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 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 system for automatic optimization of an ejection system for an aircraft includes the ejection system having a plurality of adjustable settings. The system further includes a sensor configured to detect weight data corresponding to a weight of a user of the ejection system. The system further includes a controller coupled to the ejection system and to the sensor and configured to adjust at least one of the plurality of the adjustable settings of the ejection system based on the weight data.

A method and system for automating airline procedures, used is surveying passenger and checked baggage weights. A fully loaded aircraft is automatically weighed. A processing means subtracts weight values, including: aircraft OEW, fuel-weight, crew-weights, catering-weight, and cargo-weights; leaving only total passenger and checked baggage weights remaining. Opposing algorithms are applied to segregate total passenger weight from the total checked baggage weight; and each respective total weight is further divided by the known number of passengers to determine the average passenger weight, and the known number of checked bags to determine the average checked bag weight. Repeating these procedures for numerous flights, increases frequency of the automated survey process to a daily accumulation, to further refine to more precise average passenger weight and checked baggage weight; categorized by the day of the year, time of day, size of aircraft; and departure vs. destination cities.

A method and system for automating airline procedures, used is surveying passenger and checked baggage weights. A fully loaded aircraft is automatically weighed. A processing means subtracts weight values, including: aircraft OEW, fuel-weight, crew-weights, catering-weight, and cargo-weights; leaving only total passenger and checked baggage weights remaining. Opposing algorithms are applied to segregate total passenger weight from the total checked baggage weight; and each respective total weight is further divided by the known number of passengers to determine the average passenger weight, and the known number of checked bags to determine the average checked bag weight. Repeating these procedures for numerous flights, increases frequency of the automated survey process to a daily accumulation, to further refine to more precise average passenger weight and checked baggage weight; categorized by the day of the year, time of day, size of aircraft; and departure vs. destination cities.

A hollow profile for a WIM sensor elongates along a longitudinal direction and includes a plate-shaped force introduction element, an anchoring element and a tubular element disposed between the force introduction element and the anchoring element. The tubular element is integrally connected to the force introduction element and to the anchoring element and encloses a first cavity. The anchoring element encloses at least one second cavity. The anchoring element, tubular element and force introduction element are formed integrally with each other.

A hollow profile for a WIM sensor elongates along a longitudinal direction and includes a plate-shaped force introduction element, an anchoring element and a tubular element disposed between the force introduction element and the anchoring element. The tubular element is integrally connected to the force introduction element and to the anchoring element and encloses a first cavity. The anchoring element encloses at least one second cavity. The anchoring element, tubular element and force introduction element are formed integrally with each other.

A method of establishing a justification basis to Aircraft Regulatory Authorities, to allow a regulated aircraft to operate at increased maximum weight limitations, through the statistical identification of non-recognized weight errors being allowed in today's aircraft weight determination methods, with the recovery and utilization of the non-recognized weight errors to increase weight limitations through a Regulatory Authority finding of an Equivalent Level of Safety. A system for use in measuring aircraft weight and center of gravity, providing a method to reveal non-recognized weight errors. Sensors are attached to the landing gear struts, so to periodically and randomly measure and monitor aircraft weight and center of gravity.

A method of establishing a justification basis to Aircraft Regulatory Authorities, to allow a regulated aircraft to operate at increased maximum weight limitations, through the statistical identification of non-recognized weight errors being allowed in today's aircraft weight determination methods, with the recovery and utilization of the non-recognized weight errors to increase weight limitations through a Regulatory Authority finding of an Equivalent Level of Safety. A system for use in measuring aircraft weight and center of gravity, providing a method to reveal non-recognized weight errors. Sensors are attached to the landing gear struts, so to periodically and randomly measure and monitor aircraft weight and center of gravity.

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.