TY - GEN
T1 - Design of experimental setups for evaluating hover performance of a Martian coaxial rotorcraft
AU - Zhao, Pengyue
AU - Zhao, Zhijun
AU - Chen, Shuitian
AU - Quan, Qiquan
AU - Li, He
AU - Bai, Deen
AU - Deng, Zongquan
N1 - Publisher Copyright:
© 2017 IEEE.
PY - 2017/8/23
Y1 - 2017/8/23
N2 - In order to verify whether a small-scale rotorcraft can fly on Mars, this paper is proposed to establish a Martian atmosphere simulator and to design a hover test stand for coaxial rotorcraft rotor. Since the ultra-low air density of Mars is approximately 1/70 of that on the Earth, it is difficult to obtain enough thrust to lift the rotorcraft against Mars gravity. The proposed Martian Atmosphere Simulator (MAS) is composed of an evacuation chamber, a roots pumping system, vacuum gages, and an atmospheric pressure control unit. The seesawed hover stand mounted in the center of MAS, is employed to acquire the thrust and power characteristics with respect to blade collective pitch angle and rotational speeds. Experimental approach is proposed to evaluate the rotorcraft hover performance and endurance on Mars. The experimental setups provide a fundamental platform for further aerodynamics research of different types of blades and rotorcraft hover performance evaluation.
AB - In order to verify whether a small-scale rotorcraft can fly on Mars, this paper is proposed to establish a Martian atmosphere simulator and to design a hover test stand for coaxial rotorcraft rotor. Since the ultra-low air density of Mars is approximately 1/70 of that on the Earth, it is difficult to obtain enough thrust to lift the rotorcraft against Mars gravity. The proposed Martian Atmosphere Simulator (MAS) is composed of an evacuation chamber, a roots pumping system, vacuum gages, and an atmospheric pressure control unit. The seesawed hover stand mounted in the center of MAS, is employed to acquire the thrust and power characteristics with respect to blade collective pitch angle and rotational speeds. Experimental approach is proposed to evaluate the rotorcraft hover performance and endurance on Mars. The experimental setups provide a fundamental platform for further aerodynamics research of different types of blades and rotorcraft hover performance evaluation.
KW - Experimental approach
KW - Hover stand
KW - Martian atmosphere simulator
KW - Martian rotorcraft
UR - https://www.scopus.com/pages/publications/85030323134
U2 - 10.1109/ICMA.2017.8016026
DO - 10.1109/ICMA.2017.8016026
M3 - 会议稿件
AN - SCOPUS:85030323134
T3 - 2017 IEEE International Conference on Mechatronics and Automation, ICMA 2017
SP - 1427
EP - 1432
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 -