Abstract: 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.

Abstract: 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.

Abstract: Aircraft landing gear strut breakout friction values are used to correct measured strut pressure as related to the amount of weight supported; with the ability to generate and refine the breakout friction value database, and ability to predict a future breakout friction correction value by trending historical measurements, as compared to recent measurements, as further compared to real-time breakout friction values. The system is used in monitoring, measuring, computing and displaying the weight and center of gravity for aircraft utilizing telescopic oleo landing gear struts.

Abstract: 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.

Abstract: The method obtaining a change to approved weight limits of a regulated aircraft type comprises the steps of determining a difference between a first maximum takeoff weight limit and a second maximum takeoff weight limit and, using the difference between the first maximum takeoff weight limit and the second maximum takeoff weight limit, identifying the second maximum takeoff weight difference as a percentage of the first maximum weight limit. In other embodiments, a second maximum landing weight limit, a second maximum takeoff weight limit, a second zero-fuel weight limit, and a second maximum ramp weight limit, are each identified as a percentage of the first maximum takeoff weight limit.

Abstract: 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 signaling departure is detected from aircraft operations at a loading area. Internal strut pressure is measured and recorded upon detection for a period of time as the aircraft moves away. 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: Aircraft landing gear strut breakout friction values are used to correct measured strut pressure as related to the amount of weight supported; with the ability to generate and refine the breakout friction value database, and a farther ability to predict a future breakout friction correction value by trending historical measurements, as compared to recent measurements, as further compared to real-time breakout friction values. The system is used in monitoring, measuring, computing and displaying the weight and center of gravity for aircraft utilizing telescopic oleo landing gear struts.

Abstract: Aircraft landing gear strut breakout friction values are used to correct measured strut pressure as related to the amount of weight supported; with the ability to generate and refine the breakout friction value database, and a further ability to predict a future breakout friction correction value by trending historical measurements, as compared to recent measurements, as further compared to real-time breakout friction values. The system is used in monitoring, measuring, computing and displaying the weight and center of gravity for aircraft utilizing telescopic oleo landing gear struts.

Abstract: A method for validating or invalidating the computed weight of an aircraft, where the computed weight of the aircraft is determined by compiling various weight assumptions added to a known empty weight of the aircraft. The method measures the aircraft center of gravity, determines the percentage of computed weight supported by the combined main landing gear struts, and using a database such as a look-up table to validate if the percentage of computed weight is determined within a reasonable range to the measured load on the combined main landing gear struts. Sensors are attached to the landing gear struts, so to measure and monitor aircraft loads and center of gravity without measuring the aircraft weight.

Abstract: 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.

Abstract: 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.

Abstract: A method which determines aircraft Center of Gravity independent of measuring the aircraft weight. The method is used in monitoring, measuring and computing the Center of Gravity of an aircraft utilizing pressurized, telescopic landing gear struts with axles. Pressure sensors are mounted in relation to each of the landing gear struts to monitor, measure and record aircraft landing gear strut loads by way of pressure. Axle deflection sensors are mounted in relation to each of the landing gear axles to monitor, measure and record aircraft landing gear axle loads by way of deflection.

Abstract: 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.

Abstract: A method for determining a Center of Gravity of an aircraft, which is independent of measuring the aircraft weight. The total aircraft weight is determined by a method independent of measuring the weight supported by the main landing gear struts. The weight supported by the nose landing gear strut is subsequently measured. The measured weight associated with nose landing gear is subtracted from the independently determined total aircraft weight, to determine a calculated weight supported by the combined main landing gear struts. The resulting determined weight supported by the combined main landing gear is compared to the independently determined total aircraft weight, and allows for determination of the aircraft Center of Gravity. Inversely the measured nose strut weight is compared to the total aircraft weight, and allows for determination of the aircraft Center of Gravity. Aircraft Center of Gravity is determined without the total aircraft weight being measured.

Abstract: A method which determines aircraft Center of Gravity independent of measuring the aircraft weight. The method is used in monitoring, measuring and computing the Center of Gravity of an aircraft utilizing pressurized, telescopic landing gear struts with axles. Pressure sensors are mounted in relation to each of the landing gear struts to monitor, measure and record aircraft landing gear strut loads by way of pressure. Axle deflection sensors are mounted in relation to each of the landing gear axles to monitor, measure and record aircraft landing gear axle loads by way of deflection.

Abstract: A landing load monitor is used for aircraft during a carrier-type landing event having an arresting cable. The aircraft is provided with a tail-hook assembly that includes a tail-hook and a mounting assembly. The tail-hook is coupled to the aircraft by way of the mounting assembly. A sensor measures the load applied by the tail-hook to the aircraft. A processor is connected to the sensor. The tail-hook loads during a landing event over elapsed time are stored in memory for subsequent retrieval and analysis. The sensor may be located on the tail-hook itself or in the mounting assembly. The aircraft is also provided with inboard and outboard accelerometers on each wing. In addition, the landing gear has pressure sensors to monitor the internal pressure of the landing gear struts. These additional sensors are used during the landing event to monitor the loads on the aircraft. They are also used to identify asymmetrical landings.

Abstract: A system for use in monitoring, measuring, computing and displaying the volumes of internal gas within a telescopic aircraft landing gear strut. Pressure sensors and temperature sensors and motion sensors are mounted in relation to each of the landing gear struts to monitor, measure and record the impact movement and rates of internal landing gear strut fluids; experienced by landing gear struts, as the aircraft landing gear initially come into contact with the ground. The computer of this system measures the compression experienced by each landing gear strut and determines if the landing gear strut is improperly serviced with either excess or deficient volumes of nitrogen gas. Additional features include automating the inspections required to aircraft landing gear, prior to flight, during flight and during landing events.