Guosheng Wang

Error of a Non-driven Micromechanical Gyroscope

The vibratory gyroscope is a sensor which is designed to measure the absolute angular velocity of a non-rotating aircraft, and comprises a platform which is suspended in a frame by two elastic axes (internal and external), an electrostatic actuator and an angular pickup capacitor with two axes.

Static Performance Test of a Non-driven Micromechanical Gyroscope

The prototype of non-driven micromechanical gyroscope with a circuit is tested. The test is performed on a dynamic turntable controlled by a computer. The rotational velocity of the gyroscope is set to be 12∼22 Hz through the simulator and the environment temperature is provided by a special incubator.

Precision of a Non-driven Mechanical Gyroscope with Negative Velocity Feedback

The output signal is connected with the angular velocity by the scale factor: ( U_{{text{out} , { }text{amplitude}}} = K_{{text{SF}}}Omega ). So the study of the measurement precision of a constant angular velocity rotating around the horizontal axis of the aircraft is ultimately attributed to the stability of the calibration scale factor of the instrument. In this chapter, the precision of the gyroscope is studied based on the dynamic characteristics of the instrument.

The Operating Errors of a Non-driven Mechanical Gyroscope

The operating error of a rotating aircraft with a rotor vibrating gyroscope can be divided into two categories.

The Micromechanical Accelerometer and the Micromechanical Gyroscope

The micromechanical inertial sensors in the fabrication of micromechanical technology mainly include the micromechanical accelerometer and the micromechanical gyroscope.

Phase Shift of a Non-driven Micromechanical Gyroscope

Set the following coordinate systems: ( x_{a} ), ( y_{a} ) and ( z_{a} ) is the inertial coordinate system; ( x_{0} ), ( y_{0} ) and ( z_{0} ) is the coordinate system of a silicon pendulum; and ( x ), ( y ) and ( z ) is the frame coordinate system.

Performances of Non-driven Mechanical Gyroscope in the Condition of an Alternating Angular Velocity

In the condition of the following assumptions, the solution of Eq. ( 1.46) (the motion equation of the sensitive element of the instrument) is studied.

The Working Principle of a Non–Driven Micromechanical Gyroscope

In 1990s, with the development of microelectronic technology there was a variety of silicon micromechanical gyroscopes available and they used the Coriolis force generated by the vibration mass that is driven to rotate by the base, to be sensitive to the rotating angular velocity of the carrier.

Applications in the Flight Attitude Control System

Due to the breakthrough provided by the calculation method and software, the output of multi-information from a “non-driven structure silicon micromechanical gyroscope” can be realized.

Operating Theory of a Non-driven Mechanical Gyroscope

Before the performance of gyroscopes on the rotating carrier under different flying conditions can be studied in detail, the movement characteristics of the flying carrier must be studied.