A computationally efficient and cost effective simulation framework has been implemented to perform design space
exploration and multi-objective optimization for an advanced regenerative rotorcraft powerplant configuration at mission
level. The proposed framework is developed by coupling a comprehensive rotorcraft mission analysis code with a design
space exploration and optimization package. The overall approach is deployed to design and optimize the powerplant of a
reference twin-engine light rotorcraft, modelled after the Bo105 helicopter, manufactured by Airbus Helicopters. Firstly, a
sensitivity analysis of the regenerative engine is carried out to quantify the interrelationship between the engine
thermodynamic cycle design parameters, engine weight, and overall mission fuel economy. Secondly, through the execution
of a multi-objective optimization strategy, a Pareto front surface is constructed, quantifying the optimum trade-off between
the fuel economy offered by a regenerative engine and the associated weight penalty. The optimum sets of cycle design
parameters obtained from the structured Pareto front suggest that the employed heat exchanger effectiveness is the key design
parameter affecting the engine weight and fuel efficiency. Furthermore, through quantification of the benefits suggested by
the acquired Pareto front, it is shown that, the fuel economy offered by the simple cycle rotorcraft engine can be substantially
improved with the implementation of regeneration technology, without degrading the payload-range and airworthiness (One-
Engine-Inoperative) requirements of the rotorcraft
