โ Scribed by Howard H. Brown
No coin nor oath required. For personal study only.
The Franklin Institute Laboratories have, during the past twelve years, engaged in numerous research and development projects in the field of gyroscopes. These have included research studies on eddycurrent constrained gyroscopes, the development of rate and attitude gyroscopes for aircraft fire control systems, and others.
About one year ago, the Electrical Engineering Division undertook a program of research on angular rate gyroscopes, with the aim of uncovering non-linearities in the behavior of such systems and their effects upon the accuracy of angular rate information supplied by the gyroscopes. Gyroscope systems for measuring angular rates are widely used as sensing devices for airborne fire-control computing systems and in connection with autopilots.
The gyroscope operates according to the principles of rigid body dynamics. The heart of a gyroscope is the spinning wheel or rotor. Associated with the spinning rotor is a momentum vector having the direction of the axis of spin. Any change in the direction or magnitude of this momentum requires the application of a torque equal to the time derivative of the momentum.
In practice, the speed of the rotor is held constant, thus fixing the magnitude of the momentum. Changes in momentum can then occur only in its direction. If a torque with component perpendicular to the spin axis is applied to a free gyroscope, precession results. The necessity for high-accuracy free gyros has resulted in the development of gyros of high angular momentum and very low precession rate. These have wide application in maintaining a stable reference position in inertial guidance systems, in measuring attitude angles, and in controlling guided missiles. TRA~ UCER OUTPUT INxPUs T ' S I G/~AL Schematic diagram of rate gyro.
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