• 항공우주시스템공학회지
• /
• 제9권4호
• /
• pp.1-7
• /
• 2015

The purpose of this research is to develop co-simulation methodology of codes developed in different modeling and simulation environment. We develop aerodynamic FMU(Functional Mock-up Unit) meeting FMI(Functional Mock-up Interface) specification version2 utilizing Legacy FORTRAN aerodynamic code based on unsteady vortex lattice method. It is concluded that making FMU is possible utilizing Legacy code made in any language which can be compiled and linked with object in FMI API coded in C language. This paper explains QTronic's method of using FMU SDK(Software Development Kit) and suggestion for using FORTRAN properly. Finally, we make articulated rotor/aerodynamics co-simulation by integrating aerodynamics FMU and rotor FMU developed by Modelica.

• 전기전자학회논문지
• /
• 제23권4호
• /
• pp.1430-1439
• /
• 2019

FMI를 기반으로 하는 co-simulation의 마스터 알고리즘(MA)에서 시뮬레이션 결과의 정확도를 높이는 방법으로 zero crossing 포인트를 찾기 위한 Bisectional algorithm을 사용할 수 있다. 그러나 이 알고리즘은 많은 Rollback을 야기한다. 따라서 본 논문에서는 제안하는 MA는 Bisection algorithm을 통해 zero crossing 포인트를 검출하면서도 반복되는 구간 그래프를 분석하여 그 값을 Markov chain을 적용하여 다음 구간을 예측하여 이를 step size에 적용한다. 시뮬레이션에서 실제 Rollback이 발생했을 때 그래프 형태별로 변화되는 step size를 배열로 저장하고, 이룰 다음 예측 구간에 적용함으로서 Rollback을 최소화하는 알고리즘을 제안한다. 시뮬레이션 결과를 통해 제안하는 알고리즘이 기존 알고리즘에 비해 최대 20% 이상의 시뮬레이션 시간이 감소되는 것을 확인하였다.

• International Journal of Aerospace System Engineering
• /
• 제4권1호
• /
• pp.13-21
• /
• 2017

In this paper, we present some results on performance analysis for flap actuation system of aircraft. For this, by utilizing MATLAB/Simulink solution, which is widely used physical model-based design tool, we particularly construct the architecture of the analysis model consisting of the main three phases: 1)commanding and outer-controlling the flap angle through flight control computer; 2)generating hydraulic/mechanical power through control module and power drive unit; 3)transmitting torque and actuating the flap through torque tube and rotary geared actuators. For mimicking the motion of the actual flap, we apply each mechanical component, which is already being used in actual aircraft, to our performance analysis model so that it guarantees the congruency of the simulation results. That is, we reflect the actual specifications of flap hardware and software as parameters of the model. Finally, simulation results are presented to illustrate the model.