Go to the main menu
Skip to content
Go to bottom
REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
> Journal Vol & Issue
Journal of the Korean Society for Aeronautical & Space Sciences
Journal Basic Information
Journal DOI :
The Korean Society for Aeronautical & Space Sciences
Editor in Chief :
Volume & Issues
Volume 43, Issue 12 - Dec 2015
Volume 43, Issue 11 - Nov 2015
Volume 43, Issue 10 - Oct 2015
Volume 43, Issue 9 - Sep 2015
Volume 43, Issue 8 - Aug 2015
Volume 43, Issue 7 - Jul 2015
Volume 43, Issue 6 - Jun 2015
Volume 43, Issue 5 - May 2015
Volume 43, Issue 4 - Apr 2015
Volume 43, Issue 3 - Mar 2015
Volume 43, Issue 2 - Feb 2015
Volume 43, Issue 1 - Jan 2015
Selecting the target year
Aerodynamic Force Measurements and PIV Study for the Twisting Angle of a Swift Wing Model
Bok, Jung Jin ; Chang, Jo Won ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 9, 2015, Pages 765~772
DOI : 10.5139/JKSAS.2015.43.9.765
Aerodynamic force measurements and phase-locked PIV study were carried out to check the bio-mimetic MAV applicability of a swift flight. Two-rotational DOF robotic wing model and blowing-type wind tunnel were employed. The amplitude of twist angle were
deg. and stroke angles were manipulated by simple harmonic function with out-of-phase in regards to the stroke motion. It is acknowledged that the time-varying lift coefficients in accordance with the change of the twist angle did not result in any noticeable differences, just the small decrease and delay. However, the drag exhibited that the small change of the twist angle can produce large thrust. These findings imply why a swift uses small twist angle during flight. The PIV results displayed that the delay of aerodynamic forces is highly associated with the vortical structures around the wing. It is therefore indicated that a process of designing a swift-based Micro Air Vehicle should take the twist angle into consideration, as the essential parameter.
Verification of Structural Integrity for Cylindrical Subsonic Vehicle
Choi, Youn Gyu ; Noh, Kyung-Ho ; Gil, Geun Suk ; Jeon, Jong Geun ; Baek, Joo Hyun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 9, 2015, Pages 773~780
DOI : 10.5139/JKSAS.2015.43.9.773
In this paper, the structural integrity for a cylindrical vehicle in subsonic environments is verified. In order to confirm static structural safety for the cylindrical vehicle in extreme maneuver condition, the structure analysis and full-scale static structure test are carried out. The commercial finite element codes, MSC. Patran/Nastran is used for numerical simulation. The full-scale static structure test equipment consists of the counterbalance system, loading system and data acquisition system. Besides, the dynamic characteristics for the cylindrical vehicle are reviewed by performing an impact hammer test.
Robust Aeroelastic Analysis considering a Structural Uncertainty
Bae, Jae-Sung ; Hwang, Jai-Hyuk ; Ko, Seung-Hee ; Byun, Kwan-Hwa ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 9, 2015, Pages 781~786
DOI : 10.5139/JKSAS.2015.43.9.781
An aeroelastic stability can be degraded due to an aeroelastic modeling error and a structural uncertainty. Therefore it is necessary to predict the aeroelastic stability boundary considering an aeroelastic modeling error and a structural uncertainty. Robust aeroelastic analysis was proposed to predict the aeroelastic stability boundary considering these error and uncertainty. In the present study, the robust aeroelastic modeling and analysis were performed by using the
analysis technique and the aeroelastic model of the control fin with modal approach and MSA. The computer program for the robust aeroelastic analysis was developed and verified by comparing its results with those of conventional aeroelastic analysis methods.
GUI Development for Conceptual Design Tool of Mid-to-Small Earth Observation Satellite
Park, Kiyun ; Kim, Hong-Rae ; Chang, Young-Keun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 9, 2015, Pages 787~798
DOI : 10.5139/JKSAS.2015.43.9.787
The emergence of mid-to-small satellites has created a need for rapid development with a relatively low cost. However, the development of mid-to-small satellites requires considerable time and cost in early phase, in particular, during the development of mission and system requirements through iterations of conceptual design and mission design. In this research, Spacecraft Conceptual Design Tool(SCDT) which is based on Graphical User Interface(GUI) was developed to reduce the time and cost for early phase development. Furthermore, GUI-based software can make the input values to be editable easily and show users design results in various way. In this paper, the development results of MATLAB GUI-based SCDT are introduced.
Dynamic Effects Analysis on a Solar Array Due to Attitude Control Thruster Plume
Chae, Jongwon ; Han, Cho Young ; Jun, Hyoung Yoll ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 9, 2015, Pages 799~804
DOI : 10.5139/JKSAS.2015.43.9.799
The purpose of this study is to analyse the dynamic disturbances(disturbed forces and disturbed torques) due to attitude control thruster's plume impingement on the solar arrays. To produce database of the dynamic disturbances a sweep analysis was done, in which the two parameters are used; the distance between the thruster and solar arrays and the thruster tilt angle. Based on the database, a third order polynomial approximation is computed to represent the characteristics of the disturbed forces and torques. The final results are the coefficients of the approximation for each solar array angle position. These results as input data are used to optimize the configuration of the attitude control thrusters. This analysis is appled to the two candidate solar arrays for Geo-Kompsat-2 satellite and the results of the disturbed forces and disturbed torques are compared and analysed.
