Highlights: What are the main findings? A screwless FPV drone chassis with interlocking, interchangeable arms inspired by Japanese joinery was designed in Autodesk Inventor, analyzed through a hierarchical simulation philosophy combining global static analyses validated by simplified linear models, and nonlinear transient simulations for crash and maximum acceleration scenarios using Inventor Nastran. The structure was 3D printed in PETG as a rapid prototype to validate the design and analysis methodology, with planned production in carbon fiber to achieve final performance and durability goals. What are the implications of the main findings? The proposed design and validation workflow offer a comprehensive pathway for developing lightweight, crash-resilient sub-250 g UAVs. This approach bridges theoretical FEM modeling with real-world performance, enhancing the structural and functional reliability of micro aerial vehicles. This work presents the structural analysis and validation of a sub-250 g FPV drone chassis, emphasizing both theoretical rigor and practical applicability. The novelty of this contribution lies in four complementary aspects. First, the structural philosophy introduces a screwless frame with interchangeable arms, joined through interlocking mechanisms inspired by traditional Japanese joinery. This approach mitigates stress concentrations, reduces weight by eliminating fasteners, and enables rapid arm replacement in the field. Second, validation relies on nonlinear static and transient FEM simulations, explicitly including crash scenarios at 5 m/s, systematically cross-checked with bench tests and instrumented flight trials. Third, unlike most structural studies, the framework integrates firmware (Betaflight), GPS, telemetry, and real flight performance, linking structural reliability with operational robustness. Finally, a practical materials pathway was implemented through a dual-track strategy: PETG for rapid, low-cost prototyping, and carbon fiber composites as the benchmark for production-level performance. Nonlinear transient FEM analyses were carried out using Inventor Nastran under multiple load cases, including maximum motor acceleration, pitch maneuvers, and lateral impact at 40 km/h, and were validated against simplified analytical models. Experimental validation included bench and in-flight trials with integrated telemetry and autonomous features such as Return-to-Home, demonstrating functional robustness. The results show that the prototype flies correctly and that the chassis withstands the loads experienced during flight, including accelerations up to 4.2 G (41.19 m/ (Formula presented.)), abrupt changes in direction, and high-speed maneuvers reaching approximately 116 km/h. Quantitatively, safety factors of approximately 5.3 under maximum thrust and 1.35 during impact confirm sufficient structural integrity for operational conditions. In comparison with prior works reviewed in this study, the key contribution of this work lies in unifying advanced, crash-resilient FEM simulations with firmware-linked flight validation and a scalable material strategy, establishing a distinctive and comprehensive workflow for the development of sub-250 g UAVs.
Highlights: What are the main findings? A screwless FPV drone chassis with interlocking, interchangeable arms inspired by Japanese joinery was designed in Autodesk Inventor, analyzed through a hierarchical simulation philosophy combining global static analyses validated by simplified linear models, and nonlinear transient simulations for crash and maximum acceleration scenarios using Inventor Nastran. The structure was 3D printed in PETG as a rapid prototype to validate the design and analysis methodology, with planned production in carbon fiber to achieve final performance and durability goals. What are the implications of the main findings? The proposed design and validation workflow offer a comprehensive pathway for developing lightweight, crash-resilient sub-250 g UAVs. This approach bridges theoretical FEM modeling with real-world performance, enhancing the structural and functional reliability of micro aerial vehicles. This work presents the structural analysis and validation of a sub-250 g FPV drone chassis, emphasizing both theoretical rigor and practical applicability. The novelty of this contribution lies in four complementary aspects. First, the structural philosophy introduces a screwless frame with interchangeable arms, joined through interlocking mechanisms inspired by traditional Japanese joinery. This approach mitigates stress concentrations, reduces weight by eliminating fasteners, and enables rapid arm replacement in the field. Second, validation relies on nonlinear static and transient FEM simulations, explicitly including crash scenarios at 5 m/s, systematically cross-checked with bench tests and instrumented flight trials. Third, unlike most structural studies, the framework integrates firmware (Betaflight), GPS, telemetry, and real flight performance, linking structural reliability with operational robustness. Finally, a practical materials pathway was implemented through a dual-track strategy: PETG for rapid, low-cost prototyping, and carbon fiber composites as the benchmark for production-level performance. Nonlinear transient FEM analyses were carried out using Inventor Nastran under multiple load cases, including maximum motor acceleration, pitch maneuvers, and lateral impact at 40 km/h, and were validated against simplified analytical models. Experimental validation included bench and in-flight trials with integrated telemetry and autonomous features such as Return-to-Home, demonstrating functional robustness. The results show that the prototype flies correctly and that the chassis withstands the loads experienced during flight, including accelerations up to 4.2 G (41.19 m/ (Formula presented.)), abrupt changes in direction, and high-speed maneuvers reaching approximately 116 km/h. Quantitatively, safety factors of approximately 5.3 under maximum thrust and 1.35 during impact confirm sufficient structural integrity for operational conditions. In comparison with prior works reviewed in this study, the key contribution of this work lies in unifying advanced, crash-resilient FEM simulations with firmware-linked flight validation and a scalable material strategy, establishing a distinctive and comprehensive workflow for the development of sub-250 g UAVs. Read More
Related posts:
Analysis of some preliminary simulations of Keplerian turbulence
Thermoelastic evaluation of the payload module of the ARIEL mission
Vehicle’s Lateral Motion Control Using Dynamic Mode Decomposition Model Predictive Control for Unknown Model
Methodology for robust analysis of bolts slippage in cryogenic space missions
Verification and validation of almaraz NPP trace model
A multi-strategy fuzzy control method based on the Takagi-Sugeno model