This paper presents use Proportional-Integral controller and lead-lag compensator to design torque balance loop of gyro by optimization parameter of compensation loop and reasonable pole-zero assignment,then the bandwidth of gyro system is increased to 150Hz but output noise less than 10mV.

The dynamical equations of a flexible spacecraft with VSCMGs(variable speed control moment gyroscopes) are established via the Lagrange equations in terms of quasi-coordinates and the momentum theorem.

The domestic and foreign fault diagnosis methods for the gyroscopes and the latest development are analyzed and concluded.

Stabilization properties of airborne imaging platform based on position gyro and rate gyro;

Principle of the effect of gyro misalignment on the stabilization platforms accuracy;

Design and simulation of accelerometer based gyro-free inertial navigation system;

On-orbit calibration algorithm for gyros/star sensor;

On-orbit calibration algorithm with star sensors of gyros;

a RBF neural network for gyro fault diagnosis of a placement of six one-freedom gyros is designed.

Electromagnetic induction pendulum and electromagnetic induction top;

Precession and nutation of top and gyrosscope is discussed by elementary method,equations of motion are solved using simplified models, and an elementary analysis is made.

A top is supported horizontally and the counterweight is connected by a spring,the direction of angular momentum of the top varies horizontally when the counterweight vibrates vertically.