• 로봇학회논문지
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• 제17권4호
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• pp.438-446
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• 2022

In this paper, we propose an intelligent three-legged landing system that can maintain stability and level even on rough terrain than conventional four-legged landing systems. Conventional landing gear has the limitation that it requires flat terrain for landing. The 3-leg landing system proposed in this paper extends the usable range of the legs and reduces the weight, allowing the quadcopter to operate in various environments. To do this, kinematics determine the joint angles and coordinates of the legs of the two-link structure. Based on the angle value of the quadcopter detected via the IMU sensor, the leg control method that corrects the posture is determined. A force sensor attached to the end of the leg is used to detect contact with the ground. At the moment of contact with the ground, landing control starts according to the value of the IMU sensor. The proposed system verifies its reliability in various environments through an indoor landing test stand. Finally, in an outdoor environment, the quadcopter lands on a 20 degree incline and 20 cm rough terrain after flight. This demonstrates the stability and effectiveness of the 3-leg landing system even on rough terrain compared to the 4-leg landing system.

• 로봇학회논문지
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• 제17권1호
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• pp.48-57
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• 2022

In this paper, we propose a legged landing platform for the quadcopter taking off and landing in the ship environment. In the ship environment with waves and winds, the aircraft has risks being overturned by contact impact and excessive inclination during landing on the ship. This landing platform has four landing legs under the quadcopter for balancing and shock relief. In order to make the quadcopter balanced on ships, the position of each end effector was controlled by PID control. And shocks have mainly happened when quadcopter contacts the ship's surface as well as legs move fast. Hence, impedance control was used to cope with the shocks. The performance of the landing platform was demonstrated by a simulation and a prototype in three sea states based on a specific size of a ship. During landing and tracking the slope of the ship's surface, oscillations of rotation and translation from the shock were mitigated by the controller. As a result, it was verified that transient response and stability got better by adding impedance control in simulation models and prototype experiments.

• 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.

• International Journal of Aeronautical and Space Sciences
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• 제12권1호
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• pp.84-91
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• 2011

A finite element analysis for the wing and landing gear of a composite target-drone air vehicle was performed. For the wing analysis, two load cases were considered: a 5g symmetric pull-up and a -1.5g symmetric push-over. For the landing gear analysis, a sinking velocity of 1.4 m/s at a 2g level landing condition was taken into account. MSC/NASTRAN and LS-DYNA were utilized for the static and dynamic analyses, respectively. Finite element results were verified by the static test of a prototype wing under a 6g symmetric pull-up condition. The test showed a 17% larger wing tip deflection than the finite element analysis. This difference is believed to come from the material and geometrical imperfections incurred during the manufacturing process.

• Advances in aircraft and spacecraft science
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• 제7권2호
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• pp.91-113
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• 2020

This paper analyzes the terminal descent phase of a space lander on a surface of a celestial body. A multibody approach is adopted to build the physical model of the lander and the surface. In this work, a legged landing gear system is considered. Opportune modelling of the landing gear crashbox is implemented in order to accurately predict the kinetic energy. To ensure the stability of the lander while impacting the ground and to reduce the contact forces that arise in this maneuver, the multibody model makes use of a co-simulation with a dedicated control system. Two types of control systems are considered; one with only position variables and the other with position and velocity variables. The results demonstrate the good reliability of modern multibody technology to incorporate control algorithms to carry out stability analysis of ground impact of space landers. Moreover, from a comparison between the two control systems adopted, it is shown how the velocity control leads to lower contact forces and fuel consumption.

• Journal of Mechanical Science and Technology
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• 제16권5호
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• pp.647-654
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• 2002

This study deals with the characteristic of quenching refrigerant for heat treatment deformation control of SM45C steel. Heat-treatment deformation must be controlled for the progress of production parts for landing gear. Most of deformation is occurred on inconsistent cooling. The inconsistent cooling is caused by a property of quenching refrigerant. When a heated metal is deposited in the quenching refrigerant, the cooling speed is so slow in early period of cooling because of a steam-curtain. After additional cooling, the steam-curtain is destroyed. In this progress, the cooling speed is very fast. The object of this study is to control the deformation of heat-treatment for landing gear by improving the conditions of quenching. The cooling curves and cooling rates of water, oil and polymer solution are obtained and illustrated. From the characteristics of the quenching refrigerant, the effects of heat-treatments on thermal deformation and fatigue strength are also investigated.

• International Journal of Aeronautical and Space Sciences
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• 제2권1호
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• pp.28-43
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• 2001

Developed in these two series of paper is a complex dynamic model representing the motion of aircraft on the ground and a computer program for numerical simulation. The first part of paper presents the theoretical derivation of equations of motion of the landing gear system based on the physical principle. Developed model is 'structured' in the sense that the undercarriage system is regarded as an assembly of strut, tire, and wheel, where each component is modeled by a separate module. These modules are linked with two external modules-the aircraft and the runway characteristics-to carry out dynamic analysis and numerical simulation of the aircraft motion on the ground. Three sets of coordinate system associated with strut, wheel/tire and runway are defined, and external loads to each component and response characteristics are examined. Lagrangian formulation is used to derive the undercarriage equations of motion relative to the moving aircraft, and the resultant forces and moments from the undercarriage are transformed to aircraft body axes.

• 한국항공운항학회:학술대회논문집
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• 한국항공운항학회 2005년도 춘계학술발표대회 논문집
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• pp.128-134
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• 2005

• 한국항공운항학회:학술대회논문집
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• 한국항공운항학회 2006년도 추계학술대회 논문집
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• pp.129-132
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• 2006

• 대한기계학회논문집A
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• 제37권7호
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• pp.921-927
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• 2013

본 연구는 운용 파라미터의 불확실성을 고려한 착륙장치 완충성능 해석 기법을 제시한다. 실제 운용 환경에서 완충성능에 영향을 미치는 많은 파라미터는 어느 정도의 불확실성을 가지게 되는데, 완충장치 가스 압력과 오일 체적, 타이어 압력, 외부 온도 등을 예로 들 수 있다. 본 연구에서는 Convex Modeling 과 Interval Analysis 기법을 적용하여, 이러한 불확실성이 착륙 시의 지면 반력에 미치는 효과를 해석하였다. 불확실한 파라미터를 고려할 경우, 완충효율 및 구조 건전성에 중요한 영향을 주는 Peak load 가 Deterministic analysis 의 결과보다 크게 증가하였다. 안전성과 신뢰성의 확보를 위해서는 이러한 불확실성을 반영하는 것이 필요하며, 제시한 방법은 이를 효율적으로 처리할 수 있음을 보여준다.