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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 39, Issue 12 - Dec 2011
Volume 39, Issue 11 - Nov 2011
Volume 39, Issue 10 - Oct 2011
Volume 39, Issue 9 - Sep 2011
Volume 39, Issue 8 - Aug 2011
Volume 39, Issue 7 - Jul 2011
Volume 39, Issue 6 - Jun 2011
Volume 39, Issue 5 - May 2011
Volume 39, Issue 4 - Apr 2011
Volume 39, Issue 3 - Mar 2011
Volume 39, Issue 2 - Feb 2011
Volume 39, Issue 1 - Jan 2011
Selecting the target year
Free Vibration Characteristics of the Rectangular Plates under Uniform Thermal Loading Part I. Analytic and FEM analysis
Jeon, Byoung-Hee ; Kang, Hui-Won ; Lee, Young-Shin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 2, 2011, Pages 97~105
DOI : 10.5139/JKSAS.2010.39.2.97
This paper was conducted on analytical solution using superposition and FEM analysis in the free vibration analysis of rectangular plates under uniform thermal loadings. Materials of three rectangular plates were aluminum, steel and stainless-steel respectively. Applied temperature conditions were from room temperature to
and boundary condition was free-free condition. Fully symmetric mode(FSM), fully antisymmetric mode(FASM) and symmetric-antisymmetric mode(SAM) were analyzed.
Free Vibration Characteristics of Rectangular Plates under Uniform Thermal Loading Part II. Experimental Modal Test
Jeon, Byoung-Hee ; Kang, Hui-Won ; Lee, Young-Shin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 2, 2011, Pages 106~113
DOI : 10.5139/JKSAS.2010.39.2.106
This paper was conducted on experimental analysis in the free vibration analysis of rectangular plates under uniform thermal loading. Materials of three rectangular plates were aluminum, steel and stainless-steel respectively. The dimension of rectangular plates was 0.1
0.002 m. Infrared quartz lamps were used for thermal loading. The PCS(Power Control System) electric control system was applied for control and scanning vibrometer (Poly Tech) was used for acquisition of frequency response function. Applied temperature was increased from room temperature to
. Boundary condition was free-free condition using bungee cord. Front face of rectangular plate was heated uniformly.
Cooperative Control of Multiple Unmanned Aircraft for Standoff Tracking of a Moving Target
Yoon, Seung-Ho ; Kim, You-Dan ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 2, 2011, Pages 114~120
DOI : 10.5139/JKSAS.2010.39.2.114
This paper presents a cooperative standoff tracking of a moving target using multiple unmanned aircraft. To provide guidance commands, vector fields are designed utilizing the Lyapunov stability theory. A roll angle command is generated to keep a constant distance from the target in a circular motion. A speed command and a heading angle command are designed to keep a constant phase angle with respect to the front aircraft and to prevent a collision between aircraft. Numerical simulation is performed to verify the tracking and collision performance of the proposed control laws.
Leader - Follower based Formation Guidance Law and Autonomous Formation Flight Test of Multiple MAVs
You, Dong-Il ; Shim, Hyun-Chul ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 2, 2011, Pages 121~127
DOI : 10.5139/JKSAS.2010.39.2.121
This paper presents an autonomous formation flight algorithm for micro aerial vehicles (MAVs) and its flight test results. Since MAVs have severe limits on the payload and flight time, formation of MAVs can help alleviate the mission load of each MAV by sharing the tasks or coverage areas. The proposed formation guidance law is designed using nonlinear dynamic inversion method based on `Leader-Follower` formation geometric relationship. The sensing of other vehicles in a formation is achieved by sharing the vehicles` states using a high-speed radio data link. the designed formation law was simulated with flight data of MAV to verify its robustness against sensor noises. A series of test flights were performed to validate the proposed formation guidance law. The test result shows that the proposed formation flight algorithm with inter-communication is feasible and yields satisfactory results.
