• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.6
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• pp.481-489
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• 2017

Situation awareness means recognizing everything necessary to understand progress in a flight or aircraft maintenance work. Situation awareness is based on more than simply recognizing important about the environment, and it is important to provide the meaning of information in an integrated form. The KHP provides the pilot with integrated situation display for an integrated form of situation awareness and warning that synchronizes the priority based audible signal with the visual signal. Provide integrated display and warning to reduce operator error and enable operators to focus on mission critical tasks and events. This paper introduces the integrated situation display and warning design implemented in the KHP.

• Journal of Satellite, Information and Communications
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• v.7 no.3
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• pp.110-115
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• 2012

Satellite structure should be designed to accommodate and support safely the payload and equipments necessary for its own missions and to secure satellite and payloads from severe launch environments. The launch environments imposed on satellites are quasi-static accelerations, aerodynamic loads, acoustic loads and shock loads. Currently KARI(Korea Aerospace Research Institute) is developing Geo-KOMPSAT-2(Geostationary Earth Orbit KOrea Multi-Purpose Satellite) with technologies which were acquired during COMS(Communication, Ocean and Meteorological Satellite) development. As compared to COMS Geo-KOMPSAT-2 requires more propellant due to mass increase of Advanced Meteorological Payload with high resolution and increase of miss life, it is difficult to apply the design concept of COMS to Geo-KOMPSAT-2. This paper deals with conceptual design of Structural Subsystem for Geo-KOMPSAT-2.

• The KIPS Transactions:PartC
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• v.16C no.5
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• pp.615-620
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• 2009

Nowadays, wireless infrastructures such as sensor networks are widely used in many different areas. In case of sensor networks, the wirelessly connected sensors can execute different kind of tasks in a diversity of environments, and one of the most important parameter for a successful execution of such tasks is the location information of each node. As to localization problems in WSNs, there are ToA (Timer of Arrival), RSS (Received Signal Strength), AoA (Angle of Arrival), etc. In this paper, we propose a modification of existing ToA and RSS based methods, adding a weighted average scheme to measure more precisely the distance between nodes. The comparison experiments with the traditional ToA method show that the average error value of proposed method is reduced by 0.1 cm in indoor environment ($5m{\times}7m$) and 0.6cm in outdoor environment ($10{\times}10m$).

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.11
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• pp.988-995
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• 2014

Two axis gimbal type X-band antenna system has been widely used to effectively transmit the real time image data from the observation satellite to the ground station. The micro-vibration generated by stepping motor actuation and imperfect intermeshed gear configuration of the antenna is one of the sources to degrade the image quality. To guarantee a high quality image of high resolution observation satellite, micro-vibration isolation of X-band antenna is required. In this paper, the X-band antenna vibration isolation system using pseudoelastic SMA(Shape Memory Alloy) mesh washer has been newly suggested. The basic characteristics of the SMA mesh washer isolator proposed in this study has been measured through static load tests and its effectiveness has been demonstrated by the micro-vibration isolation test of the X-band antenna.

• Journal of KIISE
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• v.43 no.8
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• pp.848-856
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• 2016

Seeking and recognizing maritime targets are very important tasks for maritime safety. While searching for maritime targets using radar is possible, recognition is conducted without automatic identification system, radio communicator or visibility. If this recognition is not feasible, radar operator must tediously recognize maritime targets using movement features on radar base on know-how and experience. In this paper, to support the radar operator's mission of continuous observation, we propose an algorithm for automatic recognition of an unknown ship using movement features on radar and a method of detecting potential ship related accidents. We extract features from contact range, course and speed of four types of vessels and evaluate the recognition accuracy using SVM and suggest a method of detecting potential ship related accidents through the algorithm. Experimentally, the resulting recognition accuracy is found to be more than 90% and presents the possibility of detecting potential ship related accidents through the algorithm using information of MV Sewol. This method is an effective way to support operator's know-how and experience in various circumstances and assist in detecting potential ship related accidents.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.9
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• pp.723-734
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• 2018

