Minimum Energy Cruise of All-Electric Aircraft with Applications to Advanced Air Mobility
This work addresses the critical challenge of limited battery energy density for sustainable Advanced Air Mobility, offering incremental improvements in energy optimization for electric aircraft.
The paper tackles the problem of minimizing total energy consumption for all-electric aircraft in steady cruise flight by formulating it as an optimal control problem, deriving closed-form solutions for optimal airspeed and final cruise time, and providing analytical feasibility conditions, with numerical simulations illustrating the influence of factors like aircraft weight and battery charge.
Electrified propulsion is expected to play an important role in the sustainable development of Advanced Air Mobility (AAM). However, the limited energy density of batteries motivates the need to minimize energy consumption during flight. This paper studies the minimum total energy problem for an all-electric aircraft in steady cruise flight. The problem is formulated as an optimal control problem in which the cruise airspeed and final cruise time are optimization variables. The battery supply voltage is modeled as an affine function of the battery charge. Pontryagin's Minimum Principle is used to derive the necessary and sufficient conditions for optimality, from which closed-form expressions for the optimal cruise airspeed and optimal final cruise time are obtained. Additional analytical conditions are derived that determine when all-electric operation is feasible, one of which is that sufficient electric charge must be available. Numerical simulations based on the BETA Technologies CX300 all-electric aircraft and a representative AAM scenario illustrate how the aircraft weight, cruising altitude, electrical system efficiency, and initial battery charge influence the optimal airspeed and the feasibility of all-electric cruise.