Hostname: page-component-586b7cd67f-t8hqh Total loading time: 0 Render date: 2024-11-25T17:23:30.418Z Has data issue: false hasContentIssue false
  • English
  • Français

Some Trends in the Development of Aircraft Electrical and Starting Systems

Published online by Cambridge University Press:  28 July 2016

R. H. Woodall
R. H. Woodall*
Affiliation:
Rotax Ltd.
Get access Rights & Permissions [Opens in a new window]

Extract

The main task of the aircraft accessory designer is to provide fully developed and type-tested equipment to meet the needs of the Aircraft Industry at the time when a new aircraft is at a stage in construction where accessories are to be fitted.

But he must do more than this, particularly with equipment for multi-engined aircraft. He must endeavour to set up and test a complete aircraft ancillary power system. This is particularly important for the electrical system, where two or more generators have to operate in parallel, successfully sharing the load on the system and providing over-voltage and other protection in such a manner that failure of the complete system does not result from failure of one engine, generator or its attendant equipment.

Type
Research Article
Information
The Aeronautical Journal , Volume 59 , Issue 537 , September 1955 , pp. 587 - 603
Copyright
Copyright © Royal Aeronautical Society 1955

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Woodall, R. H. (1949). The Relative Merits of Aircraft Auxiliary Power Systems—The Electrical Aspect. Second Anglo-American Aeronautical Conference, New York, May 1949, Institute of Aeronautical Sciences.Google Scholar
2. Sims, R. F. The Wear of Carbon Brushes at High Altitude. I.E.E. Proceedings, Part II, Vol. 101, p. 213.Google Scholar
3. Halliday, T. B. (1943). Aircraft Accessory Systems. S.A.E., January 1943.Google Scholar
Neville, S. (1943). First Report on Electric Power in Large Aircraft. April 1943. M.O.S. London.Google Scholar
4. Bradley, C. S. (1890). U.S.A. Patent No. 438,602, 1890.Google Scholar
5. Watson, E. A. British Patent No. 518,891.Google Scholar
6. Report of Advisory Committee for Aircraft Equipment Cooling Systems. Wright Air Development Center. March 1953.Google Scholar