S-Space College of Engineering/Engineering Practice School (공과대학/대학원) Dept. of Mechanical Aerospace Engineering (기계항공공학부) Theses (Master's Degree_기계항공공학부)
Development of the snapshot method for six degree-of-freedom flight dynamics simulation for a high aspect ratio wing aerial vehicle
고세장비 날개를 가지는 항공기의 6 자유도 비행동역학 시뮬레이션을 스냅샷 기법의 개발
- 공과대학 기계항공공학부
- Issue Date
- 서울대학교 대학원
- High aspect ratio wing; Flight simulation; Flow field-structure-rigid body motion coupled analysis; Flight dynamics; Aeroelasticity; MATLAB/Simulink; MSC.FlightLoads
- 학위논문 (석사)-- 서울대학교 대학원 : 기계항공공학부, 2017. 2. 신상준.
- In this thesis, a six degree-of-freedom flight simulation was developed considering the flexibility of an aircraft with high aspect ratio wings. A full three-dimensional finite element model of unmanned aerial vehicles was used. The object aircraft has main wings with aspect ratio over 20, and flight for long endurance in high altitude. To consider the flexibility of these aircraft, the present 'snapshot method' was developed that combines aerodynamic - structural dynamics - flight dynamics to analyze dynamic response. By applying this method, MATLAB/Simulink, which calculates the rigid body motion, and MSC.FlightLoads, which is responsible for aeroelastic trim analysis, were tightly linked into the present simulation framework.
Using the present simulation, aircraft response under various maneuver conditions was simulated. First, the trim analysis for the level cruise was performed. And the trim parameters, the stability derivative coefficients, and the moment of inertia were determined. Based on these results, the flight dynamics of the aircraft was simulated according to the operation of the rudder and the aileron control surface. And the effect of the rigid and flexible body assumptions were confirmed. Also, these results were compared with the other existing simulation results based on the multibody dynamics under the same conditions. In order to predict the response of the aircraft under the gust, the simulation was performed by applying the two-dimensional 1-cosine discrete gust profile.