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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
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Journal DOI :
The Korean Society for Aeronautical & Space Sciences
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Volume & Issues
Volume 42, Issue 12 - Dec 2014
Volume 42, Issue 11 - Nov 2014
Volume 42, Issue 10 - Oct 2014
Volume 42, Issue 9 - Sep 2014
Volume 42, Issue 8 - Aug 2014
Volume 42, Issue 7 - Jul 2014
Volume 42, Issue 6 - Jun 2014
Volume 42, Issue 5 - May 2014
Volume 42, Issue 4 - Apr 2014
Volume 42, Issue 3 - Mar 2014
Volume 42, Issue 2 - Feb 2014
Volume 42, Issue 1 - Jan 2014
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Analysis of Thermal Deformation of Co-bonded Dissimilar Composite considering Non-linear Thermal Expansion Characteristics of Composite Materials
Kim, Jeong-Beom ; Kim, Hong-Il ; Jeon, Ho-Chan ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 10, 2014, Pages 809~815
DOI : 10.5139/JKSAS.2014.42.10.809
The co-bonded dissimilar composite under a wide range of temperature change shows thermal distortion due to the differences in thermal expansion characteristics of the composite materials. Analysis of the thermal expansion characteristics of each composite is required for the design of co-bonded dissimilar composite structure with considering the shape distortion during the manufacturing process. In this work, digital image correlation (DIC) technique is introduced for measuring the thermal distortion characteristics of co-bonded dissimilar composite specimen, carbon/epoxy and silica/phenolic. The thermal distortion of co-bonded dissimilar composite specimen is numerically estimated and compared with the experiments. The estimated results is successfully validated using the measured results.
Nonlinear Observer Design for Satellite Angular Rate Estimation by SDRE Method
Jin, Jaehyun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 10, 2014, Pages 816~822
DOI : 10.5139/JKSAS.2014.42.10.816
The estimation of the angular rate of a satellite has been discussed. A nonlinear observer has been proposed based on the state-dependent Riccati equation method. A sufficient stability condition for the convergence of estimation error has been presented. This condition is related to a state-dependent algebraic Riccati equation. It has been derived by transforming nonlinear error dynamics into a Lipschitz nonlinearity. An observer gain is obtained from this condition. Numerical simulations are presented to verify the proposed method.
A Study on Orbit Stability and Control Method for Displaced Non-Keplerian Orbits by Using Pitch Angle Variation
Kim, Mingyu ; Lee, Jeongpyo ; Kim, Jeongrae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 10, 2014, Pages 823~832
DOI : 10.5139/JKSAS.2014.42.10.823
Displaced non-Keplerian orbit, center of mass is displaced from orbit plane, enables special spacecraft missions. It requires continuous thrust to maintain the orbit, and solar sail is useful for this purpose. Equations for feasible region and stability analysis are derived for non-Keplerian orbit for general continuous thrust. Differences for solar sail spacecraft are discussed. Non-keplerian orbits are classified into four types. Location-specific required accelerations for orbit maintenance are calculated. Orbit stabilities of each orbit type are analyzed and verified by numerical simulations. In order to control non-Keplerian orbit in unstable region, a control algorithm using the real-time LQR control is developed and evaluated by numerical simulations.
Estimation of Wind Velocity Using Motion Tracking of a Balloon
Oh, Hyeju ; Jo, Sungbeom ; Choi, Keeyoung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 10, 2014, Pages 833~841
DOI : 10.5139/JKSAS.2014.42.10.833
This paper proposes an algorithm to estimate the wind velocity by tracking free flying balloons. Balloons used in this method are expendable but inexpensive, which increases the usefulness of the method. Also we can obtain accurate 3D information by using multiple cameras and estimate the wind velocity of the local field. The proposed system consists of aerodynamic modeling of the balloon, a tracking algorithm using image processing, and the velocity estimation algorithm. We performed unit tests of each algorithm for the verification. The method is validated using a system simulation and sources of error case identified.
Trajectory Tracking Controller Design using L
Adaptive Control for Multirotor UAVs
Jung, Yeundeuk ; Cho, Sungwook ; Shim, Hyunchul ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 10, 2014, Pages 842~850
DOI : 10.5139/JKSAS.2014.42.10.842
This paper presents a trajectory tracking controller for rotorcraft UAVs to improve the tracking performances in the presence of various uncertainties. The proposed tracking method consists of a velocity guidance law based on the relative distance and L1 adaptive augmentation loop for tracking the velocity commands. In the proposed structure, the desired velocity generated by the guidance law is the reference value of the adaptive controller for accurate path tracking. In the guidance law, the desired acceleration is generated based on the relative distance and its derivatives, and then the velocity command of the inner control loop is calculated by integrating the accelerations.
augmentation loop supplements the linear controller to guarantee the flight performances such as a tracking accuracy in the presence of the uncertainties. The proposed controller was validated in actual flight tests to successfully demonstrate its capability using a quadrotor UAV.
