Power-by-wire aircraft secondary power systems

This paper describes the secondary power sources available on a large transport aircraft that supply power for the aircraft operating and payload systems. The benefits expected from integrating all of the engine-based hydraulic and pneumatic power sources into the electrical system are identified in qualitative terms. The estimated capacity of an all-electric secondary power system for a tri-jet and a new large transport are compared. An integration architecture of the pneumatic, hydraulic, and electrical power using one type of distributed power is illustrated, Particular emphasis is given to the flight control system and the electrical power system needs to ensure integrity of power and data for critical flight control functions. The data bus and power source redundancy for flight control actuation is discussed using an integrated power and cable concept in conjunction with an intelligent power controller. The need for the industry to develop comprehensive data bus architectures that network the entire vehicle information infrastructure is discussed