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Designing correct and reliable avionics architecture of a spacecraft is a complex endeavor. This paper describes the electric scheme and method of the Intermediate eXperimental Vehicle (IXV), including the electric system architecture and the avionics configuration. The IXV is the European Space Agency (ESA) technology platform conceived as the step forward from the successful Atmospheric Re-entry demonstrator (ARD) to demonstrate re-entry capabilities, which was successfully launched and flight on February 11th 2015. In order to reduce the development cost and ensure the schedule, the Commercial Off-The-Shelf (COTS) equipments and the confirmed equipments by flight were selected as best as possible in the avionics design. And the redundant design was very little except the critical equipments such as batteries and storage recorders. The engineer break up the tradition mode and design a novel data handling subsystem (DHS), the subsystem has been designed to integrate some functions such as the navigation, control, data acquisition and handle and so on. The avionics is designed around a 1553 MIL Bus and a series of serial and Ethernet interfaces. These interfaces were selected with the purpose of sustaining the amount of data exchanged throughout the system and predigesting the Electrical Ground Support Equipment (EGSE) interface. The validity and rationality of the IXV’s electric system were validated by the maiden flight.