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Deformation measurement system for UAV components to improve their safe operation
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Aeronautics Faculty, Polish Air Force University, Poland
Department of Materials Engineering, Faculty of Mechanical Engineering, Lublin University of Technology, Poland
Department of Thermodynamics, Fluid Mechanics and Aviation Propulsion Systems, Lublin University of Technology, Poland
Department of Machine Operation and Production Process Management, Faculty of Production Engineering, University of Life Sciences in Lublin, Poland
Submission date: 2023-08-06
Final revision date: 2023-09-06
Acceptance date: 2023-09-14
Online publication date: 2023-10-12
Publication date: 2023-10-12
Corresponding author
Zbigniew Czyż   

Aeronautics Faculty, Polish Air Force University, Dywizjonu 303, 08-521, Dęblin, Poland
Eksploatacja i Niezawodność – Maintenance and Reliability 2023;25(4):172358
  • The method allows the analysis of CFRP fuselage deformation for UAV design.
  • Effective PID control algorithm and stand simulate flight operations.
  • DIC system enables precise displacement and deformation analysis of specific points in the structure.
  • Method enables effective UAV deformation analysis and design optimization for enhanced safety.
The paper presents the authors’ method and test rig for performing the deformation analysis of unmanned aircraft fuselages. To conduct the analysis, the DIC system was used, as well as a test rig designed and constructed by the authors, equipped with a dedicated control and load control system. The article presents a description of the research capabilities of the test rig developed for testing the deformation of unmanned aircraft fuselages. Due to the specific operating conditions of the designed fuselage, the test rig developed allows the simulation of loads corresponding to different flight conditions. In addition, it is possible to change the forces acting on the fuselage simultaneously for all servos or each of them separately. Finally, results showing the displacement of component control points for the considered fuselage versions are presented. The tests carried out using the developed test rig allowed the verification of the maximum deformations.
This work has been financed by the Polish National Centre for Research and Development under the LIDER program; Grant Agreement No. LIDER/27/0140/L-10/18/NCBR/2019.