• Journal of the Korean Society for Aviation and Aeronautics
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• v.17 no.3
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• pp.70-77
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• 2009

We proposed the method of avionics integrated architecture using high-speed fiber optic bus. Typically, data bus of aircraft consists of electronic and optic data transmission method. Avionics systems are difficult to operate the electronic data transmission method for the high speed data processing, synchronization and interconnection between flight control system and flight management system efficiently. In this paper, it is known to look into the problem of data bus and the advanced trend in avionics systems, and propose the appropriate data bus of the advanced avionics systems.

• Proceedings of the Korea Information Processing Society Conference
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• 2009.04a
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• pp.688-691
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• 2009

항공기에는 각각의 임무에 맞게 설계된 많은 종류의 임무컴퓨터(Mission Computer)가 존재한다. 여러 센서(Sensor)에서 전송되는 신호를 처리하는 기존의 단일코어 기반 임무컴퓨터는 항공기의 성능 향상에 따른 임무 요구도의 증대와 전장 환경의 변화에 따라 기내 데이터의 양이 급격히 증가하여 정보통신의 실시간성에 한계를 보인다. 본 논문에서는 실시간 운영체제인 VxWorks를 통해서 다중채널 ARINC-429 통신모듈을 실시간으로 제어하는 멀티코어 SBC(Single Board Computer) 테스트베드(Test-Bed)를 제시한다.

• Journal of the Institute of Electronics Engineers of Korea TC
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• v.46 no.2
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• pp.89-96
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• 2009

As increasing the number of digital control devices installed on aircrafts and their transmission speed, various digital data buses have been introduced to provide reliable and high-speed characteristics. These characteristics of avionics data bus are highly related on the fault-tolerant performance which can make minimize jitter and loss during data transfer. In this paper, we concerned about a new traffic shaping scheme for increasing the reliability of Avionics Full Duplex Switched Ethernet (AFDX) systems based on ARINC 664 standard. We note that the conventional AFDX with a single regulator per virtual link system may produce aggregated traffics as the number of virtual links increasing. The aggregated traffic results in large jitters among frames. To remedy for the jitter and loss of data, we propose a dual regulator scheme for the AFDX system. The purpose of the additional regulator is to additionally regulate aggregated traffics from a number of per virtual link regulators. Using NS-2 simulator, we show that the proposed scheme provides a better performance than the single regulator one. It is worthwhile note that the proposed AFDX with Dual Regulator scheme can be employed to not only aircraft networks but other QoS sensitive networks for robot and industrial control systems.

• Journal of Applied Reliability
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• v.14 no.1
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• pp.29-35
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• 2014

To improve the reliability of a weapon system, we perform the activities: setting the target reliability, reliability allocation, and reliability management, etc. Before starting weapon system development, the target reliability of system is set through advanced research and is allocated to its subsystems at the beginning of development. Then we manage the reliability of system and subsystems to meet the target reliability until completion of system development. In this paper, we research representative reliability allocation methods and introduce the suitable reliability allocation method followed by its application to the underwater guided weapon system. The purpose of this research is to review the proposed reliability allocation techniques and find an appropriate method for underwater weapon systems followed by the validation of its application.

• International Journal of Aeronautical and Space Sciences
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• v.18 no.4
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• pp.675-687
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• 2017

In the aerospace industry, we have produced various models according to operational conditions and the environment after development of the base model is completed. Therefore, when design change is necessary, there are modification and updating costs of the circuit whenever environment variables change. For these reasons, recently, in various fields, system designs that can flexibly respond to changing environmental conditions using field programmable gate arrays (FPGAs) are attracting attention, and the rapidly changing aerospace industry also uses FPGAs to organize the system environment. In this paper, we design the controller area network (CAN) intellectual property (IP) protocol used instead of the avionics protocol that includes ARINC-429 and MIL-STD-1553, which are not suitable for small unmanned aerial vehicle (UAV) systems at the register transistor logic (RTL) level, which does not depend on the FPGA vender, and we verify the performance. Consequentially, a Spartan 6 FPGA model-based system on chip (SoC) including an embedded system is constructed by using the designed CAN communications IP and Xilinx Microblaze, and the configured SoC only recorded an average 32% logic element usage rate in the Spartan 6 FPGA model.

