• Journal of Astronomy and Space Sciences
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• v.27 no.4
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• pp.407-412
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• 2010

Software reusability is one of key factors which impacts cost and schedule on a software development project. It is very crucial also in satellite simulator development since there are many commercial simulator models related to satellite and dynamics. If these models can be used in another simulator platform, great deal of confidence and cost/schedule reduction would be achieved. Simulation model portability (SMP) is maintained by European Space Agency and many models compatible with SMP/simulation model interface (SMI) are available. Korea Aerospace Research Institute (KARI) is developing hardware abstraction layer (HAL) supported satellite simulator to verify on-board software of satellite. From above reasons, KARI wants to port these SMI compatible models to the HAL supported satellite simulator. To port these SMI compatible models to the HAL supported satellite simulator, simulation scheduler is preliminary designed according to the SMI standard.

• Journal of Korea Society of Digital Industry and Information Management
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• v.5 no.4
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• pp.263-272
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• 2009

Nowadays, lots of software that have similar functions is being produced. Hence it is getting more important to select the best and suitable software for each individual or company. Moreover, there are few trustworthy materials regarding to the objective procedure and criteria for the best evaluation of the software quality. To overcome these problems, benchmarking has been carried out. However, benchmarking is also confronting the limit of quality evaluation verification due to the difficult of the objectification of the major test items. To solve these problems, some others try to evaluate the quality of software using objective criteria of evaluation based on ISO/IEC standards. Nevertheless, this method using these defined evaluation items and criteria may result in not very reliable outcome. Therefore, this paper offers the evaluation items reflected in the characteristics of each software in order to prove the validity of the proposed method. Moreover, the objective and quantitative criterion which analyzes and reflects the organization characteristics using AHP methodology is applied to the experiment and performance evaluation. Hence we expect that the proposed method provides the needs of the re-establishment of software quality evaluation criteria and the improvement of process in terms of management.

• The Journal of the Korea Contents Association
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• v.17 no.6
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• pp.1-8
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• 2017

A smart leveling equipment was developed in this study by improving present leveling equipment. Both hardware and software of the equipment was developed and several accuracy tests of bench mark were conducted using various survey equipments. National control point (UO992-A), control points (15-00-06-24)-B and (15-00-06-23)-C were used for the accuracy test. As a result, the stable results in the range of errors were obtained in the cases of auto-level and digital level. Approximately 24mm error in the section of A-B and 26mm of B-C section was occurred in Smart Level equipment. This is due to the lack of technology completion and errors via relatively many numbers of installation tests. 46mm error of RMSE of smart level survey was occurred through the difference of section test. A small error was detected in short range but errors were accumulated far from the bench mark. It's concluded that an in-depth study emphasizing accuracy improvement can be practically applied to the various areas of industry.

• Transactions of the Korean Society of Automotive Engineers
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• v.17 no.5
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• pp.127-132
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• 2009

The transient performance of the passenger diesel engine equipped with the variable geometry turbocharger was simulated using HIL(hardware-in-the-loop) system. The system consists of engine model as software, and the turbocharger test bench as hardware. The engine model is mean value model which is programmed by the Simulink of the Mathworks. The turbocharger test bench is composed of a blower, some sensors, and DAQ boards. A real time simulation is possible since the operating system based on the real time is included. The results show the good response for the transient characteristics. Therefore this HIL system can be used for development of the new turbocharger effectively.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.16 no.2
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• pp.1-11
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• 2008

Increasing demand for improved reliability and survivability of mission-critical systems is driving the development of health monitoring and Automated Contingency Management (ACM) systems. An ACM system is expected to adapt autonomously to fault conditions with the goal of still achieving mission objectives by allowing some degradation in system performance within permissible limits. ACM performance depends on supporting technologies like sensors and anomaly detection, diagnostic/prognostic and reasoning algorithms. This paper presents the development of a generic prototype test bench software framework for developing and validating ACM systems for advanced propulsion systems called the Propulsion ACM (PACM) Test Bench. The architecture has been implemented for a Monopropellant Propulsion System (MPS) to demonstrate the validity of the approach. A Simulink model of the MPS has been developed along with a fault injection module. It has been shown that the ACM system is capable of mitigating the failures by searching for an optimal strategy. Furthermore, the concepts of Validation and Verification (V&V) of such systems are introduced with relevant examples.

