• Communications of the Korean Institute of Information Scientists and Engineers
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• v.30 no.9
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• pp.57-64
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• 2012

• Communications of the Korean Institute of Information Scientists and Engineers
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• v.30 no.9
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• pp.65-70
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• 2012

• The Journal of the Korea Contents Association
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• v.12 no.8
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• pp.77-86
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• 2012

Avionics system are composed of multiple electronic device that performs important missions the number of electronic devices for the performance of aircraft has been gradually increasing. As a result, cost of development, maintenance and operating have increased. To solve this problem, technology paradigm of avionics has been shifting from federated avionics systems that manage to each system independently to IMA(Integrated Modular Avionics) systems. Unlike federated systems, fault tolerance becomes an essential technology in IMA systems. Because each aircraft features integrated in the an IMA system, a fault can jeopardize the entire system. In this paper, we define faults which can occur on the ARINC 653 based IMA system first, and design the ARINC 653 compliant HM(health Monitoring) system for the system can continue to operate be normal when occur a fault.

• Telecommunications review
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• v.24 no.4
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• pp.468-480
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• 2014

The current-generation avionics systems are based on a federated architecture, where an electronic device runs a single software module or application that collaborates with other devices through a network. This architecture makes the internal system architecture very complicate, and gives rise to issues of Size, Weight, and Power (SWaP). In this paper, we show that the partitioning defined by ARINC 653 can efficiently deal with the SWaP issues on small unmanned aerial vehicles, where the SWaP issues are extremely severe. We especially install the integrated mission system on real hexacopter and quadcopter and perform successful flight tests. The presented software technology for integrated mission system and software consolidation methodology can provide a valuable reference for other SWaP sensitive real-time systems.

• Journal of Aerospace System Engineering
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• v.8 no.2
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• pp.21-26
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• 2014

The aircraft manufacturers are constantly driving to reduce manufacturing lead times and cost at the same time as the product complexity increases and technology continues to change. Integrated Modular Avionics (IMA) is a solution that allows the aviation industry to manage their avionics complexity. IMA defines an integrated system architecture that preserves the fault containment and 'separation of concerns' properties of the federated architectures. In software side, the air transport industry has developed ARINC 653 specification as a standardized Real Time Operating System (RTOS) interface definition for IMA. It allows hosting multiple applications of different software levels on the same hardware in the context of IMA architecture. This paper describes a study that provided the avionics software design for separation of fault and backup of core function to reduce workload of pilot with cost efficiency.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.48 no.7
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• pp.547-554
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• 2020

Airborne health management system prevents functional failure caused by errors or faults in the airborne software. On-the-fly repairing atomicity violations (AV) in an ARINC-653 concurrent software is critical for guaranteeing correctness of execution of the software. This paper proposes Repairing-AV which efficiently repairs atomicity violations. The Repairing-AV can diagnose and prevent an error on-the-fly by utilizing the training results of the software and controls access to the shared variable of the thread where the error occurred. The evaluation of the Repairing-AV measures the time overhead by applying the previous work and the Repairing-AV to five synthesis programs containing the atomicity violation. As the result of evaluation, the RepairingAV constantly shows about 1.4x time overhead regardless of count of shared variable access.

• Journal of Aerospace System Engineering
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• v.13 no.5
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• pp.1-8
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• 2019

Recently, avionics has been migrating from a federated architecture to an integrated modular architecture based on a multi-core to reduce the number of systems, weight, power consumption, and platform redundancy. The volume of data which must bo provided to the pilot through the display device has increased, because an integrated single device performs multiple functions. For this reason, the volume of data processed by the graphic processor within a fixed operation period has increased. In this paper, we provide a multi-core-based rendering engine in to perform more graphics processing within a fixed operation period. We assume the proposed method uses a multi-core-based partitioning operating system using the AMP (Asymmetric Multi-Processing) architecture.

• 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.

• 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.

• The Journal of Korean Institute of Communications and Information Sciences
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• v.39C no.11
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• pp.1094-1103
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• 2014

In this paper, we survey the works related to the system architecture of avionics and extract characteristics from the related works. On the basis of the investigation, we propose an integrated modular avionics (IMA) architecture that can be used for current avionic upgrades and future avionic developments based on the IMA Core system. To verify the feasibility of the proposed IMA architecture, we have developed the prototype of the IMA Core system that consists of both the common hardware module and the IMA software. It was verified that the developed prototype with the common hardware module contributes to the improvement of maintainability because it can save the time and expenses for the development and can reduce the number of types of hardware modules when compared with Federated architecture. It was also confirmed that the developed prototype can save not only overall system weight, size, and power consumption but also the number of hardware types because the IMA software can support the integrated processing where the single processing hardware module can process multiple software applications.