Martian Flight Prototypes
- Paper number
IAC-05-E2.3.08
- Author
Mr. Asier Ania, Royal Military College of Canada, Canada
- Coauthor
Dr. Dominique Poirel, Royal Military College of Canada, Canada
- Coauthor
Dr. Marie-José Potvin, Canadian Space Agency, Canada
- Coauthor
Mr. Gabriel Desmarais, Canadian Space Agency, Canada
- Year
2005
- Abstract
There is a need to maximize the exploration of Mars by covering a larger area of terrain. Robotic rovers are an excellent first step in engaging the Martian landscape; however they are limited in their range and ability to overcome obstacles. The next generation of robotic surveyors could be aerial vehicles that would have a significantly greater domain. A comparative analysis of varying flight technologies for use on Mars was conducted. The result of this analysis concluded that the use of a novel flapping wing approach to a Mars aerial vehicle could be the most efficient for a variety of reasons. Insect flapping wing flight is the fundamental basis of the flapping wing prototype designs that have been developed. The low Reynolds number of flapping wing flight employed by insects is of interest due to the low density atmosphere on Mars. Insects generate lift through a variety of unsteady aerodynamic mechanisms such as the so-called delayed stall, wake capture, and rotational mechanisms (i.e. clap and fling). Insect flight is extremely efficient with very high lift coefficients and unparalleled maneuverability, which are unachievable with traditional aerodynamics. The ultimate goal of the flapping wing study is to use a design-oriented approach that exploits the unsteady aerodynamic mechanisms of insects for use in planetary exploration. A rotary mechanism (rotorcraft) will be used as the reference base in order to evaluate the other prototypes because of its relative simplicity of design and better known aerodynamics. The first flapping wing prototype is based on the clap \& fling aerodynamic mechanism and the other is a patented novel rotary-flapping combination. Initial experiments have resulted in the identification of various undesired vibrations inherent in the prototype designs. The vibrations have been minimized with the redesign of several components of the prototypes. The quantification of the overall lift force produced in a set of three orthogonal axes is being achieved by using a 6-axis load cell that will measure the total forces and moments produced by the mechanism. An encoder is being used to measure the flapping frequency and will allow the ability to cross reference the force and moment data with the wing position. The wing position data along with the use of smoke visualization will be useful in inferring the aerodynamic mechanisms that are being used. The experimental testing of the lift production of the prototypes is being rigorously conducted with various wing types, wing angle of attacks, flapping speeds, as well as other aerodynamic variables. The lift characteristics of the different prototypes in varying atmospheres will also be investigated with the use of a vacuum pressure chamber.
- Abstract document
- Manuscript document
IAC-05-E2.3.08.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.