A Study of Temperature Transform Algorithm of Distinguished Grids between Thermal and Structural Mesh for Satellite Design
Kim, Min Ki ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 9, 2015, Pages 805~813
DOI : 10.5139/JKSAS.2015.43.9.805
This paper introduces the development of temperature mapping code between thermal mesh and structural mesh in KARI Satellite Design Software. Generally, temperature distribution of a satellite varies with the time by the space environment of the orbit, so thermal expansion of the structure should be analysed in design of the satellite. For the sake of the coupled thermal structural analysis, an interpolation algorithm between two finite element heterogeneous grids has been proposed by which temperature transfer is successively conducted.
Performance and Thermal Design Validation for FM STEP Cube Lab.
Kang, Soo-Jin ; Jung, Hyun-Mo ; Seo, Joung-Ki ; Oh, Hyun-Ung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 9, 2015, Pages 814~821
DOI : 10.5139/JKSAS.2015.43.9.814
The STEP Cube Lab. classified as a pico-class satellite has been successfully developed as a flight model(FM) to be launched in 2015. Its mission objective is to perform the on-orbit verification of fundamental space core-technologies. In this study, a thermal design concept based on the passive method to achieve the mission objective is introduced. The effectiveness of the thermal design and performance of the satellite has been verified through the acceptance level thermal vacuum test. In addition, to improve the reliability of thermal mathematical model, correlation was performed using the results of thermal balance test. This paper describes a series of process for the thermal vacuum test on the STEP Cube Lab. FM.
On the Performance Test of the Piezoelectric-Hydraulic Pump
Joo, Yong-Hwi ; Hwang, Jai-Hyuk ; Yang, Ji-Youn ; Bae, Jae-Sung ; Lee, Jong-Hoon ; Kwon, Jun-Yong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 9, 2015, Pages 822~829
DOI : 10.5139/JKSAS.2015.43.9.822
In this paper, the piezoelectric-hydraulic pump with a piezostack actuator as a driving source has been designed, fabricated, and evaluated for its application to UAV's brake system. The performance requirements of the piezoelectric-hydraulic pump were decided based on the requirements analysis of the target aircraft brake system. The geometric design of the piezoelectric-hydraulic pump to meet the performance requirements of the pump was conducted, and all components of the pump including the spring sheet type check valves were machined with close tolerance. By constructing a test apparatus for the performance check of the piezoelectric-hydraulic pump, the performance characteristics of the pump, such as the outlet flow rate for load-free condition and the outlet oil pressure for closed loop condition, have been evaluated. It has been found by the performance test result that the developed piezoelectric-hydraulic pump satisfies the design requirements effectively.
Laser Tracking Analysis of Space Debris using SOLT System at Mt. Gamak
Lim, Hyung-Chul ; Park, Jong-Uk ; Kim, Dong-Jin ; Seong, Kipyung ; Ka, Neung-Hyun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 9, 2015, Pages 830~837
DOI : 10.5139/JKSAS.2015.43.9.830
Space debris has been a major issue recently for the space-active nations because its growing population is expected to increase the collision risk with operational satellites. Radar and electro-optical system has been used for space debris surveillance, which may cause unnecessary anti-collision manoeuvers due to their low tracking accuracy. So an additional tracking system is required to improve the predicted orbit accuracy and then to jude the anti-collision maneouvers more efficiently. The laser tracking system has been considered as an alternative to decrease these unnecessary manoeuvers. Korea Astronomy and Space Science Institute has been developing a space object laser tracking system which is capable of laser tracking for satellites with retro-reflectors and for space debris using high power laser, and satellite imaging using adaptive optics. In this study, the tracking capability is analyzed for space debris using high power laser based on link budget, false alarm probability and signal detection probability.
Study on Acoustic Attenuation due to Particles and Flow Turning in Rocket Motors
Kim, Taejin ; Sung, Hong-Gye ; Seo, Seonghyeon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 9, 2015, Pages 838~844
DOI : 10.5139/JKSAS.2015.43.9.838
This paper includes summarization and analysis of previous research results on acoustic attenuation due to particles and flow turning in rocket motors among various damping parameters. Particle damping is the most effective mechanism in suppressing high-frequency combustion instabilities occurring in rocket combustion chambers, which is dependent on the size and the mass fraction of particles. Relatively weak attenuation by flow turning compared to particle damping depends on the geometry of propellant and a combustion chamber. Pumping driving effects need to be taken into account when realizing vorticity generation on the propellant surface. However, its driving effects become cancelled out by flow turning loss when the propellant geometry is cylindrical.
Recent Status on Active Space Debris Removal Technologies
Kim, Hae-Dong ; Kim, Min-Ki ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 9, 2015, Pages 845~857
DOI : 10.5139/JKSAS.2015.43.9.845
Recently, deterioration of space environment due to space debris is getting a lot of international attention and advanced countries in space technology are willing to comply with their space debris mitigation guidelines. With these efforts to reduce the number of space debris, active space debris removal technology means to try and to get rid of space debris directly. In this paper, the background and recent status on active space debris removal technologies of overseas agencies are presented. Also, cases of technology development and patents are introduced. Thus, this paper can be usefully referred to by the colleagues who are willing to start the research and development of active space debris removal technologies.