Abstract: An emergency supply system for maintaining the emergency flight control of a high-performance aircraft of aerodynamically unstable design having three energy systems, namely, two identical hydraulic systems, connected in parallel for redundancy, for actuation of the control surfaces of the aircraft required for its ability to fly, and an electric on-board system having at least one generator, a rechargeable battery and a non-rechargeable emergency battery, the three energy systems being interconnectible in terms of energy by a power transmission unit, and wherein the two hydraulic systems are divided into subsystems associated with single or several rudder functions which, if necessary, can be disconnected singly.

Abstract: The present electrical melting fuse is current flow direction responsive. For this purpose the melting conductor is in heat exchange contact with a surface of a Peltier element which surface changes its temperature in response to a change in the flow direction of an electrical current through the Peltier element.