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This is a constant gain model for the rate gyro, e.g. a perfect rate gyro.

The rate gyro feedback gain must be in the range |K| < 1.3 degree/(degree/sec).

The rate gyro system has two gains. At any given time, the gain being used is selectable from the pilot's radio using one of our unused radio channels. We will use the gear switch on the radio to switch the gain in-flight. We will always set the first gain to zero so that we can shut off feedback from the radio whenever we have to. With feedback, instability or poor dynamic response is always possible. There is also a gain sign switch on the gyro mixer box (on-board the aircraft). This switch sets the sign of the feedback gain. It can only be changed while the aircraft in on the ground.

The user of the rate gyro must ascertain the correct sign for stabilizing feedback. If the control surface moves in such a way as to resist the angular motion, then the feedback is stabilizing (good). This can be most easily be done when holding the aircraft with the radio and rate gyro fully powered. If the rate gyro is installed to feed back pitch angular rate to the elevator, you should pitch the nose of the aircraft up. Observe which way the elevator moves. In this case, for a nose up pitch rate the elevator should deflect training-egde down if the feedback is to be stabilizing. This trailing edge down motion of the elevator will cause the nose to go down in flight, thereby resisting the original nose up pitching motion imposed on the aircraft.

In summary, the sign for stabilizing feedback can be determined by performing the following tests.

A calibration curve showing the feedback gain as a function of the dial setting on the gain potentiometer is given in the following document (RateGyroCalCombined.pdf)

For the Tower Hobbies imformation about the SG-1 click here.

Detailed Installation procedures for the rate gyros (.pdf)

Assume that the sign switch is set for stabilizing feedback and the rate gyro mounted to measure (..)	and to generate feedback to the (..).	An angular rate of this type (..)	should produce a surface motion of this type (..).
pitch angular rate (q)	elevator	nose up	elevator trailing edge down
yaw angular rate (r)	rudder	nose right	rudder trailing edge left.
roll angular rate (p)	aileron	right wing down (viewed from the rear)	right aileron trailing edge down, left aileron training edge up. (Right and left are as viewed from ther rear of the aircraft.)