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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 41, Issue 12 - Dec 2013
Volume 41, Issue 11 - Nov 2013
Volume 41, Issue 10 - Oct 2013
Volume 41, Issue 9 - Sep 2013
Volume 41, Issue 8 - Aug 2013
Volume 41, Issue 7 - Jul 2013
Volume 41, Issue 6 - Jun 2013
Volume 41, Issue 5 - May 2013
Volume 41, Issue 4 - Apr 2013
Volume 41, Issue 3 - Mar 2013
Volume 41, Issue 2 - Feb 2013
Volume 41, Issue 1 - Jan 2013
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Numerical Analysis for Internal Leakage Flow Characteristics of Damped Bypass Valve
Lee, Seawook ; Kim, Daehyun ; Kim, Sangbeom ; Park, Sangjoon ; Cho, Jinsoo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 2, 2013, Pages 85~90
DOI : 10.5139/JKSAS.2013.41.2.85
A numerical analysis for the internal flow was carried out in order to analyze the leakage flow characteristics inside the damped bypass valve. This research has found that the valve characteristics became stable at above a specific temperature. Very small amount of leakage flow was occurred. But there was no effect in temperature. The more temperature fell, the more maximum pressure rate was increased.
Extended Unmixing-Mixing Scheme for Prediction of 3D Behavior of Porous Composites
Choi, Hoi Kil ; Shin, Eui Sup ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 2, 2013, Pages 91~97
DOI : 10.5139/JKSAS.2013.41.2.91
Pyrolysis and surface recession of charring composites are progressed primarily in the thickness direction. The unmixing-mixing scheme is applied to describe the in-plane and through-thickness behaviors of porous composites. The extended unmixing-mixing equations are based on transverse isotropy of unidirectionally fiber-reinforced composites. The strain components of gas pressure in pores, thermal expansion, and chemical shrinkage are included in the constitutive model. By analyzing micromechanical representative volume elements of porous composites, the validity of the derived equations are examined.
Fault Tolerant Control Using Sliding Mode Control with Adaptation Laws for a Satellite
Shin, Miri ; Kang, Chul Woo ; Park, Chan Gook ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 2, 2013, Pages 98~106
DOI : 10.5139/JKSAS.2013.41.2.98
This paper proposes fault tolerant control laws using sliding mode control and adaptation laws for a satellite with reaction wheel faults. Considering system parameter errors and faults uncertainties in the dynamics of satellite, the control laws were designed. It was assumed that only reaction wheel failures occurred as faults. The reaction wheel faults were reflected in the multiply form. Because the proposed control laws satisfy the Lyapunov stability theorem, the stability is guaranteed. Through computer simulation, it was assured that the proposed adaptive sliding mode controller has a better performance than the existing sliding mode controller under unstable angular rates.
A Study on High Agile Satellite Maneuver using Reaction Wheels and CMGs
Son, Jun-Won ; Rhee, Seung-Wu ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 2, 2013, Pages 107~119
DOI : 10.5139/JKSAS.2013.41.2.107
We study three axis attitude control method including two axis high agile maneuver using four reaction wheels and two control moment gyros. We investigate singularity conditions due to two control moment gyros and propose singularity escape method. Based on this, we propose actuator control algorithm for high agile maneuver. Also, we propose actuator momentum management method which preserves momentum of reaction wheels and control moment gyroscopes before and after satellite attitude control. Through numerical simulation, we show that our method achieves three axis attitude control including two axis high agile maneuver and preserves actuators' momentum.
Experimental Study on Laser-driven Miniflyer for Description of Space Debris with High-speed
Baek, Won-Kye ; Yoh, Jai-Ick ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 2, 2013, Pages 120~126
DOI : 10.5139/JKSAS.2013.41.2.120
Increasing numbers of space debris around the earth now pose a major threat to satellites as their impact velocity may reach up to several km/s. We use a pulse laser to accelerate a miniflyer for mimicking the space debris. The multi-layer coat on the confined medium is known to promote a higher acceleration. However, it requires some special techniques which take somewhat long time and cost to coat. Instead, we devised a simple concept to coat by the black lacquer paint on a flyer. It shows improvement in the flyer velocity by 1.5-2 times the uncoated, and the resulting velocity reached 1.42km/s with Nd:YAG laser energy under 1.4 joules. The resulting velocity is suitable for satellite vulnerability test for debris impact in the geostationary orbit.
A Study on Manufacture of Integrated Composite Wing with High Aspect Ratio
Joo, Young-Sik ; Jun, Oo-Chul ; Byun, Kwan-Hwa ; Cho, Chang-Min ; Han, Jin-Wook ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 2, 2013, Pages 127~133
DOI : 10.5139/JKSAS.2013.41.2.127
In this paper, the study for the manufacture of the integrated composite wing is performed. The wing has a pivoting structure and high aspect ratio to increase lift drag ratio. The wing is designed with carbon fiber composite because the wing needs to be light and have sufficient strength and stiffness to satisfy structural design requirements. The number of structural members is decreased by part integration to reduce manufacturing cost and the wing is manufactured with the integrated molding process by an autoclave. The material properties are identified by the coupon tests and the structural strength and stiffness are verified through the component tests.
