• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.9
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• pp.723-734
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• 2018

A structural weight estimation methodology for the multicopter design process is presented. In general, a multicopter is composed of an airframe, motors, propellers, battery and so on. Among these, the weight of motors, propellers and battery can be obtained from the weight trends with respect to design parameters. However, the structural weight is hard to be estimated due to the various configurations and design concepts of multicopters. Moreover, the airframe weights of most commercial multicopter products are not provided. Thus, an accurate airframe weight model is required for the reliable mutlcopter design process. Firstly, the standard configuration of multicopters is defined. Then, we proposed the structural weight estimation method using the number and diameter of propellers determined from the initial step of sizing process. Finally, we validated our suggested method using the commerical products.

• Proceedings of the Korean Society of Broadcast Engineers Conference
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• 2015.07a
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• pp.312-314
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• 2015

본 논문에서는 멀티콥터에서의 음향 취득에 필요한 프로펠러 소음 저감 방법을 제시한다. 멀티콥터의 사용성 증대에 따른 방송 및 다분야에서 응용이 늘어남에 비해 방송 분야에서 멀티콥터의 음향 취득 기술이 미비한 것이 사실이다. 높은 품질의 동영상 촬영 기술이 나날이 발전하고 있는데 비해 멀티콥터에서의 음향 취득에 대한 연구는 진행이 활발하지 않다. 이에 본 논문은 음성 신호 처리 분야에서 소음 저감 기술로 많이 쓰이는 적응 신호처리를 이용하여 프로펠러 소리를 저감하는 방법을 제시한다. 먼저, 적용한 적응 신호 처리 기술에 대한 설명을 통해 본 논문에 이용한 프로펠러 소리 저감 방법을 설명토록 하며, 프로펠러 소리에 대한 분석을 통해 발전 가능한 연구를 논의한다.

• Journal of Aerospace System Engineering
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• v.11 no.5
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• pp.20-27
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• 2017

The present paper describes the flow analysis of the flows around the multicopter for the selection of optimal position of air data sensor. For the flow analysis, the commercial fluid dynamics solver, STAR-CCM+ was used with polygon mesh and k-w SST turbulence modeling options. For the simulation of each rotating 4 propellers, unstructured overset mesh method was used. Hovering, forward flight, ascending and descending flight conditions are selected for the analysis and airspeed and flow angle errors were investigated using the CFD results. Through the flow field analysis, sensor location above one propeller diameter distance from the propeller rotating plane showed airspeed error less than 1m/s within the typical flight conditions of multicopter except descending.

• Journal of Aerospace System Engineering
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• v.15 no.1
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• pp.102-110
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• 2021

Recently, multi-copters equipped with various collision avoidance sensors have been introduced to improve flight stability. LiDAR is used to recognize a three-dimensional position. Multiple cameras and real-time SLAM technology are also used to calculate the relative position to obstacles. A three-dimensional depth sensor with a small process and camera is also used. In this study, a small collision-avoidance multi-copter system capable of in-door flight was developed as a platform for the development of collision avoidance software technology. The multi-copter system was equipped with LiDAR, 3D depth sensor, and small image processing board. Object recognition and collision avoidance functions based on the YOLO algorithm were verified through flight tests. This paper deals with recent trends in drone collision avoidance technology, system design/manufacturing process, and flight test results.

• Proceedings of the Korean Society of Broadcast Engineers Conference
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• 2016.11a
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• pp.163-164
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• 2016

이전까지 많은 연구자들은 적응 신호처리(Adaptive Signal Process)를 이용한 잡음 제거 방법을 연구해 왔다. 그러나, 최근 발전하고 있는 멀티콥터는 프로펠러 모터의 RPM(Revolution Per Minute)이 실시간으로 변하기 때문에 적응 신호처리를 이용하여도 깔끔한 결과를 얻어 내기가 어렵다는 한계가 존재한다. 또한, 특정 주파수를 기준으로 형성되는 고조파(Harmonics)는 적응 알고리즘인 (N)LMS 를 이용한 예측에서 오차를 발생시키는 문제를 발생시킨다. 따라서, 본 논문에서는 멀티콥터를 이용한 음향 취득에 대한 소음 저감 방법으로 회전 속도계(Tachometer), 콤 필터(Comb Filter), NLMS 알고리즘(Normalized Least Mean Square Algorithm)을 이용한 방법을 제안한다.

