Design of helicopter DC power distribution unit

In our modern time, all helicopters have the electrical power to supply the equipment for several systems both flight critical and operational. Helicopter may be used for SAR (Search and Rescue), combat, military tactical, cargo transportation, health (ambulance), farming and commercial, military or VIP transportation. For all usages of modern helicopters have to use electrical power for systems that are used for several missions. The Electrical Power Generation and Distribution System (EPGDS) generate and distribute electrical power to not only the aircraft electrical power utilization equipment but also enable the engine starting. There are two types for electrical power as AC and DC. AC system is mainly used for systems, which has high power consumption (generally supplied from 115VAC, 400 Hz power source) such as ice protection, window-cabin heating, main-tail rotor heating or weapon systems. DC power is used especially on the avionics equipment that are generally supplied by 28VDC and 28VDC power source. This thesis is about the design principles of a helicopter's DC power distribution unit by considering not only the electrical standards but also all the subjects that are necessary to design the power distribution unit (PDU) beginning with requirements till the end of design by using systems engineering principles. There are some assumptions PDU shall be capable of deliver DC electrical power from generators to secondary distribution units (circuit breaker panel, relay panel etc.). Keywords: Helicopter, DC Power, Electrical, Distribution, EPD, PDU