An electrical power system including a plurality of electrical devices, a distribution network and a control system. The control system is configured to detect an electrical fault associated with the distribution network based on a signal received from a sensor and to perform a fault procedure in response to a fault detection, including: (a) controlling a plurality of switches so all of the devices are isolated from the network; (b) subsequently controlling the switches to progressively re-couple at least some of the devices to the network in a re-coupling order and monitoring for re-detection of a fault; (c) identifying a set of one or more of the devices re-coupled to the distribution network to cause the re-detection of the fault, the set being a fault event set; and controlling at least one of the plurality of switches to isolate the fault event set from the network.

An aircraft solid state power controller comprises a feed node to be electrically connected to a primary electric power supply; a load node to be electrically connected to at least one electric load; and at least one electric switching device, in particular a solid state switching device, which is arranged between the feed node and the load node. The at least one electric switching device is switchable between an on-state, in which the at least one electric switching device provides a low-resistive electric connection between the feed node and the load node; and an off-state, in which the at least one electric switching device electrically isolates the load node from the feed node. The aircraft solid state power controller further comprises a secondary electric power supply, which is independent from the primary electric power supply, and which is configured for applying a test voltage between the feed node and the load node of the aircraft solid state power controller in order to allow determining the switching state of the at least one electric switching device by detecting a voltage drop between the feed node and the load node of the aircraft solid state power controller.

A hybrid power and propulsion system of a vehicle is provided and includes an engine assembly coupled to a common bus via a first plug type and including a motor-generator configured to generate electricity, a storage element coupled to the common bus via a second plug type and configured to store the electricity, a drive assembly coupled to the common bus via a third plug type and configured to receive the electricity from at least one of the engine assembly or the storage element to drive a propulsive fan and a controller. The controller is connected to the common bus and controls a flow of the electricity between at least one of the engine assembly, the storage element and the drive assembly. The common bus is configured with additional connectors of the second and third plug types to enable removable connections of additional storage elements and drive assemblies.