This structural engineering study examines topology optimization and modal frequency analysis for a quadcopter airframe. The CAD iteration reduced modeled mass by 22%, and modal analysis estimated the first bending mode at 118 Hz against the study's 110 Hz motor-excitation threshold.
Overview
Airframe engineering study using topology optimization and modal FEA to compare structural mass and predicted vibration behaviour across a CAD design iteration.
Discipline: Simulation & Validation
Project Type: Engineering Simulation (Topology Optimization + Modal FEA Study)
Application: Aerospace & Commercial Drones
YantriX Scope Ownership
Key specifications
Objectives
Challenge
Commercial survey drones benefit from low airframe mass, while structural stiffness and modal behaviour remain design considerations. This study investigated topology optimization and modal frequency analysis as inputs to a lightweight airframe CAD iteration.
Approach
Defined structural design domains in ANSYS Mechanical, preserving motor mounts and avionics plate interfaces.
Executed density-based topology optimization under combined thrust and landing reaction forces.
Interpreted organic density isosurfaces and remodeled clean parametric CAD geometry in SolidWorks.
Conducted modal analysis; the model estimated the first bending mode at 118 Hz.
Ran static stress analysis for the defined landing load case and compared predicted stresses with the modeled material limits.
Outcomes
Deliverables
Tools used
Impact
Conclusion
The study illustrates how topology and modal analysis can inform airframe CAD decisions. Physical flight endurance and vibration performance were not measured as part of this simulation study.
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Tagged
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