Raytheon Company

Hughes Aircraft Company

Russell B Cline

Charles M DeLair

Christopher P Owan

Shane P Stilson

Donald E Croft

Jason M Bain

Charles M Delair

A dynamic load fixture (DLF) for testing a unit under test (UUT) includes a lateral load system that applies a time-varying lateral load profile to the UUT drive shaft and an encoder that measures its angular rotation. An isolation stage suitably constrains the encoder from rotating about the axis while allowing it to move in other directions in which the application of the lateral force induces motion. The lateral load system includes a load bearing around the drive shaft, an actuator that applies a lateral force to the load bearing, a force sensor for measuring the applied lateral force, and a lateral controller for adjusting a command signal to the actuator to implement a lateral load profile. The DLF may also include a torsion load system that applies a time-varying torsion load profile to the drive shaft.

Dynamic load fixture for rotary mechanical systems

An actuator system having a motor that drives a pneumatic spool valve to a known position based upon the number of step commands delivered to it. Valve ports or passages uncovered by the net position difference between the spool valve and a piston create gas flow to or from a control chamber. This gas flow causes a pressure differential across the face of the piston, inducing the piston to follow the spool valve. In this two-stage system, the piston acts as a force amplifier so that large forces and/or inertias may be actuated by positioning the motor. During steady state conditions, the piston achieves the same position as the spool valve is. Proportional control and very accurate positioning of the piston are provided without active position or position rate feedback control.

Proportional pneumatic fin actuator system without feedback control

A control fin actuator (28) for a guided missile (20) includes a pressure actuator (40) having a slidable piston (44) inside a housing (42). Rolling diaphragm seals (50, 56) of the top piston face (46) and the bottom piston face (48) to the inside wall of the housing (42) divide the interior of the housing (42) into at least two chambers (54, 58). The rolling diaphragm seals (50, 56) eliminate sliding friction as the piston (44) moves within the housing. The two chambers (54, 58) are controllably pressurized to slide the piston (44) within the housing (42), thereby moving a push rod (78) attached to the piston (44) and extending out of the housing (42). The push rod (78) is connected to a missile control fin output shaft (24) by a taut band connector (80) that avoids backlash. A magnet (86) may be positioned adjacent to the push rod (78) to induce eddy currents in the push rod (78), thereby providing a damping force that increases with increasing rate of movement. Pressure in the control chamber (54) is achieved by operating the inlet valve (70) and the exhaust valve (72) in response to feedback information from a rotary position sensor (29), a linear position sensor (88), and/or pressure sensors (90, 92).

Missile control fin actuator system

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Tucson, AZ, United States of America

Russell B Cline