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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 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
FDI performance Analysis of Inertial Sensors on Multiple Conic Configuration
Kim, Hyun Jin ; Song, Jin Woo ; Kang, Chul Woo ; Park, Chan Gook ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 11, 2015, Pages 943~951
DOI : 10.5139/JKSAS.2015.43.11.943
Inertial sensors are important components of navigation system whose performance and reliability can be improved by specific sensor arrangement configuration. For the reliability of the system, Fault Detection and Isolation (FDI) is conducted by comparing each signal of arranged sensors and many arrangement configuration were suggested to optimize FDI performance of the system. In this paper, multiple conic configuration is suggested with optimal navigation condition and its FDI performance is analyzed by established Figure Of Merit (FOM) under the condition for navigation optimality. From FOM comparison, the multiple conic configuration is superior to former one in point of FDI.
Characteristics and Key Parameters of Dual Bell Nozzles of the DLR, Germany
Kim, Jeonghoon ; Huh, Hwanil ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 11, 2015, Pages 952~962
DOI : 10.5139/JKSAS.2015.43.11.952
Various types of altitude compensation nozzles have been investigated to develop an effective propulsion system. In order to obtain baseline data for future study of dual bell nozzles, main characteristics and key parameters of dual bell nozzles are summarized and described by analysing DLR dual bell nozzles. DLR`s experimental researches show that inflection angle is proportional to transition NPR, and extension length is proportional to side load, but inversely proportional to transition NPR and transition duration. Therefore, the nozzle geometry can be determined through the performance prediction process and thus the optimization process is required to meet performance requirements between parameters.
On the Pressurization Characteristics of Small Piezoelectric Hydraulic Pump for Brake System
Jeong, Min-Ji ; Hwang, Jai-Hyuk ; Bae, Jae-Sung ; Kwon, Jun-Yong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 11, 2015, Pages 963~970
DOI : 10.5139/JKSAS.2015.43.11.963
In this study, the pressurization characteristics of the small piezoelectric hydraulic pump for a brake system has been analyzed through modeling the full hydraulic pump components; the pump chamber, check valve, pump load, pump drive controller etc. To analyze the pressurization characteristics, the process of charging pressure in the chamber with stacked-layer piezoelectric actuator were firstly modeled. Secondly, the flow coefficient of the check valve in terms of valve opening has been calculated after computational fluid dynamics analysis, such as the pressure distribution around check valve and the flow rate, was conducted. Also the pump driving controller, which controls the input voltage to the actuator, was designed to make the load pressure follow the input pressure command. The simulation results find that it takes about 0.03ms to reach the operating load pressure required for the braking system. The simulation result was also verified through comparison to the result of the pump performance test.
An Exploratory Study on the Speed Limit of Compound Gyroplane(1) : Aerodynamic Analysis of Rotor and Airframe
Shin, Byung-joon ; Kim, Hak-Yoon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 11, 2015, Pages 971~977
DOI : 10.5139/JKSAS.2015.43.11.971
A numerical analysis for the performance of compound gyroplane in forward flight was performed. TSM(Transient Simulation Method) was used to analyze the performance of autorotating rotor. CFD was conducted for the fuselages to recognize the variation of aerodynamic performance according to flight speed. At given conditions; airspeed, shaft angle and collective pitch, the quasi-static states of autorotation were determined and the variation of rotor performance was observed. Performance analysis results showed that the effect of aerodynamic characteristics in accordance with the shape of fuselage is so important that the streamlined fuselage is essential to fly fast. Forward flight speed limit is dependent on the autorotation performance of rotor.
An Exploratory Study on the Speed Limit of Compound Gyroplane(2) : Speed and Wing Sizing
Shin, Byung-Joon ; Kim, HakYoon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 11, 2015, Pages 978~983
DOI : 10.5139/JKSAS.2015.43.11.978
A study on the speed limit and sizing of auxiliary fixed-wing of compound gyroplane was performed. The performance of the plane that uses the same rotor system and power of BO-105 helicopter was compared with that of BO-105 helicopter. The wing area which is used to compensate in lift, was calculated considering the aerodynamic characteristics and lift sharing ratio of the rotor. Achievable flight speeds were observed for two types of fuselage; BO-105 and streamlined bodies. The study showed that the autorotating rotor can share 1/2 of lift at high speed and the parasite power of compound gyroplane having streamlined body and small wing can be minimized, accordingly it can fly faster than helicopter with airspeed more than twice.
