TY - GEN
T1 - Design of a quadrotor flying robot capable of Mars rock sample collection
AU - Tang, Bo
AU - Quan, Qiquan
AU - Dong, Yachao
AU - Wang, Kaiyi
AU - Zhu, Kaijie
AU - Tang, Dewei
AU - Liu, Yingxiang
AU - Liu, Gangfeng
AU - Deng, Zongquan
N1 - Publisher Copyright:
© 2025 IEEE.
PY - 2025
Y1 - 2025
N2 - Due to the successful completion of the flight technology demonstration by the "Ingenuity"helicopter on Mars, employing the flying robots for exploration may become the mainstream approach for Mars exploration. Compared with the rovers, adopting flying robots for Mars exploration is not constrained by the terrain of Mars, resulting in a higher exploration efficiency. This paper designs a quadrotor flying robot with a flight duration of 3 minutes, capable of sampling Martian rock sample. Experiments are conducted to validate the performance of the propulsion unit and energy unit of the flying robot under the simulated Martian atmospheric conditions, as well as the performance of the onboard sampling robotic arm in Earth environment. The experimental results indicate that the propulsion unit can provide a thrust-to-weight ratio of 1.6 while consuming 1000 W of power for the flying robot. The energy unit not only provides energy supply for the robot's 3 min flight but also ensures the energy supply for the flying robot's survival during the Martian night. The onboard sampling robotic arm is capable of grasping Martian rock samples weighing 100 g located beneath the flying robot.
AB - Due to the successful completion of the flight technology demonstration by the "Ingenuity"helicopter on Mars, employing the flying robots for exploration may become the mainstream approach for Mars exploration. Compared with the rovers, adopting flying robots for Mars exploration is not constrained by the terrain of Mars, resulting in a higher exploration efficiency. This paper designs a quadrotor flying robot with a flight duration of 3 minutes, capable of sampling Martian rock sample. Experiments are conducted to validate the performance of the propulsion unit and energy unit of the flying robot under the simulated Martian atmospheric conditions, as well as the performance of the onboard sampling robotic arm in Earth environment. The experimental results indicate that the propulsion unit can provide a thrust-to-weight ratio of 1.6 while consuming 1000 W of power for the flying robot. The energy unit not only provides energy supply for the robot's 3 min flight but also ensures the energy supply for the flying robot's survival during the Martian night. The onboard sampling robotic arm is capable of grasping Martian rock samples weighing 100 g located beneath the flying robot.
UR - https://www.scopus.com/pages/publications/105016841279
U2 - 10.1109/RCAR65431.2025.11139814
DO - 10.1109/RCAR65431.2025.11139814
M3 - 会议稿件
AN - SCOPUS:105016841279
T3 - RCAR 2025 - IEEE International Conference on Real-Time Computing and Robotics
SP - 180
EP - 185
BT - RCAR 2025 - IEEE International Conference on Real-Time Computing and Robotics
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 2025 IEEE International Conference on Real-Time Computing and Robotics, RCAR 2025
Y2 - 1 June 2025 through 6 June 2025
ER -