• Title/Summary/Keyword: 헬리콥터 설계

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Design and Fabrication of a small Coaxial Rotorcraft UAV (동축반전 헬리콥터형 소형 무인항공기 설계 및 제작)

  • Kim, Sang-Deok;Byun, Young-Seop;Song, Jun-Beom;Lee, Byoung-Eon;Song, Woo-Jin;Kim, Jeong;Kang, Beom-Soo
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.37 no.3
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    • pp.293-300
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    • 2009
  • The rotorcraft-based unmanned aerial vehicle(UAV) capable of performing close-range surveillance and reconnaissance has been developed. Trade studies on mission feasibility led to the adoption of a coaxial rotorcraft with twin rotors counter-rotating in one axis and driven by electric motors. A commercial off-the-shelf flight control computer(FCC) and a radio frequency modem were adopted for autonomous navigation. In order to achieve an aerial view, commercial charge-coupled device camera was also integrated into the vehicle. The performance of the completed vehicle was proved with manual flight test, and mission capability was verified through waypoint navigation flight after being equipped with FCC. This paper treats the whole process of design and system integration for development of the coaxial rotorcraft UAV.

Technical Papers : Performance Test of a Two Stage Axial Compressor of a Turboshaft Engine for Helicopters (기술논문 : 헬리콥터용 터보샤프트엔진 2 단 축류압축기 성능시험)

  • Kim, Chun-Taek;Kim, Jin-Han;Yang, Su-Seok;Lee, Dae-Seong
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.30 no.3
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    • pp.139-145
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    • 2002
  • 이륙중량 4000kg, 10-12인승급 다목적 헬리콥터에 적용가능한 엔진 개량 개발을 목표로 기존 헬리콥터 엔진을 개량대상으로 선정하고 이러한 다목적 헬기의 요구조건에 부합하기 위해 기존 엔진의 요소부품을 재설계하였다. 첫 단계로 최소변경으로 720 hp에서 840 hp로 출력을 증강시키기 위하여 2단 축류압축기의 기존 입구 유도익을 제거하고 익현의 길이를 증가하여 유량 및 압축비를 증가시킴으로써 출력 증강을 얻도록 재설계를 수행하였다. 이러한 2단 축류압축기의 성능을 검증하기 위하여 두 번째 단 단독시험 및 전체 2단에 대한 성능시험이 수행되었으며 첫 번째 단의 성능은 이 결과로부터 도출되었다. 성능시험결과 전체 2단 압축기는 유량 3.088 kg/s에서 압력비 2.14, 단열효율 88%의 성능을 갖는 것으로 나타났으며 압축기 출구의 압력 및 온도 분포를 레이크를 이용하여 측정하였다.

Nonlinear Adaptive Control of Unmanned Helicopter Using Neural Networks Compensator (신경회로망 보상기를 이용한 무인헬리콥터의 비선형적응제어)

  • Park, Bum-Jin;Hong, Chang-Ho
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.38 no.4
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    • pp.335-341
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    • 2010
  • To improve the performance of inner loop based on PD controller for a unmanned helicopter, neural networks are applied. The performance of PD controller designed on the response characteristics of error dynamics decreases because of uncertain nonlinearities of the system. The nonlinearities are decoupled to modified dynamic inversion model(MDIM) and are compensated by the neural networks. For the training of the neural networks, online weight adaptation laws which are derived from Lyapunov's direct method are used to guarantee the stability of the controller. The results of the improved performance of PD controller by neural networks are illustrated in the simulation of unmanned helicopter with nonlinearities,

Flight Envelope Load Factor Limit Logic Design for Helicopter Fly-By-Wire Controller (전자식 조정장치 헬리콥터의 하중 비행영역 제한 로직 설계)

  • Choi, In-Ho
    • Journal of the Korea Academia-Industrial cooperation Society
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    • v.17 no.1
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    • pp.159-164
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    • 2016
  • This paper reports the load factor logic design for a fly-by-wire helicopter flight envelope protection. As a helicopter is very complex system with a rotor, fuselage, engine, etc., there are many constraints on the flight region. Because of these constraints, pilots should consider them carefully and have a heavy workload, which causes controllability degradation. In this respect, automatic logic is needed to free the pilot from these considerations. As one of these logics, the flight envelope protection logic for the load factor of a FBW helicopter was designed. The flight to exceed the load factor is caused by an abrupt pitch cyclic stick change. In this scheme, the load factor limit logic was added between the pilot stick command block and pitch attitude command block. From the current load value, the available attitude range was calculated dynamically and simulated on the helicopter simulator model to verify the performance. A comparison of the simulation results at the hovering and forward speed region with and without applying the load limiting logic showed that the load factor limit was exceeded more than 20% when the logic was not applied, whereas with the load factor limit logic the load factor was within the limit. In conclusion, a dynamically allocated limitation logic to helicopter FBW controller was verified by simulation.

