• International Journal of Aeronautical and Space Sciences
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• 제10권2호
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• pp.140-147
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• 2009

The paper presents the design, development and testing activities of the multi-rotorcraft-based unmanned aerial vehicle at the Center for Unmanned System Studies, Institut Teknologi Bandung (ITB), Indonesia. The multi-rotor system was selected as the design stepping stone for future development of personal aerial vehicle prototypes. A step-by-step design program is conducted to study the technology building blocks and critical issues associated with the design, development and operation of personal aerial vehicles. A number of multi-rotor configurations have been investigated providing basic guidelines for developing a stable unmanned aerial platform. The benefit of the presently selected configuration is highlighted and some preliminary testing results are presented.

• 항공우주시스템공학회지
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• 제17권6호
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• pp.133-143
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• 2023

본 논문에서는 유무인 협업을 위한 유인회전익기에 의한 다수 무인기 운용통제기술의 요구도 검증을 위한 통합검증환경의 요구도 분석, 구현 및 검증에 대해 기술하였다. 통합검증환경은 유인회전익기 비행 모의, 무인항공기 비행 및 임무장비 모의, 무인항공기 제어 및 유인회전익기와의 통제권 변경을 위한 지상통제장비 모의, 유인회전익기 및 무인항공기 임무계획 작성 및 전송을 위한 운용통제장비 모의로 구성된다. 각각 구현된 구성품들은 소프트웨어/하드웨어 통합시험을 통해 요구도를 검증하였다.

• International Journal of Aeronautical and Space Sciences
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• 제11권2호
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• pp.69-79
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• 2010

This paper describes the experimental framework for the control system design and validation of a rotorcraft unmanned aerial vehicle (UAV). Our approach follows the general procedure of nonlinear modeling, linear controller design, nonlinear simulation and flight test but uses an indoor-installed multi-camera system, which can provide full 6-degree of freedom (DOF) navigation information with high accuracy, to overcome the limitation of an outdoor flight experiment. In addition, a 3-DOF flying mill is used for the performance validation of the attitude control, which considers the characteristics of the multi-rotor type rotorcraft UAV. Our framework is applied to the design and mathematical modeling of the control system for a quad-rotor UAV, which was selected as the test-bed vehicle, and the controller design using the classical proportional-integral-derivative control method is explained. The experimental results showed that the proposed approach can be viewed as a successful tool in developing the controller of new rotorcraft UAVs with reduced cost and time.

• 한국항공우주학회지
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• 제37권3호
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• pp.293-300
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• 2009

근거리 감시정찰을 수행할 수 있는 헬리콥터형 무인항공기를 개발하였다. 임무수행 가능성을 검토한 결과 전동 모터로 구동되는 동축반전 헬리콥터형 비행체가 선정되었다. 자동비행을 위해 상용 자동비행장치와 무선통신 모뎀이 채택되었고, 공중촬영을 위한 CCD 카메라가 탑재되었다. 완성된 비행체는 수동 비행시험을 통해 성능을 검증하였으며, 자동비행장치 탑재 후 점항법 비행을 통해 임무수행이 가능함을 확인하였다. 본 논문에서는 동축반전 무인항공기의 개발을 위한 설계 및 체계종합 전 과정에 관하여 기술하였다.

• 한국항공운항학회지
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• 제29권2호
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• pp.78-83
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• 2021

In modern society, the use of small rotary-wing unmanned aerial vehicles such as drones is increasing. As the military considers tactics using drones, demand for drones is increasing. However, there is still no airworthiness certification standard for drones for safety. In this paper, we proposed airworthiness certification standards for small rotorcraft unmanned aerial vehicles based on CS-LURS in Europe and STANG-4703, 4738 (draft) of the North Atlantic Treaty Organization. In addition, airworthiness certification standards have been strengthened through the case of unmanned aerial vehicle accidents in operation by the Korean military. The airworthiness certification standards for small rotary-wing unmanned aerial vehicles will be supplemented through a demonstration project.

• 한국정밀공학회:학술대회논문집
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• 한국정밀공학회 2008년도 추계학술대회 논문집
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• pp.515-516
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• 2008

• Smart Structures and Systems
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• 제13권6호
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• pp.1065-1094
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• 2014

Civil engineers always face the challenge of uncertainty in planning, building, and maintaining infrastructure. These works rely heavily on a variety of surveying and monitoring techniques. Unmanned aerial vehicles (UAVs) are an effective approach to obtain information from an additional view, and potentially bring significant benefits to civil engineering. This paper gives an overview of the state of UAV developments and their possible applications in civil engineering. The paper begins with an introduction to UAV hardware, software, and control methodologies. It also reviews the latest developments in technologies related to UAVs, such as control theories, navigation methods, and image processing. Finally, the paper concludes with a summary of the potential applications of UAV to seismic risk assessment, transportation, disaster response, construction management, surveying and mapping, and flood monitoring and assessment.

• International Journal of Aeronautical and Space Sciences
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• 제11권2호
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• pp.126-130
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• 2010

This paper presents the conceptual design of a multi-rotor unmanned aerial vehicle (UAV) based on an axiomatic design. In most aerial vehicle design approaches, design configurations are affected by past and current design tendencies as well as an engineer's preferences. In order to design a systematic design framework and provide fruitful design configurations for a new type of rotorcraft, the axiomatic design theory is applied to the conceptual design process. Axiomatic design is a design methodology of a system that uses two design axioms by applying matrix methods to systematically analyze the transformation of customer needs into functional requirements (FRs), design parameters (DPs), and process variables. This paper deals with two conceptual rotary wing UAV designs, and the evaluations of tri-rotor and quad-rotor UAVs with proposed axiomatic approach. In this design methodology, design configurations are mainly affected by the selection of FRs, constraints, and DPs.

• 항공우주시스템공학회지
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• 제3권1호
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• pp.36-41
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• 2009

Quad-rotor is one kind of a rotorcraft in Unmanned Aerial Vehicle (UAV), which consists of four rotors in total and fixed-pitch blades located at the four corners. This vehicle is emerging as popular platform for UAV research due to the simplicity of its construction, the ability of hovering and the vertical take-off and landing (VTOL) capability, etc. Because of those specific capabilities, this vehicle can be applied to many fields: search and rescue, mobile sensor networks, fire observation, etc. However a quad-rotor is much affected by the disturbance due to the characteristics of structure. So this vehicle needs attitude control for stabilizing. In this paper, we design the control law for automatic stabilization. The PID controller is used to control a brushless DC motor. And an accelerometer is used to measure the roll and pitch angles of a quad-rotor.

• 제어로봇시스템학회논문지
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• 제11권3호
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• pp.193-199
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• 2005

VTOL(Vertical Take-Off and Landing) aircraft is attractive due to the reason that it is not necessary to have long runway. However a rotorcraft has a definite limitation to fly at the high speed due to the stall at the tip of rotor. To solve this problem, tilt rotor, tilt wing and lift fan were researched and developed. It was verified that the tilt rotor aircraft among them was more effective in disk loading. On this basis, the tilt rotor aircraft has been made into XV-15, V-22, BA-609 and Eagle Eye. This paper shows a nonlinear simulation program for general tilt rotor aircraft that was developed in order to validate the flight characteristics of tilt rotor aircraft and verified through the simulation analysis.