The Balanced-Power Actuation Concept

The technological advancement in aerody­namics, propulsion, and structures for manned air vehicles in recent years has placed an ever increasing demand on actuation systems in the form of function, power level, and environ­ment. A significant advance in actuation tech­nology is necessary to improve vehicle mass ratio for high-performance vehicles. This paper describes the results of a parametric study which indicates a high level of confidence in the potential of the Balanced-Power concept for significant weight savings in aircraft actuation systems. The advantages of the Balanced-Power actuation concept are illustrated by a comparison between this concept and a conven­tional hydraulically actuated system for an identical flight control actuation problem. The Balanced-Power concept consists of mechani­cally actuated flight control surfaces, a me­chanical servo, a flywheel and a motor. The motor maybe electrically, pneumatically, or hydraulically powered. This paper is the result of a study conducted at North American Aviation, Inc.