• The Journal of Asian Finance, Economics and Business
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• v.7 no.12
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• pp.43-52
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• 2020

This paper examines how macroeconomic variables, such as interest rate differences, inflation, exchange rates, economic growth and external debt growth, affect capital flight in the ASEAN-8 countries. We apply a panel data model with fixed effect estimation for the data for eight countries from the period 1994 to 2018. We use the residual approach used by the World Bank to measure the value of capital flight. The results show that the interest rate differences, exchange rates, economic growth and foreign debt growth had a positive and significant effect on outward capital flight. A further implication of this finding is that the interest rate differences, exchange rate, economic growth and foreign debt growth are factors that trigger an increase in capital outflow in the ASEAN-8 countries. Nonetheless, inflation rate is not considered to be the main factor influencing capital flight, as average inflation in the ASEAN-8 countries remains relatively stable. This paper will be beneficial for policymakers in the ASEAN-8 countries and encourage them to constantly pay attention to these four variables, as they significantly influence capital flight, whereas they can disregard the impact of the inflation variable that is not significant in influencing capital flight.

• Asian Journal of Business Environment
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• v.10 no.1
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• pp.29-36
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• 2020

Purpose: This study aims to analyze the effect of macroeconomic and non-macroeconomic determinants of capital flight. Research design, data and methodology: With five determinants, this survey was conducted by Eviews 10, and the ordinary least squares (OLS) as a statistical method was applied for examining the research hypothesis. The five determinants are a budget deficit, economic growth, inflation rate, the exchange rate, and sovereign rating. The capital flight measurement uses the World Bank residual approach. The data derive from the Central Bank of Indonesia, BPS-Statistics Indonesia, OECD, and Moody's Investor Service. Results: The result considers that economic growth, the exchange rate, and the sovereign rating will decrease capital flight. In addition, the budget deficit and the inflation rate will increase capital flight. The sovereign rating decreases capital flight bigger than the other determinants. In addition, the exchange rate is statistically significant. Conclusions: The most influential problem of capital flight in Indonesia is because of non-macroeconomics factor political issue, corruption, bad regulation, and others. That's why the investment climate in Indonesia is still not secure. We propose that the regime would have to amend the business rule for reducing capital, raising the investment climate, and demonstrating the creative industry.

• International Journal of Industrial Entomology and Biomaterials
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• v.9 no.2
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• pp.241-247
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• 2004

It was investigated whether or not flight has any effects on oviposition and colony development of the artificially hibernated Bombus terrestris queen and ,$CO_2$-treated queen. Flight periods were defined as 0 days (control), 1 day, 3 days and 6 days. The weights of queens after flight were 1.5-8.9% lower than those before flight depending on the flight periods. The oviposition and colony development of artificially hibernated and $CO_2$-treated B. terrestris queen were affected by the flight. Among flight periods tested, in particular, the queens start to flight for 3 days showed better flight effect than those other flight periods in the colony development, rate of colony foundation, rate of progeny-queen production, the number of worker and queen produced. But, the longer the flight periods is, the worse the oviposition and colony development of the queens hibernated artificially and $CO_2$-treated are (i.e., the 6 days-flight queen).

• 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 Korean Society for Aviation and Aeronautics
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• v.15 no.4
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• pp.9-16
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• 2007

Tilt rotor aircraft can take off and land vertically and cruise faster than any other helicopter. A scaled flight demonstration model of a tilt rotor aircraft has been developed by KARI. Because the flight characteristics of tilt rotor are not well known, the developed scaled model would be helpful to evaluate flight control algorithm of a full scale aircraft. The tethered hover test has been performed in order to improve hover flight characteristics of tilt rotor aircraft prior to flight test of the small scaled model. During the tethered hover test, the performance of rotor speed governor, rate SAS (Stability Augmentation System) and control surface mixers have been evaluated. We expect that the results of real flight hover test would be quite same as tethered hover test. Therefore the tethered hover test results will reduce the risk of flight test properly by fixing some of hidden problems which might occur during the flight test. This paper presents the results of tethered hover test in detail and shows how it could be final ground test before flight test. The control mixer gain and rate SAS feedback gains were modified in order to get higher controllability and stability during the tethered hover flight. The rotor governor showed that it could keep rotor RPM constant with very small deviation even during severe pilot collective input change. The tethered hover test results gave pilot and engineers confirmation and experience about the scheduled flight test.

