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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 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
Additive Drag Computation of Supersonic Inlet by Numerical Analysis on Inviscid Flow
Jung, Suk Young ; Lee, Jung Hwa ; Kim, Min Gyu ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 5, 2015, Pages 387~395
DOI : 10.5139/JKSAS.2015.43.5.387
A technique for calculating the additive drag of the inlet in supersonic flow was studied using commercial CFD software, STAR-CCM+, which provides a efficient way of 3 dimensional flow analysis with polyhedron-shaped grid system. Three configurations were chosen and applied to the calculation with various flow conditions of two different free stream Mach No. and some mass flow ratios. Comparisons with results from wind tunnel test gave good agreements. Though computation were carried out with the inviscid and compressible flow around the supersonic inlet for the supercritical condition, ignoring the viscous effects is concluded to give little effects on the accuracy of the additive drag calculation and to make the calculation more efficient owing to less effort and time consumed for grid system build-up and for iteration because of less grid number and simpler boundary condition.
Prediction for Large Deformation of Cantilever Beam Using Strains
Park, Sunghyun ; Kim, In-Gul ; Lee, Hansol ; Kim, Min-Sung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 5, 2015, Pages 396~404
DOI : 10.5139/JKSAS.2015.43.5.396
The UAV's wing has high aspect ratio that is suitable for the high altitude and long endurance. Knowing the real-time deformation of wing structure in flight, it can be utilized in structural health and loading status monitoring, improvement of control effectiveness and extraordinary vibration phenomena using displacement-strain relationship. In this paper, nonlinear displacement prediction algorithm was developed for prediction of large structural deflection in flight. The algorithm was validated through the comparison with finite element analysis results and also experimental results for several large tip displacements of cantilever beam. The predicted displacements using strains are agreed well with the measured values from laser displacement sensor.
Airspeed Estimation of Course Correction Munitions by Using Extended Kalman Filter
Sung, Jaemin ; Kim, Byoung Soo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 5, 2015, Pages 405~412
DOI : 10.5139/JKSAS.2015.43.5.405
This paper represents a filter design to estimate the airspeed of a spin-stabilized, trajectory-correctible artillery ammunition. Due to the limited power and space in operational point of view, the airspeed sensor is not installed, and thus the airspeed need to be estimated using limited sensor measurements. The only IMU measurements(three-axis specific forces and angular rates) are used in this application. The extended Kalman filter algorithm is applied since a linear filter can not cover the its wide operational range in airspeed and altitude. In the implementation of the EKF, the state and measurement equations are transformed into the no-roll frame for simple form of Jacobian matrix. The simulation study is conducted to evaluate the performance of the filter under various environment conditions of sensor noise and wind turbulence. In addition, the effect of the choice in filter design parameters, i.e. process error covariance matrices is analyzed on the performance of the estimation of airspeed and angular rates.
Analysis on Mission Lifetime and Collision Avoidance of Cubesat Launched from ISS
Yeom, Seung-Yong ; Kim, Hongrae ; Chang, Young-Keun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 5, 2015, Pages 413~421
DOI : 10.5139/JKSAS.2015.43.5.413
Since the first Cubesat was launched in 2003, there have been more than 230 Cubesats launched so far. Due to their small size and lightweight, Cubesats were launched by utilizing the empty space of regular launch vehicle. However, this launch method has a weakness that has been easily affecting by the schedule of major payloads. As a new solution to this problem, it has been proposed that a robot arm installed on ISS would be used to launch Cubesats. The orbits of Cubesat deployed from the ISS in various angles and directions are analyzed in this paper. We also analyze the possibility of collision between the Cubesat and ISS within the operational orbit of the CubeSat and eventually calculate the optimal angle of a robot arm, which maximizes the lifetime of Cubesat and minimizes the risk of collision between the Cubesat and ISS.
An Experimental Study for Construction of Static Aerodynamics Database of KF-16 based on Design of Experiments
Jin, Hyeon ; Shim, Ho-Joon ; Lee, Don-Goo ; Ahn, Jae-Myung ; Choi, Han-Lim ; Oh, Se-Yoon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 5, 2015, Pages 422~431
DOI : 10.5139/JKSAS.2015.43.5.422
Wind tunnel testing to construct static aerodynamic database of KF-16 was conducted for preceding research of design of experiments in wind tunnel testing. The test model is KF-16 scaled 1/33 and it has horizontal tail, flaperon, and rudder. The experiments consist of one experiment for analyzing aerodynamic coefficients under whether or not horizontal tail is present and four experiments for analyzing aerodynamic coefficients of changes of deflection angle in control surface which are flap, flaperon, rudder, and horizontal tail. After conducting wind tunnel testing, the experimental results show that the control surface changes have a great effect on Aerodynamic characteristics.
