• 한국항공운항학회지
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• 제19권4호
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• pp.51-57
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• 2011

The spin-up and the spring-back are most severe load cases in the aircraft landing gear design. These load cases are caused by reciprocal action of complex physical phenomenon such as the friction between a tire and ground, inertia of the rotation of a tire and the flexibility of a landing gear structure. Generally, the empirical formula or the theoretical formula is used to calculate the spin-up and spring-back load in the early stage of the development program of the aircraft landing gear. After the materialization of the design of a landing gear, spin-up and spring-back load are acquired by the free drop test. In this study, the spin-up and the spring-back load of the rubber shock absorber type KC-100 nose landing gear are calculated by the explicit finite element analysis. Through this analysis, more accurate and realistic spin-up and spring back loads could be applied to the early phase of the development of the aircraft landing gear.

• International Journal of Aeronautical and Space Sciences
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• 제8권1호
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• pp.46-53
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• 2007

In this paper, a guidance law for vision-based automatic landing of unmanned aerial vehicles (UAVs) is proposed. Automatic landing is a challenging but crucial capability for UAVs to achieve a fully autonomous flight. In an autonomous landing maneuver of UAVs, the decision of where to landing and the generation of guidance command to achieve a successful landing are very significant problem. This paper is focused on the design of guidance law applicable to automatic landing problem of fixed-wing UAV and rotary-wing UAV, simultaneously. The proposed guidance law generates acceleration command as a control input which derived from a specified time-to-go ($t_go$) polynomial function. The coefficient of $t_go$-polynomial function are determined to satisfy some terminal constraints. Nonlinear simulation results using a fixed-wing and rotary-wing UAV models are presented.

• 대한의용생체공학회:의공학회지
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• 제32권2호
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• pp.105-108
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• 2011

The purpose of the present study was to analyze the lower stiffness over the difference between soft and stiff landings during hopping. Five male subjects performed hopping on two legs at 2.5 Hz. During the experiments, 3D motion capture system was used to obtain the kinematic data and two force plates were synchronized to calculate the kinetic data. We determined lower extremity stiffness of the knee and ankle from kinetic and kinematic data. Leg stiffness was approximately 1.2-times significantly higher in stiff landing than in soft landing_ There was no significant difference in knee joint stiffness between soft and stiff landings. Ankle joint stiffness was approximately 1.34-times significantly higher in stiff landing than in soft landing. These results suggest that humans adjust lower extremity stiffness over the comparison of two different landing methods we evaluated.

• 항공우주시스템공학회지
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• 제18권2호
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• pp.47-55
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• 2024

공중 무인 이동체(UAV)인 드론을 해상 무인 이동체(USV)와 자율 협력하여 임무를 수행하기 위해선 자동 착륙 시스템이 필요하다. 본 논문에서는 피라미드 형상의 착륙 장치와 패드를 기반으로 한 도킹 방식의 자동 착륙 시스템을 제안하였다. 파도, 바람 등 해상 환경에 의해 영향을 받더라도 드론이 착지할 수 있도록 유도하고, 결합(Docking) 장치를 통해 순간적으로 고정할 수 있다. 3-DoF 모션 플랫폼으로 함상의 거동을 모사하여 착륙 시험을 수행하였으며, 도킹 방식 자동 착륙 시스템의 운용·활용 가능성을 확인하였다.

• 한국항공운항학회지
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• 제32권2호
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• pp.135-141
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• 2024

Despite the innovative technological advances in the aviation industry, hard landing events that occur during aircraft landing account for 13% of all accidents. Hard landing when landing an aircraft affects normal operation by generating a large load on the landing gear and the fuselage. In order to identify these risk factors, the airline monitors the high vertical acceleration event, a precursor to hard landing, through QAR (Quick Access Recorder) flight data analysis, and prepares and implements mitigation measures. In this study, it is intended to contribute to safety management based on flight data analysis that identifies the characteristics of high vertical acceleration G event data that can cause such hard landing and detailed parameters of precursor signs, and to identify the causal relationship of the occurrence of the event by applying statistical analysis methods such as variance analysis, correlation analysis, and regression analysis models to identify the characteristics of the event occurrence and eliminate the cause in advance.

• 한국항공우주학회지
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• 제37권4호
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• pp.344-349
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• 2009

본 논문은 헬기용 주륜 착륙장치의 성능을 향상시킬 목적으로 반능동형 착륙장치를 도입하였다. 상용 유한요소 코드를 이용하여 자기장해석을 한 MR 댐퍼를 완충기에 적용 하였다. 착륙 거동 시 내력으로 발생되는 공기력과 감쇠력의 합을 일정하게 유지시키는 개념의 하중제어기법을 적용하여 반능동형 착륙장치의 제어기를 구성하였다. 다른 형태의 수동형 및 스카이 훅 제어 반 능동형 착륙장치와 함께 ADAMS를 이용한 낙하 시뮬레이션을 수행하였고 착륙특성에 대한 성능평가를 위해 그 결과들을 비교하였다.

