公开(公告)号：US20170297702A1

公开(公告)日：2017-10-19

申请号：US15467449

申请日：2017-03-23

Applicant: UNIVERSITY OF SCIENCE AND TECHNOLOGY BEIJING

Inventor： Wei He ,  YuNan Chen ,  Tong Lv ,  Yao Yu ,  ChangYin Sun

IPC: B64C33/02 ,  B64C13/16

CPC classification number: B64C33/02 ,  B64C13/16

Abstract: The present invention provides a method for controlling the oscillation of flapping-wing air vehicle, which comprises the following steps: calculating the kinetic energy, potential energy and virtual work of the system using the flexible wing with the two-degree of freedom as the research object; establishing system dynamics model based on the Hamilton's principle; setting the boundary control rate according to said system dynamics model wherein said boundary control rate includes F(t) and M(t), said F(t) is the inputted boundary control force, and said M(t) is the inputted boundary torque; and controlling the flexible wings according to the system dynamics model in combination with the boundary control rate. The present invention establishes the system dynamics model based on the Hamilton's principle, set the boundary control rate according to said system dynamics model, sufficiently considers the situation of distributed disturbance occurring at the boundary and effectively prevents the flexible wings deformation caused by the external disturbances.