Some ground measurements of the forces applied by pilots to a side-located aircraft controller

Roy F. Brissenden
naca-tn-4171
Nov 1957


Ground tests have been made to determine pilots' force capabilities on a proposed side-located aircraft controller, located at one side of the cockpit and situated so the pilot's arm may be supported. The axes of the of the controller are in a plane through the center of the pilot's forearm to minimize the effects of acceleration forces. Results indicate a neutral position for the controller at 8 degrees to the right and 15 degrees forward of the vertical. The ability of the pilots to apply forces in both directions at various angles of roll and pitch indicated a usable range for the controller. At the limits of deflection suggested for the controller, the torque capability in the direction of increasind deflection was approximately one-half the maximum value. The range of deflection for roll control was plus-or-minus 45 degrees from the neutral point. The range of deflection for longitudinal control was plus-or-minus 22.5 degrees from the neutral point. Pilots participating in the tests indicated forces that they considered desirable for operation of the side-located controller. This operational torque for the controller is from 10 to 26 inch-pounds in roll and from 15 to 36 inch-pounts in pitch. The pilot's arm should be extended slightly forward of a 90 degree elbow angle. In the range of deflection proposed for the controller, the relationship between maximum torque (applied in the direction to increase the deflection) and controller deflection is linear, with the torque decreasing in the direction of rotation.

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