The Implementation of Tightly coupled SDINS/GPS System based on the Ring Laser Gyro
Yu, Haesung ; Park, Sang Eun ; Jeong, Jinseob ; Park, Heung-Won ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 2, 2013, Pages 134~141
DOI : 10.5139/JKSAS.2013.41.2.134
This paper explores a real-time system implementation to couple tightly StrapDown Inertial Navigation System(SDINS) and Global Positioning System(GPS) mounted on the aircraft. When implementing the SDINS/GPS coupled system in real-time processor, we have to deliberate SDINS's unique characteristics based on the ring laser gyro, and besides, lever-arm, measurements, and error compensation method. The novel modeling method is applied to system the misalignment error term of gyro to estimate the cumulative heading attitude errors while the aircraft banking to turn repeatedly. Captive Flight Test results show that the proposed modeling strategy has good performance.
Development of the High-Accuracy Multi-Component Balance for Fluidic Thrust Vectoring Nozzle of UAV
Song, Myung-Jun ; Chang, Hong-Been ; Cho, Yong-Ho ; Lee, Yeol ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 2, 2013, Pages 142~149
DOI : 10.5139/JKSAS.2013.41.2.142
The thrust vector control technique is essential for high maneuverability of unmanned aerial vehicles. In the present study, a multi-component balance was developed to quantitatively evaluate the thrust-vectoring performance of a supersonic rectangular nozzle based on the Coanda coflowing effect. Precise calibration and detailed data analysis were performed during the development. It was found that the cross-talk errors between load cells in the balance were less than 5%, and that the unwanted errors due to high-pressure supply tubes were almost negligible, which contributed to the high accuracy of the present balance design. Some preliminary test results of the thrust-vectoring performance of the present nozzle design were also obtained and analyzed.
The compatible non-explosive separation device for various pre-loads using the Ni-Cr wire and Kevlar rope
Hwang, Hyun-Su ; Kim, Byung-Kyu ; Jang, Young-Keun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 2, 2013, Pages 150~155
DOI : 10.5139/JKSAS.2013.41.2.150
We present a kevlar rope based Non-Explosive Actuator(NEA) device which has simple structure and is activated by burning Ni-Cr wire. Through performance test, we find it can be operated under various pre-load by simply changing turn number of Ni-Cr wire. It shows release time of 680ms and shock level of 110G under pre-load of 6.0kN. Launching environment and space environment tests are planned to verify performance of the NEA based on European Satellite Agency test manual. Conclusively, we expect the proposed NEA can be applicable to release solar panel and fairing separation.
An Analysis of three-dimensional collision probability according to approaching objects to the KOMPSAT series
Seong, Jae-Dong ; Kim, Hae-Dong ; Lim, Seong-Min ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 2, 2013, Pages 156~163
DOI : 10.5139/JKSAS.2013.41.2.156
Collision probability is the most common method to measure the risk of space debris, it is widely used that two dimensional linear collision probability using the closest approach distance. This paper represents the characteristics of object that approach KOMPSAT 2, 3, 5 that have operated or will be operated by Korea. And more precise method than two dimensional linear collision probability, we analyzed the properties of three dimensional nonlinear collision probability using STK/Nonlinear Collision Probability Tool. Through this, efficiency of three dimensional nonlinear collision probability for KOMPSAT series satellites was investigated. The result represents that three dimensional nonlinear collision probability showed the precise outcome at a relative velocity of less than 350m/s. Also, KOMPSAT series satellites appeared to few low relative velocity approaches and showed low efficiency for the three dimensional nonlinear collision probability.
An Analysis of CSM orbit for Conjunction Assessment of Space Debris
Choi, Su-Jin ; Kim, Hae-Dong ; Jung, Ok-Chul ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 2, 2013, Pages 164~171
DOI : 10.5139/JKSAS.2013.41.2.164
Since plenty of spacecrafts were launched in space after 1957, the number of space debris has been increased. According to the JSpOC, the number of space debris which diameter is bigger than 10 cm are more than 22,000. Recently there were two critical events. Which one is that China shot down their satellite using missile and the other is that two satellite, Iridium and Cosmos 2251, collied. Space environment in low-earth orbit has been severe. JSpOC analyzes the collision risk between 15,000 space debris and all operation satellites and then they send CSM to the satellite operator to utilize its orbital information if collision risk might be occurred. This paper analyzes the CSM orbit data by comparing with KOMPSAT-2 precise orbit data and shows conjunction assessment results.