• The Journal of Korea Institute of Information, Electronics, and Communication Technology
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• v.12 no.6
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• pp.666-671
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• 2019

The flight controller(FC) used in small-sized drone was developed as simple structure does not perform complex operations because it uses different MCU with large-sized drone. Also, the balance control of small-sized drone should be simpler than Kalman filter using complex filter and the method using Complementary filter has relatively more operations. So, the method to realize the balance control on small-sized drone effectively using two-track control operating as proper method for above is suggested in this research. This method is a system maintaining effective balance with simple structure and less operations by operating adaptively for the unbalance of the drone with the acceleration sensor with the advantage which performing accurate correction by data processing for long term change and gyroscope sensor maintaining the balance of the drone by data processing for short term change. It is confirmed that stable operation was performed mostly based on the test result for repeatable test more than 100 times using two-track control and it maintained normal state operation more than 98% excluding the difficulty of maintaining normal operation when meets sudden and rapid wind yet.

• Proceedings of the Korea Information Processing Society Conference
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• 2012.11a
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• pp.72-74
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• 2012

위성의 상태를 모니터링하고 임무수행 준비 및 결과를 분석하기 위해 위성에서는 주기적으로 텔레메트리 프레임을 생성하여 지상으로 전송한다. 텔레메트리 프레임을 통해 많은 데이터가 전송될수록 정확한 위성의 상태 분석이 가능하고 위성 운용을 용이하게 할 수 있다. 그러나 위성에서 지상으로 전송할 수 있는 텔레메트리의 전송속도는 하드웨어의 성능에 따라 제한되며, 특히 저궤도 위성의 경우에는 지상과 교신이 가능한 시간이 짧다는 제약으로 인해 한정된 시간 안에 정해진 전송속도로 보낼 수 있는 데이터의 양에는 한계가 있다. 이러한 제약조건 하에서 최대한 많은 정보를 효율적으로 전송할 수 있도록 위성의 텔레메트리를 생성할 때 비트 정보들을 모아 하나의 바이트로 묶어서 텔레메트리 크기를 최소화하는 방법을 이용한다. 위성비행소프트웨어는 태스크 스케쥴링, 열제어, 전력제어, 자세제어, 원격명령처리, 원격측정데이터 처리 등의 기능별로 모듈화 되어있다. 각 모듈마다 텔레메트리로 전송되는 데이터들이 존재하고 비트 정보들을 모으는 기능도 해당하는 모듈에서 각각 담당한다. 따라서 각 모듈들이 독립적이지 못하고 텔레메트리 처리를 담당하는 모듈과 다른 모듈들 간의 커플링(coupling)이 존재하게 되어 하나의 텔레메트리 데이터 변경이 여러 모듈에 영향을 미치게 된다. 본 논문에서는 모듈들 간의 커플링을 최소화하고 텔레메트리의 변경사항이 위성비행소프트웨어 코드 자체에는 영향을 주지 않도록 하기위한 데이터베이스 테이블을 이용한 텔레메트리 처리 방안에 대하여 설명한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.9
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• pp.113-119
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• 2005

The methods that are used for receiving data from attached devices under real-time preemptive multi-task operating system (OS) by general processors can be categorized as polling and interrupt driven. The technical approach to these methods may be different due to the application specific scheduling policy of the OS and the programming architecture of the flight software. It is one of the most important requirements on the development of the flight software to process the data received from satellite subsystems or components with the exact timeliness and accuracy. This paper presents the analysis of the I/O method of device related scheduling mechanism and the reliable data I/O methods between processor and devices.

• KIPS Transactions on Software and Data Engineering
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• v.3 no.1
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• pp.7-18
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• 2014

Flight software operated on the on-board computers in the satellite has requirements such as real-time and high reliability. These requirements make dependency between the flight software and operating environments. Further, whenever a new system is built, such problem drives that all flight software are redeveloped. Thus, the dependency between them should be removed. And the work can be achieved by improving the portability of the flight software. In this paper, we propose a platform architecture based on the IMA architecture. The platform architecture is a hybrid one built by blending two kinds of realizations of the IMA architecture in order to maximize portability. In addition, we implement a prototype system and analyze the execution results of the system to justify the proposed architecture. The proposed architecture enables us to remove the dependency between fight software and operating environments.

• International Journal of Aeronautical and Space Sciences
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• v.17 no.2
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• pp.232-239
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• 2016

Recently, in order to increase the efficiency and mission success rate of UAVs (Unmanned Aerial Vehicles), the necessity for formation flights is increased. In general, GPS (Global Positioning System) is used to obtain the relative position of leader with respect to follower in formation flight. However, it can't be utilized in environment where GPS jamming may occur or communication is impossible. Therefore, in this study, monocular vision is used for measuring relative position. General PC-based vision processing systems has larger size than embedded systems and is hard to install on small vehicles. Thus FPGA-based processing board is used to make our system small and compact. The processing system is divided into two blocks, PL(Programmable Logic) and PS(Processing system). PL is consisted of many parallel logic arrays and it can handle large amount of data fast, and it is designed in hardware-wise. PS is consisted of conventional processing unit like ARM processor in hardware-wise and sequential processing algorithm is installed on it. Consequentially HW/SW co-designed FPGA system is used for processing input images and measuring a relative 3D position of the leader, and this system showed RMSE accuracy of 0.42 cm ~ 0.51 cm.

