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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 44, Issue 9 - Sep 2016
Volume 44, Issue 8 - Aug 2016
Volume 44, Issue 7 - Jul 2016
Volume 44, Issue 6 - Jun 2016
Volume 44, Issue 5 - May 2016
Volume 44, Issue 4 - Apr 2016
Volume 44, Issue 3 - Mar 2016
Volume 44, Issue 2 - Feb 2016
Volume 44, Issue 1 - Jan 2016
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Effects of Time-Varying Mass on the Dynamic Behavior of a Descending Parachute System
Jang, Woo-Young ; Baek, Sang-Tae ; Myong, Rho-Shin ; Jin, Yeon-Tae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 4, 2016, Pages 281~289
DOI : 10.5139/JKSAS.2016.44.4.281
Accurate prediction of the trajectory and time of a time-varying mass parachute system remains essential in the mission requiring a precision airdrop to the ground. In this study, we investigate the altitude-varying behavior of a cross-type parachute system designed to deliver a time-varying mass object like flare. The dynamics of the descending parachute system was analyzed based on the Runge-Kutta method of the ordinary differential system. The drag coefficients of the cross-type parachute and flare were calculated by a CFD code based on the incompressible Navier-Stokes equation. Finally, by using a simplified gust wind model in troposphere, the combined effects of gust wind and time-varying mass were examined in detail.
LES on breakup and atomization of a liquid jet into cross turbulent flow in a rectangular duct
Yoo, Young-Lin ; Han, Doo-Hee ; Sung, Hong-Gye ; Jeon, Hyuk-Soo ; Park, Chul-Hyun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 4, 2016, Pages 290~297
DOI : 10.5139/JKSAS.2016.44.4.290
A two-phase Large Eddy Simulation(LES) has been conducted to investigate breakup and atomization of a liquid jet in a cross turbulent flow in a rectangular duct. Gas-droplet two-phase flow was solved by a coupled Eulerian-Lagrangian method which tracks every individual particles. Effects of liquid breakup models, sub-grid scale models, and a order of spatial discretization was investigated. The penetration depth in cross flow was comparable with experimental data by varying breakup model and LES scheme. SMD(Sauter Mean Diameter) distribution downstream of jet was analyzed.
Attitude determination of cubesat during eclipse considering the satellite dynamics and torque disturbance
Choi, Sung Hyuk ; Kang, Chul Woo ; Park, Chan Gook ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 4, 2016, Pages 298~307
DOI : 10.5139/JKSAS.2016.44.4.298
Attitude determination of satellite is categorized by deterministic and recursive method. The recursive algorithm using Kalman filter is widely used. Cubesat has limitation for payload to minimize then only two attitude sensors are installed which are sun sensor and magnetometer. Sun sensor measurements are useless during eclipse, however cubesat keeps estimating attitude to complete the successful mission. In this paper, Attitude determination algorithm based on Kalman filter is developed by additional term which considering the dynamics for SNUSAT-1 with disturbance torque. Verification of attitude accuracy of the algorithm is conducted during eclipse. Attitude determination algorithm is simulated to compare the performance between typical method and proposed algorithm. In addition, Attitude errors are analysed with various magnitude of disturbance torque caused by space environment.
Vibration-Robust Adaptive Attitude Reference System Using Sequential Measurement Noise Covariance
Kim, Jongmyeong ; Leeghim, Henzeh ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 4, 2016, Pages 308~315
DOI : 10.5139/JKSAS.2016.44.4.308
A new technique for Attitude & Heading Reference System (AHRS) by using sequential measurement noise covariance (SMNC) is addressed in a vibration environments in this paper. In particular, a low-cost inertial measurement unit in general diverges in the acceleration phase or vibrating environments due to inherent properties of gravity and acceleration. In this paper, by considering current and prior measurements to estimate actual attitudes and headings in a local frame, the proposed technique overcomes these problems efficiently. Finally, the performance of the suggested approach is verified by numerical simulations.
A Study on UAV Flight Control System HILS Test Environment
Byun, Jinku ; Hur, Gi-Bong ; Lee, KwangHyun ; Suk, Jinyoung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 4, 2016, Pages 316~323
DOI : 10.5139/JKSAS.2016.44.4.316
A UAV(Unmanned Aerial Vehicle) flies along pre-programed navigation points(in-flight, take-off, or landing) automatically without pilot input. Even though UAVs fly differently from general piloted aircraft as the pilot controls the aircraft from a ground station through means of a data-link system. Occasionally, the data-link connection can be lost for any number of reasons, in which case, the FLCC(Flight control Computer) must automatically switch to autopilot to continue flying. Hence, the FLCC is a flight-critical component that must be throughly tested and validated. This paper discusses the development of a HILS(Hardware in the Loop Simulation) test environment designed to simulate real flight conditions to verify the FLCC satisfies flying quality requirements and maintains robustness despite any potential malfunctions or emergency situations.
Look-Angle-Control Homing Loop Design with a Strapdown Seeker and Single Gyroscope
Hong, Ju-Hyeon ; Park, Kuk-Kwon ; Park, Sang-Sup ; Ryoo, Chang-Kyung ; Cho, Han-Jin ; Cho, Young-Ki ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 4, 2016, Pages 324~332
DOI : 10.5139/JKSAS.2016.44.4.324
In this paper, the terminal homing loop with a IIR-type strapdown seeker and a roll rate gyroscope is proposed. Basically, the proposed homing loop is based on the look-angle-control guidance. Since the range of the seeker is strictly limited, the missile is delivered to a point to lock the target on the seeker via non-guided flight during the midcourse guidance. The non-standard firing table is developed to compensate the wind and the target movement. To secure the delay margin is very important to prevent the instability of the homing loop when the time delay of the seeker is included. To validate the proposed homing loop, the 6-DOF nonlinear simulation is performed, and the Monte-Carlo simulation is also done for checking the robustness for the various kinds of uncertainty.