Helicopter FBW Flight Control Law Design for the Handling Quality Performance (비행조종성능을 위한 헬리콥터 FBW 비행제어법칙 설계)

  • Choi, In-Ho;Kim, Eung-Tai;Hyun, Jung-Wook
    • Journal of the Korea Academia-Industrial cooperation Society
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    • v.14 no.4
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    • pp.1561-1567
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    • 2013
  • This paper is regarding the helicopter flight control law design for the handling quality performance. MIL-F-83300 and ADS-33E specification is used of the helicopter flight handling quality and to meet these requirements, ACAH type controller is required. This paper described the ACAH type controller design and performance evaluations. Helicopter dynamics first developed as nonlinear dynamics including rotor dynamics and then linear model was extracted from hovering to forward flight mode using trim condition. Control law used the model following to meet the handling qualities, the simple inverse model as feed forward gain, decoupling logic and phase model to decouple the axes, and linear model to calculate the coefficients. Handling quality evaluation used the matlab based Conduit tool and verified that Level 1 requirement is satisfied.

A Study on Identification using Particle Swarm Optimization for 3-DOF Helicopter System (3-자유도 헬리콥터 시스템의 입자군집최적화 기법을 이용한 시스템 식별)

  • Lee, Ho-Woon;Kim, Tae-Woo;Kim, Tae-Hyoung
    • Journal of the Korean Institute of Intelligent Systems
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    • v.25 no.2
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    • pp.105-110
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    • 2015
  • This study proposes the more improved mathematical model than conventional that for the 3-DOF Helicopter System in Quanser Inc., and checks the validity about the proposed model by performance comparison between the controller based on the conventional model and that based on the proposed model. Research process is next : First, analyze the dynamics for the 3-DOF helicopter system and establish the linear mathematical model. Second, check the eliminated nonlinear-elements in linearization process for establishing the linear mathematical model. And establish the improved mathematical model including the parameters corresponding to the eliminated nonlinear-elements. At that time, it is used for modeling that Particle Swarm Optimization algorithm the meta-heuristic global optimization method. Finally, design the controller based on the proposed model, and verify the validity of the proposed model by comparison about the experimental results between the designed controller and the controller based on the conventional model.

TSK Type Fuzzy Controller Design for Altitude Control of an Unmanned Helicopter (무인헬리콥터의 고도제어를 위한 TSK형 퍼지제어기 설계)

  • Kim, Jong-Kwon;Seong, Ki-Jun;Cho, Kyeum-Rae;Jang, Chul-Soon
    • Journal of Advanced Navigation Technology
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    • v.9 no.2
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    • pp.87-92
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    • 2005
  • An altitude control using a fuzzy controller was performed for a series of research for autonomous flight control of industrial unmanned helicopters. The 3m class gasoline engined unmanned helicopter was designed, and using the designed specifications, Takagi-Sugeno-Kang type fuzzy controller was designed. The input membership functions were generated using target altitude, altitude error and velocity of unmanned helicopter. With these membership functions, the control inputs for altitude control were calculated. These control input signal can control the main rotor's pitch and determine the velocity and altitude of the unmanned helicopter. Also, the altitude control performance of the designed fuzzy controller was evaluated by computer simulations

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Systematic Determination of Empirical Parameters Used in Helicopter Conceptual Design (헬리콥터 개념설계에 사용하는 경험적파라메터의 체계적인 결정기법)

  • Kim, Won-Jin;Chae, Sang-Hyun;Oh, Se-Jong;Kim, Seung-Bum;Ahn, Iee-Ki;Yee, Kwan-Jung
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.40 no.8
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    • pp.703-710
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    • 2012
  • At the stage of conceptual design of a helicopter, it is a general way using low fidelity analysis methods because of a large number of design calculations and trade-off studies. Determination of empirical parameters used in analysis codes for more practical design, depends on an user's design experiences, which effects on the accuracy and the fidelity of conceptual design results. Thus, more precise and logical method should be required to determine the empirical parameters used in the conceptual design of a helicopter. The present method is to be used not only in verifying the empirical parameters generated by design requirements, but also regenerate them if they contain any errors. Empirical parameters produced by present method were used to design a helicopter with a payload objective and performance constraints of an operating helicopter. As a result, weights and geometries of designed helicopter matched the target value within 5% significance level, proving that the suggested parameter generating method can be useful in the conceptual design of a helicopter.