• Journal of the Korea Convergence Society
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• v.9 no.6
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• pp.25-31
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• 2018

Captive Flight Test (CFT) is one of the most important tests to acquire data when developing complex weapon systems. In this paper, we introduce the design and test result of our POD system for CFT. POD system uses POD set which consists of left and right POD. The exterior and mass properties of POD set are equal to those of fuel tank for aircraft so that we can omit Airworthiness Certification. Also, we adequately placed inner-equipments in order to acquire data including target image, navigation result and reference data to verify and analyse software algorithm. The POD system for CFT we developed is complex system as both mechanical and electronic factors are applied. As we repeatedly performed CFT, useful and various data for weapon development were acquired.

• Journal of the Korea Institute of Military Science and Technology
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• v.27 no.2
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• pp.189-196
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• 2024

Classification of drones and birds is challenging due to diverse flight patterns and limited data availability. Previous research has focused on identifying the flight patterns of unmanned aerial vehicles by emphasizing dynamic features such as speed and heading. However, this approach tends to neglect crucial spatial information, making accurate discrimination of unmanned aerial vehicle characteristics challenging. Furthermore, training methods for situations with imbalanced data among classes have not been proposed by traditional machine learning techniques. In this paper, we propose a data processing method that preserves angle information while maintaining positional details, enabling the deep learning model to better comprehend positional information of drones. Additionally, we introduce a training technique to address the issue of data imbalance.

• Journal of Advanced Navigation Technology
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• v.10 no.2
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• pp.173-180
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• 2006

An airborne radar is an essential aviation electronic system of the aircraft to perform various missions in all weather environments. This paper presents the design, development, and test results of the multi-mode pulsed Doppler radar system test model for helicopter-borne flight test. This radar system consists of 4 LRU units, which include ANTU(Antenna Unit), TRU(Tx Rx Unit), RSDU(Radar Signal & Data Processing Unit) and DISU(Display Unit). The developed technologies include the TACCAR processor, planar array antenna, TWTA transmitter, coherent I/Q detector, digital pulse compression, DSP based Doppler FFT filtering, adaptive CFAR, IMU, and tracking capability. The design performance of the developed radar system is verified through various helicopter-borne field tests including MTD (Moving Target Detector) capability for the Doppler compensation due to the moving platform motion.

• Journal of Advanced Navigation Technology
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• v.19 no.5
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• pp.370-378
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• 2015

The data acquisition unit, signal acquiring and processing equipment, processes and provides major data of an aircraft such as engine system, power train system, hydraulic system, etc. However, it had lots of failure related to the system during production test flight, and it is necessary to fix them perfectly as soon as possible because of the significance of the equipment. In this paper, it contains failure classification and analysis for each defect element to improve whole software as well as electrical circuit. Particularly, utilizing Fault Injection Method based interworking test, more efficient improvement activity was performed for not only equipment level but also aircraft level, and as a result, it is achieved that considerable betterment of Surion quality and flight safety.

• Proceedings of the Korea Information Processing Society Conference
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• 2011.04a
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• pp.641-642
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• 2011

저궤도 위성은 지상과의 접축시간이 극히 제한되어 있어 위성에서 생성된 원격측정 데이터들을 위성의 대용량 메모리에 저장하였다가 지상과의 접촉시간에 저장된 데이터를 지상으로 전송하는 방식으로 운영된다. 위성에 저장할 수 있는 전체 데이터 크기는 대용량 메모리의 크기와 지상과의 통신 가용시간에 따라 제한을 받게 된다. 대용량 메모리 저장용량과 다운링크 버짓을 만족해야 하므로 일반적으로 각 탑재체로부터 수신하여 위성에 저장되는 원격측정 데이터들은 종류별로 일정한 주기를 가지게 되고 그 크기도 고정되어 있다. 그리고 각 데이터 종류별로 저장여부를 지상명령으로 조절할 수 있도록 되어 있다. 그러나 생성되는 데이터가 일정하지 않고 비주기성을 갖는 경우 데이터량을 예측할 수 없으므로 지상명령으로 데이터 저장여부를 제어하는 것은 거의 불가능하다. 이러한 경우에 생성되는 데이터량을 모니터링하면서 데이터를 전송할 수 있는 자동화된 데이터 통신 방식이 요구된다. 본 논문은 저궤도 위성 탑재체에서 비주기적으로 생성되는 데이터를 자동으로 전송받기 위한 데이터 자동 전송기능과 시험 결과에 대해서 기술하였다.