Introduction to Chang`e-3 and Analysis of Estimated Mission Trajectory
Choi, Su-Jin ; Lee, Donghun ; Bae, Jonghee ; Rew, Dong-Young ; Ju, Gwanghyeok ; Sim, Eun-Sup ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 11, 2015, Pages 984~997
DOI : 10.5139/JKSAS.2015.43.11.984
Chang`e-3 consisting of a lunar lander and exploration rover was launched on December 1, 2013 aboard a Long March 3B rocket flying from Xichang space launch center. Chang`e-3 was inserted into the lunar orbit after about a 5-day transit to the Moon and landed on the targeted landing site after orbiting around the Moon for 8 days. The successful landing of the Chang`e-3 gives a lot of help to analyze the future needs of the subsystem technologies and to figure out the trajectory from launch to lunar landing as well as operation sequences in the development of Korean lunar exploration is scheduled. Therefore, the configuration and analysis of overall mission of Chang`e-3 is performed based on the public information from the press and website. As a result, overall mission trajectory is reconstructed by solving boundary condition and then estimating control variable. Visibility status and eclipse status also analyzes so communication and power charge condition is as good as to operate lunar lander. Mass budget of the lander is derived using
according to specific impulse.
Radial Type Satellite Attitude Controller Design using LMI Method and Robustness Analysis
Rhee, Seung-Wu ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 11, 2015, Pages 998~1007
DOI : 10.5139/JKSAS.2015.43.11.998
control theory using LMI method is applied to design an attitude controller of radial type satellite that has strongly coupled channels due to the large product of inertia. It is observed that the cross-over frequency of open-loop with
controller is lower than that of open-loop without controller, which is not typical phenomenon in an optimal control design result: it is interpreted that due to a large product of inertia, there is certain limit in increasing agility of satellite by just tuning weighting function.
-analysis is performed to verify the stability and performance robustness with the assumption of +/-5% MOI variation.
-analysis result shows that the variation of principal MOI degrades the stability and performance robustness more than the variation of POI does.
Design and Performance Tests of a Cryogenic Blower for a Thermal Vacuum Chamber
Seo, Heejun ; Cho, Hyokjin ; Park, Sungwook ; Moon, Gueewon ; Huh, Hwanil ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 11, 2015, Pages 1008~1015
DOI : 10.5139/JKSAS.2015.43.11.1008
Thermal vacuum test should be performed prior to launch to verify satellites` functionality in extremely cold/hot temperatures and vacuum conditions. A thermal vacuum chamber used to perform the thermal vacuum tests of a satellite system and its components. A cryogenic blower is a core component of the gaseous nitrogen (GN2) closed loop thermal control system for thermal vacuum chambers. A final goal of this research is development of cryogenic blower. Design requirements of a blower are 150 CFM flow rate, 0.5 bara pressure difference, hot and cold temperatures. This paper describes the performance analysis of impeller by 1D, CFD commercial software, the design of the thermal protection interface between the driving part and the fluid part. The performance of the cryogenic blower is confirmed by test at the standard air condition and is verified by on the thermal vacuum chamber at the real operating condition.
Analysis of Orbit Determination of the KARISMA Using Radar Tracking Data of a LEO Satellite
Cho, Dong-Hyun ; Kim, Hae-Dong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 11, 2015, Pages 1016~1027
DOI : 10.5139/JKSAS.2015.43.11.1016
In this paper, a orbit determination process was carried out based on KARISMA(KARI Collision Risk Management System) developed by KARI(Korea Aerospace Research Institute) to verify the orbit determination performance of this system, in which radar tracking data of a space debris was used. The real radar tracking data were obtained from TIRA(Tracking & Imaging Radar) system operated by GSOC(German Space Operation Center) for the KITSAT-3 finished satellite. And orbit determination error was approximately 60m compared to that of the GSOC`s orbit determination result from the same radar tracking data. However, those results were influenced due to the insufficient information on the radar tracking data, such as error correction. To verify and confirm it, the error analysis was demonstrated and first observation data arc which has huge observation error was rejected. In this result, the orbit determination error was reduced such as approximately 25m. Therefore, if there are some observation data information such as error correction data, it is expected to improve the orbit determination accuracy.
Design of Space Launch Vehicle Solenoid Valve for Cryogenic Environment
Kim, Byunghun ; Han, Sangyeop ; Ko, Youngsung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 11, 2015, Pages 1028~1034
DOI : 10.5139/JKSAS.2015.43.11.1028
Solenoid valves for space launch vehicles require the strict limitations on the size, weight and current consumption comparing to industrial solenoid valves. The preliminary design of a cryogenic and high pressure solenoid valve for propellant tank pressurization which can ensure the operation of solenoid valve under such strict limitation conditions was preformed. The Copper and Constantan materials in coil design have used to prevent the excessive rise of the current at cryogenic state. The measured current of solenoid valve at cryogenic temperature satisfies a design requirement.