• 한국항공우주학회지
• /
• 제37권7호
• /
• pp.685-692
• /
• 2009

본 논문에서는 회전익 비행체 개발과정에서 사용되는 다양한 해석데이터를 관리하기 위한 KHP - SDM 시스템 개발 및 회전익 비행체 개념설계를 위한 다분야통합 최적설계 프레임워크 개발에 관해 기술하였다. KHP-SDM 시스템 상에 개발된 다분야 해석 모듈을 통합하고 KHP-SDM의 최적화 모듈을 적용하여 KHP-SDM RMDO 프레임워크를 구축하였다. KHP-SDM RMDO 프레임워크를 이용한 회전익 비행체 개념설계 결과 프레임워크가 성공적으로 구성되었음을 보여주었다.

• International Journal of Aeronautical and Space Sciences
• /
• 제10권2호
• /
• pp.134-139
• /
• 2009

Various modules are generally combined with one another in order to perform rotorcraft preliminary design and its optimization. At the stage of the preliminary design, analysis fidelity is less important than the rapid assessment of a design is. Most of the previous researchers attempted to implement sophisticated applications in order to increase the fidelity of analysis, but the present paper focuses on a rapid assessment while keeping the similar level of fidelity. Each small-sized module will be controlled by an externally-operated global optimization module. Results from each module are automatically handled from one discipline to another which reduces the amount of computational effort and time greatly when compared with manual execution. Automatically handled process decreases computational cycle and time by factor of approximately two. Previous researchers and the rotorcraft industries developed their own integrated analysis for rotorcraft design task, such as HESCOMP, VASCOMP, and RWSIZE. When a specific mission profile is given to these programs, those will estimate the aircraft size, performance, rotor performance, component weight, and other aspects. Such results can become good sources for the supplemental analysis in terms of stability, handling qualities, and cost. If the results do not satisfy the stability criteria or other constraints, additional sizing processes may be used to re-evaluate rotorcraft size based on the result from stability analysis. Trade-off study can be conducted by connecting disciplines, and it is an important advantage in a preliminary design study. In this paper among the existing rotorcraft design programs, an adequate program is selected for a baseline of the design framework, and modularization strategy will be applied and further improvements for each module be pursued.

• 한국항공우주학회지
• /
• 제38권8호
• /
• pp.806-812
• /
• 2010

회전익항공기 연료탱크는 추락시 승무원의 생존성과 직결되는 구성품이다. 1950년대부터 미육군에서는 항공기 추락 후 화재에 의한 사상자를 줄일 수 있는 방안으로 내충돌성 연료탱크에 적합한 특성을 갖는 소재를 개발하기 위해 다양한 노력을 기울여왔다. 그 결과로 1961년에 MIL-T-27422A라는 항공기 연료탱크 설계규격이 처음 등장하였고, 1970년부터 2002년까지 수회의 개정을 거쳐 2007년 MIL-DTL-27422D라는 미군사 규격으로 발전되었다. 한국형 기동헬기의 연료탱크는 미군사규격(MIL-DTL-27422D)에 따라 개발 및 성능인증시험이 수행되었으며, 연료탱크의 내추락 성능은 미군사 규격에 구체화된 충돌/충격시험으로 검증되도록 규정되어 있다. 본 연구는 한국형기동헬기 연료탱크의 내추락 성능 검증을 위해 수행된 충돌/충격시험 결과를 제시하고 있다.

• 한국항공우주학회지
• /
• 제31권8호
• /
• pp.50-57
• /
• 2003

헬리콥터를 공간상에서 비교적 가까운 거리에 불규칙하게 주어진 여러 경로점을 따라 비행하는 것은 아주 실제적인 임무인데 이러한 임무에서 최적의 경로를 찾는 것은 어려운 문제에 속한다. 역제어나 직접법을 사용하는 전통적 접근은, 역제어의 경우에는 전 구간의 경로를 시간의 함수로 미리 설정해야 한다거나, 직접법의 경우 계산시간이 너무 많이 소요 된다는 등의 제약으로 그 활용성이 제한적이었다. 본 논문에서는 최적제어기법을 적용하여 다중경로점이 주어진 문제에 대해 최적경로를 구하는 알고리듬을 개발하고 이를 이용하여 slalom 운동과 전체적으로 곡선이 경로에서 일부구간만 선형으로 주어지는 문제 등에 있어서의 헬리콥터의 최적경로를 구하고 그 효용성을 검증하였다.

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

• 품질경영학회지
• /
• 제45권3호
• /
• pp.365-377
• /
• 2017

Purpose: In the A rotorcraft, the division of a long yaw control rod was studied to improve the heat treatment capability. The purpose of this study was to analyze whether division of yaw control rod affects quality reliability in the A rotorcraft and analyze whether it secured flight safety. Methods: The structural static test and the vibration durability test on the split shape of yaw control rod were carried out in order to examine and verify the existing structural analysis results. Results: Structural static test results showed that there were no cracks and vibration durability test results showed that there was no damage or breakage on the split yaw control rod. Conclusion: This study showed that the quality reliability was confirmed and thus the flight safety of the A rotorcraft was secured. And it is expected that the split technique of the yaw control rod will contribute to the development of the rotorcraft industry in the future.

• 대한기계학회:학술대회논문집
• /
• 대한기계학회 2008년도 추계학술대회A
• /
• pp.497-501
• /
• 2008

To improve occupants' safety in an emergency, crashworthy design is necessary to rotorcraft design and development. To improve crashworthiness capability, most of the crash energy should be absorbed by rotorcraft and the energy transmitted to the occupants should be minimized. To absorb the crash energy efficiently, the individual energy attenuation provided by landing gear, structure, fuel tank and seats should be considered totally. Especially, landing gear has the important role for crashworthy design because landing gear absorbs relatively large energy for the crash landing. In addition, military specifications require failure of landing gear shall not increase danger to any occupants by penetration of the airframe. To meet the specification requirements, failure mechanism should be prepared so that landing gear is collapsed safely and doesn't penetrate the airframe. In this study, design of failure mechanism which is necessary for the rotorcraft landing gear was performed and the results were presented.

• 한국기계가공학회지
• /
• 제21권9호
• /
• pp.21-27
• /
• 2022

The rotorcraft engine gearbox transmits the power generated by the turboshaft engine to the rotor by reducing the rotational speed and increasing the torque. The core of the rotorcraft engine gearbox is lightweight performance, which requires maximum weight reduction within the range that meets various requirements and constraints. Therefore, lightweight design through gear macro geometry optimization is necessary. In this study, gear macro geometry optimization was performed to reduce the weight of a rotorcraft engine gearbox. NSGA-III was used for the optimization, resulting in a combination of the gear ratio and macro geometry that minimizes the weight of the total gear. In addition, the safety factor of the gears satisfied the given conditions.

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

• 항공우주기술
• /
• 제6권1호
• /
• pp.6-13
• /
• 2007

본 논문에서는 언제 어디서나(유비쿼터스) 빠르게 지정간 수송을 가능하게 해주며 현재 의 자동차를 대체할 수 있는 개인용 항공기, 즉 PAV(personal Air Vehicle)에 대하여 요구 조건을 살펴보고, 기존의 고속 회전익기 개념과 현재 진행 중인 고속회전익기 개발사업을 개괄적으로 검토하여, PAV 적용가능 플랫폼으로서 고속 회전익기 개념 및 기술적 이슈를 탐색하였다.