SYSTEMS AND METHODS OF POWER ALLOCATION FOR TURBOPROP AND TURBOSHAFT AIRCRAFTS

Systems and method (400) for an electrical system on an aircraft (10) are provided. In example aspects, the electrical system can be for an aircraft (10) having a turbine engine (102, 104). The turbine engine having a high pressure (HP) spool (34, 35) and a low pressure (LP) spool (36, 37). The HP spool (34,35) can be configured to drive a first generator (350, 351) to provide a first electrical output. The LP spool (36, 37) can be configured to drive a second generator (352, 353) to provide a second electrical output. The first generator (350, 351) and the second generator (352, 353) can be coupled to an electrical power distribution bus (310) that provides electrical power to multiple high power demand loads (382a-c). A propulsion system (320) and a multiple aircraft systems bus (380) can both be coupled to the electrical power distribution bus (310). The electrical system can further include a control system (500) configured to allocate power among the first generator (350, 351), the second generator (352, 353), and the propulsion system (320), and the secondary aircraft systems bus (380).