Safety-driven baselining of hybrid electric aircraft electrical power system architectures

Electrification of aircraft power and propulsion systems is critical for reduction of aircraft emissions (greenhouse
gases and acoustic noise). The disruptive nature of electrical propulsion systems for aircraft, and the
associated lack of legacy electrical power system (EPS) solutions presents as an opportunity for new solutions
to optimize the overall performance of these new aircraft. However, the lack of legacy architecture solutions,
combined with the increased power levels of hybrid electric aircraft, is a major challenge to the design of EPS
to meet performance requirements (reliability, weight, volume, efficiency).

Existing approaches to EPS design for aircraft with electrical propulsion (all or hybrid) assume a starting point
with a comprehensive set of baseline requirements, sufficient to commence informed EPS design. This paper
directly addresses the challenge of how to determine these baseline requirements for a new concept aircraft
with minimal initial design criteria, and ensure that architectures developed will meet safety requirements. This
is achieved by translation of expected certification criteria to failure modes, during the occurrence of which flight
must be maintained. From these, baseline requirements for subsequent EPS designs, including system trades
for optimized EPS architecture solutions and interfaces with non-electrical power systems, are captured.
Through a case study for a concept, low emission distributed, hybrid electric propulsion, long aspect wing ratio
aircraft, capture of baseline criteria and subsequent EPS design (including system design trades) and interfaces
to associated non-EPS systems design is demonstrated.