Mars Airborne Canyon Explorer for Mars surface exploration.
- Paper number
IAC-06-E2.2.01
- Author
Mr. Jeffrey Apeldoorn, Technical University of Delft (TUDelft), The Netherlands
- Year
2006
- Abstract
The MACE (Mars Airborne Canyon Explorer) was the subject of a recent design synthesis project at the faculty of Aerospace Engineering in Delft. In which I was responsible for the propulsion system of the flyer.
The MACE will demonstrate an innovative and reliable method for scientific investigation of the Valles Marineris canyon on Mars. It will also provide better insight in the geology and history of the planet and gather information satellites, landers and rovers cannot. With a mass of 121 kg and with a flight velocity of 124 m/s it will have a maximum mission lift time of 6 hours.
The operating environment of the flyer is very different from that on Earth. The relative low density of the atmosphere, the different gravitational acceleration and the limitations of the sizing of the flyer to fit into the entry capsule (aeroshell), pose a major challenge on the design of the MACE. Due to its unique mission and the constraints just mentioned the MACE requires very efficient electric engines, lightweight propeller blades and an ingenious folding system.
The design of the propulsion system consists out of four main aspects:
- The shape of the propeller blades.
- The material of the propeller blades.
- The electric engines.
- The folding mechanism of the propeller blades.
The atmosphere on Mars has a relatively low density in comparison to that of the atmosphere on Earth. This causes the propeller blades to be much bigger than they would be on Earth to get the same amount of thrust with acceptable efficiency. By optimising the twist of the blades it was achieved to get sufficient amount of thrust with a propeller blade length of 0.9 meter.
For the material of the blades it was chosen to use an exterior skin made of (T300)/epoxy Uni-Directional (UD) laminate. The exterior of carbon epoxy will carry almost all the loads that are submitted on the blades. The only two things that are not handled by the carbon epoxy shell are the carrying of the buckling stresses and maintaining the shape of the carbon epoxy shell, this is done by Core Cell A300 foam. This foam will fill up the open space in the carbon epoxy shell. This comes down to a total weight of approximately 200 grams per blade. Due to the fact that the carbon fibres will be multidirectional layered, they will be able to handle all the tensile loads. Because an epoxy resin is used, also the compressive loads due to different bending forms can be carried.
To provide the required mechanical energy for the propellers an electric engine will be used. Because the required mechanical energy for the MACE is very specific, no existing engine can be used. Therefore a new specific electric engine is needed. A suitable engine was designed with the co-operation of an electric engine manufacturer, with a total mass of 3.65 kg and a total electric energy consumption of 4273.815 Wh.
The final obstacle that had to be overcome was the folding requirement. For folding, one blade will slide through a milled rail in the shaft. This will result in a V-shape, due to this configuration; it will be able to fit the propellers into the aeroshell.
In conclusion it can be stated that the MACE is feasible from a propulsion point of view. (All the requirements for the propulsion system were met). The generated propulsion system will contribute greatly to the high performance of the canyon surveyor, which can make a great step in the investigation of Mars.
- Abstract document
- Manuscript document
IAC-06-E2.2.01.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.