• Journal of Advanced Navigation Technology
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• v.25 no.1
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• pp.40-51
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• 2021

In this paper, the design requirements was produced by analyzing domestic and foreign regulations of the vertical takeoff and landing site required to operate the urban air mobility (UAM) system in Korea and the size of the take-off and landing pads were defined, and the configuration of vertiport was proposed. First, for the metropolitan area with high population density, pilot locations of the vertical take-off and landing site were selected based on the demonstration routes suggested by the Ministry of Land, Infrastructure and Transport and analyzed the characteristics of each location and determined the number of possible installations of vertiport by measuring each site. After that, variables necessary for the operation of the vertical takeoff and landing area were set, and the hourly, daily, monthly aircraft operating cycle, the number of acceptable people, and efficiency were calculated according to the number of simultaneous operation and the number of stand. Finally, using CATIA, the configurations of the virtual vertiport was created by applying the design requirements.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.8
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• pp.583-590
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• 2022

This paper presents a framework, MADAM(Multidisciplinary Analysis and Design for Advanced Mobility). For the actual UAM operation, not only aircraft performances but also demand, cost and flight scenarios are in connection; the overall framework is essential for the multidisciplinary design. In this study, the framework is developed and introduced. Demand and cost analysis of Gimpo-Samseong line in the Seoul area using the framework is conducted as an example result. Also, future ticket prices are estimated by applying changes in the aspects of major cost components and the price, ￦76,000, is calculated with the target for maximizing the total profit in the year 2035.

• Journal of Advanced Navigation Technology
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• v.26 no.6
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• pp.380-392
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• 2022

In this paper, the new vertiport regulations of the FAA and EASA are analyzed for urban air mobility(UAM), and the major components of the vertipad and the new specifications of each component are analyzed, and UAM operation in various environments is analyzed. Additional components for vertiport and regulations for surrounding airspace were also reviewed. Afterwards, based on the size of the S-A1 aircraft being developed by Hyundai Motors, domestic vertiport specifications and layouts were investigated for UAM operation, and these were applied to the city of Incheon. In addition, the time required for using a taxi or car were compared with the time required for using UAM between major locations in Incheon and Seoul.

• Journal of Advanced Navigation Technology
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• v.28 no.3
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• pp.272-277
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• 2024

In most countries, instrument flight procedures are designed by applying one of the following standards: the International Aviation Organization's DOC 8168, Air Navigation Services and Operation Procedures (PANS-OPS), or the US Federal Aviation Administration's TERPS, Terminal Procedures. In particular, the circling approach procedure has many differences between the two standards, and the US terminal procedure (TERPS) has become more complicated since 2013 by applying expanded standards depending on altitude. The circling approach procedures are more risky than straight-in approach procedures because it involves maneuvering the aircraft close to the ground at low energy for landing. In order to accurately understand these differences, this study provides to distinguish by what criteria the circling approach procedure is designed according to individual domestic airports in Korea, to calculate the radius for the range of circling approach areas that guarantee minimum obstacle avoidance during circling approach maneuvers, and to present methods for performing safe circling approach procedures.

• Journal of the Korean Society of Industry Convergence
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• v.23 no.5
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• pp.709-716
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• 2020

Recently, the drone's equipment development and software technology have dramatically improved. With such developments, the applicability is increasing in various fields that require rapid geospatial information, and in practice, regulations and systems have been established, and the fields in use are increasing. Also, in Korea, corporations and public institutions are actually using and researching drones in fields such as aircraft development, communication technology development, construction site use, and surveying. However, there are no fields where drones are actually used in road construction sites. Therefore, in this study, to utilize drones that have been actively used in the civil engineering and construction fields for road construction, we investigated the current status of the Korea Highway Corporation's field drone use research and classified the possibility of drone introduction by road construction. Finally, a method of using drones at road construction sites was proposed to prepare a method for using drones at road construction sites.

