• Journal of the Korean Society for Aviation and Aeronautics
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• v.10 no.1
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• pp.57-68
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• 2002

The economical aspects should be evaluated to decide the LCC(Life Cycle Cost) of the long life facilities or equipments. Airplane operators evaluate the economical aspects to decide whether they maintain the existing airplane or substitute the new one. This paper presents economic life cycle and economic life cost for both Cessna 172R and Mooney 20J that are operated for flight training in 'H' University. The residual value that is used to calculate the capital recovery rate of the airplane is calculated based on the data from Blue Book published in USA. The annual equivalent on operation cost is calculated based on the 500 flight hours per year which is the annual flight hour for the airplane in 'H' university. This paper showed that economic life cycle of Cessna 172R is nine years since it was introduced in 2001, and Mooney 20J which was introduced in 1991 exceeds the economic life cycle in 2002.

• Journal of Korean Society of Transportation
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• v.21 no.3
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• pp.23-35
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• 2003

This paper investigates the effectiveness of flight operation between airplane maintenance engineers and pilots who work together. The developed model is to identify the relationship between the attitudes of airplane maintenance engineers and pilots and the effectiveness of flight operation. The results indicate that the shared values and balanced power between airplane maintenance engineers and pilots are positively related with trust and job satisfaction, but conflict is negatively related. Further, trust and job satisfaction positively affect the effectiveness of flight operation. These findings suggest that the improvements of the relationships between airplane maintenance engineers and pilots need more efforts to ensure the aviation safety and efficient flights.

• Journal of Aerospace System Engineering
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• v.7 no.3
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• pp.39-44
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• 2013

On this study, climb performance related airworthiness requirements for small airplane on KAS Part 23 and flight test techniques for climb performance (Sawtooth climb) are introduced. Also, applicable procedures, test conditions and required test parameters of sawtooth climb flight test techniques are reviewed.

• Journal of the Korea Society for Simulation
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• v.12 no.3
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• pp.1-11
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• 2003

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. The paper describes 3D flight visual training program of driving airplane in practice. It is for beginners using joystick in PC, implements airplane physical equations. And it uses rendering technology to implement vision parts of flying object.

• Proceedings of the Korea Society for Simulation Conference
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• 2003.06a
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• pp.37-42
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• 2003

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. The paper describes 3D flight visual training program of driving airplane in practice. It is for beginners using joystick in PC, implements airplane physical equations. And it uses rendering technology to implement vision parts of flying object.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.5 no.1
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• pp.17-30
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• 1997

FIight Test procedures are studied from FAR 23, AC 23-8, and Order 8110.7. We have been studied the main procedures for the type certification of light airplane from the experiences of Chang Gong 91. This study is intended as a reference for small airplane manufacturers, engineers, flight test engineers, and engineering flight test pilots, including government personnel. This study covers flight test items of interest during type certification. These methods and procedures are promulgated, in the interest of standardization, for use during normal category airplane flight test certification activities.

• Advances in aircraft and spacecraft science
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• v.3 no.4
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• pp.399-425
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• 2016

The dynamical requirements are obtained for airplanes to travel on inclined circular trajectories. Formulas are provided for determining the load factor, the bank angle, the lift coefficient and the thrust or power required for the motion. The dynamical properties of the airplane are taken into account, for both, airplanes with internal combustion engines and propellers, and airplanes with jet engines. A procedure is presented for the construction of tables from which the flyability of trajectories at a given angle of inclination can be read, together with the corresponding minimum and maximum radii allowed. Sample calculations are shown for the Cessna 182, a Silver Fox like unmanned aerial vehicle, and a F-16 jet airplane.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.16 no.3
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• pp.1-6
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• 2008

The stalling speed flight test of light airplane, ChangGong-91, was performed to acquire the certification. With power-off engine condition, the wings level stall flight tests were conducted at the aircraft configuration of various flap angle - clean, 20degree, and full flap, respectively. They were performed considering with the combination of the maximum and minimum test weight, and forward and afterward center of gravity. The stalling speeds and the minimum speeds of light airplane were determined from the results of flight test. Also, the appropriateness of stall warning speeds are evaluated through the flight test measures. The airplane is recoverable only with pitch control and engine throttle from stall state without exceptional operation.

• Proceedings of the KSME Conference
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• 2007.05a
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• pp.891-896
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• 2007

This paper contained the flight test calibration for the airspeed indicator and the altimeter of the light airplane ChangGong-91, which is the first type certified aircraft from Korean Ministry of Construction and Transportation, as a part of the flight test validation. The flight test for airspeed position error calibration was performed using tower fly by method in order to calibrate swivel head testboom which is attached to the right wing tip of the airplane, and using system to system method for airspeed indicator. The altimeter calibration was calculated using flight test data for airspeed calibration. The flight test was conducted at the basis of the 'Korean Airworthiness Standard' regulation of Korean Ministry of Construction and Transportation.

• Advances in aircraft and spacecraft science
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• v.5 no.5
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• pp.551-579
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• 2018

This work is concerned with the motion of propeller driven airplanes, flying at constant velocity on ascending or descending rectilinear trajectories. Its purpose is to provide important features of rectilinear flights that are required for airplane trajectory planning but that cannot be found already published. It presents a method for calculating the amount of fuel used, the restrictions on the trajectory parameters, as inclination and speed, which result from the load factor, the lift coefficient, the positivity and upper boundedness of the power available. It presents a complete discussion of both ascending and descending flights, including gliding. Some original remarks are made about the parameters of gliding. It shows how to construct tables of parameters allowing to identify rapidly flyable trajectories. Sample calculations are shown for the Cessna 182 and a Silver Fox like unmanned aerial vehicle.