Unmaned Aircraft Vehicle are often used in trafic monitoring and rescue patrolling in civil areas. Because of their benefits, nowadays, there's a growing tendoncy to design, construct and develop of economic UAV that can land electronic and civil equipment. Landing instrument must reduce the speed of goods so that they can land in a reasonable speed that reduce of landing and prevent any harm to delicate electronic parts and other equipment in cargo.In this project with usage of self rotating condition of helicopter, a rotor has been designed and developed. Functions of this rotor evaluated in ground tests with regard of the effective parameters: Pith angle , pricon. angle and hing angle In operation condition this rotor should abk to carry a load that releases from an altitude and settle it smoothly on ground .In order to rotor starts its departure in a correct direction- that fore edge is in front - the pitch angle must be negative .For more trust force pith angle must change to positive automatically after releasing .To approaching this purpose, in design procedure clamp- the medium of plug and blade-made of polyamide material and a groove created on it to provide its flexibility of changing pitch angle. After analyzing and loading designed parts including plug ,clamp and composite blade with analysis software, parts developed and mounted. After fixing parts , with a car and some accurate equipments like load cell and takometer trust force and rotor rpm measured in some different cases. Finally the rate of each angle and parameter effect analyzed. Keywords: self rotating , hing angle, pitch angle, pricon angle, leading edge.
