• Title, Summary, Keyword: Micro Air Vehicle

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Aerodynamic Design and Analysis of a Propeller for a Micro Air Vehicle

  • Cho Lee-Sang;Yoon Jae-Min;Han Cheol-Heui;Cho Jin-Soo
    • Journal of Mechanical Science and Technology
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    • v.20 no.10
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    • pp.1753-1764
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    • 2006
  • A U-80 propeller and its modified version, U-75 propeller, are used for a micro air vehicle. The performance characteristics of a U-80 propeller and a U-75 propeller have not much known in the published literature. Thus, their aerodynamic characteristics are investigated using a lifting surface numerical method. The lifting surface method is validated by comparing computed results with measured data in a wind tunnel. From the computed results, it is found that the U-75 propeller produces larger thrust with higher efficiency than the U-80 propeller. To enhance the performance of these propellers, a new propeller is designed by following the sequential design procedures with the design parameters such as hub-tip ratio, maximum camber and its position, and chord length distribution along the radial direction. The performance of the designed propeller is shown to be improved much comparing with those of both the U-80 and U-75 propellers.

Design and Fabrication of Coaxial Rotorcraft-typed Micro Air Vehicle for Indoor Surveillance and Reconnaissance (실내감시정찰용 동축반전 헬리콥터형 미세비행체 설계 및 제작)

  • Byun, Young-Seop;Shin, Dong-Hwan;An, Jin-Ung;Song, Woo-Jin;Kim, Jeong;Kang, Beom-Soo
    • Journal of the Korean Society for Precision Engineering
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    • v.28 no.12
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    • pp.1388-1396
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    • 2011
  • This paper is focused on the procedure of the development of a micro air vehicle which has vertical take-off and landing capability for indoor reconnaissance mission. Trade studies on mission feasibility led to the proposal of a coaxial rotorcraft configuration as the platform. The survey to provide a guide for preliminary design were conducted based on commercial off-the-shelf platform, and the rotor performance was estimated by the simple momentum theory. To determine the initial size of the micro air vehicle, the modified conventional fuel balance method was applied to adopt for electric powered vehicle, and the sizing problem was optimized with the sequential quadratic programming method using MATLAB. The designed rotor blades were fabricated with high strength carbon composite material and integrated with the platform. The developed coaxial rotorcraft micro air vehicle shows stable handling quality with manual flight test in indoor situation.

Longitudinal Flight Dynamic Modeling and Stability Analysis of Flapping-wing Micro Air Vehicles (날갯짓 비행 로봇의 세로방향 비행 동역학 모델링 및 안정성 해석)

  • Kim, Joong-Kwan;Han, Jong-Seob;Kim, Ho-Young;Han, Jae-Hung
    • Journal of Institute of Control, Robotics and Systems
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    • v.21 no.1
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    • pp.1-6
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    • 2015
  • This paper investigates the longitudinal flight dynamics and stability of flapping-wing micro air vehicles. Periodic external forces and moments due to the flapping motion characterize the dynamics of this system as NLTP (Non Linear Time Periodic). However, the averaging theorem can be applied to an NLTP system to obtain an NLTI (Non Linear Time Invariant) system which allows us to use a standard eigen value analysis to assess the stability of the system with linearization around a reference point. In this paper, we investigate the dynamics and stability of a hawkmoth-scale flapping-wing air vehicle by establishing an LTI (Linear Time Invariant) system model around a hovering condition. Also, a direct time integration of full nonlinear equations of motion of the flapping-wing micro air vehicle is conducted to see how the longitudinal flight dynamics appear in the time domain beyond the reference point, i.e. hovering condition. In the study, the flapping-wing air vehicle exhibited three distinct dynamic modes of motion in the longitudinal plane of motion: two stable subsidence modes and one unstable oscillatory mode. The unstable oscillatory mode is found to be a combination of a pitching velocity state and a forward/backward velocity state.

