• Journal of the Korean Society for Aviation and Aeronautics
• /
• v.17 no.1
• /
• pp.29-38
• /
• 2009

This paper surveys the historical perspective and design considerations for developing the human powered aircraft(HPA). Especially the weight and materials, aerodynamics, flight controls, and power trains are focused. The average power a human can produce and sustain is approximately 200${\sim}$250 W which is a critical design constraint of HPA. The survey shows that the empty weight of HPA was in the 30${\sim}$40 kg range(90${\sim}$110 kg include pilot). Thus, in order to design a successful HPA, the value of power to weight ratio should be 2.0 W/kg or above. The HPA design technique could be applied directly to the development of an unmanned high altitude airplanes used for atmospheric research, where light structures, low Reynolds number aerodynamics and high efficiency propeller design are required as well.

• Proceedings of the KIEE Conference
• /
• 2009.07a
• /
• pp.325_326
• /
• 2009

For the sake of the safety of aircraft, aviation obstacle lights should be installed on the towers of transmission line in accordance with the Aviation Act. At present, the used solar-cell aviation obstacle lights are composed of LED lamp and a regulator, batteries, solar-cells which are divided into four parts. And, the divided four parts are connected by cable. Also, aviation obstacle lights are consisted of 150 LED lamps. therefore, the scale of sollar-cells, batteries and the power consumption of aviation obstacle light is big. For that reason, this paper would introduce the development of the solar-cell type single body LED aviation obstacle using the high brightness LED in order to make aviation obstacle more lightened and small-sized.

• Journal of the Korean Society for Aviation and Aeronautics
• /
• v.22 no.1
• /
• pp.44-50
• /
• 2014

In this study, we surveyed the operating status of the LSA Airpark in Metropolitan Area of Korea, and compared the Airfield Facilities Manual for the Air Leisure. We analyzed the problems of the closure and the currently used of the LSA Airpark, through site visits. We presented the re-usability for the closure LSA Airpark, the improvements for the currently used of the LSA Airpark.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.45 no.7
• /
• pp.566-573
• /
• 2017

A type certificate is required to ensure the safety of aircraft design. If a person is to pursue major design change to the certified aircraft, an applicant has to apply for a new type certificate, an amended type certificate, or a supplemental type certificate appropriately. Design changes to be applied for a supplemental type certificate are abstractly defined in ICAO, FAA, and EASA regulations. In this paper, authors reviewed certification procedures regarding design changes, analysed certification examples of leading countries, and presented the criteria to determine "major design changes not extensive" for a supplemental type certificate.

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

• 한국항공운항학회:학술대회논문집
• /
• 2005.05a
• /
• pp.116-119
• /
• 2005

• 한국항공운항학회:학술대회논문집
• /
• 2015.11a
• /
• pp.25-28
• /
• 2015

Aircraft conceptual design usually uses low to medium fidelity analysis to determine the basic configuration of an aircraft. Optimum solution is bounded by at least one of the constraints in most cases. This solution has risk to fail at later stage when analyzed with more sophisticated analysis tools. This research uses pre-constructed database to estimate the analysis prediction errors associated with simplified analysis methods. A possibility based design optimization framework is developed to utilize the newly proposed piecewise-linear fuzzy membership functions that compensate the discrepancies caused by simplified analysis. The proposed approach for aircraft design produces the optimum aircraft configurations that are less likely to fall into infeasible region when analyzed using higher fidelity analysis at later design stages.

• Journal of Advanced Navigation Technology
• /
• v.21 no.6
• /
• pp.638-642
• /
• 2017

FOD is a generic term for substances with potential threats that can pose a fatal risk to aircraft. Therefore, FOD should be noted in all areas of the airport. Especially, the method of detecting and collecting FOD in runway and aircraft movements is very low efficiency and economical efficiency of airport operation, so it is essential to develop FOD automatic detection system suitable for domestic environment. As part of the aviation safety technology development project, the development of an automatic detection system for foreign matter in the moving area of the aircraft inside the airport is underway. In this paper, it is confirmed that EO / IR camera is used for detection of foreign objects at Taean Airfield of Hanseo University. EO camera is used during the day and IR camera is used at night.

• Journal of Aerospace System Engineering
• /
• v.1 no.2
• /
• pp.6-12
• /
• 2007

Flight modes of automatic flight control system for light general aviation flight deck. Garmin G1000, were realized using Stateflow. In developing aircraft, it is difficult to verify the operational flight program in particular branch statement because developer can not see any visual logical steam. So, Stateflow has been used to visualize logical stream, transition from one flight mode to another flight mode. The performance was approved by applying flight mode transition conditions of G1000 to proposed transition system that is composed of states, switches, events, data and transition conditions. DURMI-II was used as 6-DOF simulation model.

• Current Industrial and Technological Trends in Aerospace
• /
• v.9 no.1
• /
• pp.64-76
• /
• 2011

The current development trend and status of a personal air vehicle, known as the novel concept of a transportation that combines a personal car with a light general aviation aircraft, is summarized to investigate its feasibility as a future transportation. In the paper, the development programs of a personal air vehicle such as AGATE, PAVE, SATS and NGATS are first summarized, and then the design, technical development and testing activities of Terrafugia's Transition and Moller International's M400 Skycar, which will be commercialized in a short time, are reviewed. Based on the assessment of technical issues with those vehicles, the key technologies for the future development of the personal air vehicle are suggested with two basic requirements of safety and mobility.