| Abstract | U ovom diplomskom radu je prikazana i objašnjena konstrukcija bespilotne letjelice autogira uz proračune performansi. Opisane su karakteristike autogira koje se razlikuju od aviona i helikoptera, osobito na malim brzinama. Također je opisan i prikazan način upravljanja autogirom, koji se razlikuje od načina upravljanja helikoptera i aviona. Detaljno je opisano i prikazano konstrukcijsko rješenje rotora koji je izrađen za bespilotnu letjelicu autogira, i mehanizma upravljanja, za što je napravljen CAD model letjelice. Također je prikazan i opisan način izrade i modifikacije dijelova rotora i priložena tehnička dokumentacija. Performanse bespilotne letjelice autogira izračunate su iz snage potrebne za let i raspoložive snage. Raspoloživa snaga je dobivena iz izmjerenog statičkog potiska i podataka za propeler od proizvođača. Napravljena je i alternativna metoda za slučaj da podataka propelera nema, koja se zasniva na teoriji diska, i pokazala se kao pouzdana za manje brzine leta, ali nije korištena u proračunu performansi. Snaga potrebna za let izračunata je iz dostupne literature, napravljena je i alternativna metoda gdje je rotor zamijenjen diskom istog promjera. Proračun je napravljen za obje metode i uspoređeni su rezultati iz kojih se mogu izvući zanimljivi zaključci. |
| Abstract (english) | This paper presents and explains the design the design of an unmanned autogiro and calculates its performance. It explains characteristics of autogiro, that are different from planes and helicopters, especially at low speeds. The control mechanism of the aircraft is illustrated and explained. The rotor that has been designed for the aircraft, and its control mechanism are being described in detail, followed by drawings, for which CAD model of the aircraft was made. The paper also explains manufacturing and modification process of rotor parts, and is followed with technical documentation. Performance of the unmanned autogiro was calculated from power required for horizontal flight and power available. Available power was calculated from the measured static thrust, and propeller specifications. Alternative method for propeller performance was done, for the case if they would be unknown, and it is based on the disc theory, and it proved to be reliable for smaller velocity, but it wasn’t used for the performance calculations. The power required for flight was calculated from the available literature, an alternative method was also made, where rotor was replaced by a disc of the same diameter. Performance was calculated for the both methods, data, compared, and interesting conclusions made. |
