• Journal of the Korea Society for Simulation
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• v.27 no.1
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• pp.111-117
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• 2018

It is indispensable for a missile to track a target under the flight condition since the tracking capability affects the system performance considerably. The best way to verify the tracker's performance is flight test while it costs too much. Consequently, captive flight test or CFT has an important role in the development of a missile system. CFT, however, cannot simulate missile dynamics and is an offline and open-loop test. In this paper, we propose a new integrated-flight simulation(IFS) method using CFT imagery to overcome the limitation of synthetic image-based IFS method. This method increases the utilization of CFT's outputs and compensates the reality of imagery which lacks in the synthetic image-based IFS. Using this method make it possible to verify the system capability in various simulation modes.

• Journal of the Korea Institute of Military Science and Technology
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• v.22 no.4
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• pp.536-544
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• 2019

During the assembly and function inspection of missile system, flight simulation process is required. In the conventional flight simulation check of missiles, an inertial navigation system simulator was used to transmit the navigation output data acquired in HILS. There are several disadvantages in terms of check configuration complexity and data synchronization when using the simulator. So we proposed a new flight simulation method that utilizes the nonvolatile built-in memory of the aviation control unit. The data processing procedure and operation procedure of the proposed method for type I and type II missiles are presented. And we analyzed the causes of the difference between proposed method result and the HILS result for type II missile. By comparing the results obtained by the experiments using the proposed method with the results of HILS, the validity of proposed method was confirmed.

• Journal of Institute of Control, Robotics and Systems
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• v.4 no.1
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• pp.38-44
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• 1998

The modified maximum likelihood estimation method is used to estimate the nondimensional aerodynamic derivatives of a single turbo-prop aircraft at a specified flight condition for the best deduction of the dynamic characteristics. In wind axes the six degree of freedom equations are algebraically linearized so that the linear state equation contains aerodynamic derivatives in a state-space form and is used in the maximum likelihood method. The simulated data added with the measurement noise is used as a flight test data which is necessary to the estimation of nondimensional aerodynamic derivatives. It is obtained by implementing the 6-DOF nonlinear flight simulation. In the flight simulation, the effects of several control input types, control deflection amplitudes, and the turbulence intensities on the statistical convergence criteria are also examined and quantitative analysis of the results is discussed.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.29 no.3
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• pp.117-121
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• 2021

The Multi-crew Pilot License (MPL) is a new pilot qualification introduced by ICAO to train co-pilots for transport aircraft based on efficient and stable competency to respond to changes in the operating environment and technology. ICAO and the European Union Aviation Safety Agency (EASA) require a minimum flight of 240 hours for MPL qualification training, and allow the use of flight simulation training devices (FSTDs) for most of the training, specifying the performance requirements for FSTDs. As South Korea is also preparing for the operation of the MPL training program, it is essential to establish the operating standards for FSTDs required for MPL training. This study aims to identify the international standards for FSTDs related to MPL training, and to compare them with the current operating standards for FSTDs in South Korea for presenting a standard (draft) that can be used when introducing domestic MPL training programs in the future.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.19 no.1
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• pp.1-6
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• 2011

The free-wing tilt-body aircraft is researched in the flight performance characteristics such as short take-off and landing capability, and reduced sensitivity to gust and center of gravity (CG) change. Due to the main wing separating from the fuselage, the high tiltable empennage, and the stub-wing strongly influencing from the propeller wake, the resulting vehicle aerodynamics and flight dynamics are quite different from those of a conventional fixed-wing aircraft. Using the governing flight dynamics model was studied previously, all of speed and body tilt angle is simulated to determine the flight envelope by a non-linear 3-DOF flight simulation analysis. Though flight performance and trimmability are studied, the flight model of free-wing tilt-body aircraft is to reduce the hidden risk and to achieve the successful flight test. It is analyzed the flight characteristics that distinguishes free-wing tilt-body aircraft from the conventional aircraft.

• Proceedings of the KSME Conference
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• 2003.11a
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• pp.1045-1050
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• 2003

In this study, to investigate the effects of omitting low-amplitude cycles from a flight-simulation loading, crack growth tests are conducted on 2124-T851 aluminum alloy specimens. Three test spectra are generated by omitting small load ranges as counted by the rain-flow count method. The crack growth test results are compared with the data obtained from the flight-simulation loading. The experimental results show that omission of the load ranges below 5% of the maximum load does not significantly affect crack growth behavior, because these are below the initial stress intensity factor range. However, in the case of omitting the load ranges below 15% of the maximum load, crack growth rates decrease, and therefore crack growth curve deviates from the crack growth data under the flight-simulation loading. To optimize the load range that can be omitted, crack growth curves are simulated by the stochastic crack growth model. The prediction shows that the omission level can be extended to 8% of the maximum load and test time can be reduced by 59%.

• Journal of the Korea Institute of Military Science and Technology
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• v.14 no.6
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• pp.1026-1030
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• 2011

This paper presented here contains development of variable stability system(VSS) control laws for the KIFS (Korean In-Flight Simulator) aircraft to simulate the dynamics of F-16 aircraft. Development of VSS Control law for pitch rate, roll rate, yaw rate simulation for three specified flight conditions using Model Following Technique with rate feedback autopilot for stability provision. The direct lift force controller was also added to the developed VSS control law to simulate the pitch rate and normal g-load simultaneously. The simulation results show high accuracy of F-16 aircraft's pitch, roll, yaw rate and g-load simulation.

• Journal of the Korea Institute of Military Science and Technology
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• v.21 no.3
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• pp.349-360
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• 2018

This paper proposes various methods for constructing a HWIL simulation system including Inertial Navigation System(INS) and Guidance Control Unit(GCU) under the assumption that the INS identifies the initial attitude of an aviation body through its own alignment and that it is a package consisting of an inertial sensor and a navigation computation module. This paper also presents a real-time computing technology and a way to calculate the command of the Flight Motion System(FMS) analogous to the acutal flight environment. The proposed HWIL simulation system is constructed by applying the above-mentioned methods and the results of running a series of simulations confirm high effectiveness and usefulness of the system. Finally, minor error factors that could be acquired only in HWIL simulation Environment are analyzed.

• Journal of Power System Engineering
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• v.8 no.4
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• pp.11-16
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• 2004

In this study, to investigate the effects of omitting low-amplitude cycles from a flight-simulation loading, crack growth tests were conducted on 2124-T851 aluminum alloy specimens. Three test spectra were generated by omitting small load ranges as counted by the rain-flow count method. The crack growth test results were compared with the data obtained from the flight-simulation loading. The experimental results show that the ranges equal to or smaller than 5% of the maximum load do not contribute to crack growth behavior because these are below the initial stress intensity factor range. Omitting these from the flight-simulation loading, test time can be reduced by 54%. However, in the case of omitting the load ranges below 15% of the maximum load, crack growth rates decreased, and crack growth curve deviated from the crack growth data under the flight-simulation loading because loading cycles above fatigue fracture toughness were omitted.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.30 no.2
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• pp.7-13
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• 2022

As the demand for simulated flight training and interest in new technology training increase, this study analyzed the performance of flight simulator training and actual flight training subjects to confirm efficient flight simulator training curriculum. Summarizing the results of the study, found that flight simulator training had a significant positive effect on the actual flight training performance and in particular had a relatively large effect on the air maneuver, traffic pattern, cross country flight subjects. As a result of analyzing theoretical major classes that affect flight simulator training to verify the correlation, found that principle of air navigation, air traffic service, and helicopter flight theory were affected in order. The significance of this study was to identify the curriculum and ground lesson that should be focused on effectively performing flight simulator training in the helicopter private pilot course.