Performance improvement of SDINS attitude error estimation using GPS for bank-to-turn flight vehicle
Yu, Hae-Sung ; Yoo, Ki-Jeong ; Kim, Hyun-Seok ; Lee, Youn-Seon ; Park, Heung-Won ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 2, 2011, Pages 128~136
DOI : 10.5139/JKSAS.2010.39.2.128
An approach to improve the performance of SDINS and GPS integrated system for bank-to-turn flight vehicles is described. Then, it is shown through the simulation that a specific gyro misalignment error results in an increased heading error of SDINS. A new modelling method is presented herein for identifying of sensor and attitude error. The main advantage of the proposed method is that it not only estimates the gyro misalignment error of SDINS, but also improves estimate performance of heading error of SDINS in the presence of the gyro misalignments.
Chaos Control of the Pitch Motion of the Gravity-gradient Satellites in an Elliptical Orbit
Lee, Mok-In ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 2, 2011, Pages 137~143
DOI : 10.5139/JKSAS.2010.39.2.137
The pitch motion of a gravity-gradient satellite can be chaotic, depending on the ratio of mass moments of inertia and the eccentricity of the satellite orbit. For a precise prediction of motion, chaotic pitch motion has to be changed to non-chaotic motion. Feedback control can be used to obtain nonchaotic pitch motion. For chaos control and stabilization of the pitch motion of a gravity-gradient satellite, a feedback control system is designed, based on the linear nonautonomous system obtained by linearizing the nonlinear pitch motion. The control law obtained has two parameters and is applied to chaotic nonlinear pitch motion. The nonlinear control system satisfies the proposed control objectives in the range of the nonchaotic parameter space.
Satellite Fault Detection and Isolation Using 2 Step IMM
Lee, Jun-Han ; Park, Chan-Gook ; Lee, Dal-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 2, 2011, Pages 144~152
DOI : 10.5139/JKSAS.2010.39.2.144
This paper presents a new scheme for fault detection and isolation in the satellite system. The purpose of this paper is to develop a fault detection, isolation and diagnosis algorithm based on the bank of interacting multiple model (IMM) filter for both total and partial faults in a satellite attitude control system (ACS). In this paper, IMM are utilized for detection and diagnosis of anticipated actuator faults in a satellite ACS. Other fault detection, isolation (FDI) schemes using conventional IMM are compared with the proposed FDI scheme. The FDI procedure is developed in two stages. In the first stage, 11 EKFs actuator fault models are designed to detect wherever actuator faults occur. In the second stage of the FDI scheme, two filters are designed to identify the fault type which is either the total or partial fault. An important feature of the proposed FDI scheme can decrease fault isolation time and figure out not only fault detection and isolation but also fault type identification.
Verification Test for GBAS Correction Information of KARI IMT
Yun, Young-Sun ; Lim, Joon-Hoo ; Cho, Jeong-Ho ; Heo, Moon-Beom ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 2, 2011, Pages 153~161
DOI : 10.5139/JKSAS.2010.39.2.153
Korea Aerospace Research Institute (KARI) has implemented an integrity monitor testbed (IMT) to provide archived GPS data and test results for integrity monitoring algorithm development. To verify that the system is implemented based on international standard requirements, this paper represents the basic functional verification test results of the implemented testbed as a GBAS reference station. It compares the IMT generated GBAS message fields with those of PEGASUS, which is a baseline toolset accepted by international GBAS experts, to show the validity of the correction information. It also verifies the integrity and availability of the system through analysis on GBAS user data in the range and position domain.
