Open AccessDEFINITION THE STABILITY AND CONTROL DERIVATIVES IN THE LONGITUDINAL CHANNEL OF SMALL SUBSONIC UAV
Author(s) -
Олександр Васильович Збруцький,
Роман В. Карнаушенко,
Олександр Петрович Мариношенко
Publication year - 2013
Publication title -
mehanika giroskopičeskih sistem/mehanìka gìroskopìčnih sistem
Language(s) - English
Resource type - Journals
eISSN - 2519-2272
pISSN - 0203-3771
DOI - 10.20535/0203-377126201330674
Subject(s) - pitching moment , longitudinal static stability , aerodynamics , stability derivatives , mechanics , airspeed , control theory (sociology) , lift (data mining) , aerodynamic center , drag , physics , angle of attack , acoustics , aerospace engineering , engineering , computer science , control (management) , artificial intelligence , data mining
The problems of determining the stability and control derivatives of small subsonic UAV in the longitudinal channel are solved.An approach to the stability and control derivatives determination based on the analysis results of wind tunnel investigation and analyzes conducted .To the longitudinal movement usually referred traffic aircraft where it is in the plane of symmetry of one and the same vertical plane. Thus the aerodynamic lateral force, rolling moment and yaw angles of heel and slip and angular velocity of roll and glide zero. To investigate the longitudinal motion of the aircraft (movement in the longitudinal channel) important issue is to determine the components of the aerodynamic forces and moments as a function of the kinematic parameters of the flight, the so-called aerodynamic derivatives.Given that the object is a lightweight UAV that has subsonic range of operating speeds, significantly less than the speed of sound, it should be noted that the derivative of the coefficient of lift coefficient and drag coefficient for longitudinal moment of flight speed can be taken to be zero at subsonic speed range. This is due to the fact that these values are almost constant with airspeed , lower the speed of sound . Change the value of these parameters with growth rate appears only when approaching the speed of sound, due to changes in the position of the center of pressure and the additional impedance. Also, when calculating stability derivatives are generally neglected by changing the drag because the drag value of derivatives are small and commensurate with the error of the calculation methods.Derivatives of lift coefficient by the following kinematic parameters: angle of attack, the angular velocity of rotation around the transverse axis , rate of change of angle of attack and angle of elevator deflection are defined.Obtained results make it possible to analyze the movement of the UAV in the longitudinal channel and determinate the coefficients of a mathematical model of the UAV. Also possible to determinate the stability and controllability of the UAV during automatic control systems design.