English (United Kingdom)

https://curated-unify.zendy.io/wp-json/zendy-region/v1/featured_content/oa?rat=en

https://curated-unify.zendy.io/wp-json/zendy-region/v1/highlighted_journal/

Zendy Plus

Presents the access of premium content as premium feature

Premium Content

Presents the keyphrase highlighting as premium feature

Keyphrase Highlighting

Presents the summarisation as premium feature

Summarisation

Insights

Presents the pdf analysis as premium feature

PDF Analysis

Presents the zaia usage as premium feature

ZAIA

Zendy Tools

Zendy Open

MAV (Micro air vehicle) has become the most extensive research field in academia and industry because of its strong maneuverability and the capability of VTOL (vertical take-off and landing). Vibration is a key factor affecting the long-term autonomous navigation of MAV, and the dominant source of MAV vibration is the rotor vibration. In order to reduce the impact of rotor vibration on MAV, rotor vibration characteristic of MAV named BHNC-1 developed by our lab is analyzed based on the FW-H (Ffows Williams-Hawkings) equation, and a model of rotor vibration of the BHNC-1 is proposed. The rotor vibration model is validated by comparing the real vibration spectrum and the simulative vibration spectrum. The rotor vibration characteristics of different airfoil are analyzed based on the proposed MAV vibration model, consequently, the optimal installation location of IMU (Inertial Measurement Unit) on the BHNC-1 is seeked out by moving the location of IMU from the middle to the bottom of the BHNC-1.

Vibration Modelling of Micro Air Vehicle Based on the FW-H Equation