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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
Definition of Impact Angle and Impact Angle Control Law Against Maneuvering Target
Kim, Hyun-Seung ; Park, Sang-Sup ; Ryoo, Chang-Kyung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 8, 2015, Pages 669~676
DOI : 10.5139/JKSAS.2015.43.8.669
In this paper, a guidance law for intercepting maneuvering target with a desired impact angle is proposed. The proposed guidance law is modified from the optimal impact angle control law for a fixed target and given by a biased PN law with the impact angle control term in addition to the conventional PN law. Three different kinds of desired impact angles in the respect of LOS angle, flight path angle, and relative flight path angle to the target are defined. The performance of the proposed guidance law is investigated via numerical simulations for various air-to-air engagement scenarios.
Flow Visualization by Light Emission in the Post-chamber of Hybrid Rocket
Park, Kyung-su ; Choi, Go Eun ; Lee, Changjin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 8, 2015, Pages 677~683
DOI : 10.5139/JKSAS.2015.43.8.677
Hybrid rocket combustion displays low frequency instability(LFI, 10~30Hz) at a certain condition. Vortex shedding in the post-chamber is suspected to cause the occurrence of LFI. This study focused on the visualization of flow image using light emissions from high temperature combustion gas. Results shows that combustion pressure oscillates at a frequency of about 18 Hz, which is in phase with oscillations of light emission. Since LFI is not a property of thermo-acoustic instability, this result suggested there exists a physical coupling of pressure fluctuations with light emissions proportional to chemical reaction. Also POD analysis shows that dominant symmetric spatial modes in the stable combustion shift suddenly into asymmetric spatial pattern with the appearance of LFI. Especially, the appearance of mode 3 is a typical change of flow dynamics in unstable combustion representing a rotational fluid motions associated with vortex shedding.
A Sudden Increase in Combustion Pressure of Gas Generator of Ducted Rocket by Thermal Choking
Kim, Doyeong ; Shin, Kyung-Hoon ; Lee, Changjin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 8, 2015, Pages 684~691
DOI : 10.5139/JKSAS.2015.43.8.684
A sudden increase in combustion pressure is observed in the ducted rocket combustion test equipped with pipe shaped and converging nozzle exhaust tubes. This study aims to understand the physical mechanism of abrupt change in combustion pressure using thermal choking in the exhaust tube. Results confirmed that the thermal choking of the flow inside the exhaust tube was responsible for the sudden increase in combustion pressure. Also, high pressure exponent of solid propellants is critical sensitive to the occurrence of thermal choking exhaust pipe. Additionally, numerical simulation showed that the sudden increase in combustion pressure was less possible in diverging pipe because thermal choking is more reluctant to occur.
Preliminary Study on Interplanetary Trajectory Design using Invariant Manifolds of the Circular Restricted Three Body Problem
Jung, Okchul ; Ahn, Sangil ; Chung, Daewon ; Kim, Eunkyou ; Bang, Hyochoong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 8, 2015, Pages 692~698
DOI : 10.5139/JKSAS.2015.43.8.692
This paper represents a trajectory design and analysis technique which uses invariant manifolds of the circular restricted three body problem. Instead of the classical patched conic method based on 2-body problem, the equation of motion and dynamical behavior of spacecraft in the circular restricted 3-body problem are introduced, and the characteristics of Lyapunov orbits near libration points and their invariant manifolds are covered in this paper. The trajectories from/to Lyapunov orbits are numerically generated with invariant manifolds in the Earth-moon system. The trajectories in the Sun-Jupiter system are also analyzed with various initial conditions in the boundary surface. These methods can be effectively applied to interplanetary trajectory designs.