• 한국운동역학회지
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• 제21권1호
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• pp.1-7
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• 2011

The purpose of this study was to investigate changes in kinetic and kinematic variables associated with an increase in upper body weight. Eighteen healthy male university students($175.96{\pm}4.19\;cm$, $70.79{\pm}8.26\;kg$) participated. Eight motion analysis cameras(Qualysis Oqus 500) and 2 force AMTI platforms(Advanced Mechanical Technologies Inc. OR6-7, US) were used to record motion and forces during the drop landing at a frequency of 120 Hz and 1200 Hz, respectively. QTM software(Qualisys Track Manager) was used to record the data, and the variables were analyzed with Visual 3D and Matlab 2009. For the drop landing, a box of $4{\times}2{\times}0.46\;m$ was constructed from wood. Knee and ankle maximum flexion angle, knee flexion angle, knee and ankle angle at landing, time for maximum ankle flexion after landing, and time for maximum knee flexion after landing were calculated. There was a significant change in the time for maximum and minimum ground force reaction and the time for maximum dorsal flexion after landing(p<.05) with increasing weight. There was no significant change for the hip, knee, and ankle ROM, whereas there was an increase in the angle ROM as the weight increased, in the order of ankle, knee, and hip ROM. This result shows that the ankle joint ROM increased with increasing weight for shock attenuation during the drop landing. There was a trend for greater ankle ROM than knee ROM, but there was no clear change in the ROM of the hip joint with increasing weight. In conclusion, this study shows the importance of ankle joint flexibility and strength for safe drop landing.

• 로봇학회논문지
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• 제11권4호
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• pp.262-269
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• 2016

Flight of an autonomous unmanned aerial vehicle (UAV) generally consists of four steps; take-off, ascent, descent, and finally landing. Among them, autonomous landing is a challenging task due to high risks and reliability problem. In case the landing site where the UAV is supposed to land is moving or oscillating, the situation becomes more unpredictable and it is far more difficult than landing on a stationary site. For these reasons, the accurate and precise control is required for an autonomous landing system of a UAV on top of a moving vehicle which is rolling or oscillating while moving. In this paper, a vision-only based landing algorithm using dynamic gimbal control is proposed. The conventional camera systems which are applied to the previous studies are fixed as downward facing or forward facing. The main disadvantage of these system is a narrow field of view (FOV). By controlling the gimbal to track the target dynamically, this problem can be ameliorated. Furthermore, the system helps the UAV follow the target faster than using only a fixed camera. With the artificial tag on a landing pad, the relative position and orientation of the UAV are acquired, and those estimated poses are used for gimbal control and UAV control for safe and stable landing on a moving vehicle. The outdoor experimental results show that this vision-based algorithm performs fairly well and can be applied to real situations.

• 한국항공우주학회지
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• 제44권1호
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• pp.12-22
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• 2016

달착륙선의 라이다 기반 위험회피 착륙시스템은 기본적으로 목표 착륙지역에 대한 지형 파라미터인 경사와 험준도로 위험도를 계산하고 해당 지역에 대하여 위험도가 최소값을 갖는 점을 안전한 착륙 지점으로 선정한다. 이때, 경사와 험준도만을 고려할 경우 라이다 측정오차에 의해 착륙지가 위험요소 근처로 선정될 수 있으며 이는 착륙선에 위협적이다. 이러한 문제를 해결하고 최대한 안전한 착륙지점을 선정하기 위하여 위험상대거리 기반의 위험도를 기존의 지형파리미터 기반의 위험도와 함께 고려하여야 한다. 본 논문에서는 경사와 험준도 각각에 대한 위험상대거리 기반 위험도가 지형 특성에 따라 착륙지 선정결과에 미치는 영향을 분석하였고, 두 가지 위험상대거리를 동시에 고려하였을 때 가장 좋은 위험회피 착륙 성능을 나타냄을 시뮬레이션과 3차원 뎁스 카메라를 이용한 실험을 통해 확인하였다.

• 한국항행학회논문지
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• 제25권6호
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• pp.485-492
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• 2021

무인항공기의 영상 기반 자동 정밀 착륙 기술은 착륙 지점에 대한 정밀한 위치 추정 기술과 착륙 유도 기술이 요구된다. 또한, 안전한 착륙을 위하여 지상 장애물에 대한 착륙 지점의 안전성을 판단하고, 안전성이 확보된 경우에만 착륙을 유도하도록 설계되어야 한다. 본 논문은 자동 정밀 착륙을 수행하기 위하여 영상 기반의 항법과 착륙 지점의 안전성을 판단하기 위한 알고리즘을 제안한다. 영상 기반 항법을 수행하기 위해 CNN 기법을 활용하여 착륙 패드를 탐지하고, 탐지 정보를 활용하여 통합 항법 해를 도출한다. 또한, 위치 추정 성능을 향상시키기 위한 칼만필터를 설계 및 적용한다. 착륙 지점의 안전성을 판단하기 위하여 동일한 방식으로 장애물 탐지 및 위치 추정을 수행하고, LSM을 활용하여 장애물의 속도를 추정한다. 추정한 장애물의 상태를 활용하여 계산한 CPA를 기반으로 장애물과의 충돌 여부를 판단한다. 최종적으로 본 논문에서 제안된 알고리즘을 비행 실험을 통해 검증한다.