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<p>Lift and cruise type unmanned aerial vehicles (UAVs) under MTOW (maximum take-off weight) of 200&#xa0;kg are widely developing for long-range delivery or other purposes. Most of these UAVs are designed to have fixed wings because they need to cruise for long-term operations. Also, to land or take-off at a designated location, lifting motors and propellers are required. Thus, the configuration of these UAVs is similar to the conventional fixed wing aircraft but also different. Although they have similar configurations, the existed weight estimation methods for conventional aircrafts cannot be applied due to their small MTOW. Thus, it is difficult to estimate the initial airframe weight in the early design phase. The inaccurate estimation of airframe weight can reduce the accuracy of performance analysis, so that it is hard to meet its target requirements. In this paper, the airframe weight is calculated using the parameters from the initial UAV configuration. The parameters can be determined in the early design phase, and linked to other design parameters for the aerodynamic and power performance calculations of the UAV. From this proposed weight estimation method, the effects of parameter changes to the airframe weight can be also investigated. This method was validated from the measured weight data of the lift and cruise type UAV developed by Korea Aerospace Research Institute (KARI).</p>

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Configuration-Based Airframe Weight Estimation of Lift and Cruise Type Unmanned Aerial Vehicle

  • 期刊论文

  • 发表日期：

    2025年4月24日

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  • Byeong-Wook Jang

摘要

Lift and cruise type unmanned aerial vehicles (UAVs) under MTOW (maximum take-off weight) of 200 kg are widely developing for long-range delivery or other purposes. Most of these UAVs are designed to have fixed wings because they need to cruise for long-term operations. Also, to land or take-off at a designated location, lifting motors and propellers are required. Thus, the configuration of these UAVs is similar to the conventional fixed wing aircraft but also different. Although they have similar configurations, the existed weight estimation methods for conventional aircrafts cannot be applied due to their small MTOW. Thus, it is difficult to estimate the initial airframe weight in the early design phase. The inaccurate estimation of airframe weight can reduce the accuracy of performance analysis, so that it is hard to meet its target requirements. In this paper, the airframe weight is calculated using the parameters from the initial UAV configuration. The parameters can be determined in the early design phase, and linked to other design parameters for the aerodynamic and power performance calculations of the UAV. From this proposed weight estimation method, the effects of parameter changes to the airframe weight can be also investigated. This method was validated from the measured weight data of the lift and cruise type UAV developed by Korea Aerospace Research Institute (KARI).