Zobrazit v EDS

Flight dynamics modelling and simulation of a tailless UCAV lambda wing configuration.

Uloženo v:
Podrobná bibliografie
Název: Flight dynamics modelling and simulation of a tailless UCAV lambda wing configuration.
Autoři: S., Sudhakar (AUTHOR) sudhakar@mech.sastra.ac.in, C., Ramprasadh (AUTHOR) crprasadh@mech.sastra.edu, Savarinathan, Prem (AUTHOR) premavilas@mech.sastra.edu, J., Avila (AUTHOR) avila@ece.sastra.ac.in
Zdroj: Aircraft Engineering & Aerospace Technology. 2025, Vol. 97 Issue 8, p930-943. 14p.
Témata: *DYNAMIC stability, *COMPUTATIONAL aerodynamics, *AIRPLANE wing design, *AIRPLANE wings, *FEEDBACK control system stability, *DRONE aircraft, *FLIGHT simulators
Reviews & Products: SIMULINK (Computer software)
Abstrakt: Purpose: This research work aims to develop and validate a flight dynamics model for an unmanned combat aerial vehicle (UCAV) that has a tailless flying wing configuration with a lambda wing planform. This study includes the generation of complete aerodynamic data by both computational fluid dynamics (CFD) and US Air Force (USAF) DATCOM methods to facilitate six-degree-of-freedom (6-DOF) flight simulation, providing an understanding of the aircraft's performance. Design/methodology/approach: The UCAV model was developed using 3D CAD modelling in SolidWorks, referencing SACCON geometric properties. Stability, control and dynamics derivatives of the UCAV model are generated using CFD and DATCOM methods and then validated with wind tunnel experimental data. 6-DOF flight simulations are conducted using both DATCOM and integrated CFD-DATCOM approaches. Findings: The analysis is presented at various angles of attack and sideslip angles. CFD analysis provided static stability derivatives, and USAF DATCOM methods computed static stability, control and dynamics derivatives. Flight simulation results are compared, and the integrated CFD-DATCOM approach demonstrated greater accuracy and reliability, particularly for steady-state pitch responses and dynamic stability. The pitch attitude controller enhanced system stability, reduced steady-state error and improved overall performance. Research limitations/implications: This present research study should consider transonic and high-speed performance aspects and also implement an automatic robust controller for UCAV flight performance analysis. Practical implications: This research work can be useful for developing a variety of control strategies for a tailless UCAV, including different combat missions in a flight simulation scenario. Originality/value: UCAV flight dynamic data is limitedly available for flight simulations in the literature, particularly for tailless UCAV configurations. This study contributes by obtaining such data through integrated CFD-DATCOM methods. The 6-DOF flight simulation was set up in MATLAB Simulink using an indigenously developed UCAV flight dynamic model. [ABSTRACT FROM AUTHOR]
Databáze: Academic Search Index
Popis
Abstrakt:Purpose: This research work aims to develop and validate a flight dynamics model for an unmanned combat aerial vehicle (UCAV) that has a tailless flying wing configuration with a lambda wing planform. This study includes the generation of complete aerodynamic data by both computational fluid dynamics (CFD) and US Air Force (USAF) DATCOM methods to facilitate six-degree-of-freedom (6-DOF) flight simulation, providing an understanding of the aircraft's performance. Design/methodology/approach: The UCAV model was developed using 3D CAD modelling in SolidWorks, referencing SACCON geometric properties. Stability, control and dynamics derivatives of the UCAV model are generated using CFD and DATCOM methods and then validated with wind tunnel experimental data. 6-DOF flight simulations are conducted using both DATCOM and integrated CFD-DATCOM approaches. Findings: The analysis is presented at various angles of attack and sideslip angles. CFD analysis provided static stability derivatives, and USAF DATCOM methods computed static stability, control and dynamics derivatives. Flight simulation results are compared, and the integrated CFD-DATCOM approach demonstrated greater accuracy and reliability, particularly for steady-state pitch responses and dynamic stability. The pitch attitude controller enhanced system stability, reduced steady-state error and improved overall performance. Research limitations/implications: This present research study should consider transonic and high-speed performance aspects and also implement an automatic robust controller for UCAV flight performance analysis. Practical implications: This research work can be useful for developing a variety of control strategies for a tailless UCAV, including different combat missions in a flight simulation scenario. Originality/value: UCAV flight dynamic data is limitedly available for flight simulations in the literature, particularly for tailless UCAV configurations. This study contributes by obtaining such data through integrated CFD-DATCOM methods. The 6-DOF flight simulation was set up in MATLAB Simulink using an indigenously developed UCAV flight dynamic model. [ABSTRACT FROM AUTHOR]
ISSN:17488842
DOI:10.1108/AEAT-08-2024-0241