Paralleling and Regulation of 24-28-Volt D-C Generators in Multiengine Aircraft

This paper presents the findings of a rather extensive program of testing electric systems in aircraft. Only the system which is presently being used in most United States Army Air Forces multiengine aircraft and a proposed system, which has been designed as the result of the tests, are described. All intermediate steps are not discussed since it is felt that the effects of these steps have been reflected in the proposed system. The proposed system differs from the present system primarily in that it employs separate networks for power feed and distribution instead of a common bus. Several desirable features of such a system are pointed out. Equipment is discussed in a general manner since the aircraft designer is concerned with the design of equipment only insofar as it affects the operation of the system. However, quite often the aircraft designer is in a position to make suggestions for improvement of the equipment.