Integrated fuel and bleed system control architecture

A configuration for an aircraft comprising:

• a fuel and bleed controller, the fuel and bleed controller comprising, a processor and a memory storing program instructions thereon,
• a plurality of aircraft systems including:
• a gas turbine engine controller;
• a bleed system that uses bleed air to provide pneumatic power for internal cooling of the aircraft and to provide pneumatic power for one or more of:
• inert gas system (IGS), internal cooling of the engine, cross starting another engine on the aircraft, anti-icing for the engine, and anti-icing for the airframe;
• and
• a plurality of bleed user controllers controlling operation of an environmental control system (ECS) and one or more of wing anti-ice (WAI) systems, the IGS and water supply systems;
• the fuel and bleed controller is configured for bi-directional electronic communication with each of the plurality of aircraft systems;
• the program instructions executable by the processor to cause the libel and bleed controller to:
• send status updates requests to the plurality of aircraft systems;
• receive status responses from to the plurality of aircraft systems;
• determine fuel requirements based on the status responses in advance of operational needs by the plurality of aircraft systems;
• the fuel requirements including predictive estimations of an amount of fuel needed by future power requests by the bleed system or the a plurality of bleed user controllers;
• and
• control the engines of the aircraft based on the fuel requirements.