01.2 - Aircraft Design and Integrated System (Applications)
CONCEPTUAL DESIGN AND SIZING OF A SOLAR POWERED QUAD-ROTOR FIXED WING HYBRID UAV FOR EXPLORATION OVER MARS
A. Kalgutkar¹, P. Gupta¹, P. Priyadarshi, Vikram Sarabhai Space Centre, India, India; R.S. Pant¹; ¹Indian Institute of Technology Bombay, India, India
This paper presents a comprehensive conceptual design for a solar-powered hybrid unmanned aerial vehicle (UAV)rnspecifically tailored for Mars exploration. The proposed configuration combines quadcopter vertical take-off andrnlanding capabilities with fixed wings for horizontal propulsion, supported by solar energy harvesting. The study utilizesrna design methodology derived from a literature review of a similar UAV configuration on Earth, adapting it to thernunique challenges and environmental conditions of Mars. Additionally, simulation parameters are modified to accuratelyrnrepresent Martian conditions, including the incorporation of an illumination model and solar cell methodologies. Therndesign process involves the generation and evaluation of multiple design points based on desired mass, payload capacity,rnand endurance, offering a range of feasible options for Martian UAV missions. The selected configuration has fourrnmotors in a quadcopter configuration for Vertical Take-Off and Landing (VTOL) along with fixed wings and a singlernmotor for horizontal propulsion. Energy is harvested using body-mounted solar cells over the duration of a Martianrnday to enable high endurance flight. The literature review is conducted to obtain a design methodology for a similarrnconfiguration of vehicle for earth, albeit without solar power. This methodology is implemented and the code is validated.rnThe simulation parameters are altered to represent conditions on Mars and an illumination model is added. Designrnpoints are generated and evaluated as per the process presented above. The analysis of various feasible design pointsrnis also conducted, presenting several options based on the desired mass, payload, and endurance. Simulations arernperformed for different mission profiles to generate a plot of the battery State of Charge versus time.