• Journal of Aerospace System Engineering
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• v.9 no.4
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• pp.1-7
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• 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.

• Journal of IKEEE
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• v.23 no.4
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• pp.1430-1439
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• 2019

In Functional Mockup Interface(FMI)-based co-simulation, a bisectional algorithm can be used to find the zerocrossing point as a way to improve the accuracy of the simulation results. In this paper, the proposed master algorithm(MA) analyzes the repeated interval graph and predicts the next interval by applying the Markov Chain to the step size. In the simulation, we propose an algorithm to minimize the rollback by storing the step size that changes according to the graph type as an array and applying it to the next prediction interval when the rollback occurs in the simulation. Simulation results show that the proposed algorithm reduces the simulation time by more than 20% compared to the existing algorithm.

• International Journal of Aerospace System Engineering
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• v.4 no.1
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• pp.13-21
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• 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.