• Journal of Aerospace System Engineering
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• v.15 no.3
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• pp.99-104
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• 2021

The characteristics of wind sensors were experimentally analyzed and compared for purposes of application in multicopter type drones. For rotating wind sensors, the dynamics effect causes measurement errors, while manufacturing errors and signal processing errors were found to constitute significant errors in ultrasonic sensors. In the ultrasonic sensor, the errors decrease as the distance of the transducer increases. These characteristics were experimentally confirmed, and it was established that ultrasonic sensors capable of outputting voltage or data of 10 Hz or more are suitable for use in multicopters.

• 한국항공운항학회:학술대회논문집
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• 2016.05a
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• pp.35-38
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• 2016

본 논문에서는 실외 환경에서 GPS 센서 보다 빠른 주기의 위치 추정 기법을 소개한다. 빠른 제어주기가 필요한 멀티콥터 시스템에서 위치 제어에 GPS 센서를 사용하기 위해서는 상대적으로 느린 GPS 데이터의 출력주기를 보완하는 처리가 필요하다. 이 문제를 해결하기 위해 오픈소스 프로젝트를 분석하고 활용하여 가능성을 확인하는 선행 연구를 진행하였다. matlab에서 알고리즘을 검증하고 임베디드 장비에 직접 구동해봄으로써 성능을 확인하였다. 이 알고리즘에서는 멀터콥터의 위치 추정 계산을 위해 AHRS, GPS센서, barometer 센서를 사용한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.6
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• pp.455-462
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• 2017

In recent decades, many researchers have been struggling to developing the compound aircraft that is capable high speed and VTOL flight. And in recent years, multi-copters are very popular because of having advantages of VTOL and easy handling, but they are lack of doing long-range mission. Therefore, we presents simple aircraft architecture which is equipped fixed wing, multi propellers and no control surfaces. In this paper, we designed the attitude control for the compound aircraft prototype and measured the attitude control performance with flight test for validating prototype's performance. We analysed the attitude control test result comparing with similar size of a fixed wing aircraft. The performance was almost same as fixed wing aircraft.

• Journal of Aerospace System Engineering
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• v.13 no.1
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• pp.47-53
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• 2019

To improve an aerodynamic characteristic of the eVOTL aircraft, Korea Aerospace Research Institute (KARI) performed a validity test of the cross-rotating propeller technology. First, CFD analysis was carried out and an idea of the cross-rotating propeller to imply on a multi-copter confirmed with a commerce pitch control multi-copter that has two different blades, 0.11 and 0.21 m. After verifying the idea, a multi-copter with about 3 kg maximum take-off weight (MTOW) was custom designed to complete a ground test to measure thrust and noise. The test was performed with 15 and 22 in. propellers at the identical tip speed. The test results show that the 22 in. propeller with the cross-rotating technology required about 30 % less power and reduced 3~5 dB aerodynamic noise as compared to 15 in. propeller without cross-rotating.

• Journal of Aerospace System Engineering
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• v.16 no.5
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• pp.78-85
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• 2022

Multicopter-type unmanned aerial vehicles (UAV) are increasingly for cargo transportation to mountainous and island regions, image information acquisition in disaster areas, and emergency rescue transport. In order to successfully perform these tasks, the aircraft structure must be able to safely support the loads induced by flight conditions while ensuring the vibration and aeroelastic stability of the prop-rotor. This study introduced a structural analysis model of a 40kg payload multicopter with an engine-generator hybrid power system. The deformation and stress distribution are investigated depending on the load conditions. In addition, the vibration characteristics and aeroelastic stability of the prop-rotor were also presented to flight speed and aircraft pitch angle. The maximum thrust generated by the prop-rotor and the landing load applied to the multicopter under normal and emergency landing conditions were reviewed., It confirmed that the structure could support without failure. In addition, it confirmed that the damping characteristics of each primary locate in the constant region according to the aircraft's flight speed and the prop-rotors rotating speed.