Benefit evaluation method for aviation hybrid electric propulsion system

Abstract

The invention discloses a benefit evaluation method for an aviation hybrid electric propulsion system. The benefit evaluation method comprises the following steps: S1, obtaining input of benefit evaluation from an aircraft manufacturer; s2, establishing component coefficient tables of hybrid power, pure power and traditional propulsion systems; s3, calculating the equal weight of the gas turbine engine according to the input of benefit evaluation and the component coefficient table; s4, obtaining a cruise stage distance iterative calculation formula suitable for different propulsion systems, and determining a cruise stage distance through iterative calculation; s5, calculating related parameters such as the comprehensive total cost per kilometer of unit commercial load and the maximum power capability index under the sea level high temperature condition; and S6, calculating the relative proportion of the corresponding indexes of the propulsion system by taking the related parameters of the traditional propulsion system as the reference and combining the related parameters of the to-be-evaluated propulsion system, configuring a weight coefficient, and calculating to obtain the comprehensive income coefficient of the to-be-evaluated propulsion system. The precision of the evaluation result is improved, and a reliable basis is provided for scheme design and power type selection of the flight platform.

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