Search Results

A most promising approach in the field of flight control surface actuation is the use of independent integrated hydraulic actuator packages located at each flight surface actuation station. This concept eliminates hydraulic plumbing throughout the vehicle thus reducing the external connections to only electric power and command signals which are easily made redundant. The most compact and universal configuration of these packages will use a liquid metal hydraulic fluid thus making them capable of sustained operation in high-temperature environments without need of coolant systems. This paper summarizes the research, development, and experimental work that has been done so far.