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This paper proposes a balanced approach to design, analyze, and optimize the quadcopter landing gear strut. Designed to support the drone and mitigate landing impacts, this design is studied under static and impact loads for a quadcopter with a total mass of 2 kg and an additional 200 g payload on average. According to this, in addition to the literature review, the following studies are applied, and the design is implemented in SOLIDWORKS®: responsible for the drop test calculation, responsible for the impact force calculation, and drop test analysis. After connecting this with the SOLIDWORKS®-based design, ANSYS Workbench finite element analysis was used to make sure the parts designed can undergo these static loads. Moreover, FEA tasks are measured for two materials, determining deformation, maximum stress, and safety factor. In sum, weight reduction was the leading optimization aspect that reduced angles. Ultimately, the landing performance was enhanced by reducing the optimal strut to 10° and 35°. These analyses were completed through ANSYS Workbench, as discussed later.

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Optımization of Inclined Landing Strut Angle in UAV

  • 会议论文

  • 发表日期：

    2025年

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  • Adarsh Patil,
  • Nishad Hooli,
  • Bhagyashree Yelamali,
  • Om Prashanth,
  • M. Sridhar,
  • Achal Takale

摘要

This paper proposes a balanced approach to design, analyze, and optimize the quadcopter landing gear strut. Designed to support the drone and mitigate landing impacts, this design is studied under static and impact loads for a quadcopter with a total mass of 2 kg and an additional 200 g payload on average. According to this, in addition to the literature review, the following studies are applied, and the design is implemented in SOLIDWORKS®: responsible for the drop test calculation, responsible for the impact force calculation, and drop test analysis. After connecting this with the SOLIDWORKS®-based design, ANSYS Workbench finite element analysis was used to make sure the parts designed can undergo these static loads. Moreover, FEA tasks are measured for two materials, determining deformation, maximum stress, and safety factor. In sum, weight reduction was the leading optimization aspect that reduced angles. Ultimately, the landing performance was enhanced by reducing the optimal strut to 10° and 35°. These analyses were completed through ANSYS Workbench, as discussed later.