Flight Test Measurement and Assessment of a Flapping Micro Air Vehicle

  • Kim, Jong-Heon;Park, Chan-Yik;Jun, Seung-Moon;Chung, Dae-Keun;Kim, Jong-Rok;Hwang, Hee-Chul;Stanford, Bret;Beran, Philip;Parker, Gregory;Mrozinski, Denny
    • International Journal of Aeronautical and Space Sciences
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    • v.13 no.2
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    • pp.238-249
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    • 2012
  • Flight test of flapping micro air vehicles (FMAVs) is carried out using an instrumented measurement system to obtain various engineering parameters and hence to assess the flight performance of the vehicles through the data investigation. An indoor flight test facility equipped with a motion capture system and tracking cameras is used for the work presented in this paper. Maneuvers including straight-level flight, ground flapping, takeoff and landing are tested. Spatial position and orientation data are obtained from the retro-reflective tracking markers attached to the vehicles. Subsequent test analysis is carried out by generating performance parameters from raw data and then assessing the flight performance by comparison of the vehicles. The main findings of this work confirm that the test method and procedures presented here enable the systematic numerical data measurement and assessment of the flying performances of these vehicles, and show the applicability for the test and evaluation of general flapping MAVs.

Parametric Studies and Performance Analysis of a Biplane Micro Air Vehicle

  • Maqsood, Adnan;Go, Tiauw Hiong
    • International Journal of Aeronautical and Space Sciences
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    • v.14 no.3
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    • pp.229-236
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    • 2013
  • This paper presents the experimental investigation of a biplane micro air vehicle. The effects of geometric parameters, gap, stagger, and decalage angle are investigated at low Reynolds number (~150,000) in a low-speed wind tunnel. A rigid flat plate with an aspect ratio of one and square planform shape is used to evaluate all three geometric parameters. The side dimension of the single flat plate is 0.15 m. The goal is to find an optimal biplane configuration that should exceed monoplane performance by generating high lift and flying as slow as possible, in order to capture high-quality visual recordings. This configuration will directly help to fly at a lower velocity and to make tighter turns that are advantageous in restricted environments. The results show that the aerodynamic performance of the biplane MAV is significantly enhanced through the combination of gap and stagger effects. A performance comparison demonstrates the superiority of the optimal biplane configuration compared to a monoplane in cruise and glide phases. Moreover, no significant compromise is found for the range, endurance, and climb performance.

Velocity Profile Optimization of Flapping Wing Micro Air Vehicle (초소형 날갯짓 비행체의 최적 날갯짓 속도 분포 연구)

  • Cho, Sungyu;Lee, Junhee;Kim, Chongam
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.48 no.11
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    • pp.837-847
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    • 2020
  • A velocity profile for flapping flight is optimized to increase the power efficiency of 20g weighted flapping wing micro air vehicle in hover. The experimental optimization of flapping velocity profile is carried out with a real sized flapper, and various velocity profiles are realized by non-circular gear. Kriging with noise is adopted as a meta model of the profile optimization to reflect the data noise by uncertainty. The optimization results confirm that the flapping efficiency (thrust-to-power ratio) is substantially improved (11.3%) through the elastic deformation that carries the angular kinetic energy from previous stroke.

Numerical Analysis and Experimental Study for Low Reynolds number region around Micro Air Vehicle (초소형 비행체 주위의 저 레이놀즈수 영역에 대한 수치 해석 및 실험적 연구)

  • Kim Y. H.;Kim W. R.;Kim C.;Rho O. H.
    • 한국전산유체공학회:학술대회논문집
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    • pp.53-58
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    • 2002
  • A three-dimensional incompressible Navier-Stokes solver is developed for the flow analysis around Micro Air Vehicle(MAV) designed by MACDL(Micro Aerodynamic Control and Design Lab), Seoul National Univ., Validations of this solver are presented for two cases, first flow over the circular cylinder with infinite length, second flow over infinite wing with wing section, E387 airfoil. Simultaneously, Wind Tunnel test is performed with Flatform Wire type sir-component balance and model designed by MACDL. The numerical results are also examined through comparison with experimental data.

