JSBSim: An Open Source Flight Dynamics Model in C++

2004 ◽  
Author(s):  
Jon Berndt
Keyword(s):  
Open Source ◽  
Flight Dynamics ◽  
Dynamics Model ◽  
Flight Dynamics Model

scholarly journals Giant Big Stik R/C UAV Computer Model Development in JSBSim for Sense and Avoid Applications

Drones ◽  
2019 ◽  
Vol 3 (2) ◽  
pp. 48
Author(s):  
Oihane Cereceda ◽  
Luc Rolland ◽  
Siu O’Young
Keyword(s):  
Unmanned Aerial Vehicles ◽  
Open Source ◽  
Computer Model ◽  
Model Development ◽  
Flight Dynamics ◽  
Unmanned Aircraft ◽  
Dynamics Model ◽  
Sense And Avoid ◽  
Fit For Purpose ◽  
Flight Dynamics Model

Open-source aerospace simulation packages often lack unmanned aerial vehicles (UAVs) models, limiting the study of their interaction with other elements in the airspace. These events, which are a consequence of encounters between manned and unmanned aircraft, have recently attracted interest due to the uncertainties created by UAVs in real environments. In this paper, a fit-for-purpose flight dynamics model specific for sense and avoid (SAA) strategies in near mid-air collision scenarios is developed based on existing model development practices and adjusted from flight data. The Giant Big Stik is recognized as the representative aircraft for testing SAA manoeuvres due to its capabilities. The simulation platform is based on the JSBSim open-source flight dynamics model, and the SAA application is carried out following the current regulations and flight recommendations for UAVs in Canada. Through this methodology, the error between the real and the computer model is reduced in every step that is minimal for the SAA application. The relevance of this paper is also shown in future applications, where this model will be incorporated into more complex simulations with manned aircraft for the study of avoidance manoeuvres that will serve the safe integration of UAVs into the airspace.

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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