Systems and method for an electrical system on an aircraft are provided. In example embodiments, the electrical system can be for an aircraft having a turbine engine. The turbine engine having a high pressure (HP) spool and a low pressure (LP) spool. The HP spool can be configured to drive a first generator to provide a first electrical output. The LP spool can be configured to drive a second generator to provide a second electrical output. The first generator and the second generator can be coupled to an electrical power distribution bus that provides electrical power to a load. A hybrid electric propulsion system and a secondary aircraft systems bus can both be coupled to the electrical power distribution bus. The electrical system can further include a control system configured to allocate power among the first generator, the second generator, and the hybrid electric propulsion system, and the secondary aircraft systems bus.