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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
The Study of Advanced Propeller Blade for Next Generation Turboprop Aircraft -Part I. Aerodynamic Design and Analysis
Choi, Won ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 12, 2012, Pages 1017~1024
DOI : 10.5139/JKSAS.2012.40.12.1017
The aerodynamic design and analysis on advanced propeller with blade sweep was performed for recent turboprop aircraft. HS1 airfoil series are selected as a advanced propeller blade airfoil. Adkins method is used for aerodynamic design and performance analysis with respect to the design point. Adkins method is based on the vortex-blade element theory which design the propeller to satisfy the condition for minimum energy loss. Propeller geometry is generated by varying chord length and pitch angle at design point of target aircraft. Advanced propeller is designed by apply the modified chord length, the tip sweep which is based on the geometry of conventional propeller. The aerodynamic characteristics of the designed Advanced propeller were verified by CFD(Computational Fluid Dynamic) and evaluated to be properly designed.
Study on Concept Design of Supersonic Inlet and Flow Control of Bleeding under Operating Condition
Choi, Jaehwan ; Cheon, Somin ; Choe, Yohan ; Hong, Wooram ; Kim, Chongam ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 12, 2012, Pages 1025~1031
DOI : 10.5139/JKSAS.2012.40.12.1025
The present paper deals with concept design of supersonic inlet based on compressible flow theory and flow control of bleeding in order to guarantee stability of supersonic inlet of ramjet engine in broad range of operating conditions. Shock instability, shock wave-boundary layer interaction and flow separation should be properly controlled to improve performance of the supersonic inlet. Considering shock strength, boundary layer and flow separation, the supersonic inlet is modified from the basic model which is designed under inviscid theory. Consequently, shock is stabilized, and required mass flow rate is obtained. Furthermore, bleeding is applied to the supersonic inlet to maintain performance in off-design conditions. Mass flow condition is adopted for modeling of bleeding effect, and performance of the supersonic inlet is evaluated by changing bleeding locations and numbers.
Precise Relative Positioning for Formation Flying Satellite using GPS Carrier-phase Measurements
Park, Jae-Ik ; Lee, Eunsung ; Heo, Moon-Beom ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 12, 2012, Pages 1032~1039
DOI : 10.5139/JKSAS.2012.40.12.1032
The present paper deals with precise relative positioning of formation satellites with long baseline in low Earth orbit making use of L1/L2 dual frequency GPS carrier phase measurements. Kinematic approach means to describe the motion of objects without taking its mass/dynamics model into consideration. The advantage of the kinematic approach is that information about dynamics of the system is not applied, which gives more flexibility and could improve the scientific interest of the observations made by the mission. The ionosphere terms, which are not canceled by double differenced measurement equation in the case of the long baseline, are explicitly estimated as unknown parameters by extended Kalman filter. The estimated float ambiguities by EKF are solved by existing efficient integer vector search strategy under integer least square condition. For the integer vector search, we employ well known MLAMBDA. Finally, The feasibility and accuracy of processing scheme are demonstrated using the GPS measurements for two satellites in low Earth orbit separated by baselines of 100 km.
Signal-based Fault Diagnosis Algorithm of Control Surfaces of Small Fixed-wing Aircraft
Kim, Jihwan ; Goo, Yunsung ; Lee, Hyeongcheol ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 12, 2012, Pages 1040~1047
DOI : 10.5139/JKSAS.2012.40.12.1040
This paper presents a fault diagnosis algorithm of control surfaces of small fixed-wing aircraft to reduce maintenance cost or to improve repair efficiency by estimation of fault occurrence or part replacement periods. The proposed fault diagnosis algorithm consists of ANPSD (Averaged Normalized Power Spectral Density), PCA (Principle Component Analysis), and GC (Geometric Classifier). ANPSD is used for frequency-domain vibration testing. PCA has advantage to extract compressed information from ANPSD. GC has good properties to minimize errors of the fault detection and isolation. The algorithm was verified by the accelerometer measurements of the scaled normal and faulty ailerons and the test results show that the algorithm is suitable for the detection and isolation of the control surface faults. This paper also proposes solutions for some kind of implementation problems.
GPS Carrier Phase Fault Detection with Consideration on User Dynamics
Won, Dae Hee ; Ahn, Jongsun ; Sung, Sangkyung ; Lee, Eunsung ; Heo, Moon-Beom ; Lee, Young Jae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 12, 2012, Pages 1048~1054
DOI : 10.5139/JKSAS.2012.40.12.1048
This paper presents a Carrier phase fault detection (FD) method for GPS RTK (Global Positioning System Real Time Kinematic) in dynamic environment. There are various error sources in dynamic environment and these errors decrease the reliability of FD results. Due to the reason, Carrier phase measurements are separated into satellite induced signal, user induced signal and other remaining errors. Especially the user-induced signal is computed by user dynamic which is estimated by time-differenced Carrier phase (TDCP) and Doppler shift. TDCP makes it possible to avoid integer ambiguity resolution. Computer simulation is conducted to verify the suggested method. By applying impulse, step and ramp faults, the FD performance is analyzed.
A Study on Control Algorithm of Thrust Control Valve for a Liquid Rocket Engine
Jung, Taekyu ; Lee, Soo-Yong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 12, 2012, Pages 1055~1062
DOI : 10.5139/JKSAS.2012.40.12.1055
In this paper, the mathematical models and control algorithm of a thrust control valve were described as a precedent study on the design of thrust control algorithm for a liquid rocket engine (LRE). Numerical simulations were performed using a simplified simulation system of an LRE and the developed mathematical models were validated by comparison with the experimental results. Through these research, basic data were acquired for the development of a thrust control algorithm for a LRE.
