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접개식 착륙장치 내구성 시험을 통한 접개장치 내구도 평가
이정선(Jeong Sun Lee),강신현(Shin Hyun Kang),조정준(Jeong Jun Jo),박주형(Joo Hyung Park),정상준(Sang Jun Jung) 대한기계학회 2011 대한기계학회 춘추학술대회 Vol.2011 No.10
After aircraft take-off, the retractable landing gear is folded into the aircraft bay by retraction operation of the retract actuator and locked by the uplock box to maintain retraction position. When the aircraft is on landing phase, the landing gear is extended by unlock of the uplock box and extension operation of the retract actuator. Because the retractable landing gear repeats retraction and extension during aircraft operation life, the possibility of fatigue failure of the components which compose the retraction mechanism exists. To verify fatigue life of the retraction mechanism, the endurance test which repeats retraction and extension of the landing gear is performed. In this study, the procedure and result of the landing gear endurance test was presented and the appropriateness of fatigue analysis result was verified by test results.
신정우(Jeong Woo Shin),김태욱(Tae-Uk Kim),황인희(In-Hee Hwang),조정준(Jeong Jun Jo),이정선(Jeong-Sun Lee),박총영(Chong-Yeong Park) 대한기계학회 2010 大韓機械學會論文集A Vol.34 No.1
비상착륙상황에서 승객의 안전을 향상시키기 위한 내추락 설계는 회전익기 설계 개발에 있어 필수적이다. 특히, 추락 시 착륙장치는 상대적으로 많은 에너지를 흡수할 수 있기 때문에, 내추락 설계에 있어 중요한 역할을 한다. 군사규격에서는 착륙장치의 에너지 흡수능력 뿐만 아니라, 파손 후 동체를 뚫고 들어가 승객에게 2차 피해를 주지 않아야 함을 규정하고 있다. 이와 같은 군사규격을 만족하기 위해서는 파손장치와 같은 내추락 장치를 마련하여, 착륙장치가 파손 후 안전하게 붕괴되어 동체를 뚫고 들어가지 않도록 해야 한다. 본 연구에서는 회전익기 착륙장치에 필수적인 파손장치의 설계 및 설계개발시험을 수행하였다. 먼저 착륙장치가 동체를 뚫고 들어가지 않도록 하기 위한 붕괴 과정을 결정하였다. 다음으로 파손장치에서 가장 중요한 부품인 파손 핀을 설계하였고, 설계기준을 만족하도록 2가지 강도 범위로 설계되었다. 최종적으로 설계개발시험을 통해 파손장치 설계를 성공적으로 검증하였다. To improve occupants' safety in an emergency, crashworthy design is necessary to rotorcraft design and development. 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, crashworthiness device like failure mechanism should be prepared so that landing gear is collapsed safely and doesn't penetrate the airframe. In this study, design and design development test of the failure mechanism which is necessary for the rotorcraft landing gear was performed. First, collapse scenario was determined for the landing gear not to penetrate the airframe. Then, the failure pin which is the most important part of the failure mechanism was designed with 2 strength range in order to meet design criteria. Finally, design of the failure mechanism was verified successfully by design development test.
신정우(Jeong Woo Shin),김태욱(Tae-Uk Kim),황인희(In-Hee Hwang),조정준(Jeong Jun Jo),이정선(Jeong-Sun Lee),박총영(Chong-Yeong Park) 대한기계학회 2009 대한기계학회 춘추학술대회 Vol.2009 No.5
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, crashworthiness device like failure mechanism should be prepared so that landing gear is collapsed safely and doesn't penetrate the airframe. In this study, design and design development test of failure mechanism which is necessary for the rotorcraft landing gear was performed and the results were presented.
신정우(Jeong Woo Shin),김태욱(Tae-Uk Kim),황인희(In-Hee Hwang),조정준(Jeong Jun Jo),이정선(Jeong-Sun Lee),박총영(Chong-Yeong Park) 대한기계학회 2008 대한기계학회 춘추학술대회 Vol.2008 No.11
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.