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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
A Study on the Damage of Satellite caused by Hypervelocity Impact with Orbital Debris
Kang, Pil-Seong ; Im, Chan-Kyung ; Youn, Sung-Kie ; Lim, Jae-Hyuk ; Hwang, Do-Soon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 7, 2012, Pages 555~563
DOI : 10.5139/JKSAS.2012.40.7.555
In earth orbit, a great number of orbital debris move around in extremely high velocity, and they become serious threats to satellites. In this study, smoothed particle hydrodynamics(SPH) is used to analyze the damage of a low earth orbit satellite due to the hypervelocity impact with orbital debris. The damage of honeycomb sandwich panel(HC/SP) used for walls of a satellite is analyzed with respect to impact velocities. For the additional analysis to examine the safety of interior components of the satellite, an attached electronic box and an offset electronic box are considered. As a result of the analysis considering the orbital debris having a probability of collision more than 2% at altitude of 685km, it is shown that the HC/SP can be perforated but only small craters are formed on both the attached electronic box and the offset electronic box.
A Study on Composite Blades of 1 MW Class HAWT Considering Fatigue Life
Kim, Min-Woong ; Kong, Chang-Duk ; Park, Hyun-Bum ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 7, 2012, Pages 564~573
DOI : 10.5139/JKSAS.2012.40.7.564
In this work, 1 MW class horizontal axis wind turbine blade configuration is properly sized and analyzed using the newly proposed aerodynamic design procedure and the in-house code developed by authors, and its design results are verified through comparison with experimental results of previously developed wind turbine blade. The structural design of the wind turbine blade is carried out using a composite materials and the netting and rule of mixture deign methods. The structural safety of the designed blade structure is investigated through the various load cases, stress, deformation, buckling and vibration analyses using the commercial FEM code, MSC.NASTRAN. Finally the required fatigue life is investigated using the modified Spera`s experimental equation.
Dynamic Modeling and Stabilization of a Tri-Ducted Fan Unmanned Aerial Vehicles using Lyapunov Control
Na, Kyung-Seok ; Won, Dae-Hee ; Yoon, Seok-Hwan ; Sung, Sang-Kyung ; Ryu, Min-Hyoung ; Cho, Jin-Soo ; Lee, Young-Jae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 7, 2012, Pages 574~581
DOI : 10.5139/JKSAS.2012.40.7.574
Because of the exposed blade, the UAV using the rotors entail the risks during operation. While a wrapped duct around the fan blades reduces risks, it is a higher thrust performance than the same power load rotor. In this paper, for applying advantages of a ducted fan, the tri-ducted fan air vehicle configuration is proposed. The vehicle has three ducted fans. Two of them are the same shape and size and the third one is the smaller. It is possible to control a rapid attitude stability using thrust vector control. The equations of motion of the tri-ducted fan were derived. Lyapunov control input was applied to the system and stable inputs were derived. A nonlinear simulation was fulfilled by using parameters of a prototype vehicle. It verified a stable attitude and analyzed results.
Development of Car Type Classification Algorithm on the UAV platform using NCC
Jeong, Jae-Won ; Kim, Jeong-Ho ; Heo, Jin-Woo ; Han, Dong-In ; Lee, Dae-Woo ; Seong, Kie-Jeong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 7, 2012, Pages 582~589
DOI : 10.5139/JKSAS.2012.40.7.582
This paper describes the algorithm recognizing car type from the image received from UAV and the recognition results between three types of car images. Using the NCC(Normalized Cross-Correlation) algorithm, geometric information is matched from template images. Template images are obtained from UAV and satellite map and indoor experiment is performed using satellite map. After verification of the possibility, experiment for verification of same car type recognition is performed using small UAV. In the experiment, same type cars are matched with 0.6 point similarity and truck with similar color distribution is not matched with template image of a sedan.
Aircraft Sizing Methods for the Design of an Electrically Propelled Aircraft
Hwang, Ho-Yon ; Nam, Tae-Woo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 7, 2012, Pages 590~600
DOI : 10.5139/JKSAS.2012.40.7.590
In this research, generalized sizing methods were studied that can be applied to an aircraft which uses solar cell or fuel cell as energy sources. To consider multiple propulsion systems and energy resources, multiple power paths were modeled and the weight of consumable and non-consumable energy was reflected in the weight change calculation for each mission segments. In the constraint analysis, power to weight ratio was selected instead of thrust to weight ratio and used in the sizing process of balancing power and energy.
