Electrical supply system of an aircraft

An electrical supply system for an aircraft comprising:

• a first electrical source, wherein the first electrical source is mechanically coupled to a primary energy source which is coupled to at least one energy consumer other than the first electrical source,
• a second electrical source coupled to the first electrical source and configured to electrically supply electrical power a group of electrical loads in the aircraft, and
• a controller configured to:
• determine an instantaneous electrical consumption consumed by the group of electrical loads;
• determine an instantaneous nominal power capable of being delivered by the primary energy source;
• determine an instantaneous power drawn by the at least one energy consumer from the primary energy source;
• and
• control the first electrical source and the second electrical source so that:
• the power drawn by the first electrical source from the primary energy source corresponds to a difference between the instantaneous nominal power capable of being delivered by the primary energy source and the instantaneous power drawn by the at least one energy consumer, so as to ensure that the mechanical power drawn by the first electrical source and by the at least one energy user is never greater than the instantaneous nominal power capable of being delivered by the primary energy source, and
• an electrical power delivered by the second electrical source is such that a sum of an electrical power delivered by the first electrical source and the electrical power delivered by the second electrical source corresponds to the instantaneous electrical consumption.