles, like a forklift, truck, maritime vessel. The same system could be used to determine stresses or movement on stationary structures is disclosed. This system employs commercially available, off the shelf or existing, proven, and inexpensive technology and utilizes empirical data. Further, it is designed as a supplemental check on calculated results, which are subject to data errors and are circumvented by this invention's equipment. The system includes a set of pressure and load, strain, bending, and/or other sensors, a voltage source, a voltmeter, a computer, a display, an empirically derived database, a temperature sensor, a set of switches, wireless transmission, and a power source that allows the system to be used for determining the weight and center of gravity location of an airplane or other vehicle.

A method and system for determining and implementing weight distribution of payload on an aircraft for optimizing centre of gravity of the aircraft by providing an individual weight factor for each passenger and/or crew member and their respective hand luggage and allocating at least a portion of the passengers and/or crew members seats according to the effect of passenger and/or crew member's positions on the aircraft on centre of gravity position provides advantages in determining accurately cabin payload data and cabin payload distribution for optimum fuel efficiency of an aircraft on a flight. Thus, fuel may be saved and carbon dioxide emissions may be reduced.

An aircraft undercarriage has an axle for carrying at least one wheel. The undercarriage further includes a magnetic measurement target and at least one magnetic movement sensor cooperating with the magnetic measurement target to measure bending of the axle. The magnetic measurement target has a body that extends inside the axle and includes a fastener end fastened to one end of the axle. The body also include a target surface that extends over an inside surface of the body. The magnetic movement sensor is positioned inside the axle to measure movement of the target surface.

The Lopsided Payload Carriage Gimbal in al its embodiments allow Aerial Vehicles and Water-borne vehicles to carry payloads far from the vehicle Geometric Center without significant travel of the vehicle's overall Center of Gravity. Large travel of the CG limits vehicle's performance or renders it inoperable. The embodiments rely on the interaction of the payload and the counter balancing weight through the payload link 18, balancing link 10 main link 14 and battery pylon 8 to substantially reduce the torque generated by the payload in a lopsided position. The embodiments also allow the vehicle carrying the payload to change thrust direction agilely. Finally, the embodiment acts as a mechanical stabilization device for the payload as well. This invention is adaptable to all forms of hover-capable aerial vehicles as well as water-borne vehicles.