• Advances in aircraft and spacecraft science
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• v.5 no.4
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• pp.431-444
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• 2018

Numerical simulations have been conducted to study the unstart/restart characteristics of an over-under turbine-based combined-cycle propulsion system (TBCC) inlet during the inlet transition phase. A dual-solution area exists according to the Kantrowitz theory, in which the inlet states may be different even with the same input parameters. The entire transition process was divided into five stages and the unstart/restart hysteresis loop for each stage was also obtained. These loops construct a hysteresis surface which separates the operating space of the engine into three parts: in which a) inlet can maintain a started state; b) inlet keeps an unstarted state; c) inlet state depends on its initial state. During the transition, the operation of the engine follows a certain order with different backpressures and splitter angles, namely control route, which may result in disparate inlet states. Nine control routes with different backpressures and transition stages were designed to illuminate the route-dependent behavior of the inlet. The control routes operating towards the unstart boundary can make the inlet transit from a started state into an unstarted one. But operating backward the same route cannot make the inlet restart, additional effort should be made.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.10
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• pp.901-909
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• 2012

This paper describes characteristics of solid-state $NaBH_4$ hydrogen generation and supply system for fuel cell UAV. Flow rate and pressure of the generated hydrogen were dramatically changed during $NaBH_4$ decomposition using acid. Hydrogen supply was stabilized by a self-pressurized reactor, and hydrogen stabilization method was introduced. For hydrogen generation in below zero-temperature, hydrochloric acid was diluted by propylene glycol-water mixtures. Solid-state $NaBH_4$hydrogen generation and supply system was designed. Basic operation experiments was performed to reveal the characteristics of this hydrogen generation system.

• Journal of the military operations research society of Korea
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• v.1 no.1
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• pp.131-135
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• 1975

One of the pending issues of the Ministry of Defense is the efficient management of space parts for the weapon systems. It has been known that more than 000 million dollars are needed for spare parts for the weapon systems annually. Though the problem demands a serious consideration, there has not been any systematic study on the problem as far as the author knows. One way to approach the problem is through an investigation of the system reliability under constraints. A measure of how well a system performs or meets its design objectives is provided by the concept of system reliability. If successful operation is desired for a specified period of time, reliability is defined as the probability that the system will perform satisfactorily for the required time period. This interpretation of reliability is normally applied to devices which are subject to random failures such as electrical or mechanical systems. It has been found necessary to express system reliability in terms of the reliability of the components or subsystems which comprise the system. The major subsystems of an aircraft, for example, include the electronics, powerplant, airframe and armament subsystems. Therefore, the optimal spare part kit can be found by maximizing the system reliability subject to cost or other constraints.

• Journal of the Korean Society for Precision Engineering
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• v.14 no.3
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• pp.156-165
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• 1997

In the practical control systems, the dynamic range of actuatiors is limited(or saturated) when actuators are driven by sufficiently large signals. This gives rise to a nonlinearity as a result of actuator saturation. For example, the upper limit is imposed on productive capability by available factory space and capital equipment. Other examples of those kinds of actuator saturations are a maximum torque of the actua- ting motors and a throttle position in an aircraft speed control A saturating actuator may lead not only to a large overshoot during start-up and shut-down, but also to deterioration of the performance due to the uncertainties. That is, the speed of response is decreased and, possibly, the system output may not follow the lalrge reference inputs. The large-overshoot may be accompanied by rest wind-up(or called by integra- tor wind-up) which comes from controllers with integral action in saturation operation regions. Eventually, as the overshoot increases, the system has a limit cycle or becomes oscillatorily unstable. Due to these cir- cumstances, many studies are focused on the stability and robustness of the nonlinear systems with satu- rating actuator in the time-domain as well as in the frequency-domain.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.15 no.4
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• pp.24-32
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• 2007

In this study, computational structural vibration analyses of a smart unmanned aerial vehicle (SUAV) with tilt-rotors due to dynamic hub loads have been conducted considering detailed supporting structures of installed equipments. Three-dimensional dynamic finite element model has been constructed for different fuel conditions and tilting angles corresponding to helicopter, transition and airplane flight modes. Practical computational procedure for modal transient response analysis is successfully established. Also, dynamic loads generated by rotating blades and wakes in the transient and forward flight conditions are calculated by unsteady computational fluid dynamics technique with sliding mesh concept. As the results of present study, transient structural displacements and accelerations of the vibration sensitive equipments are presented in detail. In addition, vibration characteristics of structures and installed equipments of which safe operation is normally limited by the vibration environment specifications are physically investigated for different flight conditions.