Abstract :
The steady-state and transient characteristics of the utilization and power-source equipment connected to the aircraft busbar can be used to determine the response of the system to shock loading and the nature of its subsequent recovery to normal conditions. The effect of the resulting busbar disturbances on connected load can then be predicted, and limits determined for maximum permissible excursion from the controlled values. Protection of the system against generally accepted fault conditions can be achieved by a variety of types of circuit-breakers and protective circuits, the characteristics of which require to be correlated to give a co-ordinated system.
