• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.8
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• pp.101-108
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• 2004

The thermomechanical tensile characteristics were evaluated for A12024-T3 under heating rates from $1^{\circ}C/sec\;to\;30^{\circ}C/sec$ by using an infrared heating equipment to simulate aerodynamic heating. The rapid heating test results were compared with tensile test results after 1/2 hour exposure in terms of yield stress to investigate the influence of heating condition. A heating rate-yield temperature parameter was suggested for rapid heating based on time-temperature parameters, and master yield stress curve was obtained by using these parameter. These test results can be used for margin of safety of supersonic vehicle structures subjected to aerodynamic heating.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.5
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• pp.87-92
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• 2005

This paper presents a design concept of smart UAV console system and the analysis of its dynamic response to shock and vibration. The console system design is determined by two main elements; the shape design and the mechanical design. The shape design refers to the human engineering aspects according to the military standards for ship borne equipment. The goal of the mechanical design is to provide the required shock and vibration endurance. The endurance of the system is numerically verified by means of Finite Element Method. The results of verification show that six resilient mounts installed on the console allow to sufficiently decrease the influence of the input impact wave on endurance of the system.

• International Journal of Aeronautical and Space Sciences
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• v.1 no.1
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• pp.1-12
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• 2000

The wake geometries of a two-bladed rotor in axial flights using a time-marching free-wake method without a non-physical model of the far wake are calculated. The computed free-wake geometries of AH-1G model rotor in climb flight are compared with the experimental visualization results. The time-marching free-wake method can predict the behavior of the tip vortex and the wake roil-up phenomena with remarkable agreements. Tip vortices shed from the two-bladed rotor can interact with each other significantly. The interaction consists of a turn of the tip vortex from one blade rolling around the tip vortex from the other. Wake expansion of wake geometries in radial direction after the contraction is a result of adjacent tip vortices begging to pair together and spiral about each other. Detailed numerical results show regular pairing phenomenon in the climb flights, the hover at high angle of attack and slow descent flight too. On the contrary, unstable motions of wake are observed numerically in the hover at low angle of attack and fast descent flight. It is because of the inherent wake instability and blade-vortex-interaction rather then the effect of recirculation due to the experimental equipment.

• International Journal of Aeronautical and Space Sciences
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• v.15 no.2
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• pp.173-182
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• 2014

The structured singular value (${\mu}$) analysis based method has many advantages for the robust stability analysis of missiles with uncertain parameters. Nevertheless, the present linear fractional transformation (LFT) modeling process, which is the basis of ${\mu}$ analysis, is complex, and not suitable for automatic implementation; on the other hand, ${\mu}$ analysis requires a large amount of computation, which is a burden for large-scale application. A constructive procedure, which is computationally more efficient, and which may lead to a lower order realization than existing algorithms, is proposed for LFT modeling. To reduce the calculation burden, an analysis method is developed, based on skew ${\mu}$. On this basis, calculation of the supremum of ${\mu}$ over a fixed frequency range converts into a single skew ${\mu}$ value calculation. Two algorithms are given, to calculate the upper and lower bounds of skew ${\mu}$, respectively. The validity of the proposed method is verified through robust stability analysis of a missile with real uncertain parameters.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.12
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• pp.1045-1050
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• 2014

A Head-Up-Display is an avionic equipment to identify targets and flight data at same time the pilot looks over the external environment outside canopy. The HUD displays various symbols to depend on avionic mode which is composed of navigation mode, air-to-air mode, air-to-ground mode. In air-to-air mode, HUD should provide the intuitive symbols for pilot to aim the target exactly in a short time. In this paper, we propose a design method to improve the visibility of the HUD Symbols.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.10
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• pp.813-819
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• 2013

The authors have developed a test system for a hemispherical resonator gyroscope by using NI FPGA equipment. We have verified its suitability for the research of resonator gyroscopes through several tests: deriving resonance, controlling amplitudes, and estimating resonator parameters. The authors have adjusted a vibrating pattern to be aligned with the driving axis (or electromagnets). This pattern alignment is a basic and important operation of the FTR mode, which is one of operating modes for resonant gyroscopes.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.5
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• pp.56-61
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• 2002

Experimental flutter test for a flat plate wing is performed and the flutter analysis methods are verified by comparing with the experimental results. Wing model and experimental equipment are established in the subsonic wind-tunnel. From the response of the wing, the flutter speed is estimated by using the system identification technique. MSC/NASTRAN, V-g method and root-locus method are used for the flutter analysis of the wing. The computed flutter speed is compared with the estimated one from the experiment, and they show good agreement. Wing model in the present study can be used as a benchmark model for the flutter analysis.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.3
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• pp.95-100
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• 2003

Electronic equipment used in satellites are demanding extremely high reliability, so they should be designed to have immunity for some critical faults by using redundancy component. Generally, Communication satellites are assigned to meet the 15 years mission lifetime, of the analysis about faults must be performed to electronic equipments of satellite. This paper is a summary of the fault tolerance design research of command processor, the improvement of reliability and trade-off study of fault tolerance design result. The reliability prediction value of the satellite component used in this research was taken from Koreasat 3 and Kompsat 1. It is important to perform many trade-off studies for fault tolerance design, especially to choose the most proper fault tolerance method for the specified fault scenario.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.9
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• pp.773-778
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• 2014

Aircraft communication system which provides internal communications between pilots in an aircraft and external communications between pilots and operators in ground tower with them. It is very important equipment in terms of mission and safety. It wouldn't meet performance requirements with only functions of transmission and receiving of signals. It should provide highly clear voice quality without any noise. This paper analyzes the cause of noise during internal communications and summarizes the design changes applying single point ground concept to solve the problem. It also describes the results of fight test to verify the design changes.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.4
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• pp.378-384
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• 2011

During the flight test of KSLV-I, various sensors are installed in the launch pad and the flame deflector to measure the flame characteristics and their influences on the launch complex when a launch vehicle lifts off. Parameter Measurement System is responsible for acquiring the above flight test data. The measurement methodology such as the configuration of measurement system, sensor locations and data acquisition procedures are presented. And this paper compares and explains the characteristics of data sets measured during two flight tests.