Method for autonomous stable energy management of aircraft/spacecraft turbo-electric distributed propulsion (TEDP) systems

A system for providing feasible and stable power to an aircraft, comprising:

• a turbo-electric distributed propulsion system (TeDP) having:
• one or more generator modules, wherein each generator module includes a respective generator and a respective rectifier having one or more pairs of switches;
• one or more propulsor modules, wherein each propulsor module includes a respective propulsor, a respective inverter having one or more pairs of switches, and a respective permanent magnet synchronous machine with a governor;
• a direct current (DC) link module consisting of a DC link electrically coupling the one or more generator modules to the one or more propulsor modules and a single capacitor;
• and
• a flywheel module electrically coupled to the DC link module, wherein the flywheel module includes a flywheel, having a flywheel module permanent magnet synchronous machine, and a flywheel module inverter having one or more pairs of switches;
• one or more nonlinear dynamic power-electronic controllers connected to the modules of the TeDP holding operation of the TeDP to one or more set points, the one or more controllers include:
• a respective generator controller for each generator module, wherein each generator module is controlled by adjustment of the switches in that generator module's rectifier;
• a respective propulsor controller for each propulsor module, and each propulsor module is controlled by adjustment of the switches in that propulsor module's inverter or speed adjustment through instructions to the governor;
• a DC link controller;
• and
• a flywheel controller;
• a Dynamic Monitoring and Decision System comprising the one or more nonlinear dynamic power-electronic controllers connected through one or more communication links to a software implemented optimization system;
• wherein the software implemented optimization system monitors the TeDP through the one or more controllers and determines the one or more set points;
• wherein each generator controller regulates real and reactive power out of the respective generator module, each propulsor controller regulates real and reactive power into the respective propulsor module, and the flywheel controller regulates reactive power into the flywheel module according to respective values specified by the one or more set points;
• and
• wherein the DC link controller gives a set point to the flywheel controller to regulate the DC link module voltage by regulating the flywheel module power.