Abstract
The silicon micromechanical gyroscope, which will be introduced in this paper, represents a novel MEMS gyroscope concept. It is used for the damping of a single-channel control system of rotating aircraft. It differs from common MEMS gyroscopes in that does not have a drive structure, itself, and only has a sense structure. It is installed on a rotating aircraft, and utilizes the aircraft spin to make its sensing element obtain angular momentum. When the aircraft is subjected to an angular rotation, a periodic Coriolis force is induced in the direction orthogonal to both the angular momentum and the angular velocity input axis. This novel MEMS gyroscope can thus sense angular velocity inputs. The output sensing signal is exactly an amplitude-modulation signal. Its envelope is proportional to the input angular velocity, and the carrier frequency corresponds to the spin frequency of the rotating aircraft, so the MEMS gyroscope can not only sense the transverse angular rotation of an aircraft, but also automatically change the carrier frequency over the change of spin frequency, making it very suitable for the damping of a single-channel control system of a rotating aircraft. In this paper, the motion equation of the MEMS gyroscope has been derived. Then, an analysis has been carried to solve the motion equation and dynamic parameters. Finally, an experimental validation has been done based on a precision three axis rate table. The correlation coefficients between the tested data and the theoretical values are 0.9969, 0.9872 and 0.9842, respectively. These results demonstrate that both the design and sensing mechanism are correct.
Highlights
For rotating aircraft, the attitude motion usually has three degrees-of-freedom including pitch, yaw and rolling
The MEMS gyroscope is mounted on the table board, and rolling axis is set to 12 Hz to simulate the spin frequency of a rotating aircraft
Its solution reveals that the vibration amplitude of the proof-mass is proportional to the input angular velocity, and the vibration frequency responds to the spin frequency of the aircraft, so the proposed MEMS gyroscope is very suitable for damping of a single-channel control system of a rotating aircraft
Summary
The attitude motion usually has three degrees-of-freedom ( called three channels) including pitch, yaw and rolling. In the stable loop of a single-channel control system, the angular rate gyroscope is the key device It is responsible for measuring the pitch and yaw of the rotating aircraft body, it feeds the output signal back to the input end of the control system so that control system can adjust flight accuracy in time. MEMS gyroscope does not need to compensate for the influence of the Magnus effect What is more, it can automatically change the carrier frequency of the output signal with the change of spin frequency of the rotating aircraft, making it very suitable for damping in the stable loop of a single-channel control system for a rotating aircraft
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