An effort has been made to take into account the aerodynamic and inertial coupling between the longitudinal and lateral dynamics of the helicopter. As a result of the on-going research on the dynamic modeling of the UAV helicopter, a complete six-degree-of-freedom (6-DoF) LPV model has been developed in the MathWork's MATLAB and Simulink environment. The previous paper also highlighted the flight test instrumentation and data collection procedures. The response obtained from this model showed a high degree of correlation with the actual flight test data. Previously, an uncoupled three-degree-of-freedom (3-DoF) linear parameter varying (LPV) dynamic model based on stability and control derivatives was presented. The discrepancy between the simulation and flight test response showed significant improvement, which satisfies the regulation tolerance.This paper presents the continued research on UAV dynamic modeling at the Aerospace Engineering Department of the University of Kansas using a Thunder Tiger Raptor 50 V2 remote control (RC) helicopter. The presented results demonstrate that the applied enhancement procedure has improved the simulation accuracy in longitudinal motion.
A simulation validation process is introduced to evaluate the accuracy of the enhanced 6 DOF simulation model.
Next, the classical Maximum Likelihood (ML) estimation method is applied to calculate aerodynamic derivatives from flight test data, these parameters are utilised to correct the initial aerodynamic table. The enhancement process starts with identifying longitudinal equations of motion for sensitivity analysis, where the effect of crucial parameters is analysed and then adjusted using the model tuning technique.
The baseline simulation model database is constructed using multi-fidelity analysis methods such as wind tunnel (W/T) test, computational fluid dynamic (CFD) and empirical calculation. In this study, the full-scale flight testing of a 2-seater aircraft has been performed in specific longitudinal manoeuver for model enhancement and simulation validation purposes. This paper proposes a procedure to improve the accuracy of the light aircraft 6 DOF simulation model by implementing model tuning and aerodynamic database correction using flight test data.
0 kommentar(er)