Crashworthy Design and Test of Landing Gear
Kim, Tae-Uk ; Lee, Sang-Wook ; Shin, Jeong-Woo ; Lee, Seung-Kyu ; Kim, Sung-Chan ; Hwang, In-Hee ; Jo, Jeong-Jun ; Lee, Je-Dong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 7, 2012, Pages 601~607
DOI : 10.5139/JKSAS.2012.40.7.601
The main function of a landing gear is to absorb the impact energy during touchdown. It it occasionally required for landing gear to have crashworthiness for improving survivability and safety in case of emergency landing. This paper introduces the design concept, performance analysis and drop test procedures for the development of the crashworthy landing gear. The shock absorbing ability and the crash behavior are proved by analyzing various sensor data and video clips from high speed camera recording during drop tests.
Design Verification of Environmental Control System by Flow Balance Test
Park, Dong-Myung ; Joung, Yong-In ; Moon, Woo-Yong ; Park, Sung-Sun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 7, 2012, Pages 608~615
DOI : 10.5139/JKSAS.2012.40.7.608
In this study, we analyzed the system impedance of Unmanned Aerial Vehicle avionics bay and Environmental Control System(ECS), and estimated the proper air flow rate to be supplied avionics equipments. As the result of estimation, we evaluated the performance of ECS after analysing the flow balance rate and the air flow rate about each outlet port, and simultaneously decided the flow balance rate after evaluating the thermal substantiality by the thermal analysis of avionics bay. In order to verify the property of analysis result, we conducted the flow balance test using the actual avionics equipments and finally deduced the flow rate to be met system requirements of avionics equipments. Also, as the analysis results, we verified the satisfaction of system requirements at midium altitude condition and proved the performance characteristics of an Environmental Control System(ECS).
A Study of Flare Operation Method for The Fighter with An External Center Fuel Tank
Kang, Chi-Hang ; Jang, Young-Il ; Kwon, Ky-Beom ; Yoon, Young-In ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 7, 2012, Pages 616~622
DOI : 10.5139/JKSAS.2012.40.7.616
In this paper, we examined the problems of the flare operation of tactic maneuvering flight of fighter aircraft with 150GL center external fuel tank and proposed the possible solution of it`s operation. The damage scope of horizontal fin of fuel tank and flare trajectory when the flare ejected from the maneuvering aircraft were analyzed by the wind tunnel test and the numerical analysis. We investigated the two different option to avoid the damage of fin; i) the adjustment of flare dispenser angle and ii) the change of horizontal fin`s shape. For the considering of practical operation of present system, we chose the second option. We estimated the drop safety of external fuel tank with redesigned fin by the wind tunnel experiments.
Design and Verification of Built In Test For KUH
Kim, Sung-Woo ; Lee, Byoung-Hwa ; Chang, Won-Hong ; Oh, Woo-Seop ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 7, 2012, Pages 623~628
DOI : 10.5139/JKSAS.2012.40.7.623
Mission Equipment Package(MEP) system is a collection of avionic components that are integrated to perform the mission of the Korean Utility Helicopter(KUH). Built In Test(BIT) reduces the need for skilled personnel and special test equipment, and reduces maintenance down-time of system. The increasing complexity of avionics equipments has resulted in an increased need to provide BIT functions. This paper describe the development and verification for the KUH MEP system BIT.
Performance Analysis of LEO Satellite GPS Receiver
Kwon, Ki-Ho ; Lee, Sang-Jeong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 7, 2012, Pages 629~635
DOI : 10.5139/JKSAS.2012.40.7.629
This paper presents a performance analysis of the GPS(Global Positioning System) receiver on board in LEO satellites, based on the comparison of its in-orbit performances and corresponding ground test results. An extensive ground tests on the subject GPS receiver has been performed in diverse conditions under the right frame of ground test environments and the analysis of in-orbit performances has also been performed with the huge amount of accumulated GPS data which has been in operation for 6 years since its launch on 2006. For this analysis, we chose three sets of in-orbit data; the data during the early mission period, the data at the 3-year mission completion time, and the most recent in-orbit data. As the performance measures, we selected the position and time synchronization accuracy, and the comparative analysis shows the concurrency between the in-orbit performances and the ground test results with in these performance measures, verifying the validity of the ground test. It is expected that the test configuration and analysis method presented in this paper can be applied to developing and verifying the future Koreanized satellite GPS receivers.
Very Small Satellite Program for Expending the Space Technology Base: CanSat Competition
Won, Su-Hee ; Jun, Hyoung-Yoll ; Kim, Sung-Hoon ; Lee, Sang-Ryool ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 7, 2012, Pages 636~645
DOI : 10.5139/JKSAS.2012.40.7.636
This paper presented the CanSat competition as one of very small satellite programs for expending the space technology base. The CanSat was compared and characterized with a real satellite and the foreign CanSat competition cases and domestic CanSat development trends were summarized. On the basis of the above information, the organizational structure and function were suggested for domestic CanSat competition and the required technologies, such as satellite, launcher and ground station were described. And also, the prior plan for competition, including mission, education and schedule were suggested.