Numerical Study of Chemical Reaction for Liquid Rocket Propellant Using Equilibrium Constant
Jang, Yo Han ; Lee, Kyun Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 4, 2016, Pages 333~342
DOI : 10.5139/JKSAS.2016.44.4.333
Liquid rocket propulsion is a system that produces required thrust for satellites and space launch vehicles by using chemical reactions of a liquid fuel and a liquid oxidizer. Monomethylhydrazine/dinitrogen tetroxide, liquid hydrogen/liquid oxygen and RP-1/liquid oxygen are typical combinations of liquid propellants commonly used for the liquid rocket propulsion system. The objective of the present study is to investigate useful design and performance data of liquid rocket engine by conducting a numerical analysis of thermochemical reactions of liquid rocket propellants. For this, final products and chemical compositions of three liquid propellant combinations are calculated using equilibrium constants of major elementary equilibrium reactions when reactants remain in chemical equilibrium state after combustion process. In addition, flame temperature and specific impulse are estimated.
LES Investigation on The Cryogenic Nitrogen Injection of Swirl Injector Under Supercritical Envionment
Kang, JeongSeok ; Heo, JunYoung ; Sung, Hong-Gye ; Yoon, YoungBin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 4, 2016, Pages 343~351
DOI : 10.5139/JKSAS.2016.44.4.343
Cryogenic spray characteristics of a nitrogen swirl injector operating in supercritical environment have been numerically investigated. By comparing the equation of states(EOS) used for supercritical condition, SRK EOS was applied to predict the nitrogen thermodynamic property under supercritical environment. A Chung`s method was implemented for the calculation of viscosity and conductivity and Takahashi`s correlation based on Fuller`s Theorem was implemented for the calculation of diffusion coefficient. By injecting the nitrogen with 5 bar differential pressure into 50 bar chamber filled with nitrogen, numerical simulation has been conducted. The dynamic Smagorinsky sub-grid scale (SGS) model has been compared with the algebraic Smagorinsky SGS model using FFT frequency analysis. The instability at the liquid film and gas core inside injector and the propagation of pressure oscillation into the injector has been investigated. The spreading angle of swirl injector obtained by numerical calculation has been validated with experimental result.
A Study of the Disposal Maneuver Planning for LEO Satellite
Seong, Jae-Dong ; Kim, Hae-Dong ; Choi, Ha-Yeon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 4, 2016, Pages 352~362
DOI : 10.5139/JKSAS.2016.44.4.352
In this paper, a disposal maneuver which complies the space debris mitigation guideline was analysed for KOMPSAT-2 as an example of LEO satellite. Definition of disposal altitude which comply the `25 year rule`, re-entry survivability analysis of KOMPSAT-2 parts inside and casualty area analysis were performed using STK and ESA`s DRAMA. Finally, assuming that there were several survival objects during uncontrolled re-entry stage, the re-entry initial orbit elements which show the low casualty probability were found even if there were various uncertainties about the initial orbit. As a result, KOMPSAT-2 should be descended its altitude at least 43km or up to 105km to comply `25 year rule` and there were heavy or heat resistant survival objects which generated
casualty area. And if RAAN of re-entry initial orbit was 129 degree, total casualty probability was lower than standard value of space debris mitigation guideline even if there were uncertainties about the initial orbit.
Development of Flight Software for SIGMA CubeSat
Lee, Jeongho ; Lee, Seongwhan ; Lee, JungKyu ; Lee, Hyojeong ; Shin, Jehyuck ; Jeong, Seonyeong ; Oh, YoungSeok ; Jin, Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 4, 2016, Pages 363~372
DOI : 10.5139/JKSAS.2016.44.4.363
SIGMA(Scientific cubesat with Instruments for Global Magnetic field and rAdiation) CubeSat has been developed for magnetic field measurement of the Earth and space radiation measurement at Kyung Hee university. The flight software plays important roles in controlling the satellite and processing the data in the space mission. In this paper, the Flight Software has been implemented to process all the tasks in the one thread without RTOS(Real Time Operating System). This is an effective mothed not only to concentrate the space mission of CubeSat but also to reduce the overhead of the Flight Software by considering the mission perform procedures and the system control methods.
Numerical Study on the Thermal Control Device for Satellite Components Using the Phase Change Material Combined with Heat Pipe in Parallel
Shin, Yoon Sub ; Kim, Tae Su ; Kim, Taig Young ; Seo, Young Bae ; Seo, Jung-gi ; Hyun, Bum-Seok ; Cheon, Hyeong Yul ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 4, 2016, Pages 373~379
DOI : 10.5139/JKSAS.2016.44.4.373
The thermal control device for the periodic working component combined solid-liquid phase change material (PCM) with heat pipes is designed and numerically studied. Due to high latent heat and retaining constant temperature during melting process the component peak temperature, not withstanding small radiator size, is reduced. The warm-up heater power consumption to keep the minimum allowed temperature is also cut down since the accumulated thermal energy is released through the solidification. The thermal buffer mass (TBM) made of Al can give the similar effect but the mass and power consumption of warm-up heater should increase compared to PCM. The amount of PCM can be optimized depending on the component heat dissipation and on/off duty time.