Attitude control of a novel tilt-wing UAV in hovering flight

查看全文 作　　者：Jihong [1]ZHU;Yunjie [1]YANG;Xiangyang [2]WANG;Xiaming [1]YUAN;Xiao [2]YANG

机构地区：[1]Department of Precision Instrument,Tsinghua University,Beijing 100084,China;[2]Institute for Aero Engine,Tsinghua University,Beijing 100084,China

出　　处：《Science China(Information Sciences)》索引2023年第66卷第5期,共3页

基　　金：supported by National Natural Science Foundation of China(Grant Nos.62203259,62073185,61903216,61973182);China Postdoctoral Science Foundation(Grant No.2021TQ0179)。 摘　　要：Flexibility and endurance are the continuous pursuits of unmanned aerial vehicle(UAV)research.A fixed-wing UAV with vertical takeof and landing ability is ideal because it combines the advantages of long flight durations and freedom from runways[1].Therefore,tilt-wing and tilt-rotor UAVs have been developed.The former is more suitable for long-duration flight because the propeller slip-stream is less disturbed,and a longer wingspan can be designed[2]. 关键词：ATTITUDE disturbed FLIGHT

相关文献

参考文献（8）
引证文献（3）
耦合文献（0）

参考文献(8)

引证文献(3)

互联网出版许可证新出网证(渝)字10号全国400电话 - 免长途话费

Attitude control of a novel tilt-wing UAV in hovering flight

参考文献(8)

引证文献(3)

用户提示