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.

Abstract: A method which creates a justification basis to expand an aircraft's Center of Gravity limitations, which are established by the aircraft designer; relating to aircraft landing gear strength assumptions. Strut load sensors such as pressure sensors are mounted in relation to each of the landing gear struts to monitor, measure and record aircraft landing gear strut compression loads. A history of measured landing gear load values is compiled and related to any assumed landing gear loads, which define the life-cycle limit of the landing gear, allowing relief from existing aircraft Center of Gravity limitation caused by landing gear strength assumptions to further expanded CG limitations beyond current limits, based on measured landing gear loads.

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.

Abstract: A method and apparatus for determining the weight of a C-130 aircraft with jack-screw landing gear compression loads applied to a C-130 aircraft main landing gear strut jack-screw friction washer. For each main landing gear, a thru-hole load cell is mounted to the bottom of the jack-screw so that the weight of the aircraft bears on the load cell. The load cells are connected to a computer which measures the loads and determining the weight and center of gravity of the aircraft.

Abstract: A system for use in monitoring, measuring, computing and displaying the volumes of internal liquid and 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 hydraulic oil and nitrogen gas. Additional features include automating the inspections required to aircraft landing gear, prior to flight, during flight and during landing events.

Abstract: A system for use in monitoring, measuring, recording, computing and transmitting the oxygen levels and identification of oxygen contamination within an aircraft telescopic landing gear strut. An oxygen sensor is mounted in relation to each of the landing gear struts as to monitor, recognize, measure and record the identification of oxygen within the telescopic landing gear struts. The amount of oxygen within each landing gear strut is measured and recorded and downloaded to the responsible aircraft maintenance department. By detecting the amount of oxygen in a strut, steps can be taken to purge the gas from the strut to minimize corrosion of strut components and to prevent internal combustion of the gas and oil in the strut.

Abstract: A system and method for the determination for automated initiation of onboard aircraft weight and balance measurement systems. The system is used in monitoring, measuring, computing and displaying the weight and balance of aircraft utilizing telescopic landing gear struts. Pressure sensors, axle deflection sensors, and/or linkage rotation sensors are mounted in relation to each of the landing gear struts to monitor, measure and record strut and aircraft movement and rates of said movement experienced by landing gear struts, as the aircraft proceeds through typical ground and flight operations. Also, acceleration sensors and GPS can be used to monitor aircraft movements and positions during ground and flight operations. The system and method identify the position of the aircraft as related to airport ground operations to determine the optimum time to initiate an aircraft weight and balance measurement.

Abstract: A system for use in monitoring, measuring, recording, computing and transmitting the oxygen levels and identification of oxygen contamination within an aircraft telescopic landing gear strut. An oxygen sensor is mounted in relation to each of the landing gear struts as to monitor, recognize, measure and record the identification of oxygen within the telescopic landing gear struts. The amount of oxygen within each landing gear strut is measured and recorded and downloaded to the responsible aircraft maintenance department. By detecting the amount of oxygen in a strut, steps can be taken to purge the gas from the strut to minimize corrosion of strut components and to prevent internal combustion of the gas and oil in the strut.

Abstract: A method of establishing a justification basis to Aircraft Regulatory Authorities, to allow for a reduction in aircraft sink-speed assumptions. To further allow the aircraft to operate an increased maximum landing weight limitation. A system for use in measuring aircraft vertical velocity at initial contact with the ground, experienced while aircraft are executing either normal or hard landing events. Pressure sensors are attached to the working pressure within the landing gear strut, so to monitor in-flight landing gear strut pre-charge pressure, until such time as the pre-charge pressure suddenly increases, to detect the aircraft has come into initial contact with the ground. Rotation sensors are attached to the hinged elements of the landing gear strut, so to monitor in-flight landing gear strut extension, until such time as the strut extension suddenly decreases, to detect the aircraft has come into initial contact with the ground.

Abstract: A system for use in monitoring, measuring, computing and displaying the rate of compression of aircraft landing gear struts, experienced while aircraft are executing either normal or hard landing events. Further by measuring the vertical compression rate of the landing gear strut, thus with aircraft hull angle correction to horizontal, determining the vertical sink-rate of the aircraft, as it comes into initial contact with the ground. Accelerometers are attached to opposing sides of a compressible landing gear strut, monitoring and measuring parallel data streams; then identifying differential acceleration data streams, which computed through mathematical algorithms measure the collapse rate of the landing gear strut. Pressure sensors are attached to the working pressure within the landing gear strut, so to monitor in-flight landing gear strut pre-charge pressure, until such time as the pre-charge pressure suddenly increases, to detect the aircraft has come into initial contact with the ground.

