engleski

Optimization of flapping wing dynamics for Martian atmosphere via DMOC approach

NASA's Ingenuity Mars Helicopter has recently performed the first powered controlled flight on another planet. However, in spite of success of this mission, rotary wing solution might not be the optimal technology for flying in thin Martian atmosphere. The low density of the atmosphere (only 1% of the Earth's) forces the aircraft to fly at low Re numbers, which significantly deteriorates the performance of a rotary wing. On the other hand, insects fly very efficiently at the same Reynolds numbers, with great aerial capabilities, which makes the insect-type aircraft a promising concept for Mars exploration. To this end, the novel optimization algorithm for development of insect-type aerial vehicle, capable of flight in Martian atmosphere, is proposed. The optimization algorithm combines Discrete Mechanics and Optimal Control (DMOC) approach with quasi- steady aerodynamical model. Results of the numerical experiment indicate that the developed optimization algorithm can be successfully used for computationally efficient optimization of design and dynamics of an insect-type flapping aerial vehicle for Mars exploration purposes — where higher fidelity fluid-structure coupled procedures fail to deliver because of computational non-efficiency. The next natural step, in the development process of the presented algorithm and research of flapping flight on Mars, is to expand the existing aerodynamic model with forward flight features.

Flapping-wing ; Discrete mechanics and optimal control ; Optimization

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