A structural weight estimation methodology for the multicopter design process is presented. In general, a multicopter is composed of an airframe, motors, propellers, battery and so on. Among these, the weight of motors, propellers and battery can be obtained from the weight trends with respect to design parameters. However, the structural weight is hard to be estimated due to the various configurations and design concepts of multicopters. Moreover, the airframe weights of most commercial multicopter products are not provided. Thus, an accurate airframe weight model is required for the reliable mutlcopter design process. Firstly, the standard configuration of multicopters is defined. Then, we proposed the structural weight estimation method using the number and diameter of propellers determined from the initial step of sizing process. Finally, we validated our suggested method using the commerical products.

• Korean Journal of Remote Sensing
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• v.16 no.3
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• pp.261-279
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• 2000

Today, the development of spaceborne Earth remote sensing is characterised by the increasing number and various types of remote sensing satellites, which are being operated in the low altitude and geostationary orbits with the help of rapid development of modern space technologies. It is believed that around 15 countries have programs to own their spaceborne Earth remote sensing systems, and the number of systems will be reached to some tens until the end of 2000 years. It is expected that Korean remote sensing satellites will be launched in sequence according to the national space program. The befinits will be magnificient because of the wide range of application area. Application of remote sensing information to the social infra implies that the potential customers can access the information, mission and the characteristics of the operation, and it is necessary to be supplied more information about systems and mission areas to our domestic users for proper applications. In this review we will survey the applications of the information acquired by the systems of USA, Russia and other countries. In this review we will discussed withing general application area, missions and systems.

• Journal of the Korea Society of Computer and Information
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• v.24 no.10
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• pp.1-9
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• 2019

Fighter pilots are taking 'Advanced Pilot Training' courses to perform their missions perfectly even under adverse conditions. However, there are accidents that fall due to problems with the human body's equilibrium in the acceleration of flight, falling into the 'Vertigo, Spatial disorientation' phenomenon. As such, accidents that fighters fall due to spatial disorientation frequently occur not only in Korea but also abroad. In this study, we implemented the 'Vertigo' warning function in the fighter. First, we analyzed the aircraft's mission computer and the currently implemented warning functions. And we studied the coordinate system to utilize the aircraft attitude information. Based on this, we wanted to provide a visual warning to the HUD when the fighter flies over a certain time in the inverted flight position. Implementing this feature is expected to improve pilot flight safety. In addition, based on the results of this study, we propose a method to implement warning functions through linkage with other subsystems.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.2
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• pp.114-121
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• 2019

Tailless aircraft have advantages of low visibility compared to conventional aircraft, but drawback of poor stability as well which makes designing controller difficult. The controller design is more difficult, especially when the center of gravity moves due to store release or fuel consumption during flight. In this paper, an L1 adaptive controller is proposed as a way to overcome these problems. The reliability and performance of the controllers were verified by non-linear simulations. RPV Flying Quality Design criteria were used for design criteria. Using the simulation, it is shown that the adaptive controller maintains stability of the unmanned aircraft for sudden large change in the inertial properties. It is also shown that the calculation burden can be reduced when it is used with the gain scheduling method.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.12
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• pp.1028-1036
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• 2018

KARI plans to launch Korea Pathfinder Lunar Orbiter (KPLO) to the Moon by December 2020 for the first step of the Korea Lunar Exploration Project. This orbiter will be launched to obtain lunar exploration technologies and science data in advance before launching a main orbiter and a lunar probe. This paper describes the verification of thermal design for the orbiter. It is exposed to more extreme thermal environment than that of low Earth orbit satellite due to the heavy infrared emission of the Moon. Accordingly, a thermal design considering this environment is needed to maintain the temperature of payloads and components equipped in the orbiter within operating temperature range in all orbits. We performed the thermal analysis for Earth-Moon transfer orbit, lunar mission orbit and lunar eclipse required for thermal design verification of the lunar orbiter. As a result, this thermal design met the design requirements.