Experimental Forward Flight Rotor Performance Testing from Terrestrial to Martian Atmospheric Densities

Perez Perez, Brenda Natalia ; Ament, Geoffrey A ; Koning, Witold J F

关键词: ROTORS;    FLIGHT TESTS;    PERFORMANCE TESTS;    MARS EXPLORATION;    MARS ATMOSPHERE;    ATMOSPHERIC DENSITY;    ATMOSPHERIC PRESSURE;    HELICOPTER DESIGN;    HELICOPTER PERFORMANCE;    SIMULATION;    WIND TUNNEL TESTS;    COMPUTATIONAL FLUID DYNAMICS;   

RP-ID  :  NASA/CR-2019-220229,ARC-E-DAA-TN70060

美国|英语

来源: NASA Technical Reports Server

【 摘 要 】

With the recent interest in Martian exploration using Unmanned Aerial Vehicles (UAV), an experimental study was conducted to investigate rotor performance at Martian atmospheric conditions. Both simulation and testing of rotors is vital for the evaluation of performance and behavior of rotor, especially for operations at Martian atmospheric densities and pressures. Testing and measuring rotor forward flight performance at Martian atmospheric conditions is a relatively unexplored area. Therefore, an experimental study was performed in a wind tunnel to investigate helicopter forward flight performance and to demonstrate successful rotor operation at Martian atmospheric densities. This work was a continuation of the first ever wind tunnel test of a simulated rotorcraft in forward flight at Martian atmospheric densities. A test was conducted in a facility, which could be evacuated to the atmospheric pressure and density of Mars. A 40-in diameter rotor, roughly approximating the scale of the proposed Mars Helicopter design by the NASA Jet Propulsion Laboratory (JPL), was tested in forward flight at Mars atmospheric pressure at the NASA Ames Planetary Aeolian Laboratory (PAL). In this forward flight testing, the drive system of the Martian Surface Wind Tunnel (MARSWIT) was never turned on. The goal of this experiment was to collect rotor thrust, rotational speed, power, torque, and wind speed measurements. Subsequently, these results can be used for correlation with simulated cases using a mid-fidelity Computational Fluid Dynamics (CFD) simulation. Rotor thrust and power seem to decrease approximately proportional to the decrease in density. However, the Reynolds number has an effect on rotor performance that might also be contributing to the change in thrust and power. This effect plays a vital role in rotor performance at reduced pressure that cannot be neglected in the simulation. Despite the challenges involved in testing at a large difference of atmospheric densities between Earth and Mars, repeatable data is obtained in all the measurements at Martian atmospheric conditions.