Helicopter trim analysis

U ovom diplomskom radu provedena je analiza ravnotežnog leta helikoptera konvencionalne konfiguracije s glavnim i repnim rotorom. Opisane su geometrijske, inercijalne i aerodinamičke karakteristike helikoptera pri čemu sile i momenti koji djeluju na helikopter, osim glavnog i repnog rotora, dolaze i od trupa, te horizontalnog i vertikalnog stabilizatora. Opisan je iterativni postupak izračuna potrebnih varijabli te je napravljen programski model ravnotežnog leta. Također, provedena je analiza parametara algoritma te su dobiveni rezultati, za tri različita helikoptera, uspoređeni sa drugim dostupnim modelima i sa podacima dobivenim tijekom leta.In this master’s thesis trim analysis of a helicopter with a conventional configuration was carried out. The geometric, inertial and aerodynamic characteristics of the helicopter are described where forces and moments that act on the helicopter are caused by the main rotor, fuselage, empennage and tail rotor. An analytical description of the iterative procedure is also explained and a numerical model of flight trim was constructed. The parameter analysis was carried out and the results of the three different helicopters were compared with other available models and with data obtained during the flight