Performance analysis for sailplane with optional electric propulsion

Svrha ovog rada je detaljno opisati performanse jedrilice opremljene električnom pogonskom jedinicom i usporediti podatke za različite konfiguracije jedrilice, onu sa uvučenom i izvučenom pogonskom jedinicom iz trupa jedrilice. U prvom dijelu rada, napravljen je model jedrilice ASG 32-EL tvrke Alexander Schleicher kako bi se vizualno prikazale njezine karakteristike i opisale dimenzije. Prikupljeni su podatci o cijeloj jedrilici kao i elementima koji čine pogonsku jedinicu koji su poslužili za izračun nultog i induciranog otpora jedrilice. Na temelju tih podataka, napravljena je polara. U analizi performansi leta promatrali smo tri različita režima: penjanje, spuštanje i horizontalni let. Let jedrilice detaljno je razmatran kroz dva scenarija. Prvi scenarij obuhvaća situaciju u kojoj jedrilica samostalno izvodi uspon na određenu visinu, trošeći svu energiju iz baterije tijekom penjanja. Nakon dosegnute visine, počinje faza spuštanja tijekom koje se pogon vraća u trup. Drugi scenarij uključuje pomoć drugog zrakoplova u usponu jedrilice na željenu visinu. Nakon toga, jedrilica prelazi u režim horizontalnog leta koristeći svoj pogon i nakon određenog vremena kada se sva energija baterije istroši, ulazi u fazu spuštanja. Također, uspoređene su dvije konfiguracije jedrilice, s izvučenom i uvučenom pogonskom jedinicom, posebno tijekom faze spuštanja.The purpose of this research is to describe in detail the performance of a sailplane equipped with an electric propulsion unit and to compare the data for different configurations of the sailplane, the one with the propulsion unit retracted and the propulsion unit pulled out of the hull of the sailplane. In the first part of the research, a model of the sailplane ASG 32-EL of the Alexander Schleicher company was made in order to visually show its characteristics and describe its dimensions. Data were collected on the entire sailplane as well as the elements that make up the propulsion unit, which were used to calculate the zero-lift drag of the sailplane. On the basis of these data, a polar was made. In the flight performance analysis, we observed three different regimes: climb, descent and horizontal flight. For each of these flight regimes, characteristic equations describing the behavior of the glider are given. We considered the glider flight in detail through two scenarios. The first scenario includes a situation in which the glider independently climbs to a certain height, consuming all the energy from the battery during the climb. After the height is reached, the descent phase begins, during which the drive is returned to the fuselage. Another scenario involves the assistance of another aircraft in the ascent of the sailplane to the desired altitude. After that, the sailplane switches to the horizontal flight mode using its drive and after a certain time when all the battery energy is used up, it enters the descent phase. What is also compared is two glider configurations, with the propulsion unit extended and retracted, especially during the descent phase