Design of an Autonomous Mars VTOL Aerobot

Paper number

IAC-08.A3.3.B5

Author

Dr. Craig Underwood, Surrey Space Centre, University of Surrey, United States

Coauthor

Prof. Martin Sweeting, Surrey Satellite Technology Ltd, United Kingdom

Coauthor

Ms. Hanbing Song, United Kingdom

Year

2008

Abstract

In this paper, we propose the use of a novel fixed-wing vertical take-off and landing (VTOL) electrically powered aerobot for the exploration of the planet Mars. A baseline mission profile to investigate the Isidis Planitia region is proposed, based on the knowledge of the planet’s geophysical characteristics, its atmosphere and terrain. The mission would comprise the vehicle taking off vertically (for about 1 minute) and flying horizontally for about an hour each Martian day around mid-day. The vehicle would then autonomously select a landing site and land vertically, using the remaining daylight to re-charge its battery through wing mounted solar cells. The vehicle would also carry out a series of scientific investigations during this period. During the Martian night, the vehicle would use electrical heaters to keep its vital systems warm, recharging its battery again ready for flight in the morning. In this way, the vehicle would traverse the selected region in 10 days or so, traveling 100 to 150 km each day. 

The fixed wing VTOL capability is explored, showing that this combination uniquely allows for multiple flights, long endurance, high-resolution imagery and multiple surface sampling. The Aerobot takes advantage of the electrical motor/propeller for both the VTOL and forward flight propulsion, using solar cells to provide the power for forward flight, and for recharging the flight batteries for the high-power-demand VTOL manoeuvres. The power system uses a combination of the state-of-the-art rechargeable battery and thin film solar cell technology. The suggested 3kg science payload would accomplish a basic scientific investigation and provide valuable information in searching for life. Insulator, heater and forced convection cooling devices will constitute the thermal control system. The preliminary structural layout is a flying wing combined with a coaxial contra-rotating ducted propellers.
A mass budget of 25kg is shown to be achievable with the current technologies. The Aerobot design proposed in this paper is believed to be a practical and realistic solution to the problem of investigating the Martian surface. 

A six-degree-of-freedom flight simulator has been created to support the Aerobot design process by providing performance evaluations. The Vortex Lattice method is used to obtain the stability derivatives. An important aspect of the design is the autonomous guidance and control system. Two longitudinal control modes are investigated and the controller proves to be effective. The results of the simulation would seem to indicate that the Aerobot design is appropriate and is a suitable aerial platform to carry out the mission profile.

Abstract document

IAC-08.A3.3.B5.pdf

Manuscript document

IAC-08.A3.3.B5.pdf (🔒 authorized access only).

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