Abstract: A system for use in monitoring, measuring, computing and displaying the volumes of internal liquid and 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 hydraulic oil and nitrogen gas. Additional features include automating the inspections required to aircraft landing gear, prior to flight, during flight and during landing events.

Abstract: A system for use in monitoring, measuring, computing and displaying the rate of compression of aircraft landing gear struts experienced while aircraft are executing either normal or hard landing events. A high speed computer attached to high speed cameras, or range-finders, mounted in relation to each of the landing gear struts are used to monitor, measure and record the landing gear compression rates and aircraft touch-down vertical velocities experienced by landing gear struts, as the aircraft landing gear initially comes into contact with the ground. The system also determines through landing gear strut compression rates if aircraft landing limitations have been exceeded.

Abstract: A system for use in monitoring, measuring, computing and displaying the initial touch-down descent velocity experienced while aircraft are executing either normal, overweight or hard landing events. Pressure sensors and motion sensors are mounted in relation to each of the landing gear struts to monitor, measure and record the impact loads and aircraft touch-down vertical velocities experienced by landing gear struts, as the aircraft landing gear initially comes into contact with the ground. Velocity adjustments are made to correct for errors caused by landing gear per-charge pressure and landing gear strut seal friction. The system also measures the landing loads experienced by each landing gear strut during the landing event and determines if aircraft limitations have been exceeded.

Abstract: A system for use in monitoring, measuring, computing and displaying the Kinetic Energy generated and experienced while aircraft are executing either normal, overweight or hard landing events. Pressure sensors and motion sensors are mounted in relation to each of the landing gear struts to monitor, measure and record the impact loads and aircraft touch-down vertical velocities experienced by landing gear struts, as the aircraft landing gear initially comes into contact with the ground. Velocity adjustments are made to correct for errors caused by landing gear per-charge pressure and landing gear strut seal friction. The system also measures the landing loads experienced by each landing gear strut during the landing event and determines if aircraft limitations have been exceeded.

Abstract: A system for use in monitoring, measuring, computing and displaying the landing loads experienced while aircraft are executing either normal, overweight or hard landing events. Pressure sensors and motion sensors are mounted in relation to each of the landing gear struts to monitor, measure and record the impact loads and aircraft sink rates; experienced by landing gear struts, as the aircraft landing gear initially come into contact with the ground. The computer of this system measures the landing loads experienced by each landing gear strut and determines if a hard landing event has occurred. Additional features include automating the inspections required to aircraft components, after overweight or hard landing events.

Abstract: An onboard system for use in measuring, computing and displaying the weight and center-of-gravity for aircraft, while keeping aircraft movement to a minimum. Pressure sensors are mounted in relation to each of the landing gear struts. An onboard pump and reservoirs are attached to each of the landing gear struts and are activated by a computer/controller, while landing gear strut pressures are monitored in the determination of strut stiction. The computer/controller calculates the stiction of each landing gear strut and compensates for the pressure distortions caused by landing gear strut stiction. Additional features include reducing strut stiction, measuring landing gear strut fluid levels, monitoring landing gear strut health, weight adjustments for external ice and de-icing fluids, weight adjustments for wind, monitoring aircraft landing gear strut movement.

Abstract: An onboard system for use in measuring, computing and displaying the weight and center-of-gravity for aircraft, while keeping aircraft movement to a minimum. Pressure sensors are mounted in relation to each of the landing gear struts. An onboard pump and reservoirs are attached to each of the landing gear struts and are activated by a computer/controller, while landing gear strut pressures are monitored in the determination of strut stiction. The computer/controller calculates the stiction of each landing gear strut and compensates for the pressure distortions caused by landing gear strut stiction. Additional features include reducing strut stiction, measuring landing gear strut fluid levels, monitoring landing gear strut health, weight adjustments for external ice and de-icing fluids, weight adjustments for wind, monitoring aircraft landing gear strut movement.