Anvelope leta letelice u atmosferi Marsa

Abstract

Doktorska disertacija „Anvelope leta letelice u atmosferi Marsa" prikazuje detaljnu analizu aerodinamike i performansi, a na osnovu novog konceptualnog dizajna, lake letelice za atmosferu Marsa, ALPEMA. Takva letelica, omogućava atmosfersko ubacivanje (primena koncepta aeroshell), ali i direktno poletanje sa površine Marsa. Složena atmosfera Marsa zahteva pojednostavljenu, a opet efikasnu geometriju, koja može maksimizirati finesu. Marsov atmosferski pritisak, gustina, temperatura i varijacije brzine zvuka zahtevaju pomno izabrani motor, koji letelici ALPEMA donosi značajne prednosti u vezi sa iskorišćenjem snage. Efikasna vitkost i polara otpora dovode do optimalnih anvelopa leta, kao dokaza pune održivosti ALPEMA projekta. Posebne performanse i osnovna aerodinamika postavljaju granice i ograničenja projekta, u skladu s sličnim uporedivim pristupima. Izabrani propeler, tema kojoj je u disertaciji posvećena posebna pažnja, omogućuje ALPEMA da koristi maksimalnu snagu svog motora, prikazanu kroz Vmin i Vmax, koji su značajni ulazni podaci za anvelope leta. Anvelopa leta, kao ishodište celokupne analize, ima efikasnu širinu i profil za različite moguće misije. Specifični propeler i motor ALPEMA su jasna komparativna prednost u odnosu na slične, uporedive projekte, kao i u radu prikazana anvelopa leta.

Doctoral dissertation „Flight Envelopes of an Aircraft in Mars Atmosphere" presents detailed aerodynamics and performances analysis, based on a new conceptual design of the light aircraft for Mars atmosphere, ALPEMA. Such aircraft allows atmospheric dropping (aeroshell concept application), as well as direct take-off from Martian surface. Complex Martian atmosphere demands for simplified yet efficient wing geometry, capable of maximizing Lift-to-Drag ratio. Martian atmospheric pressure, density, temperature and speed of sound variations, demand a scrutinized powerplant choice, which gives significant advantages to ALPEMA in the area of power exploitation. Efficient aspect ratio and drag polar lead to optimal flight envelopes as a proof of sustainability of ALPEMA project. Special performances and basic aerodynamics provide boundaries and constraints of the project, in line with similar and comparable approaches. Chosen propeller, topic which had significant attention in this dissertation, allows for ALPEMA to use maximum power capabilities of its engine, described through Vmin and Vmax, which are significant inputs for flight envelope. Flight envelope, as the goal of this entire analysis, provides effective width and profile for a variety of possible missions. ALPEMA’s specific propeller and engine are a certain decisive advantage when observed along comparable projects, together with its flight envelope.