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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 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
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Coupled Thermal/Structural Analysis of Mechanical Ablation by Domain/Boundary Decomposition Method
Shin, Eui-Sup ; Kim, Sung-Jun ; Kim, Jong-Il ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 1, 2011, Pages 1~8
DOI : 10.5139/JKSAS.2010.39.1.1
A coupled thermal/structural analysis of mechanical ablation is performed based on domain/boundary decomposition and finite element method. The ablative material non-linearity and boundary non-linearity can be easily localized within a few subdomains and/or on the boundary interfaces. An enthalpy method is applied to simplify the effect of heat of pyrolysis in the ablative subdomains. In addition, maximum in-plane shear stress is considered as a surface recession criterion for the mechanical ablation simulation. The basic characteristics of the proposed method are examined carefully through numerical experiments.
Experimental and Numerical Analysis for Superelastic Behaviors of SMAs with Strain-rate Dependence
Roh, Jin-Ho ; Park, Jeong-In ; Lee, Soo-Yong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 1, 2011, Pages 9~15
DOI : 10.5139/JKSAS.2010.39.1.9
The influence of the strain-rate on the superelastic behaviors of shape memory alloys (SMAs) wires is experimentally and numerically investigated. The one-dimensional SMA constitutive equations considering strain-rate effect is developed. The evolution of stress-strain curves of SMA wires is examined with various strain-rates. Results show that the superelastic behaviors of SMAs may significantly be changed depending on the variation of strain-rate.
Time-to-go Polynomial Guidance Law for Target Observability Enhancement
Kim, Tae-Hun ; Lee, Chang-Hun ; Tahk, Min-Jea ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 1, 2011, Pages 16~24
DOI : 10.5139/JKSAS.2010.39.1.16
In this paper, we propose a new guidance law for target observability enhancement, which can control both terminal impact angle and acceleration. The proposed guidance law is simple form, combined conventional time-to-go polynomial guidance and a additional bias term which consists of relative position and proportional gain. The guidance law provides oscillatory flight trajectory and it maintains the conventional time-to-go polynomial guidance performance. To investigate the characteristics of the guidance law, we derive the closed-form solution, and various simulations are performed for proving the validity of the proposed guidance.
Performance Improvement of Maneuvering Target Tracking with Radar Measurement Noise Estimation
Jeon, Dae-Keun ; Eun, Yeon-Ju ; Ko, Hyun ; Yeom, Chan-Hong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 1, 2011, Pages 25~32
DOI : 10.5139/JKSAS.2010.39.1.25
Measurement noise variance of the radar is one of the main inputs of a state estimator of surveillance data processing system for air traffic control and has influences on the accuracy performance of maneuvering target tracking. A method is presented of estimating measurement noise variances every frame of target tracking using likelihood functions of multiple IMM filter. The results by running of Monte Carlo simulation show that variances are estimated within 5% of errors compared with true values and the tracking accuracy performance is improved.
Missile Flight Condition for Slip-in Booster`s Safe Separation
Oh, Hyun-Shik ; Lee, Ho-Il ; Cho, Jin ; Kim, Ik-Soo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 1, 2011, Pages 33~41
DOI : 10.5139/JKSAS.2010.39.1.33
A mathematical model of slip-in booster separation dynamics is described. A longitudinal 3-DOF(degree of freedom) 2-body dynamic model is developed to simulate the separation dynamics. Aerodynamic models of the missile and the exposed area of booster are built. And, gas generator pushing the booster out and internal channel pressure drop are modelled. To simulate the model, it is assumed that the missile can maintain the 1g level-fight condition during the separation. With this assumption, the interaction forces between missile and booster through the separation phases: phase 0: initial, phase 1: linear translation, and phase 2: free flight motion are defined. Using the simulation, missile flight conditions for slip-in booster`s safe separation, which can be represented by Mach vs. height envelope, are suggested.
Performance Analysis of Maximum Data Rate for Telemetry Links in Space Communications for Lunar Explorations
Lee, Woo-Ju ; Yoon, Dong-Weon ; Lee, Jae-Yoon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 1, 2011, Pages 42~49
DOI : 10.5139/JKSAS.2010.39.1.42
Telemetry link requires high data rate to transmit the multimedia data for lunar explorations in space communications. In this paper, we analyze a data rate with the modulation and channel coding schemes based on Consultative Committee for Space Data Systems (CCSDS) in S, X, Ku and Ka bands, respectively. Then, we suggests modulation and channel coding schemes to meet the link margins and have a maximum data rate for lunar explorations in telemetry links.
Simultaneous Aero-Structural Design of HALE Aircraft Wing using Multi-Objective Optimization
Kim, Jeong-Hwa ; Jun, Sang-Ook ; Hur, Doe-Young ; Lee, Dong-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 1, 2011, Pages 50~55
DOI : 10.5139/JKSAS.2010.39.1.50
In this study, simultaneous aero-structural design was performed for HALE aircraft wing. The span and the shape of main spar were considered as design variables. To maximize aerodynamic performance and to minimize weight, multi-objective optimization was used. Nonlinear static aeroelastic analysis was performed to compute large deflection of wing. Design of experiment and response surface method were used to reduce computation cost in the design process. Also, aerodynamic performances of deformed wing and rigid wing were compared.