• Smart Structures and Systems
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• v.11 no.2
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• pp.135-161
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• 2013

This work presents a test platform for the assessment and benchmarking of modern actuators which have been specifically developed for the new field and service robotics applications. This versatile platform has been designed for the comparative analysis of actuators of dissimilar technology and operating conditions. It combines a modular design to adapt to linear and rotational actuators of different sizes, shapes and functions, as well as those with different load capacities, power and displacement. This test platform emulates the kinematics of robotic joints while an adaptive antagonist-load actuator allows reproducing the variable dynamic loads that actuators used in real robotics applications will be subjected to. A data acquisition system is used for monitoring and analyzing test actuator performance. The test platform combines hardware and software in the loop to allow actuator performance characterization. The use of the proposed test platform is demonstrated through the characterization and benchmarking of three controllable impedance actuators recently being incorporated into modern robotics.

• Journal of information and communication convergence engineering
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• v.11 no.2
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• pp.112-117
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• 2013

In order to reuse a register transfer level (RTL)-based IP block, it takes another architectural exploration in which the RTL will be put, and it also takes virtual platforms to develop the driver and applications software. Due to the increasing demands of new technology, the hardware and software complexity of organizing embedded systems is growing rapidly. Accordingly, the traditional design methodology cannot stand up forever to designing complex devices. In this paper, I introduce an electronic system level (ESL)-based approach to designing complex hardware with a derivative of SystemVerilog. I adopted the concept of reuse with higher levels of abstraction of the ESL language than traditional HDLs to design multiplication server farms. Using the concept of ESL, I successfully implemented server farms as well as a test bench in one simulation environment. It would have cost a number of Verilog/C simulations if I had followed the traditional way, which would have required much more time and effort.

• Proceedings of the Korean Society For Composite Materials Conference
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• 2003.04a
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• pp.57-60
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• 2003

This Paper contains the development procedure of Mach small-scaled composite rotor blade for helicopter articulated rotor system. This mach small-scaled composite blade design is conducted by using CORDAS program developed by KARI. The Dynamic analysis for an articulated rotor system with this blade is conducted by using FLIGHTLAB which is commercial software for helicopter analysis. Also the optimizing procedure of iterative design was described. The designed composite blades were manufactured after establishing the effective curing method. For small-scaled rotor test, strain gauges were embedded in composite blade spar to obtain bending & torsion strain value. To verify sectional properties of a blade, the bench test is accomplished. After comparing a designed data and tested data, Dynamic Calculation was repeated using tested data. Through this research, experiences of mach small-scaled composite blade development were accumulated and will be applied to the related research field.

• Transactions of the Korean Society of Automotive Engineers
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• v.11 no.4
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• pp.204-210
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• 2003

A PC-based analysis and design system of exhaust muffler is described. It makes use of software packages such as Sysnoise and STAR-CD to calculate transmission loss(TL) and back pressure. The system is applied to redesign a main muffler of passenger car to improve its performance. The effects of design parameters on acoustic and pressure loss characteristics are examined. Taguchi method Is used to determine optimal combination of parameters which affects muffler performances such as TL and back pressure. Three models are chosen and compared in laboratory bench test and engine dynamometer test to prove their performances.

• International Journal of Aeronautical and Space Sciences
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• v.17 no.3
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• pp.442-453
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• 2016

A significant source of vibration in helicopters is the main rotor system, and it is a technical challenge to reduce the vibration in order to ensure the comfort of crew and passengers. Several types of passive devices have been applied to conventional helicopters in order to reduce the vibration. In recent years, helicopter manufacturers have increasingly adopted active vibration control systems (AVCSs) due to their superior performance with lower weight compared with passive devices. AVCSs can also maintain their performance over aircraft configuration and flight condition changes. As part of the development of AVCS software for light civil helicopter (LCH) applications, a test bench is constructed and vibration control tests and simulations are performed in this study. The test bench, which represents the airframe, is excited using a pair of counter rotating force generators (CRFGs) and a multiple input single output (MISO) AVCS that consists of three accelerometer sensors and a pair of CRFGs; a filtered-x least mean square (LMS) algorithm is applied for the vibration reduction. First, the vibration control tests are performed with uniform sensor weights; then, the change in the control performance according to changes in the sensor weight is investigated and compared with the simulation results. It is found that the vibration control performance can be tuned through adjusting the weights of the three sensors, even if only one actuator is used.