Abstract: 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.

Abstract: 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.

Abstract: A method of designing an aircraft component formed by a number of elements that includes a phase to estimate the effect of a variation of a design variable on the component weight which method includes the following steps: a) providing the main primary structure basic data of the aircraft component and the Reserve Factors associated to its design criteria; b) obtaining a breakdown of the component weight by such design criteria using a fictitious weight calculated taking into account the relative importance of their critical design criteria; c) obtaining the weight effect of a design variable variation, recalculating firstly the new Reserve Factors using suitable functions for the variation of the Reserve Factors vs. the variation of the design variable and, secondly, recalculating the component weight using suitable functions for the variation of the element dimensions vs. the variation of the Reserve Factors.

Abstract: A method of designing an aircraft component formed by a number of elements (j), that includes a phase to estimate the effect of a variation of a design variable on the component weight comprising the following steps: a) providing the main primary structure basic data of the aircraft component and the Reserve Factors (RFij) associated to its design criteria (i); b) obtaining a breakdown of the component weight by said design criteria (i) using a fictitious weight (mefRFij) calculated taking into account the relative importance of their critical design criteria; c) obtaining the weight effect of a design variable variation, recalculating firstly the new Reserve Factors (RFij) using suitable functions for the variation of said Reserve Factors (RFij) vs. the variation of said design variable and, secondly, recalculating the component weight using suitable functions for the variation of the element (j) dimensions vs. the variation of said Reserve Factors (RFij).