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Meeting	ACGS Committee Meeting 92 - Dayton - October 2003
Agenda Location	8 SUBCOMMITTEE E – FLIGHT AND PROPULSION CONTROL SYSTEMS 8.1 History of Aircraft Flight Control Actuation Systems For Military Tactical Aircraft
Title	History of Aircraft Flight Control Actuation Systems For Military Tactical Aircraft
Presenter	Henry Harschburger
Available Downloads*	presentation
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Abstract	The design of flight control actuation systems has progressed from the simple lever and fulcrum systems developed by the Wright Brothers to the redundant fly-by-wire systems being used today. This paper presents a “time line” of significant developments in flight control actuation systems. Specific aspects covered are: mechanical controls, actuation for automatic flight control systems, boosted systems, hydraulically powered irreversible actuation, and the development of fly-by-wire actuation systems used in today’s military aircraft. Until the mid 1930’s flight control actuation was provide by pilot muscle power. When aircraft requirements reached the limitations of pilot forces, control surface tab were developed to provide an aerodynamic boost. In the 1940’s and 1950’s power boosted and power operated flight control actuation systems were introduced. The Wright Brothers introduced automatic flight control concepts in a 1908 patent application. In 1933 Willey Post completed a solo flight around the world using a Sperry autopilot with gyro controlled air valves and hydraulic servo actuators. Autopilots were not standard equipment in fighter aircraft until the mid 1950’s. In the 1960’s high authority control augmentation systems led to the development of redundant actuation systems. Development of the fly-by-wire actuation systems used in today’s aircraft was started in the early 1970’s.