Design and Fabrication of an 8000 PSI Control-by-Wire Actuator for Flight Testing in a T-2C Airplane.

This report describes the design and fabrication of an 8000 psi control-by-wire hydraulic rudder actuator for future flight testing in a T-2C airplane. Actuator output is commanded by a single stage spoolsleeve valve driven directly by a permanent magnet force motor. Actuator design criteria were based on T-2C aerodynamic considerations and envelope constraints. A system analysis was conducted to determine heat dissipation and hydraulic line sizes and routing. Modifications required on the T-2C airplane to accommodate the test system installation were outlined. Author