TY - GEN
T1 - Experimental evaluating approach to a suitable Martian coaxial rotorcraft blade
AU - Quan, Qiquan
AU - Zhao, Pengyue
AU - Chen, Shuitian
AU - Wang, Dan
AU - Li, He
AU - Bai, Deen
AU - Deng, Zongquan
N1 - Publisher Copyright:
© 2017 IEEE.
PY - 2017/8/23
Y1 - 2017/8/23
N2 - This paper presents a detailed experimental approach for understanding and optimizing the hover performance of Martian UAV rotor, including a systematic discussion about several coefficients for hover characteristics and a detailed design approach for rotor blades of Martian UAV at Reynolds numbers lower than 50000. The discussed hover performance coefficients include figure of merit, thrust coefficient, thrust weighted solidity, power loading and disk loading, and these coefficients are also used to evaluate the hover performance of a specific rotor configuration. In addition, rotor parameters are investigated and analyzed in this experimental approach, including airfoil, camber, solidity, blade chord, number of blades and blade twist. These parameters are the major factors significantly influence the rotor hover performance. A detailed rotor design approach is proposed based on the experimental result by optimizing the hover performance coefficients and rotor parameters.
AB - This paper presents a detailed experimental approach for understanding and optimizing the hover performance of Martian UAV rotor, including a systematic discussion about several coefficients for hover characteristics and a detailed design approach for rotor blades of Martian UAV at Reynolds numbers lower than 50000. The discussed hover performance coefficients include figure of merit, thrust coefficient, thrust weighted solidity, power loading and disk loading, and these coefficients are also used to evaluate the hover performance of a specific rotor configuration. In addition, rotor parameters are investigated and analyzed in this experimental approach, including airfoil, camber, solidity, blade chord, number of blades and blade twist. These parameters are the major factors significantly influence the rotor hover performance. A detailed rotor design approach is proposed based on the experimental result by optimizing the hover performance coefficients and rotor parameters.
KW - Experimental approach
KW - Hover performance coefficients
KW - Martian UAV rotor
KW - Rotor parameters
UR - https://www.scopus.com/pages/publications/85030319958
U2 - 10.1109/ICMA.2017.8016118
DO - 10.1109/ICMA.2017.8016118
M3 - 会议稿件
AN - SCOPUS:85030319958
T3 - 2017 IEEE International Conference on Mechatronics and Automation, ICMA 2017
SP - 1958
EP - 1963
BT - 2017 IEEE International Conference on Mechatronics and Automation, ICMA 2017
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 14th IEEE International Conference on Mechatronics and Automation, ICMA 2017
Y2 - 6 August 2017 through 9 August 2017
ER -