• Journal of Advanced Navigation Technology
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• v.27 no.5
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• pp.574-579
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• 2023

The radar flight test has many restrictions on simulating various targets, clutter and jamming signal. Therefore, in this study, a radar HILS system that performs a radar operation simulation function according to an operation scenario was developed. Radar HILS simulates the radar mission environment through radar beam operation simulation, radar operation control, simulated signal generation, and flight attitude simulation.. HILS generates and modulates simulated target signals(single, multiple targets) containing radar mission environments(clutter, jamming etc.) based on flight scenarios, and transmits them to AESA radar over RF. And Scenario-based radar performance was verified by detecting simulated targets and confirming detection results.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.31 no.2
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• pp.100-107
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• 2023

This study intends to present the UAM pilot qualifications and training and education systems based on the roadmap of technology for K-UAM operation system, which is being promoted for commercialization in 2025. There are currently about 250 eVTOL manufactures around the world, and they are gearing up to produce a variety of UAM aircrafts. In Korea, 35 companies including Hyundai Motor company, Korean Air, Lotte and SKT are accelerating the development of UAM aircrafts. UAM is being developed as a public goods concept centered on public transportation and urban aviation rather than private transportation. Therefore, the UAM pilot qualification and education and training system should be suitable for operations in densely populated areas and complex urban enviroments. In other words, in order to ensure safe UAM operations, the competencies and qualifications of UAM pilots should be clearly established.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.7
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• pp.91-97
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• 2004

The first Korean liquid propellant rocket KSR-III successfully finished its flight test on Nov. 28, 2002. Herein, we summarize the results of range safety system operation which is employed for the first time in flight tests of rockets developed by Korea Aerospace Research Institute(KARI). During the flight, safety-critical flight data including instantaneous impact points are monitored in realtime by range safety officers utilizing Range Safety Display Systems. The recorded screen of the display system is presented for the explanation of safety operation. In addition, comparisons are made between onboard navigation system based and radar based results in calculating instantaneous impact points, and also errors from the finally recorded impact point are described.

• Journal of Advanced Navigation Technology
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• v.23 no.4
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• pp.281-288
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• 2019

A Flight test is an important process that must be performed to maintain airworthiness in the aircraft lifecycle, including aircraft development and certification. Flight test can be conducted for the purpose of demonstrating or verifying compliance with the applicable standard. Results of the flight test air accident analysis confirm that it is caused by a combination of various factors as well as aircraft. The International Civil Aviation Organization recommends the establishment and implementation of a safety management system to prevent aircraft accidents, but it does not reflect the specificity of the flight test. As such, advanced countries are providing separate criteria to assist stakeholder in conducting flight test safety management. This study investigates and analyzes relevant regulations of advanced countries, in accordance with the construction of a national flight performance test site in Korea, and proposes government-level guidelines to help stakeholders develop their flight test operation manuals. The guidelines discuss topics such as organizational composition, safety and risk management, flight operation, personnel management, and administrative issues.

• Journal of Aerospace System Engineering
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• v.7 no.3
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• pp.33-38
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• 2013

The air data measured from the static pressure, the dynamic pressure and etc. of an airplane is used for calculation of many flight parameters(altitude and airspeed and so on) and these values applied to flight safety and navigation flight. The pitot-static system of the development airplane is calibrated by finding of pitot-static system's error using tower fly-by, trailing cone method and etc. This paper is describing for the introduction of the trailing cone method and major items for test planning, preparation, operation and results for air data calibration flight test performed, considering efficiency and safety during KC-100 development project.

• Journal of Aerospace System Engineering
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• v.6 no.3
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• pp.34-39
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• 2012

In this paper, analysis of airworthiness requirements which require flight test to show compliance and flight test method as means of compliance to those requirements are provided. For unusable fuel test, sufficient discussion between certification authority and applicant is required to select test conditions. For hot weather fuel system operation test, preservation and heating of test fuel should be done carefully not to adversely affect to test result.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.6
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• pp.526-532
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• 2015

In order to relieve limitation of flight operation under icing condition and verify its operation in adverse weather condition for Surion, military helicopter developed in Korea, airworthiness certification in icing condition is required. The process of Surion icing certification should be considered by implementation of four methods by step such as CFD analysis, simulated flight tests, artificial icing flight tests, and natural icing flight tests. For Surion icing flight tests, these are required 20~30 sorties and 20~23 hours in artificial icing condition; 20~30 sorties and 20~22 hours in natural icing condition. In addition, to proceed with efficient flight tests, it is necessary to implement artificial icing flight tests in LWC $0.5{\sim}1.0g/m^3;$ natural icing flight tests in less than LWC $0.5g/m^3$.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.219-224
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• 2005

In order to investigate transient behaviour of the CRW(Canard Rotor Wing) type UAV(Uninhabited Aerial Vehicle) propulsion system during flight mode transition considering flow control valve operation, the propulsion system was modelled using SIMULINK commercial program. For transient simulation of the main engine system, the ICV(Inter-Component Volume) method was applied. The valve system is to control the gas flow of the rotary duct system and the main duct system, and the analysis was performed with an assumption that the total gas mass flow of the main engine is the same as summation of the rotary duct flow and the main duct flow, and with consideration of valve loss, flow rate and effective area in valve angle variation. The performance analysis was carried out during flight mode transitions from the rotary flight mode to the fixed wing flight mode and vice versa mode at altitude of 1Km, flight Mach number 0.1 and maximum engine rpm.

• Journal of Advanced Navigation Technology
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• v.27 no.1
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• pp.23-35
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• 2023

Evidence-based training (EBT) improves a pilot's competency and confidence based on the data(Evidence) from actual aircraft accidents, incidents, operations, and training for safe operation in the fast-paced and large-scale air transportation field. It is a training/assessment program that strengthens resilience for problem solving. As a way to apply this evidence-based training(EBT) to the educational system of ATO and to resolve the problems, I propose 3 improvement plans. They are evaluation criteria that apply the core competencies of EBT to the educational evaluation system, the way to improve the system for standardization of practical test examiners and instructors and also the ways to use Flight Simulation Training Devices(FSTD).

• Journal of the Korean Society of Propulsion Engineers
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• v.9 no.3
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• pp.127-132
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• 2005

In order to investigate transient behavior, of the CRW(Canard Rotor Wing) type UAV(Uninhabited Aerial Vehicle) propulsion system during flight mode transition considering flow control valve operation, the propulsion system was modelled using SIMULINK commercial program. The valve system is to control the gas flow of the rotary duct system and the main duct system, and the analysis was performed with an assumption that the total gas mass flow of the main engine is the same as summation of the rotary duct flow and the main duct flow, and with consideration of valve loss, flow rate and effective area in valve angle variation. The performance analysis was carried out during flight mode transitions from the rotary flight mode to the fixed wing flight mode and vice versa mode at altitude of 1km, flight Mach number 0.1 and maximum engine rpm.