• Journal of Aerospace System Engineering
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• v.8 no.4
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• pp.24-31
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• 2014

The modern version of aircrafts is allowed to guarantee the superior handing qualities within the entire flight envelope by imposing the adequate stability and flying qualities on a target aircraft through the various techniques of flight control law design. Generally, the flight control law of the aircraft in service applies the various techniques of the verified control algorithm, such as dynamic inversion and eigenstructure assignment. The supersonic trainer employs the RSS(Relaxed Static Stability) concept in order to improve the aerodynamic performance in longitudinal axis and the longitudinal control laws employ the dynamic inversion with proportional-plus-integral control method. And, lateral-directional control laws employ the blended roll system of both beta-betadot feedback and simple roll rate feedback with proportional control method in order to guarantee aircraft stability. In this paper, the lateral-directional flight control law is designed by applying dynamic inversion control technique as a different method from the current supersonic trainer control technique, where the roll rate command system is designed at the lateral axis for the rapid response characteristics, and the sideslip command system is adopted at the directional axis for stability augmentation. The dynamic inversion of a simple 1st order model is applied. And this designed flight control law is confirmed to satisfy the requirement presented from the military specification. This study is expected to contribute to design the flight control law of KF-X(Korean Fighter eXperimental) which will proceed into the full-scale development in the near future.

• Journal of Advanced Navigation Technology
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• v.28 no.1
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• pp.60-67
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• 2024

The majority of civil aviation accidents are caused by human factors, and especially for rotary-wing aircraft, accidents often occur in situations where pilots unexpectedly or unintentionally enter into instrument meteorological conditions (IIMC). This research analyzed the error rates of rotary-wing aircraft pilots under low visibility conditions from various angles to gain insights into flight characteristics and to explore measures to reduce accidents in IIMC situations. The occurrence rate of errors by pilots under low visibility conditions was examined using a flight simulator equipped with motion, with 65 pilots participating in the experiment. Flight data obtained through the experiment were used to aggregate and analyze the number of errors under various conditions, such as reductions in flight visibility, the presence or absence of spatial disorientation, and the pilot's qualifications. The analysis revealed peculiarities in flight characteristics under various conditions, and significant differences were found in the rate of error occurrence according to the pilot's qualification level, possession of instrument flight rules (IFR) qualifications, and during different phases of flight. The results of this research are expected to contribute significantly to the prevention of aircraft accidents in IIMC situations by improving pilot education and training programs.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.20 no.2
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• pp.1-6
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• 2012

Four dimensional(4-D) trajectory modeling is conducted based on flight plan. The flight plan is divided into several segments which represent certain operating flight modes. Thrust, drag and fuel consumption rate of an aircraft are calculated using BADA provided by Eurocontrol. The trajectory is modeled with the rate of climb/descent calculated with Total-Energy Equation. The simulation results with a typical aircraft and its flight plan indicate that the trajectory modeled corresponds well with the suggested flight plan. The performance profiles including total endurance time and time history for speed, thrust, drag and fuel consumption were also appropriately generated.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.29 no.4
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• pp.28-36
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• 2021

Surprise and Startle are often cited as potential or contributing factors in the cause of aircraft accidents because they can negatively affect pilots' situational awareness and decision-making. Accordingly, it is necessary to more clearly understand the effect on flight safety through the psychological and physiological reactions that occur to the pilots. Therefore, this study empirically analyzed the effects of Surprise and Startle on the pilot's psychological and physiological responses using a helicopter flight training device for the first time in Korea. As a result of the analysis, the ratio of recognition of Startle and Surprise, heart rate, and respiration rate showed a high difference between private pilots and commercial pilots. This is analyzed as the difference between long-term flight experience and flight time. In addition to presenting effective information for improving the education and training field of helicopter pilots in the future, it is intended to provide basic data for related research.

• Journal of the Korea Society for Simulation
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• v.10 no.4
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• pp.31-40
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• 2001

The flight simulator should be made like a actual flight. For the scene of sight, instrument should show the condition of flight and the pilot should catch the altitude, speed, pose and rate of lift of the airplane. This paper describes visual training program of driving airplane in practice. It is for beginners using joystick in PC, implements airplane physical equations. Flight simulator in it implements airplane panel parts in order to make simple modeling, And it uses rendering technology to implement vision parts of panel. It uses double buffering In make it faster and more efficient..