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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
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Journal of the Korean Society for Aeronautical & Space Sciences
Journal Basic Information
Journal DOI :
The Korean Society for Aeronautical & Space Sciences
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Volume & Issues
Volume 38, Issue 12 - Dec 2010
Volume 38, Issue 11 - Nov 2010
Volume 38, Issue 10 - Oct 2010
Volume 38, Issue 9 - Sep 2010
Volume 38, Issue 8 - Aug 2010
Volume 38, Issue 7 - Jul 2010
Volume 38, Issue 6 - Jun 2010
Volume 38, Issue 5 - May 2010
Volume 38, Issue 4 - Apr 2010
Volume 38, Issue 3 - Mar 2010
Volume 38, Issue 2 - Feb 2010
Volume 38, Issue 1 - Jan 2010
Selecting the target year
A Prediction Study on the Roll Lock-in Phenomena of Freely Spinning Tailfins
Yang, Young-Rok ; Cho, Tae-Hwan ; Myong, Rho-Shin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 9, 2010, Pages 849~855
DOI : 10.5139/JKSAS.2010.38.9.849
This paper investigated the roll lock-in phenomena of a canard-controlled missile with freely spinning tailfins by applying Falanga`s roll-rate equation. To confirm and validate the accuracy of the results of the roll-rate and roll lock-in prediction for freely spinning tailfins, the results were compared with Blair`s wind tunnel test data. For calculation of the roll-rate of freely spinning tailfins, rolling moment coefficients of the tailfins were obtained from the wind tunnel test data and roll-damping coefficients were calculated by missile DATCOM. The roll-rate and roll lock-in of the freely spinning tailfins were calculated by applying these values to the roll-rate equation for freely spinning tailfins. The calculation results showed good agreement with the wind tunnel test data, and the roll lock-in could be anticipated as well.
Experimental Study on the Static Stability of a Sounding Rocket Model in the Supersonic Wind Tunnel
Lee, Sang-Hyun ; Cho, Hwan-Kee ; Sung, Hong-Gye ; Kim, Jin-Kon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 9, 2010, Pages 856~861
DOI : 10.5139/JKSAS.2010.38.9.856
In this work, experiments on hybrid sounding rocket were conducted to investigate the aerodynamic characteristics and analyze longitudinal static stability. Tests were performed on 1/10 scale models of sounding rocket through Mach number ranging from 1.75 to 2.5 and for angle of attack from
. Aerodynamic forces and moments were measured by means of a 4 component internal balance. With measured forces and moments, static stability characteristics of rocket were calculated. Tests were made for three models with different length to determine the effect of body length. The visualization of shock waves was carried out by Schlieren optical system to observe variations of shock waves with Mach number and angle of attack.
Investigation on Strength Recovery after Repairing Impact Damaged Aircraft Composite Laminate
Kong, Chang-Duk ; Park, Hyun-Bum ; Lee, Kyung-Sun ; Shin, Sang-Jun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 9, 2010, Pages 862~868
DOI : 10.5139/JKSAS.2010.38.9.862
Development of a small scale aircraft has been carried out for the BASA(Bilateral Aviation Safety Agreement) program in Korea. This aircraft adopted all the composite structures for environmental friendly by low fuel consumption due to its lightness behavior. However the composite structure has s disadvantage which is very weak against impact due to foreign object damages. Therefore the aim of this study is focusing on the damage evaluation and repair techniques of the aircraft composite structure. The damages of composite laminates including the carbon/epoxy UD laminate and the carbon/epoxy fabric face sheets-honeycomb core sandwich laminate were simulated by a drop weight type impact test equipment and the damaged specimen were repaired using the external patch repair method after removing damaged area. The compressive strength test and analysis results after repairing the impact damaged specimens were compared with the compressive strength test and analysis results of undamaged specimens and impact damaged specimens. Finally, the strength recovery capability by repairing were investigated.
