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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 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
Selecting the target year
Experimental Study of the Quantitative Characteristics of Fluidic Thrust Vectoring Nozzle for UAV
Park, Sang-Hoon ; Lee, Yeol ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 9, 2014, Pages 723~730
DOI : 10.5139/JKSAS.2014.42.9.723
Experimental study for supersonic co-flowing fluidic thrust vectoring control utilizing the secondary flow is performed. The characteristics of the thrust vectoring of two dimensional supersonic flow (Mach 2.0) are studied by Schlieren flow visualization and highly-accurate multi-component force measurements using the load cells. It is observed that the thrust deflection angle initially decreases and increases again forming a V-shaped variation as the pressure of the secondary flow increases. Characteristics of the performance coefficients of the system are also studied, and the detailed operating conditions for higher performance of the technique are suggested.
Sea Wave Modeling Analysis and Simulation for Shipboard Landing of Tilt Rotor Unmanned Aerial Vehicle
Yoo, Chang-Sun ; Cho, Am ; Park, Bum-Jin ; Kang, Young-Shin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 9, 2014, Pages 731~738
DOI : 10.5139/JKSAS.2014.42.9.731
The mission of UAV has been expanded from a land to an ocean based on an enhancement of its technologies. Korea Aerospace Research Institute (KARI) also tries to expand the mission of tilt rotor UAV to an ocean, in which the shipboard landing of UAV is required. However the environment of an oceanic operation is severer than that of land due to salty, fogy, and windy condition. The landing point for automatic landing is not fixed due to movement of shipboard in roll, pitch, and heave. It makes the oceanic operation and landing of UAV difficult. In order to conduct an oceanic operation of tilt rotor UAV, this paper presents that the sea wave modeling according to the sea state is conducted and the shipboard landing of tilt rotor UAV under the sea wave is tested and evaluated through the flight simulator for UAV.
An Interindustry Analysis Considering Complexity of Space Exploration Project
Lee, Eui-Kyung ; Hur, Hee-Young ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 9, 2014, Pages 739~744
DOI : 10.5139/JKSAS.2014.42.9.739
Space exploration project usually consists of so many fields of sub projects that it has a diverse ripple effect throughout the economy. Further studies could not consider the complexity of the space exploration project because they regarded it as one project in spite of the diversity. This study found a way to consider complexity of space exploration project using the concept of WAC(weighted average coefficient). The moon exploration project (2014~2020) is the subject of this study. We classified the moon exploration project into 8 industries and calculated the WAC of production inducement coefficient, value added inducement coefficient, and employment inducement coefficient. The result of analysis using these WACs is that production inducement effect amounts to 1,229.6 billion won, value added inducement effect 324.6 billion won, employment inducement effect 4,844 men. And the linkage effect analysis shows that moon exploration project has more backward linkage effect than forward linkage effect.
An Evaluation on Rupture Behavior of Nozzle Closure in Multi-Nozzle System
Ro, Young-Hee ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 9, 2014, Pages 745~751
DOI : 10.5139/JKSAS.2014.42.9.745
For the multi-nozzle propulsion, the rupture pressure of nozzle closure has an effect on the initial strain rate of ignition. Moreover, the deviation of rupture pressure for each nozzle closure leads to side forces which can disturb the attitude control of rocket. When designed, it should be considered whether nozzle closures are ruptured equally and exactly in the intented pressure. In this paper, the rupture behavior is analyzed by analytical and experimental methods for plate and "+" notched nozzle closures. The rupture pressure and deviation for operating temperature, whether notched or not and notched directions are analyzed. This paper provides a comparison between rupture pressure prediction of finite elements method which tool is Abaqus/Explicit and results of the rupture test. Jonson-Cook shear failure model which corresponds to the damage initiation criterion were used in this simulation.
Collision Avoidance Maneuver Design for the Multiple Indoor UAV by using AR. Drone
Cho, Dong-Hyun ; Moon, Sung Tae ; Jang, Jong Tai ; Rew, Dong-Young ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 9, 2014, Pages 752~761
DOI : 10.5139/JKSAS.2014.42.9.752
With increasing of interest in quad-rotor which has excellent maneuverability recently, a various types of multi-rotor aircraft was developed and commercialized, and there are many kinds of leisure products to be easily operated. In these products, the AR.Drone manufactured by Parrot has an advantage that it is easily operated by user due to the its internal stabilization loop in the on-board computer. Thus it is possible to design the unmanned UAV system easily by using this AR.Drone and its inner loop for the stabilization. For this advantage, KARI(Korea Aerospace Research Institute) has been developing the indoor swarming flight system by using multiple AR.Drones. For this indoor swarming flight, it is necessary that not only the position controller for each AR.Drone, but also the collision avoidance algorithm. Therefore, in this paper, the collision avoidance controller is provided for the swarm flight by using these AR.Drones.
