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 40, Issue 12 - Dec 2012
Volume 40, Issue 11 - Nov 2012
Volume 40, Issue 10 - Oct 2012
Volume 40, Issue 9 - Sep 2012
Volume 40, Issue 8 - Aug 2012
Volume 40, Issue 7 - Jul 2012
Volume 40, Issue 6 - Jun 2012
Volume 40, Issue 5 - May 2012
Volume 40, Issue 4 - Apr 2012
Volume 40, Issue 3 - Mar 2012
Volume 40, Issue 2 - Feb 2012
Volume 40, Issue 1 - Jan 2012
Selecting the target year
Investigation of the Radiative Heating from Aircraft Plume with Particles
Go, Gun-Yung ; Yi, Kyung-Joo ; Lee, Sung-Nam ; Kim, Won-Cheol ; Baek, Seung-Wook ; Kim, Man-Young ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 9, 2012, Pages 737~744
DOI : 10.5139/JKSAS.2012.40.9.737
The finite volume method for radiation is applied for the analysis of radiative base heating by SE and PE of the aircraft exhaust plume. The exhaust plume is considered as an absorbing, emitting, and scattering medium, while the base plane is assumed to be cold and black. The radiative properties of non-gray gases are obtained through the WSGGM, and the particle is modelled as spheres. The present method is validated by comparing the results with those of the backward Monte-Carlo method and then the radiative base heating characteristics are analyzed by changing such various parameters as particle concentration, temperature, and scattering phase function. The results show that the radiative heat flux coming into the base plane decreases with altitude and distance, but it increases as the particle temperature increases. The forward scattering of particles increases PE while it decreases SE.
LES for Turbulent Duct Flow with Surface Mass Injection and Vortex Shedding
Mon, Khin Oo ; Koo, Hee-Seok ; Lee, Chang-Jin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 9, 2012, Pages 745~751
DOI : 10.5139/JKSAS.2012.40.9.745
Hybrid rocket shows interesting characteristics of complicated mixing layers developed by interactions between turbulent oxidizer flow and mass flow from surface due to fuel vaporization. In this study, compressible LES with a ring structure attached at the entrance of the combustor are performed. According to one recent report, adding a ring structure in the middle of the combustor helps increasing regression rate. From the numerical results, it is seen that vortex structures near the wall becomes stronger due to the interaction with surface mass injection, and the local heat flux increases due to the vortices. This phenomenon is obviously related to the generation of dimple structures which are seen in the number of experiments. Also, the ring structure at the entrance induces strong vortex flow which enhances heat transfer to the wall surface and mixing between fuel and oxidizer as well as reaction efficiency.
Mission-based Operational Orbit Design for Sun-synchronous Spacecraft
Lee, Ji-Marn ; No, Tae-Soo ; Jung, Ok-Chul ; Chung, Dae-Won ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 9, 2012, Pages 752~759
DOI : 10.5139/JKSAS.2012.40.9.752
This paper presents a mission orbit design method for spacecraft which use the sun-synchronous and ground repeat orbits. In this work, we have proposed a new design procedure, "Nonlinear simulation-based numerical optimization technique" using the commercial S/W's such as STK (Satellite Tool kit) and Matlab, which are widely adopted S/W's in the area of orbital mechanics and engineering analysis. Inclusion of all the perturbation effects on the spacecraft not only can more precisely satisfy the mission requirements for sun-synchronicity and repeated ground track, and also operational requirements such as minimum change in the S/C local time, maximization of the contact time with a specified ground station, etc. can be appropriately considered. Design examples for LEO sun-synchronous mission are presented to demonstrate the usefulness of the proposed method in this paper.
Statistical Test for Performance Evaluation of Code Carrier Divergence Detection at a GBAS Reference Station
Yun, Young-Sun ; Kim, Joo-Kyoung ; Cho, Jeong-Ho ; Heo, Moon-Beom ; Nam, Gi-Wook ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 9, 2012, Pages 760~770
DOI : 10.5139/JKSAS.2012.40.9.760
In order to provide precision approach service based on GBAS, air navigation service providers should validate the GBAS system performance against international standard requirements and receive approval. The GBAS manufacturer should define integrity threat, analyze the integrity monitors and evaluate performance of the implemented monitors to verify integrity performance which is critical to the aircraft safety. This paper describes a statistical test result to evaluate performance of the code carrier divergence monitors implemented in KARI Integrity Monitor System software. The paper introduces analysis and test procedure which is developed for the performance evaluation and describes the analysis, the test scenario generation and the test results. The results show that the implemented monitors can detect the expected minimum detectable errors with satisfying the probability of missed detection requirements.
Dynamic Behavior Responses and Investigation of a Small-Class Satellite Having Sandwich Panel Structures
Cho, Hee-Keun ; Lee, Sang-Hyun ; Cha, Won-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 9, 2012, Pages 771~780
DOI : 10.5139/JKSAS.2012.40.9.771
Naro-science satellite which will be launched by KSLV-1 has been successfully developed. Naro-science satellite is a 100kg-class small size science satellite whose structure is composed of one of a typical light and high strength aluminum honeycomb sandwich panel. In this research, dynamic responses of the satellite with respect to the design requirements were investigated by means of real experiments and numerical finite element analyses. The core technologies of the structure design and analysis about fracture and safety has been obtained through a wide range of analyses and tests. The results obtained in this study can be significantly utilized for the next generation satellite development.
