Mathematic model and technical solution for surveillance and autonomous monitoring system based on endurance unmanned aerial vehicle TEODOR - VIOREL CHELARU, PHD University Politehnica of Bucharest / Romanian Space Agency, Str. Gheorghe Polizu , no. 1, PC 011061,Sector 1, Bucharest, ROMANIA teodor.chelaru@upb.ro http://wwww.pub-rcas.ro VASILE NICOLAE CONSTANTINESCU, PHD University Politehnica of Bucharest, Str. Gheorghe Polizu , no. 1, PC 011061, Sector 1, Bucharest, ROMANIA vncaero@yahoo.com http://wwww.pub-rcas.ro ADRIAN CHELARU Comfrac R&D Project Expert SRL, Str. Decebal nr.1, Sector 3, Bucharest, ROMANIA adrian.chelaru1988@gmail.com Abstract: - The paper purpose is to present some aspects regarding the calculus model and technical solutions for autonomous system based on endurance UAV (unmanned aerial vehicle), used to local observations, surveillance and monitoring interest area. The calculus methodology allows a numerical simulation of UAV evolution in bad atmospheric conditions using regular guidance structure. The UAV model which will be presented has six DOF (degrees of freedom), and autonomous control system. A simple but robust guidance system will be evaluated for different fly conditions and the results will be presented. The flight parameters and guidance will be analyzed. The paper is inspired by national project SAMO (Autonomous Aerial Monitoring System for Interest Areas of Great Endurance). Key-Words: - UAV, simulation, mathematical model, guidance, endurance, surveillance, monitoring NOMENCLATURE α - Attack angle (tangent definition); β - Sideslip angle (tangent definition); a δ - Aileron deflection; e δ - Elevator deflection; 0 e δ The balance deflection angle for the elevator; r δ - Rudder deflection; T δ - Thrust command: ψ - Azimuth angle; θ - Inclination angle; φ - Bank angle; ρ - Air density; Ω - Body angular velocity; E C B A , , , - Inertia moments; A z A y A x C C C ; ; - Aerodynamic coefficients of force in the mobile frame; A n A m A l C C C ; ; - Aerodynamic coefficients of momentum in the mobile frame; T z T y T x C C C ; ; - Thrust coefficients in the mobile frame; T n T m T l C C C ; ; - Thrust momentum coefficients in the mobile frame; S V F 2 2 0 ρ = - Reference aerodynamic force; l F H A o 0 = - Reference aerodynamic couple; 0 T - Reference thrust force; l T H T o 0 = -Reference couple thrust; RECENT ADVANCES in AUTOMATION & INFORMATION ISSN: 1790-5117 149 ISBN: 978-960-474-193-9