HIGH POWER DENSITY ACTUATORS

THIS PROJECT WILL DEVELOP A HIGH POWER DENSITY ACTUATOR FOR A 9 INCH DIAMETER AIRFRAME HIGH PERFORMANCE MISSILE TAIL FIN SERVO. THE END RESULT OF THIS EFFORT WILL BE A STATEOF-THE-ART ACTUATOR THAT ACHIEVES RATES UP TO 1000 DEGREES/SEC IN THE PRESENCE OF TORQUES UP TO 2000 LB-IN WITH TYPICAL FLIGHT TIMES OF 20 SECONDS OR LESS. SUCH A SYSTEM WILL BE POWERED BY ADVANCED THERMAL BATTERIES WHICH .NAY BE INTEGRATED INTO THE VOLUME OF THE CONTROL ACTUATOR OR ALTERNATELY LOCATED ELSEWHERE ON THE MISSILE. THIS SYSTEM WILL GREATLY ENHANCE THE PERFORMANCE AND AGILITY OF SMALL DIAMETER MISSILES NOT PRESENT1Y EXISTING IN THE U.S. INVENTORY OR ELSEWHERE. THIS EFFORT WILL BE BASED ON OUR PREVIOUS EXPERIENCE WITH HIGH PERFORMANCE ELECTROMECHANICAL ACTUATOR SYSTEMS. SEVERAL INNOVATIVE FEATURES WILL BE INCORPORATED IN THE DESIGN. THESE ARE: * A COMPACT, VERY HIGH SPEED, LOW INDUCTANCEBRUSHLESS MOTOR. * A HIGH POWER DENSITY PWM ELECTRONIC DRIVER. * A MOTOR TO DRIVER COMMUTATION INTERFACE DESIGNED TO MAXIMIZE PEAK POWER THRUPUT. THE FOUR MAJOR AREAS OF THE CONTROL SYSTEM DESIGN ARE THE: * THERMAL BATTERY * PULSE WIDTH MODULATED (PWM) ELECTRONIC DRIVER * HIGH SPEED BRUSHLESS MOTOR AND HIGH STRENGTH REDUCTION SYSTEM THE PHASE I OBJECTIVES ARE SUMMARIZED AS FOLLOWS: COMPUTER MODEL THE CONTROL ACTUATOR SYSTEM; DETAILED COMPUTER MODEL OF THE PWM DRIVER AND BRUSHLESS MOTOR; THERMAL BATTERY SIZING VOLTAGE/CURRENT ANALYSIS; PACKAGING AND REDUCTION DRIVE TRADE STUDY. BASED ON THE RESULTS OF THEMODEL: * MODIFY AND TEST EXISTING MOTORS AND DRIVER TO VERIFY SIMULATION AND MAKE A PRELIMINARY SCHEMATIC OF THE PWM DRIVER AND LAYOUTOF THE SYSTEM DESIGN.