Onboard weight and balance detection system for an aircraft

A method comprising:

• obtaining, at a computer system of an aircraft during loading and unloading of the aircraft, pressure data and temperature data for gas in respective ones of shock struts of a plurality of landing gear of the aircraft;
• obtaining, at the computer system during the loading and the unloading of the aircraft, load data for each landing gear of the plurality of landing gear from one or more load sensors associated with the landing gear;
• determining, at the computer system, a gross weight of the aircraft based on a pitch of the aircraft from output of one or more attitude sensors, the pressure data, the temperature data, the load data, model parameters, or combinations thereof;
• accumulating, at the computer system, selected pressure data, selected temperature data, selected load data, and the pitch of the aircraft as calibration data for transitions of shock struts from dynamic states to static states;
• obtaining, at the computer system, updated model parameters based on the calibration data;
• and
• replacing, via the computer system, one or more of the model parameters with corresponding updated model parameters in response to satisfaction of a threshold.

A non-transitory, computer-readable medium comprising instructions that, when executed by one or more processors associated with an onboard weight and balance system of an aircraft, cause the one or more processors to:

• obtain, during loading and unloading of the aircraft, pressure data and temperature data for gas in respective ones of shock struts of a plurality of landing gear of the aircraft;
• obtain, during the loading and the unloading of the aircraft, load data for each landing gear of the plurality of landing gear from one or more load sensors associated the landing gear;
• determine a gross weight of the aircraft based on a pitch of the aircraft from output of one or more attitude sensors, the pressure data, the temperature data, the load data, model parameters, or combinations thereof;
• accumulate selected pressure data, selected temperature data, selected load data, and the pitch of the aircraft as calibration data for transitions of shock struts from dynamic states to static states;
• obtain updated parameters for the model parameters based on the calibration data;
• and
• replace one or more of the model parameters with corresponding updated model parameters in response to satisfaction of a threshold.