Improvement of Unexpected Pitch Down Tendency of an Aircraft
Kim, Chong-Sup ; Kwon, Hui-Man ; Koh, Gi-Ok ; Han, Kwang-Ho ; Lee, Seung-Deok ; Hwang, Byung-Moon ; Kim, Seong-Jun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 2, 2011, Pages 162~169
DOI : 10.5139/JKSAS.2010.39.2.162
The flight control system utilize RSS(Relaxed Static Stability) criteria in both longitudinal axes to achieve performance enhancements and improve stability. The aircraft using digital flight-by-wire flight control system receives aircraft flight conditions such as pitch, roll and yaw rate, normal acceleration from RSA(Rate Sensor Assembly) and ASA(Acceleration Sensor Assembly). These sensors has permissible measurement error related to system safety of an aircraft but, unexpected flight motions are happened by sensing errors such as offset, noise and etc. The unexpected pitch down tendency occurred by ASA sensor bias in 1g level flight with pilot hands-off. This paper addresses the design and verification of flight control law to improve of pitch down or up tendency caused by ASA sensor bias. The result of analysis and flight test reveals that pitch down tendency can be improved by pitch attitude feedback system.
Telemetry Performance Enhancement Using the Time-delayed data
Koh, Kwang-Ryul ; Lee, Sang-Bum ; Kim, Whan-Woo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 2, 2011, Pages 170~177
DOI : 10.5139/JKSAS.2010.39.2.170
This paper proposes a telemetering method that transmits the real-time data together with the time-delayed data and that merges both data after flight test. The method can minimize the error data which occur in the communication environment affected by the multipath fading and transmit antenna pattern when telemetry data are received during the flight test. This method was applied to the design of the telemetry unit and the development of data merging program. By merging the resulting data of flight test and analyzing synchronization errors, its efficiency for the telemetry link is verified.
Design of DubaiSAT-1 S-band Receiver RF block
Park, In-Yong ; Min, Seung-Hyun ; Kim, Byung-Jin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 2, 2011, Pages 178~182
DOI : 10.5139/JKSAS.2010.39.2.178
A FSK receiver RF block has been developed for Dubaisat-1 Low Earth Orbit satellite. The receiver has Doppler tracking function which compensate frequency shift on uplink channel for commanding the satellite. It consist of LNA, downconverter and IF module. The IF module has Doppler tracking circuitry which sweep and lock on to input signal. It satisfies the requirement of the Dubaisat-1 in mass, power consumption, tracking speed and BER performance.
Development and application of simulator for spotlight SAR image formation and quality assesment using RMA
Kwak, Jun-Young ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 2, 2011, Pages 183~194
DOI : 10.5139/JKSAS.2010.39.2.183
Synthetic aperture radar (SAR) is widely used because of high resolution imaging capability in all weather and day/night condition. In this paper development of Spotlight SAR simulator is proposed for image quality analysis. Proposed SAR simulator is based on the SAR system design parameters so that SAR image performance can be expected which is essential throughout the full system development procedure from the initial concept design stage to the final in-flight calibration and validation stage. The raw data of ideal point target is first generated by taking account of the flight and imaging geometry and the various SAR system design parameters, and the Spotlight image formation algorithm is implemented in order to obtain the point target response. Finally the image quality of the generated raw data is analyzed in terms of spatial resolution, peak to sidelobe ratio and integrated sidelobe ratio.
Comparison Study of the Low Power Hall Thrusters Performance
Kang, Seong-Min ; Kim, Youn-Ho ; Jeong, Yun-Hwang ; Seon, Jong-Ho ; Lee, Jong-Sub ; Seo, Mi-Hui ; Choe, Won-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 2, 2011, Pages 195~200
DOI : 10.5139/JKSAS.2010.39.2.195
A low power Hall thruster is under development for orbit maintenance of a small Earth observing satellite. Both cylindrical and annular type thrusters were manufactured and tested to characterize the performance of cylindrical Hall thrusters. Results were described through comparative analyses. Cylindrical thrusters were manufactured in two different channel diameter dimensions, 28 mm and 50 mm. Thrust, ion velocity and ion current were measured in various operating conditions. The results show that cylindrical thrusters are more efficient in mass utilization and voltage utilization, but less efficient in current utilization than annular one.