Dragonfly Lander Flight Dynamics Model Enhancement Using FLIGHTLAB-Viscous Vortex Particle Method

Enhancements of a Dragonfly Titan lander flight dynamics model to incorporate aerodynamic interference effects derived from Viscous Vortex Particle Method (VVPM) are presented in this study. The methodology for model enhancement is based on the use of the FLIGHTLAB®- VVPM application to simulate a representative range of aircraft operating conditions. Results from the simulations were then used to quantify and tabulate interference effects. This database is then used to provide adjustments to a finite state inflow model to incorporate aerodynamic interference effects across the anticipated flight envelope. The enhanced finitestate inflow model was validated through comparative analysis with results obtained from Reynolds-Averaged Navier-Stokes (RANS) Computational Fluid Dynamics (CFD), VVPM, and wind tunnel experiments. Moreover, the enhanced finite-state inflow model of the full vehicle was compared to analogous VVPM simulations for control response, and good agreement is found.