Design of Auto Race-Track and Figure-8 Flight Mode for UAV
Lee, Sangjong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 10, 2014, Pages 851~857
DOI : 10.5139/JKSAS.2014.42.10.851
This paper addresses the design of the auto race-track and figure-8 flight mode which can be applied to expand the loitering flight mode and increase the safety of UAV. To implement these flight modes, necessary waypoints and entry points can be calculated automatically from several information of the ground control system. The flight logic is proposed to pass the desired waypoints as well as entry points and transfer to the desired flight path by combining the light-of-sight and loitering guidance controller. The proposed algorithm and logic is verified using the 6-DOF UAV model and nonlinear simulation under the several flight conditions.
Research Activities on PGC Propulsion Systems based on PDE
Kim, Ji-Hoon ; Kim, Tae-Young ; Jin, Wan-Sung ; Choi, Jeong-Yeol ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 10, 2014, Pages 858~869
DOI : 10.5139/JKSAS.2014.42.10.858
Most of the aerospace propulsion is based on the Brayton cycle, in which the combustion is held through the constant pressure process, but further improvement of performance by increasing compression ratio is challenged by mechanical limits. Detonation propulsions, regarded promising for high-speed propulsion for a lase decade, is more rigorously studied in these days as a game-changer for the improvement of thermodynamic efficiency of propulsion and power generation systems. Since, the additional compression by the strong shock of the detonation wave is considered increasing thermodynamics efficiency that is hardly achievable by the conventional compression systems. Present paper will give an introduction the latest technical trends on the Pulse Detonation Engines(PDEs) and the activities on the Pressure Gain Combustion (PGC) based on Constant Volume Combustion (CVC).
Residual Propellant Gauging Methods for Geostationary Satellites and Recent Technology Status
Park, Eungsik ; Huh, Hwanil ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 10, 2014, Pages 870~877
DOI : 10.5139/JKSAS.2014.42.10.870
Geostationary satellites undergo various orbital perturbations and this results in location change. Therefore, all the geostationary satellites use the thruster in order to control the location change. For this purpose, the suitable amount of liquid propellant is mounted and the amount of propellant is reduced as time goes by. This means that the lifetime of the satellite depends on the residual propellant amount. Therefore precise residual propellant gauging is very important for the mitigation of economic losses arised from premature removal of satellite from its orbit, satellites replacement planning, slot management and so on. In this paper, we introduce the propellant gauging methods used in the geostationary satellites and the propellant gauging method studied in the laboratory level.
EMC Test of Deimos-2 satellite
Park, In-Yong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 10, 2014, Pages 878~883
DOI : 10.5139/JKSAS.2014.42.10.878
This paper presents the test result of system level EMC of LEO satellite Deimos-2 FM that has been launched in June 20, 2014. The Deimos-2 satellite was designed considering the EMC of unit modules level in addition to the structure aspects. The Auto-Compatibility, Radiated Emission and Radiated Susceptibility test was conducted. The test result has meet the standard of system EMC of Deimos-2 program.
A Study on Performance Enhancement in Simulation Fidelity Using a Meta Model
Cho, Donghyurn ; Kwon, Kybeom ; Seol, Hyunju ; Myung, Hyunsam ; Chang, YoungChan ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 10, 2014, Pages 884~892
DOI : 10.5139/JKSAS.2014.42.10.884
In this paper, a meta model using neural network substituting for the simulator aerodynamic database is proposed to improve simulation fidelity near the critical flight area and real-time performance. It is shown that the accuracy of the meta model is relatively higher than the existing table lookup methods for arbitrary nonlinear database and the calculation speed is also improved for a specific F-16 maneuver simulation. The increase in the number of hidden nodes in the meta model for better accuracy of database representations causes a delay in function generation due to increased time required for computing exponential functions. In order to make up this drawback, we additionally study the fast exponential function method.
A study of the status of UAS Certification System and Airworthiness Standards
Ahn, Hyojung ; Park, Jonghyuk ; Yoo, Seungwoo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 10, 2014, Pages 893~901
DOI : 10.5139/JKSAS.2014.42.10.893
UAS and related technology have been mainly developed for military use but, in recent years, various types of civil UAS have been using in a variety of applications. For example, there are multicopters to shoot aerial photography, pesticide spraying unmanned helicopter, and in addition there are radio control (R/C) aircraft to be used for hobbyists. UAV has spread rapidly enough that permitted experts as well as the public can use it but the related safety regulations are not properly equipped. We investigated the status of domestic and international UAS certification system and airworthiness standards. And the trends in research for the development and modification of the certification system were studied in this paper. As a result, most countries have studied to develop the related regulations and especially ICAO has tried to develop RPAS manual, standards and recommended plans and modify the related ICAO annex through the research group, ICAO UASSG. Based on the manual and SARPs, authorities, related organizations and companies have prepared to develop and modify regulations in accordance with the actual situation of each country.