A Tensor 6-DOF Flight Dynamics Model for a Low-Cost, Real-Time Flight Simulator

2008 ◽  
Author(s):  
Eduardo Zapico ◽  
Pedro Giraudo ◽  
Horacio Abbate
Keyword(s):  
Real Time ◽  
Low Cost ◽  
Flight Dynamics ◽  
Flight Simulator ◽  
Dynamics Model ◽  
Flight Dynamics Model

Towards real-time pilot-in-the-loop CFD simulations of helicopter/ship dynamic interface

2017 ◽  
Vol 08 (04) ◽  
pp. 1743005 ◽  
Author(s):  
Ilker Oruc ◽  
Joseph F. Horn ◽  
Jeremy Shipman ◽  
Susan Polsky
Keyword(s):  
Real Time ◽  
Flight Dynamics ◽  
Ground Effect ◽  
Dynamics Simulation ◽  
Computational Domain ◽  
Dynamics Model ◽  
Disk Model ◽  
Performance Improvements ◽  
Dynamic Interface ◽  
Flight Dynamics Model

This study presents the development of computationally efficient coupling of Navier–Stokes Computational Fluid Dynamics (CFD) with a helicopter flight dynamics model with the ultimate goal of real-time simulation of airwake effects in the helicopter/ship Dynamic Interface (DI). The flight dynamics model is free to move within a computational domain, where the main rotor forces are converted to source terms in the momentum equations of the CFD solution using an actuator disk model. Simultaneously, the CFD solver calculates induced velocities that are fed back to the simulation and affect the aerodynamic loads in the flight dynamics. The CFD solver models the inflow, ground effect and interactional aerodynamics in the flight dynamics simulation, and these calculations can be coupled with the solution of the external flow (e.g., ship airwake effects). The simulation framework for fully-coupled pilot-in-the-loop (PIL) flight dynamics/CFD is demonstrated for a simplified shedding wake. Initial tests were performed with 0.38 million structured grid cells running on 352 processors and showed near-real-time performance. Improvements to the coupling interface are described that allow the simulation run at near-real-time execution speeds on currently available computing platforms. Improvements in computing hardware are expected to allow real-time simulations.

scholarly journals Study on longitudinal stability of ducted vertical take-off and landing fixed-wing UAV

2021 ◽  
Vol 39 (4) ◽  
pp. 712-720
Author(s):  
Chunyang Wang ◽  
Zhou Zhou ◽  
Rui Wang ◽  
Kelei Wang
Keyword(s):  
Experimental Data ◽  
Flight Dynamics ◽  
Model Parameters ◽  
Dynamics Model ◽  
Flight Stability ◽  
Aerodynamic Model ◽  
Characteristic Cross Section ◽  
Flight Dynamics Model ◽  
Six Degree Of Freedom ◽  
Blade Element

The longitudinal flight stability of the ducted vertical take-off and landing fixed-wing UAV during the flight state of hovering and transition is studied. Firstly, based on the Blade-Element Momentum Theory (BEMT) and experimental data, a coaxial dual-rotor ducted aerodynamic model and a thrust ducted aerodynamic model based on characteristic cross-section calculations are established. The model parameters are identified according to the experimental data. Secondly, a UAV flight dynamics model with thrust duct deflection is established according to the six-degree-of-freedom equations. Finally, the case UAV was used to solve the longitudinal balance and stability analysis of hovering and transition state with the established model method, and compared with the hovering experimental results. The results show that the UAV flight dynamics model combined with the ducted dynamic model established in the article can accurately describe the longitudinal flight stability characteristics of this type of aircraft.

Pilot Sensitivity to Simulator Flight Dynamics Model Formulation for Stall Training

2019 ◽  
Author(s):  
Kevin Cunningham ◽  
Gautam H. Shah ◽  
Patrick C. Murphy ◽  
Melissa A. Hill ◽  
Brent Pickering
Keyword(s):  
Flight Dynamics ◽  
Dynamics Model ◽  
Model Formulation ◽  
Flight Dynamics Model
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