Flow Analysis of the Oxidizer Manifold for a Liquid Rocket Combustor using OpenFOAM
Joh, Mi-Ok ; Han, Sang-Hoon ; Kim, Seong-Ku ; Choi, Hwan-Seok ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 9, 2012, Pages 781~788
DOI : 10.5139/JKSAS.2012.40.9.781
Flow in the oxidizer manifold of a liquid rocket combustor has been analysed using an open source CFD toolbox, OpenFOAM. The applicability of OpenFOAM to the problems with complex geometries involving porous media zones for simulating the pressure drop induced by the injectors has been evaluated by performing turbulent, incompressible steady-state flow analysis. The usefulness and applicable area of the OpenFOAM as a design evaluation and analysis tool will be confirmed and enlarged by further evaluation with various computational cases representing major physical phenomena in rocket combustion devices.
Preliminary Sizing of a High Temperature Superconducting Motor for the Application to Electrically Propelled Aircraft
Shin, Kyo-Sic ; Hwang, Ho-Yon ; Ahn, Jon ; Nam, Tae-Woo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 9, 2012, Pages 789~799
DOI : 10.5139/JKSAS.2012.40.9.789
In this research, a high temperature superconducting(HTS) motor is designed which is adequate for an electrical aircraft by generating high power density and the potentiality of its application to an aircraft is studied. The designed motor is based on YBCO plates, HTS coils composed of Bi-2223, and ironless air cooled resistive armature. The HTS motor is designed to generate power equivalent to O-360 engine with 180HP at 2700RPM which is used for Cessna and equivalent to CFM56 engine with 18000HP at 5000RPM which is used for B-737. Also, power densities of HTS motors are compared with power densities of aircraft engines so that we can estimate the potentiality of the HTS motor as an aircraft engine.
Development of Integrated Ground Support System for Integrated Flight Test of Small UAVs
Jeong, Jae-Hyeon ; Lim, Byoung-Do ; Kim, Sung-Su ; Ryoo, Chang-Kyung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 9, 2012, Pages 800~806
DOI : 10.5139/JKSAS.2012.40.9.800
This paper proposes design and development of the Integrated Ground Support System (IGSS) for the flight test of the Unmanned Aerial Vehicle (UAV), which combines ground support and ground control. The integrated flight test of the UAV is a necessary procedure to validate the functionality of the Unmanned Aerial System (UAS). In order to execute cost-effective and systematic flight tests, the IGSS is regarded as an inevitable infrastructure of UAS for small laboratories. The proposed IGSS has functions of ground control, radio communication, power generation, transportation and the maintenance of the UAV.
Attitude Scenarios of Star Observation for Image Validation of Remote Sensing Satellite
Yu, Ji-Woong ; Park, Sang-Young ; Lee, Dong-Han ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 9, 2012, Pages 807~817
DOI : 10.5139/JKSAS.2012.40.9.807
An optical payload needs to be validated its image performance after launched into orbit. The image performance was validated by observing star because ground site contains uncertainties caused by atmosphere, time of the year, and weather. Time Delayed and Integration(TDI) technique, which is mostly used to observe the ground, is going to be used to observe the selected stars. A satellite attitude scenario was also developed to observe the selected stars. The scenario is created to enable TDI to operate. Rotation angles of optical payload are determined in order for the selected stars to properly be passed at a desired angular velocity about rotation axis. The result of this research can be utilized to validate the quality of optical payload of a satellite in orbit. In addition, a quaternion for pointing selected stars is calculated minimizing the path from a given arbitrary attitude of satellite.
A study on the Computational Efficiency Improvement for the Conjunction Screening Algorithm
Kim, Hyoung-Jin ; Kim, Hae-Dong ; Seong, Jae-Dong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 9, 2012, Pages 818~826
DOI : 10.5139/JKSAS.2012.40.9.818
In this paper, the improvement methods of the computational efficiency of the conjunction screening algorithm, which calculates the closest distance between primary satellite and space objects are presented. First method is to use GPU(Graphics Processing Unit) that has high computing power and handles quickly large amounts of data. Second method is to use Apogee/Perigee filter which excludes non-threatening objects that have low probability of collision and/or minimum distance rather than that of thresh hold. Third method is to combine first method with second method. As a result, the computational efficiency has been improved 34 times and 3 times for the first method only and second method only, respectively. On the contrary, the computational efficiency has been dramatically improved 163 times when two kinds of methods are combined.
The Implementation of the Speed Measurement Board for the Reaction Wheel on the LEO Satellite using the T, M-Method
Lee, Jae-Nyeung ; Park, Sung-Hun ; Heu, Su-Jin ; Lee, Yun-Ki ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 9, 2012, Pages 827~832
DOI : 10.5139/JKSAS.2012.40.9.827
In this paper, we will design the speed measurement board of LEO Satellite's reaction wheel which has two speed measuring methods as M-Method type and T-Method type. therefore we can use the advantage of two methods. and we will verify the availability of design on the on-board computer at the real LEO Satellite(KOMPSAT-3). In the reaction wheels satellite that can change the satellite's attitude is one of the leading drivers by the rotational inertia of the motor will perform attitude control. Reaction methods for detecting wheel rotation speed generated during a certain period T internal reaction wheel tacho pulse counting M-Method to detect wheel speed and wheel tacho pulses are generated by measuring the time between the detection rate can be divided into T-Method. M-method is simple to implement and benefit measurement time is constant, but slow fall in the velocity measurement accuracy is a disadvantage. In contrast, the time between tacho pulses to measure the T-Method to measure the precise speed at low speed and to measure the time delay is small, has the advantage. However, this method also in the actual implementation and the complexity of the operation at different speeds depending on the speed of operation has the disadvantage.