Onboard aircraft weight and balance detection system

A method of determining weight of an aircraft having a plurality of landing gear, wherein each landing gear includes a shock strut, the method comprising:

• obtaining, at a computer system, pressure data and temperature data for gas in respective ones of shock struts of the plurality of landing gear during loading or unloading of the aircraft;
• determining, by the computer system for each shock strut of the plurality of landing gear for a first time corresponding to an end of a first change in gas pressure due to movement of a piston of the shock strut during the loading or the unloading of the aircraft, a friction value associated with the shock strut based on a gas pressure at the first time indicated by the pressure data and a gas temperature at the first time indicated by the temperature data;
• and
• computing, by the computer system for a particular time before the loading or the unloading of the aircraft causes a second change in gas pressure of one or more of the shock struts as indicated by the pressure data for the shock struts, a weight of the aircraft based on the gas pressures of the shock struts at the first times and the friction values associated with the shock struts at the first times.

A non-transitory computer-readable medium comprising instructions executable by one or more processors associated with an aircraft, wherein the instructions are configured to:

• obtain pressure data and temperature data for gas in respective ones of shock struts of landing gear of the aircraft during loading or unloading of the aircraft;
• obtain an attitude of the aircraft;
• obtain load sensor data from load sensors associated with each landing gear, wherein the load sensor data for each landing gear corresponds to vertical load exerted by the landing gear on the aircraft;
• determine, for each shock strut for a first time corresponding to an end of a first change in gas pressure due to movement of a piston of the shock strut during the loading or the unloading of the aircraft, a friction value associated with the shock strut based on a gas pressure at the first time indicated by the pressure data and a gas temperature at the first time indicated by the temperature data;
• determine for each shock strut for a particular time before the loading or the unloading of the aircraft causes a second change in gas pressure of one or more of the shock struts as indicated by the pressure data for the shock struts, a load delta value for each shock strut at the particular time;
• compute, for the particular time, a weight of the aircraft based on the attitude, the gas pressures, the friction values associated with the shock struts, the load delta values associated with the shock struts at the particular time, and unsupported weights of components of each landing gear not supported by the gas pressure in the shock strut for each of the shock struts at the particular time;
• and
• provide, to one or more display devices, first output that indicates the weight of the aircraft.