• Journal of the Korea Institute of Military Science and Technology
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• v.14 no.2
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• pp.213-221
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• 2011

Avionics system tends to be designed to have the integrated architecture, and it is getting difficult and complex to verify the flight-critical function because of sophisticated structure. In Korean Utility Helicopter, mission computer acts as the MUX Bus Controller to handle the data from both communication, identification, mission/display and survivability equipment inside Mission Equipment Package and aircraft subsystems such as fuel system and electrical system while it is interfacing with Automatic Flight Control System and Full-Authority Digital Engine Control via ARINC-429 bus. The Flight Displays which is classified as flight-critical function in aircraft is implemented on Primary Flight Display after mission computer processes data from AFCS in order to generate graphics. This paper defines the flight-critical function implemented in mission computer for KUH, and presents the static and dynamic test procedures which is performed on System Integration Laboratory along with Playback Recorder prior to flight test.

• Journal of Aerospace System Engineering
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• v.13 no.5
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• pp.57-64
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• 2019

Recently, avionics systems are being developed as integrated modular architecture applying the modular integration design of the functional unit to reduce maintenance costs and increase operating performance. Additionally, a partitioning operating system based on virtualization technology was used to process various mission control functions. In virtualization technology, the CPU processing load distribution is a key consideration. Especially, the uncertainty of the I/O processing time is a risk factor in the design of reliable avionics systems. In this paper, we examine the influence of the I/O processing method by comparing and analyzing the CPU processing load by the I/O processing method through use of case analysis and applying it to the example of spatial-temporal partitioning.

• Journal of the Institute of Electronics Engineers of Korea TC
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• v.44 no.9
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• pp.46-53
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• 2007

The link-fault recovery in the normal Ethernet bridged networks has relied on the Spanning Tree Protocol(STP) or Rapid STP. However, STP can not offer fast error recovery which is needed real-time services such as aircraft. In this paper, we compare automatic protection switching(APS) providing fault-tolerant function in the BcN back bone system with Avionic Full Duplex Switched Ethernet(AFDX) which is recently equipped in the A380 for Airbone Databuses. Also, we propose a link-bypass scheme for improving fault-tolerant performance of the AFDX by connecting switches and bypass fault section when a fault is originated on the link. For comparing and verifying the performance of proposed scheme, we simulated Ethernet, AFDX, APS and proposed AFDX with link-bypass scheme using NS-2. The proposed AFDX with link-bypass scheme can be applied to aircrafts, BcN backbone networks and industrial automatic networks.

• Journal of Applied Reliability
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• v.18 no.3
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• pp.201-207
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• 2018

Purpose: To develop the reliability growth planning for a subsystem of guided weapon system using PM2-Continuous model. Methods: The target MTBF of the subsystem is set by allocating the system target MTBF to the lower level, where ARINC method is applied. Other model parameters such as initial MTBF, management strategy ratio and average fix effectiveness factor are chosen from historical growth parameter estimates. Given the values of model parameters, the reliability growth planning curve using PM2-Continuous model is constructed and the sensitivity analyses are performed for the changes of model parameters. Results: We have developed the reliability growth plan for a subsystem of guided weapon system using PM2-Continuous model. It was found that the smaller the ratio of initial MTBF to target MTBF, the smaller the management strategy ratio, the smaller the average fix effectiveness factor, and the shorter the development test period, the higher reliability growth is required. Conclusion: The result of this study will be used as a basis for establishing the reliability growth plan, the test period setting and the budget appropriation for the similar system entering the system development stage in the future.

• KIISE Transactions on Computing Practices
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• v.21 no.1
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• pp.29-39
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• 2015

When new inertial navigation systems for an unmanned aerial vehicles are being developed and tested, construction of a fault-tolerant system is required because of various types of hazards caused by S/W and H/W faults. In this paper, a new fault-tolerant flight system that can be deployed into one or more FCCs (Flight Control Computers) is introduced, based on a partition scheme wherein each OFP (Operational Flight Program) partition uses an independent CPU and memory slot. The new fault-tolerant navigation system utilizes one or two FCCs, and executes a primary navigation OFP under development and a stable shadow OFP partition on each node. The fault-tolerant navigation system based on a single FCC can be used for UAVs with small payloads. For larger UAVs, an additional FCC with two OFP partitions can be used to provide both H/W and S/W fault-tolerance. The developed fault-tolerant navigation system significantly removes various hazards in testing new navigation S/Ws for UAVs.