Performance assessment of Magnesium Bipolar Plates for Light Weight PEM Fuel Cell
Park, To-Soon ; Lee, Dong-Woo ; Kim, Kyung-Hwan ; Kwon, Se-Jin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 12, 2012, Pages 1063~1069
DOI : 10.5139/JKSAS.2012.40.12.1063
In present paper, we used magnesium alloy having a lower density and higher electrical conductivity for bipolar plate to reduce the weight of PEM fuel cell. The silver was coated to prevent corrosion and form passivation film on the metal surface with sputtering. In acid proof evaluation for setting optimal coating conditions, the homogeneity of coating thickness was improved by coating with the thickness of 3
which not indicated any micro cracks and the temperature
. The performance test and evaluation based on the clamping pressure and channel depth to determine the configuration of bipolar plate for assembling single cell was implemented. And then we assembled single cell with this bipolar plate and implemented the performance test to ensure and compare the current-voltage performance followed as several factors such as coating or non-coating, the change of clamping pressure, the change of channel depth, etc. As these results, the maximum power density of single cell with the coated bipolar plate was 192
and it was confirmed that the power density per unit mass was better than existing metal bipolar plate.
Analysis of Crashworthiness Characteristics of a Regional Aircraft Fuselage using an Explicit Finite Element Method
Park, Ill-Kyung ; Kim, Sung-Joon ; Hwang, In-Hee ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 12, 2012, Pages 1070~1079
DOI : 10.5139/JKSAS.2012.40.12.1070
The impact energy absorbing is a very important characteristic of an aircraft to enhance the survivability of occupants when an aircraft is under the survivable accident such as an emergency landing condition. The impact energy is generally transmitted into the occupant and absorbed through a landing gear, a subfloor (lower structure of fuselage), and a seat. The characteristic of crash energy absorbing of a subfloor depends on the type of an aircraft, a shape of structure, and an applied material. Therefore, the study of crashworthiness characteristics of a subfloor structure is very important work to improve the safety of an aircraft. In this study, a finite element model of a narrow body fuselage section for the 80~90 seats regional aircraft was developed and crash simulation was executed using an explicit finite element analysis. Through survey of the impact energy distribution of each structural part of a fuselage and floor-level acceleration response, the crashworthiness characteristics and performance was evaluated.
Design of Sharp-edged Type Damping Orifices for an Aircraft Door Damper
Hong, Yeh-Sun ; Kwon, Yong-Cheol ; Kim, Chong-Hyeok ; Park, Seol-Hye ; Park, Ho-Yeol ; Kim, Sang-Beom ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 12, 2012, Pages 1080~1085
DOI : 10.5139/JKSAS.2012.40.12.1080
In this paper a sharp-edged type damping orifice for an aircraft door damper were designed, where the dynamic viscosity of working fluid were assumed to change up to 400cSt. The discharge coefficient of the damping orifice were investigated by CFD analyses and experiments. In particular, the influences of orifice diameter, edge angle, flow direction and the Reynolds number were taken into consideration. Based on this, it has been deduced how high Coulomb friction forces of damper seals is to be allowed to meet the performance criterion with respect to the orifice size.
Lever Arm Compensation of Reference Trajectory for Flight Performance Evaluation of DGPS/INS installed on Aircraft
Park, Ji-Hee ; Lee, Seong-Woo ; Park, Deok-Bae ; Shin, Dong-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 12, 2012, Pages 1086~1092
DOI : 10.5139/JKSAS.2012.40.12.1086
It has been studied for DGPS/INS(Differential Global Positioning System/Inertial Navigation System) to offer the more precise and reliable navigation data with the aviation industry development. The flight performance evaluation of navigation system is very significant because the reliability of navigation data directly affect the safety of aircraft. Especially, the high-level navigation system, as DGPS/INS, need more precise flight performance evaluation method. The performance analysis is performed by comparing between the DGPS/INS navigation data and reference trajectory which is more precise than DGPS/INS. The GPS receiver, which is capable of post-processed CDGPS(Carrier-phase DGPS) method, can be used as reference system. Generally, the DGPS/INS is estimated the CG(Center of Gravity) point of aircraft while the reference system is output the position of GPS antenna which is mounted on the outside of aircraft. For this reason, estimated error between DGPS/INS and reference system will include the error due to lever arm. In order to more precise performance evaluation, it is needed to compensate the lever arm. This paper presents procedure and result of flight test which includes lever arm compensation in order to verify reliability and performance of DGPS/INS more precisely.
Reliability Evaluation of COTS Integrated Circuits for Military and Space Applications
Chan, Sung-Il ; Han, Chang-Woon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 12, 2012, Pages 1093~1098
DOI : 10.5139/JKSAS.2012.40.12.1093
Commercial Off the Shelf(COTS) Integrated circuits(ICs) are being increasingly considered for use in space and military applications. Therefore, There is a need to implement standard tests and requirements to ensure reliability of COTS ICs. This paper presents an overview of the ICs screen procedure and methods under the European Cooperation for Space Standardization (ECSS) and Tests Method Standard Microcircuits (MIL-STD-883). We describes the COTS ICs screen test guidelines that are mainly focused after encapsulating. In addition, COTS linear bipolar IC is investigated to evaluate the reliability requirements. The experiment results showed that COTS IC is satisfied with high reliability requirements.