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The importance of avionics systems has increased to a significant level in modern aircraft development. Modern avionics system is a complex integrated system of state-of-art hardware and software technology. Specifying the avionics system architecture is the most important task throughout the avionics system design process. This paper reviews modern avionics system architectures and proposes an effective avionics architecture suitable for modern attack helicopters.

To perform effective integration test of avionics equipments, the importance of a setup for integration test environment has been increasing in recently developed aircraft. Especially, the development of integration test equipment is necessary for minimizing the development period and reliability of integration test. This paper treats the model development for optimal working of integration test after analyzing the characteristics of each MEP equipments for Surion(KUH). Models, whose main role is troubleshooting of equipment and simulation for missing equipments, consists of dynamic, behavior, and ICD models depending on the dynamic characteristics. Software test for both unit level and system level are performed to verify the model reliability. By conducting integration test using SIL, it is confirmed that the developed models are suitable for integration function test of the MEP system.

Integrated data processing for display of flight critical data and mission critical data was conducted without additional display instruments using glass cockpit design. Based on a pre-designed flight critical system and a mission critical system, this paper shows an optimal design of subsystem integration. The design satisfies safety requirements of flight control systems(FCS) and requires minimized modification of pre-designed systems. By conducting integration test using System Integration laboratory(SIL), it is confirmed that the introduced design approach meets the safety requirements of the MEP system.

The paper introduces a set of static and dynamic experiments to more fully characterize a linear permanent magnet (PM) oscillatory machine. The proposed set of tests was performed on a PM brushless linear oscillatory machine with surface PM and PM flux concentration movers, respectively. Though the testing arrangement allows for it, temperature, noise and vibration have not been investigated in this paper.

In order to realize a true WoT environment, a reliable power circuit is required to ensure interconnections among a range of WoT devices. This paper presents research on sensors and their effects on the reliability and response characteristics of power circuits in WoT devices. The presented research can be used in various power circuit applications, such as energy harvesting interfaces, photovoltaic systems, and battery management systems for the WoT devices. As power circuits rely on the feedback from voltage/current sensors, the system performance is likely to be affected by the sensor failure rates, sensor dynamic characteristics, and their interface circuits. This study investigated how the operational availability of the power circuits is affected by the sensor failure rates by performing a quantitative reliability analysis. In the analysis process, this paper also includes the effects of various reconstruction and estimation techniques used in power processing circuits (e.g., energy harvesting circuits and photovoltaic systems). This paper also reports how the transient control performance of power circuits is affected by sensor interface circuits. With the frequency domain stability analysis and circuit simulation, it was verified that the interface circuit dynamics may affect the transient response characteristics of power circuits. The verification results in this paper showed that the reliability and control performance of the power circuits can be affected by the sensor types, fault tolerant approaches against sensor failures, and the response characteristics of the sensor interfaces. The analysis results were also verified by experiments using a power circuit prototype.

The avionic systems of newly developed aircraft platforms are demanded to be a fully integrated avionics system of enhanced functions supporting the operator for successful mission operations. Prior to its installation to the aircraft, the developed avionics system should have to be fully tested in an integrated lab, SIL (system integration laboratory), to validate its successful integration and demonstrate OFP tests as an integrated avionics suite. Actually, system level test conducted at a system integration laboratory is now mostly required for aircraft development programs or for avionics system upgrade programs. This comes up to a need for developing a SIL system of the MEP system which is being developed for the KUH (Korean utility Helicopter). This paper shows the design results of the KUH MEP SIL system. Requirements for the SIL system and SIL design results are shown. For a better understanding, the MEP system of the KUH is also introduced. The design options that were considered during the design process are shown and compared. The requirements, design results and design considerations introduced in this paper will be able to inspire upcoming similar programs including avionics system upgrade for classical aircrafts.