Design of a Linear Motor using Piezoelectric actuator
Jo, Jae-Uk ; Hwang, Jai-Hyuk ; Kim, Byung-Kyu ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 9, 2010, Pages 869~874
DOI : 10.5139/JKSAS.2010.38.9.869
Recently, a piezo actuator based linear motor has been actively studied because of its higher power density, compactness and quick response. However, the characteristic of small displacement makes the application of a piezo actuator limitative. In order to overcome this limitation, some actuation mechanisms using a piezo actuator are designed by bi-metal composite or more than two piezo actuators. Therefore, it enables to generate large displacement and have high resolution. In the proposed piezo motor, we have designed a bi-directional linear motor that can be operated by only one piezo actuator. In addition, it is activated with low frequency of the applied voltage, since, we utilize first mode shape of structure of motion generator to vibrate. Finally, moving direction can be simply controlled by changing the ratio of input frequency to natural frequency of structure of motion generator.
Satellite Trajectory Correction Maneuver for Lunar Mission based on Three-Body Dynamics
Cho, Dong-Hyun ; Jung, Young-Suk ; Lee, Dong-Hun ; Jung, Bo-Young ; Bang, Hyo-Choong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 9, 2010, Pages 875~881
DOI : 10.5139/JKSAS.2010.38.9.875
During the lunar mission, spacecraft are subject to various unexpected disturbance sources such as third body attraction, solar pressure and operating impulsive maneuver error. Therefore, efficient trajectory correction maneuver (TCM) strategy must be required to follow the designed mission trajectory. In the early days of space exploration, the mission trajectory has been designed by using patched conic approach based on two-body dynamics for the lunar mission. Thus the TCM based on two-body dynamics has been usually adopted. However, with the advanced in computing power, the mission trajectory based on three-body dynamics is attempted recently. Thus, these approaches based on two-body dynamics are essentially different from real environment and large amount of energy for the TCM is required. In this work, we study the trajectory correction maneuver based on three-body dynamics.
Performance Investigation of Semi-Active Control Logic to Minimize a Pointing Performance Degradation of On-Board Payload by Chattering Effects
Oh, Hyun-Ung ; Choi, Young-Jun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 9, 2010, Pages 882~889
DOI : 10.5139/JKSAS.2010.38.9.882
Semi-active vibration control is one of the attractive control methods for space application due to its robustness as passive damping system and much higher damping performance than passive system. However, a chattering induced by the sudden variation of damping force at the time of On-Off switching of semi-active control device degrades pointing performance of the on-board payload. In this paper, to enhance the pointing performance of the on-board payload, we proposed a semi-active vibration isolation with a strategy for attenuating chattering effect. Numerical simulation results using simplified analysis model indicated that the proposed semi-active control strategy produced much better isolation performance than the conventional Bang-Bang control semi-active control laws derived from skyhook and LQ theories.
A Study of Operating Forces on a Partially Admitted Turbine Blade
Cho, Chong-Hyun ; Choi, Hyoung-Jun ; Chung, Dae-Hun ; Im, Yong-Hoon ; Cho, Soo-Yong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 9, 2010, Pages 890~899
DOI : 10.5139/JKSAS.2010.38.9.890
An experimental study has been conducted to analyze the operating forces on a partially admitted turbine blade using a linear cascade apparatus. Axial-type blades were used and the blade chord was 200mm. The rectangular nozzle was applied and its size was
. The experiment was done at
of Reynolds number based on the chord. The rotational force and axial force on the blade were measured at steady state by moving the blade to the rotational direction. The operating forces were measured at three different nozzle install angles of
for off-design performance test. In addition, three different solidities of 1.25, 1.38 and 1.67 were applied. From the results, the maximum rotational force was increased when the solidity was decreased and the nozzle install angle was decreased. The axial force was increased by decreasing the nozzle install angle. The reverse axial force was obtained in the partially admitted region when the nozzle install angle was increased to
Cost-benefit analysis of public investment on aircraft design assurance infrastructure
Yi, Jae-Kyung ; Kim, Myeong-Kyun ; Kim, Yong-Min ; Lee, Tae-Hee ; Kim, Do-Hyeon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 9, 2010, Pages 900~906
DOI : 10.5139/JKSAS.2010.38.9.900
We analyse benefits and costs of investment on the assurance of aircraft design and development of related infrastructure. Although the discounted cash flow from the sales of aircrafts is found to be smaller than the amount of required investment, the net present value considering the effects of export increase, import substitution, and the accident cost reduction is very high. This justifies governmental investment, for the effects are not easily appropriated by private investors.