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The Design of MAV (Micro hlr Vehicle) Flight Simulator (MAV (Micro Air Vehicle) 비행 시뮬레이터의 설계)

  • 김형철;김강수;노재춘;윤석준
    • Proceedings of the Korea Society for Simulation Conference
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    • pp.49-54
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    • 2003
  • 일반 항공기의 유형을 고정익기과 회전익기로 구별할 수 있다면, MAV (Micro Air Vehicle)의 경우는 곤충이나 조류들의 날개 짓 (flapping) 비행형태인 ornithopter 형이 추가된다. 1993년 미국 RAND사에 의하여 MAV에 대한 타당성 검토(1)가 시작된 이례로 실로 다양한 실험적 형태의 MAV들이 속속 소개되고 있는 실정이다. MAV는 초소형 무인항공기로 길이는 성인의 손바닥 크기인 2.5 inch 정도이고, 개발비용과 기간이 유인항공기에 비해서는 비교할 수 없을 정도로 적게 소요되며. 동체길이가 2~5m인 일반 무인항공기에 비해서도 상대적으로 유리하다는 장점, 그리고 새로운 소형화 기술들을 평가할 수 있는 매우 훌륭한 시험장치가 될 수 있다는 이유로 항공우주기술 분야는 물론 MEMS나 나노기술 분야에서도 상당한 관심을 갖고 있는 실정이다. MAV의 비행 시뮬레이션 또는 시뮬레이터에 대한 현재까지의 국내외 연구개발 노력(2,3)은 MAV의 기체나 부품기술개발 노력에 비하여 상대적으로 뒤쳐져 있는데, 본 논문은 그 기술적 문제가 무엇인지를 분석하고, MAV비행 시뮬레이터 환경을 통해 수행될 수 있는 효과적인 연구개발 분야는 무엇인지를 조명하고자 한다. 또한, MAV비행 시뮬레이터의 성능 요구사항 도출을 통하여 개념설계를 제시하고, 세종대학교와 (주)모델심이 공동 개발중인 "RC Virtual Flight" 비행 시뮬레이터에 MAV가 어떻게 접목되고 있는지를 소개한다.있는지를 소개한다.

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A study on fuzzy control for vehicle air conditioner (자동차용 공기조화기의 퍼지 제어에 관한 연구)

  • 김양영;봉재경;진상호
    • 제어로봇시스템학회:학술대회논문집
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    • pp.516-519
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    • 1997
  • In this paper, the control of the temperature for the vehicle air conditioner is implemented with the fuzzy controller using a micro controller. The linguistic control rules of the fuzzy controller are separated into two out variables(multi input multi output ; MIMO) : one is those for the blower motor, and the other is those for air mix door. The error in fuzzy controller, the input variable is defined as difference between the reference temperature and the actual temperature in the cabin room. The fuzzy control rules are established from the human operator experience, and based engineering knowledge about the process. The method of the center of gravity is utilized for the defuzzification.

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Fabrication of composite hinge mechanism for flapping-wing motion of micro air vehicle (초소형 날갯짓 비행운동을 위한 복합재료 힌지 메커니즘 제작)

  • Kang, Lae-Hyong;Jang, Hee-Suk;Leem, Ju-Young;Han, Jae-Hung
    • Composites Research
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    • v.22 no.6
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    • pp.7-12
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    • 2009
  • This paper deals with a fabrication method of composite hinge mechanisms for flapping-wing micro air vehicles. The fabrication process includes curing process of Graphite/Epoxyprepregs, laser cutting for high fabrication repeatability, laminating of Graphite/Epoxy prepregs with Kapton film which is used for flexure, and so on. The fabricated hinge mechanism was attached with PUMPS actuators and the measured flapping angle was $173^{\circ}$ when driving voltage was 300V 170Hz.