Aircraft propulsion system with engine ratings as a function of system components

A hybrid-electric propulsion system, comprising:

• a thermal engine;
• an electrical propulsion subsystem having a plurality of components;
• and
• a system controller in communication with the thermal engine, the electrical propulsion subsystem, and a non-transitory memory storing instructions, wherein the stored instructions include a set of first engine ratings for operating the hybrid-electric propulsion system, the first engine ratings based at least in part on one or more first performance and/or capability parameters of a first electrical propulsion subsystem component, which instructions when executed cause the system controller to:
• subsequent to the one or more first performance and/or capability parameters of the first said electrical propulsion subsystem component being replaced with one or more second performance and/or capability parameters, wherein the one or more second performance and/or capability parameters are different from the one or more first performance and/or capability parameters, use a set of alternative engine ratings based at least in part on the one or more second performance and/or capability parameters;
• and
• control the hybrid-electric propulsion system using the set of alternative engine ratings and the one or more second performance and/or capability parameters;
• wherein the set of original engine ratings and the set of alternative engine ratings are both covered by a first type certification of the thermal engine.

A method of operating an a hybrid-electric aircraft propulsion system, the system having a thermal engine and an electrical propulsion system having a plurality of components, comprising:

• providing a set of original engine ratings and limits for operating the hybrid-electric propulsion system, wherein the set of original engine ratings and limits is based at least in part on one or more first performance and/or capability parameters of an original electrical propulsion subsystem component;
• identifying an alternative electrical propulsion system component, the alternative electrical propulsion subsystem component having one or more second performance and/or capability parameters, wherein the one or more second performance and/or capability parameters are different from the one or more first performance and/or capability parameters;
• producing a set of alternative engine ratings and limits for the alternative electrical propulsion subsystem component based at least in part on the one or more second performance and/or capability parameters;
• and
• subsequent to replacing the first electrical propulsion subsystem component with the alternative electrical propulsion subsystem component, using the set of alternative engine ratings and limits based at least in part on the one or more second performance and/or capability parameters;
• and
• controlling the hybrid-electric aircraft propulsion system using the set of alternative engine ratings and limits and the one or more second performance and/or capability parameters of the alternative electrical propulsion subsystem components;
• wherein the set of original engine ratings and limits and the set of alternative engine ratings and limits are both covered by a first type certification of the hybrid-electric aircraft propulsion system.