ADAMS를 이용한 회전익 항공기 Nose Landing Gear의 Impact Analysis

The purpose of this research was to analysis impact of nose landing gear to newly designed rotorcraft, KHP. During aircraft development, the design is repeatedly modified, and result of impact analysis is also changed every time. The simulation must apply the modification of design and the result of impact analysis. Thus, each simulation part was simply modeled to be modified easily. All parts of simulation were modeled with CATIA V5 and analyzed with ADAMS. Some constraints were lost in transforming process from CATIA to ADAMS, but these constraints were ignored. Tire was assumed linear deformation Air-spring. Moreover, shock absorber was consider of pneumatic force,damping force, friction.