A Research on Take-off Weight Estimation of General Aircraft Based on Limited Design Requirements
The take-off weight of an aircraft is one of the primary parameters in the preliminary design of an aircraft.After giving the design requirements such as the payload,maximum range,cruising speed,and cruising altitude,the fuel mass ratio of the aircraft is determined by obtaining the mass ratio for each task segment.Combined with empirical formulas,the empty weight ratio of the aircraft is obtained,then the takeoff weight of the aircraft can be calculated iteratively.In the end,the effectiveness of the estimation method is validated by using the general training aircraft DA42 and business aircraft Beech Starship as examples.The absolute values of the relative errors are all around 15%.In this study,proposed estimation method combined with empirical charts are used to estimate take-off weight under limited design requirements without too much constraint on the aircraft type.It can provide technical references for the preliminary design of a new general purpose aircraft.
general aircraftpreliminary designtake-off weightaircraft empty weightfuel mass ratio
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