Development of the External Instrumentation System of a Fighter Aircraft for Flight Test
Yeom, Hyeong-Seop ; Oh, Jong-Hoon ; Sung, Duck-Yong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 9, 2010, Pages 907~913
DOI : 10.5139/JKSAS.2010.38.9.907
In this paper, we have described a development of the external instrumentation system of a fighter aircraft for flight test. The external instrumentation system consists of the instrumentation pod and the image pod. The instrumentation pod measures a flight data(attitude, velocity, altitude, etc) of the fighter aircraft by using GPS/AHRS sensor. The image pod takes high-speed images for the separation trajectory of a smart bomb with 2 high-speed cameras and video signal for it with one general camera. We have verified the performance of the external instrumentation system through the ground test, the environment test and the flight test.
Orbit Analysis for KOMPSAT-2 During LEOP and Mission Lifetime
Kim, Hae-Dong ; Jung, Ok-Chul ; Kim, Eun-Kyou ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 9, 2010, Pages 914~924
DOI : 10.5139/JKSAS.2010.38.9.914
In this paper, results on the orbit analysis for the KOMPSAT-2 satellite using a real orbit data during the LEOP and normal mission lifetime are presented. In particular, the preparation and performance of an orbit operations during the LEOP is emphasized and the effects of space environments (i.e., Solar activity) on orbit evolutions are investigated comparing to those of the KOMPSAT-1 satellite. The summarized results in this paper would be an important reference to improve the stability and effectiveness of satellite operations during the LEOP and normal mission lifetime in case of LEO satellites such as successors of KOMPSAT-2 (i.e., KOMPSAT-3, KOMPSAT-3A, KOMPSAT-5).
Implementation of SpaceWire Link Interface for STSAT-3
Ryu, Sang-Moon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 9, 2010, Pages 925~932
DOI : 10.5139/JKSAS.2010.38.9.925
SpaceWire is a standard for high-speed links and networks between spacecraft components, which was invented for better, cheaper, faster on-board data handling in spacecraft. SpaceWire is being widely used on many space missions by ESA, NASA and JAXA, and is expected to be used in future satellite development programs in Korea. For flexible and efficient application of SpaceWire, it is necessary to secure the related technologies. This paper describes the development, implementation and test of a SpaceWire link interface, which will be incorporated in MMU(Mass Memory Unit) of STSAT-3(Science & Technology Satellite-3).
Development of 0.6Nm Small CMG Hardware and Performance Test
Jang, Woo-Young ; Rhee, Seung-Wu ; Kwon, Hyoek-Jin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 9, 2010, Pages 933~942
DOI : 10.5139/JKSAS.2010.38.9.933
Control Moment Gyro(CMG) is one of the most efficient momentum exchange devices for satellite attitude control and CMG is very essential device for agile satellite. And the studies of CMG development and its application to satellite have been done extensively. In this study, the development process of SGCMG hardware for agile small satellite system, the developed hardware and its performance test results are presented. As a SGCMG test results, it is verified that the developed hardware model can produce torque more than 0.6Nm as is designed. By investigating its test data results, the issues that should be considered for the performance improvement and its application are discussed. The remedies for the identified issues are proposed for future study.
A Study on Partial Admission Characteristics of a Multi-Stage Small-Scaled Turbine
Cho, Chong-Hyun ; Jeong, Woo-Chun ; Kim, Chae-Sil ; Cho, Soo-Yong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 9, 2010, Pages 943~954
DOI : 10.5139/JKSAS.2010.38.9.943
In this study, a radial inflow type turbine was applied and the outer diameter of the turbine rotor was 108 mm. The turbine blade on a circular plate disc was designed as an axial-type because its partial admission rate was 1.4-4.1%. The turbine consisted of three stages. The performance test has been conducted with various admission rates, tip clearances and nozzle flow angles. The turbine output power was measured on each stage. The turbine performance was obtained in a wide rotational speed range in order to compare its performance according to various operating conditions. The net specific output torque was also measured to compare its overall performance. Computational analysis was conducted for predicting turbine performance. The computed results were in good agreement with the experimental results.