A weight estimation system for estimating weight of an aerospace vehicle while grounded, the weight estimation system comprising a measurement subsystem including at least one sensor configured to measure a physical property in an interface that interfaces at least one of a fuselage and a wing with an undercarriage of said aerospace vehicle, in at least one area exhibiting a measurable change in geometry that is at least partly due to said weight, said measurement subsystem configured to produce measured data indicative of said weight of said aerospace vehicle; and a processor for receiving at least part of said measured data, said processor configured to estimate said weight, by relating said measured data with predetermined physical-property-to-weight correspondence data associated with said aerospace 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.

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.

A method converts an aircraft takeoff trim setting that would be a function of several parameters to a value that is a function of CG position only. In this way, it is possible to create a direct simple equivalence between Stabilizer angle and CG. The equivalent CG can be presented in real time to the pilot.

The Lopsided Payload Carriage Gimbal in all 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

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.

A calibrating device, for measuring and calibrating a center of gravity of a remote control aircraft or an airfoil thereof, includes a crossbar, a first support, a second support and a control unit. The crossbar is arranged along a longitudinal axis, and includes a longitudinal rail and a slider. The slider is movably engaged with the longitudinal rail. The crossbar includes a drive member coupled with the longitudinal rail or the slider. The slider includes a pointer. The first support includes a seat and two receiving portions which are arranged on the seat and are movable along a transverse axis. The receiving portions are aligned with each other. Each receiving portion includes a load cell. The second support includes a base and a supporting portion, and the supporting portion includes a load cell. The control unit is coupled with the drive member and the three load cells.

A system for detecting vehicle load anomalies during ground travel includes at least one inertial sensor sensing a pitch or a roll of a vehicle and outputting at least one of a pitch or a roll value; a computing device having a processor and a memory and an input coupled to an input and monitoring module, where said input and monitoring module receives one of the pitch or roll values output by the at least one inertial sensor, and said computing system further having a measuring module measuring an oscillation based on one of the output pitch or roll values and calculating an adjusted center of gravity value based on a comparison between an expected oscillation and the measured oscillation; said computing device having an output to an alert module that outputs an alert signal through said output if the adjusted center of gravity is outside of a predetermined threshold.

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.

A method of determining and identifying acceptable and unacceptable ranges of loads applied to a nose landing gear of an aircraft on the ground during passenger loading and unloading events. A method of determining and identifying acceptable and unacceptable ranges of loads applied to a nose landing gear of an aircraft on the ground during baggage and cargo loading and unloading events. A method of determining and identifying acceptable and unacceptable ranges of loads applied to a main landing gear of an aircraft on the ground during a fuel loading event. A method for aircraft flight crew and ground support personnel to monitor and identify in real-time, unanticipated loads experienced by the aircraft landing gear; to better manage the loading and unloading of passengers, baggage and cargo to and from an aircraft. Pressure sensors are attached to telescopic landing gear, which monitor the working pressure within the aircraft landing gear, and further identify and illuminate an onboard indicator to recognize unanticipated loads experienced by the nose landing gear during the passenger movement within the aircraft cabin while the aircraft is on the ground. Unbalanced fuel loading is recognized by asymmetrical pressures within the main landing gear struts, and identified during the aircraft fueling process.