| 主权项 |
1. An aircraft comprising:
an electrical system having a primary power source and an electrical bus electrically connected to said primary power source, said primary power source having a first load capability in a standard flight condition and a second load capability in an emergency flight condition, the second load capability being less than the first load capability; a first flight component electrically connected to said electrical bus of said electrical system of the aircraft; and an electrical unit electrically connected to said electrical bus of said electrical system, said electrical unit comprising:
a secondary power source, said secondary power source being electrically isolated from said aircraft electrical system;a controller to monitor electrical power associated with said aircraft electrical system so as to determine a first factor, the first factor being proportionate to the load capability of the primary power source; anda switch to electrically connect system circuits of the electrical unit to the aircraft electrical system in a first position and to the secondary power source in a second position, wherein said controller of said electrical unit compares the first factor to a predetermined second factor, wherein if the first factor is less than the predetermined second factor, then the controller generates a signal to move the switch from the first position to the second position, wherein the first factor is less than the predetermined second factor when the primary power source has a second load capability, wherein said first flight component and said electrical component are each powered by said primary power source when said primary power source has a first load capability, wherein said first flight component is powered by said primary power source when said primary power source has a second load capability. |