Design and Implementation of Carrier Recovery Loop for Satellite Telemetry and Tracking & Command
Lee, Jung-Su ; Oh, Chi-Wook ; Seo, Gyu-Jae ; Oh, Seung-Han ; Chae, Jang-Soo ; Myung, Noh-Hoon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 1, 2011, Pages 56~62
DOI : 10.5139/JKSAS.2010.39.1.56
A Satellite transponder is mounted on the Satellite and performs radio communications with the ground station. A Digital transponder compared to The analog transponder is made easy and accurate performance prediction. Also Modulation Scheme, Data Rate, Loop Bandwidth, Modulation Index and etc. can be changed on orbit, by implementing FPGA can reduce the weight and volume. The core technology of digital transponder is Carrier Recovery loop. Dynamic Range, Frequency Tracking Range, Frequency Tracking Rate and Coherent performance are determined by the performance of the Carrier Recovery loop. In this paper, we proposed the structure of Carrier Recovery loop for the Satellite digital transponder, then tested and verified the structure.
Design and Performance Analysis of DSP Prototype for High Data Rate Transmission of Lunar Orbiter
Jang, Yeon-Soo ; Kim, Sang-Goo ; Cho, Kyong-Kuk ; Yoon, Dong-Weon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 1, 2011, Pages 63~68
DOI : 10.5139/JKSAS.2010.39.1.63
Many countries all over the world have been doing lunar exploration projects. Korea has also been doing basic research on lunar exploration. The development of communication systems for lunar exploration projects is one of the most important aspects of performing a successful lunar mission. In this paper, we design a DSP (Digital Signal Processor) prototype based on the requirement analysis of a communication link for lunar exploration and implement its core module considering the international standards for deep space communications to perform a basic research on baseband processor development. It is verified by comparing the bit error rate of the DSP prototype with that of a computer simulation.
Implementation of Deferred NAK Mode Simulator for Large-Volume Telemetry Data Transmission in Deep Space Communication Systems
Hong, Hee-Jin ; Lee, Ju-Byung ; Yoon, Dong-Weon ; Hyun, Kwang-Min ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 1, 2011, Pages 69~75
DOI : 10.5139/JKSAS.2010.39.1.69
As part of its space development program, Korea has a plan for the launch of a lunar orbiter and a lunar lander. To enable the transmission of lunar information based on multimedia, it is necessary to construct a communication system that is capable of transmitting large-volume telemetry data. The CCSDS standard recommends the deferred NAK mode as ARQ scheme for reliable long-distance deep-space communication systems. In this paper, we implement a space communication system simulator in the deferred NAK mode using models of the lunar orbiter, the earth station, and the space environment. The simulator employs modulation techniques and turbo coding schemes for transmitting large-volume telemetry data. We analyze the transmission performance of telemetry data through the simulation.
A Study on the Thermal Design for A Signal Processor in the Micro-Wave Seeker
Lee, Won-Hee ; Yu, Young-Joon ; Kim, Ho-Yong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 1, 2011, Pages 76~83
DOI : 10.5139/JKSAS.2010.39.1.76
This paper focuses on the thermal design of a signal processor in Micro-Wave Seeker. High temperature environment and ESS(Environmental Stress Screening) test condition should be considered in designing a signal processor. First, we performed the thermal analysis to know conditions under which a signal processor is thermally reliable. As a result of thermal analysis, we found that adopting heat transfer block to the thermally fragile components is most efficient, because the heat transfer block can control the thermal loads of the individual components. Next, we verified this solution by numerical simulation and experiment and concluded that thermal reliability of a signal processor can be achieved. Maximum temperature difference between numerical simulation and experiment is about
Development of Xenon Feed System for a Hall-Effect Thruster to Space-propulsion Applications
Kim, Youn-Ho ; Kang, Seong-Min ; Jung, Yun-Hwang ; Seon, Jong-Ho ; Wee, Jung-Hyun ; Yoon, Ho-Sung ; Choe, Won-Ho ; Lee, Jong-Sub ; Seo, Mi-Hui ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 1, 2011, Pages 84~89
DOI : 10.5139/JKSAS.2010.39.1.84
A Xenon Feed System (XFS) has been developed for hall-effect thruster to small satellite space-propulsion system applications. The XFS delivers low pressure gas to the Anode and Cathode of thruster head unit from a xenon storage tank. Accurate throttling of the propellant mass flow rate is independently required for each channel of the thruster head unit. The mass flow rate to each channel is controlled using the accumulator tank pressure regulation through a micron orifice and isolation valve. This paper discusses the Xenon Feed System design including the component selections, performance estimation and functional test.
The Rubber Performance Evaluation for Kick Motor Flexible Seal
Kim, Byung-Hun ; Kwon, Tae-Hoon ; Cho, In-Hyun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 1, 2011, Pages 90~95
DOI : 10.5139/JKSAS.2010.39.1.90
A Kick Motor, KSLV-I second stage propulsion system, utilizes a flexible seal for pitch and yaw axis controls during combustion. A flexible seal consists of the alternate laminate of rubber and composite reinforcement between forward and aft rings. A Kick Motor nozzle is rotated by the shear deformation of rubber layers. Consequently, the development of rubber, which is appropriate to the usage condition of flexible seal, is very important. A tensile test, QLS test (shear modulus and failure shear stress), and aging test have been carried out to confirm the performance of rubber developed. Test results show that the shear modulus of rubber are 0.4310 ~ 0.4997MPa and the failure shear stress is more than 2.5MPa.