It contains the computation of aircrafts’ structural parameters, position of the center of gravity, moment of inertia, aerodynamic parameters and the modeling of actuators.įor small-scaled fixed-wing UAVs, the structural parameters, like the wing span l, mean aerodynamic chord c ¯ and the reference area S, could be measured precisely. The establishment of Aircraft Dynamic Model (ADM) should be accomplished first before any task designing.
With the light weight, small volume and simple take-off, small UAVs could execute tasks like the close-range monitoring in a covert and flexible way. In contrast to the large-scaled high-altitude long-term Unmanned Aerial Vehicles (UAVs) for remote surveillance and combat, the small-scaled fixed-wing UAVs, like “Raven” RQ-11 and Sand Hawk of the US, or “Rainbow-802” of China, have unique superiority in civilian and military fields. Test results tell the rationality of the semi-empirical method and show the improvement of accuracy of ADM after the compensation of the parameters. Then, real flight tests are implemented to verify the calculation and identification process. Based on a small-scaled fixed-wing aircraft driven by propeller, the airborne sensors are chosen and the model of the actuators are constructed. Meanwhile, the observability of the targeted parameters is analyzed and strengthened through multiple maneuvers. Secondly, the residuals of each derivative are proposed to be identified or estimated further via Extended Kalman Filter (EKF), with the observations of the attitude and velocity from the airborne integrated navigation system.
#Aircraft wing aspect ratio calculator software#
All the longitudinal and lateral aerodynamic derivatives are firstly calculated through semi-empirical method based on the aerodynamics, rather than the wind tunnel tests or fluid dynamics software analysis. In this paper, the procedure of computing the aerodynamic parameters is developed. The establishment of the Aircraft Dynamic Model (ADM) constitutes the prerequisite for the design of the navigation and control system, but the aerodynamic parameters in the model could not be readily obtained especially for small-scaled fixed-wing UAVs.
0 kommentar(er)
