Abstract
Conceptual Design and Flight Envelopes of a Light Aircraft for Mars Atmosphere
Highlights
Efforts to overcome numerous challenges observable in Martian atmosphere are one of the ongoing and permanent topics for aerospace engineering in last decades
Chosen propeller allows for ALPEMA to use maximum power capabilities of its engine, described through Vmin and Vmax, which are significant inputs for flight envelope
ALPEMA is generally comparable with specific set of concepts (Tab. 2): 1) Conceptual aircraft - Mars Sample Aircraft (MSA); 2) Conceptual aircraft - Mars Airplane (JAXA); 3) Conceptual aircraft - Mars Airplane (Fujita, Tohoku University, Japan); 4) Conceptual aircraft - ARES Mars Scout Mission (NASA)
Summary
Efforts to overcome numerous challenges observable in Martian atmosphere are one of the ongoing and permanent topics for aerospace engineering in last decades. It is a scientific consensus to scale data between Earth and Mars, in order to compensate for variations in Martian atmosphere In such a way, parameters necessary for analysis and calculation of flight to Mars are seen in scaling relation with their respective counterpart on Earth. EKMEDŽIĆ et al.: Conceptual Design and Flight Envelopes of a Light Aircraft for Mars Atmosphere scaling heights on Earth and mars, which are compared as 11 and 7 kilometres, respectively. Another boundary and limitation is the chemical composition of Martian atmosphere (Fig. 1). Specific light brown to orange-reddish coloration of Martian atmosphere is the consequence of surface dust, which is lifted and mixed with atmosphere Those values reach 1.5 micrometres (source: Mars Exploration Rover data). Temperature and viscosity differences in Martian atmosphere represent another challenge (Fig. 3 and Fig. 4)
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