Mars science helicopter conceptual design

Johnson, Wayne; Withrow-Maser, Shannah; Young, Larry; Malpica, Carlos; Koning, Witold J.F.; Kuang, Winnie; Fehler, Mireille; Tuano, Allysa; Chan, Athena; Datta, Anubhav; Chi, Cheng; Lumba, Ravi; Escobar, Daniel; Balaram, J.; Tzanetos, Theodore; Grip, Havard F.

Abstract

Robotic planetary aerial vehicles increase the range of terrain that can be examined, compared to
traditional landers and rovers, and have more near-surface capability than orbiters. Aerial mobility is a promising possibility for planetary exploration as it reduces the challenges that difficult obstacles pose to ground vehicles. The first use of a rotorcraft for a planetary mission will be in 2021, when the Mars Helicopter technology demonstrator will be deployed from the Mars 2020 rover. The Jet Propulsion Laboratory and NASA Ames Research Center are exploring possibilities for a Mars Science Helicopter, a second-generation Mars rotorcraft with the capability of conducting science investigations independently of a lander or rover (although this type of vehicle could also be used assist rovers or landers in future missions). This report describes the conceptual design of Mars Science Helicopters. The design process began with coaxial-helicopter and hexacopter configurations, with a payload in the range of two to three kg and an overall vehicle mass of approximately twenty kg. Initial estimates of weight and performance were based on the capabilities of the Mars Helicopter. Rotorcraft designs for Mars are constrained by the dimensions of the aeroshell and lander for the trip to the planet, requiring attention to the aircraft packaging in order to maximize the rotor dimensions and hence overall performance potential. Aerodynamic performance optimization was conducted, particularly through airfoils designed specifically for the low Reynolds number and high Mach number inherent to operation on Mars. Rotor structural designs were developed that met blade frequency and weight targets, subject to material stress limits. The final designs show a substantial capability for science operations on Mars: a 31 kg hexacopter that fits within a 2.5 m diameter aeroshell could carry a 5 kg payload for 10 min of hover time or over a range of 5 km.

Citation

Johnson, W., Withrow-Maser, S., Young, L., Malpica, C., Koning, W. J., Kuang, W., …Grip, H. F. (2020). Mars science helicopter conceptual design. NASA

• Report Type: Technical Report
• Online Publication Date: Mar 1, 2020
• Publication Date: Mar 1, 2020
• Deposit Date: Mar 1, 2024
• Pages: 53
• Series Number: TM-2020-220485
• Public URL: https://uwe-repository.worktribe.com/output/11753439