Computation Algorithm for Dynamic Launch Zone of Air-to-Air Missiles
Park, Sang-Sup ; Kim, Do-Wan ; Hong, Ju-Hyeon ; Ryoo, Chang-Kyung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 9, 2014, Pages 762~772
DOI : 10.5139/JKSAS.2014.42.9.762
A weapon control algorithm equipped on a fighter is closely related to the mission accomplishment and fighter survivability during engagement. The weapon control algorithm typically provides a pilot the dynamic launch zone(DLZ), the target shoot-down range of air-to-air missiles, in the head-up display(HUD). DLZ is produced by an engagement range computation algorithm. In this paper, the components of DLZ for AIM-9 and AIM-120 air-to-air missiles are introduced. The real-time computation algorithm for DLZ based on the pseudo 6-DOF program is then addressed The operational aspects of DLZ algorithm for the air-to-air missiles to various engagement scenarios is investigated vis simulations.
A Research on the Application of Single Point Ground for Intercom of T-50 Advanced Trainer
Seok, Min Joon ; Nam, Yong Seok ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 9, 2014, Pages 773~778
DOI : 10.5139/JKSAS.2014.42.9.773
Aircraft communication system which provides internal communications between pilots in an aircraft and external communications between pilots and operators in ground tower with them. It is very important equipment in terms of mission and safety. It wouldn`t meet performance requirements with only functions of transmission and receiving of signals. It should provide highly clear voice quality without any noise. This paper analyzes the cause of noise during internal communications and summarizes the design changes applying single point ground concept to solve the problem. It also describes the results of fight test to verify the design changes.
Development of Fuzzy Logic-based MPPT and Performance Verification through EBA for Satellite Applications
Yeom, Seung-Yong ; Park, Ki-Yun ; Kim, Hong-Rae ; Chang, Young-Keun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 9, 2014, Pages 779~788
DOI : 10.5139/JKSAS.2014.42.9.779
The satellite should generate electric power efficiently to perform the mission successfully within limited power. For this reason, the electrical power system of LEO satellites usually regulates the power which is generated from the solar cells using MPPT (Maximum Power Point Tracking) method. This paper proposes advanced MPPT algorithm based on the fuzzy logic applied to small CubeSat satellite. The simulation has been performed to confirm the validity of the proposed method by interlocking between MATLAB/Simulink and STK (Systems Tool Kit). The EBA(Energy Balance Analysis) has also been performed at two different pointing modes of KAUSAT-5 for solar irradiation according to the satellite orbit and attitude, and load capacity varied with operation modes by Simulink and STK. The performance of fuzzy logic-based MPPT algorithm was verified through the EBA. The validity of the proposed MPPT algorithm based on the fuzzy logic was also confirmed by comparing with P&O (Perturbation & Observation) algorithm that is general in the MPPT.
Experimental Verification of Heat Sink for FPGA Thermal Control
Park, Jin-Han ; Kim, Hyeon-Soo ; Ko, Hyun-Suk ; Jin, Bong-Cheol ; Seo, Hak-Keum ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 9, 2014, Pages 789~794
DOI : 10.5139/JKSAS.2014.42.9.789
The FPGA is used to the high speed digital satellite communication on the Digital Signal Process Unit of the next generation GEO communication satellite. The high capacity FPGA has the high power dissipation and it is difficult to satisfy the derating requirement of temperature. This matter is the major factor to degrade the equipment life and reliability. The thermal control at the equipment level has been worked through thermal conduction in the space environment. The FPGA of CCGA or BGA package type was mounted on printed circuit board, but the PCB has low efficient to the thermal control. For the FPGA heat dissipation, the heat sink was applied between part lid and housing of equipment and the performance of heat sink was confirmed via thermal vacuum test under the condition of space qualification level. The FPGA of high power dissipation has been difficult to apply for space application, but FPGA with heat sink could be used to space application with the derating temperature margin.
On-orbit Thermal Analysis of Pico-class Satellite STEP Cube Lab. for Verification of Fundamental Space Technology
Kang, Soo-Jin ; Ha, Heon-Woo ; Oh, Hyun-Ung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 9, 2014, Pages 795~801
DOI : 10.5139/JKSAS.2014.42.9.795
STEP Cube Lab. classified as a pico-satellite has been being developed by SSTL(Space Technology Synthesis Laboratory) in Chosun University. Its main mission objective is to perform the on-orbit verification of core space technologies, which will be the potential candidates for future space missions. In this paper, to guarantee successful mission operation of the cube satellite under extremely severe space thermal environment condition, the system level thermal design and analysis has been performed. The effectiveness of the design has been verified through on-orbit thermal analysis of cube satellite.
On-orbit Thermal Control of MEMS Based Solid Thruster by Using Micro-igniter
Ha, Heon-Woo ; Kang, Soo-Jin ; Jo, Mun-Shin ; Oh, Hyun-Ung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 9, 2014, Pages 802~808
DOI : 10.5139/JKSAS.2014.42.9.802
MEMS based solid propellant thruster researched for the purpose of an academic research will be verified at space environment through CubeSat program. For this, the temperature of the MEMS thruster should be within allowable operating temperature range by proper thermal control to prevent the ignition failure caused by ignition time delay and to guarantee the structural safety of the MEMS thruster in the low temperature. In this study, we proposed an effective thermal control strategy, that is to use micro-igniter as a heater and temperature sensor for active thermal control instead of using additional heater. The effectiveness of the strategy has been verified through on-orbit thermal analysis of CubeSats with MEMS thruster.