Structural Design and Verification of MEMS Solid Thruster for CubeSat Application
Jang, Su-Eun ; Han, Sung-Hyeon ; Kim, Tae-Gyu ; Lee, Jong-Kwang ; Jang, Tae-Seong ; Oh, Hyun-Ung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 5, 2015, Pages 432~439
DOI : 10.5139/JKSAS.2015.43.5.432
MEMS solid thruster module is composed of solid thruster and its control board. It was developed for the purpose of an academic research. Therefore, thermo-mechanical design and verification for space usage were not considered in the design phase. To mount it on a cube satellite without any design modification, technical efforts at the system level structure design is required. In this study, we proposed a structural design concept to mount the MEMS thruster module by using brackets for guaranteeing structure safety under launch loads and easier mating and de-mating of MEMS thruster module during test phase. The effectiveness of the design has been verified through structural analysis and vibration test. In addition, electrical connection method using spring pins between MEMS thruster and control board is effective for guaranteeing the structural safety under launch vibration loads.
Prelinimary Engagement Effect Analysis of Isotropic Kinetic Energy Warhead
Shim, Sang-Wook ; Hong, Seong-Min ; Seo, Min-Guk ; Tahk, Min-Jea ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 5, 2015, Pages 440~448
DOI : 10.5139/JKSAS.2015.43.5.440
Kinetic energy(KE) rod warhead system is a new interceptor which combines advantages of existing ones. This system is less dependant on a precision guidance than direct hit type warhead and gives high penetration rates than blast fragmentation type warhead. In this paper, isotropic KE rod warhead system is introduced with detonation/deployment model. A penetration effects of the deployed rods are calculated using TATE penetration equation. Also, an engagement performance analysis method is suggested. Finally, an optimal detonation time and engagement geometry is derived by Monte-Carlo simulation in various engagement situation using the performance analysis factor.
Built-In-Test Coverage Analysis Considering Failure Mode of Electronics Components
Seo, Joon-Ho ; Ko, Jin-Young ; Park, Han-Joon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 5, 2015, Pages 449~455
DOI : 10.5139/JKSAS.2015.43.5.449
Built-In-Test(hereafter: BIT) is necessary functionality for aircraft flight safety and it requires a high failure detection capacity of more than 95 % in the case of avionics equipment. The BIT coverage analysis is needed to make sure that BIT meets its fault diagnosis capability. FMECA is used a lot of for the BIT coverage analysis. However, in this paper, the BIT coverage analysis based on electronic components is introduced to minimize the analytical error. Further, by applying the failure mode of the electronic components and excluding electronic components that do not affect flight safety, the BIT coverage analysis can be more accurate. Finally, BIT demo was performed and it was confirmed that the performance of the actual BIT matches the analysis of BIT performance.
Technology Review and Development Trends of Dual-Bell Nozzle for Altitude Compensation
Choi, Junsub ; Huh, Hwanil ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 5, 2015, Pages 456~465
DOI : 10.5139/JKSAS.2015.43.5.456
Dual-bell nozzle can overcome the performance losses of the conventional bell-shaped nozzles which induced by off-design operations with either over-expanded or under-expanded exhaust flow and minimize the losses of the specific impulse. In United States, Rocketdyne analyzed thrust characteristics according to the shape of the expansion nozzle and NASA conducted hot firing tests with various altitudes. DLR, which is one of the research institute of the Europe, is carrying out research for the different cases of inflection angle, nozzle length and expansion ratio. MAI of Russia applied the slot nozzle to the expansion region in order to reduce the performance losses. In Asia, both the Japan and the India are researching on the dual-bell nozzle and Mitsubishi cooperation of the Japan registered its patent. In this paper, concepts and performance of dual-bell nozzle, which can compensate altitude, are investigated and trends of current research are summarized. It is necessary for Korea to research on the dual-bell nozzle for lucrative space development.
Design Technique for Wide Swath SAR TOPS imaging Mode
Kim, Se-Young ; Sung, Jin-Bong ; Yi, Dong-Woo ; Shim, Sang-Heun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 5, 2015, Pages 466~471
DOI : 10.5139/JKSAS.2015.43.5.466
In this paper, the design technique of the wide swath TOPS(Terrain Observation by Progressive Scan) imaging mode is introduced. The TOPS mode overcomes the scalloping limitations imposed by ScanSAR mode by steering the antenna pattern along track direction during the acquisition of a burst. This paper reports the operation concept of TOPS imaging and mode design result to extract the SAR operational parameters. Finally, several analyzed results such as IRF(Impulse Response Function), NESZ(Noise Equivalent Sigma Zero) and DTAR(Distributed Target Ambiguity Ratio) are presented.
Design of the Active Optical Compensation Movements for Image Stabilization of Small Satellite
Hwang, Jai Hyuk ; Yang, Ji Youn ; Park, Jean Ho ; Jo, Jeong Bin ; Kang, Myoung Soo ; Bae, Jae Sung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 5, 2015, Pages 472~478
DOI : 10.5139/JKSAS.2015.43.5.472
This paper describes the design of the active optical compensation movements(at focal plane, secondary mirror) for the image stabilization of a small satellite camera. The movements can correct optical misalignment on-line and directly compensate vibration disturbances in the focal plane. Since the devices are installed inside the space camera, it has an remarkable advantage to deal with the structural deformation of a space camera effectively. In this paper, the requirements of the active optical compensation movements for 1m GSD small satellite camera have been analyzed. Based on the established requirements, the design of the active compensation movements have been conducted. The designed active optical compensation system can control 5 axes movements independently to compensate micro-vibration disturbances in the focal plane and to refocus the optical misaligned satellite camera.