Structural analysis of flexible wing using linear equivalent model
Kim, Sung Joon ; Kim, Dong Hyun ; Lim, Joosup ; Lee, Sang Wook ; Kim, Tae-Uk ; Kim, Seungho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 8, 2015, Pages 699~705
DOI : 10.5139/JKSAS.2015.43.8.699
Aircraft needs high lift-to-drag ratio and weight reduction of the structure for long endurance flight with a small power. Generally high aspect ratio wing is applied to HALE(High Altitude Long Endurance) aircraft. Also high modulus, and high strength CFRP(Carbon Fiber Reinforced Plastic) has been used in primary structures. and thin mylar(membrane material) film has been applied to skin of wing. As a result, wing is more flexible than the other structures. and the stiffness of thin mylar film has an affect on dynamic stability. In this study, the membrane characteristic of mylar film has been simulated using nonlinear gap elements. And equivalent modeling method using shell elements is presented using the nonlinear simulation result. The linear equivalent model has verified using the results of nonlinear membrane method. Proposed linear equivalent shell model has applied to mode analysis for estimate the effect of mylar mechanical properties on natural frequency.
A Study on Improvement of Roll Autopilot System
Kim, Chong-Sup ; Koh, Gi-Oak ; Ji, Chang-Ho ; Cho, In-Je ; Lee, Dong-Kyu ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 8, 2015, Pages 706~711
DOI : 10.5139/JKSAS.2015.43.8.706
The fighter aircraft uses several different loading configurations for air-to-surface and air-to-air combat missions. To maintain wings-level flight with an asymmetric weapon configuration, a pilot controls a roll trim system. However, it is difficult to apply an accurate roll trim input for wings-level flight in the actual flight under disturbance. The inaccurate roll trim input degrades the performance of the roll autopilot system. In this paper, to solve this problem, an integrator was additionally designed in the command part of the roll autopilot system. The initial transient response was improved by scheduling the limiter to restrict the roll attitude error. As a result of the evaluation of the simulation for the designed flight control law, the roll attitude following performance was found to be improved in the autopilot system operation under the inaccurate roll trim condition.
Research Activities on Subsystem Technologies of PDE Propulsions
Jin, Wan-Sung ; Kim, Ji-Hoon ; Hwang, Won-Sub ; Kim, Jeong-Min ; Choi, Jeong-Yeol ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 8, 2015, Pages 712~721
DOI : 10.5139/JKSAS.2015.43.8.712
Pulse Detonation Engine (PDE) has been considered as a future propulsion system for broad range of operation and higher thermal efficiency. Various subsystem technologies have been studied for more than decade to improve the performance of the potential system. New valve systems has been developed for the stable operation at high frequency including inflow-driven valve, rotary valve and valveless system. To foster the detonation initiation with a little ignition energy, plasma ignition method and DDT (deflagration to detonation transition) acceleration method such as swept ramp mechanism have been studied. Fluidic nozzle system and other nozzle system are the ongoing research topics to maximize the propulsion performance of the PDE. Present paper introduces the state of the art of PDE subsystem technologies developed in recent years.
Study on Coupling Drive Mechanism for Multi-Axis Pintle Thrusters
Lee, Jaecheong ; Huh, Hwanil ; Lee, Hosung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 8, 2015, Pages 722~730
DOI : 10.5139/JKSAS.2015.43.8.722
Drive mechanism of multi-axis pintle thrusters for DCS(Divert Control System) was designed to meet the needs of minimizing the number of driving motors. In this study, preliminary model was designed in order to implement appropriate pressure control and thrust distribution. Based on the preliminary model study, the drive mechanism for DCS multi-axis pintle thrusters using piston was designed and evaluated by using AMESim software. Results show that three driving motors are enough to actuate four pintle thrusters.
A Design of Helicopter Control Law Rapid Prototyping Process Using HETLAS
Yang, Chang Deok ; Jung, Ho-Che ; Kim, Chang-Joo ; Kim, Chong-Sup ; Kim, Cheol-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 8, 2015, Pages 731~738
DOI : 10.5139/JKSAS.2015.43.8.731
The rapid prototyping process and development tool which enable the control law evaluation efficiently are needed to minimize the development cycle, cost and risk of aircraft flight control system. This paper describes a development process that integrates the designed control law into HETLAS to evaluate simulation effectively using nonlinear mathematical models. The desktop engineering simulator was developed using HETLAS for the piloted simulation evaluation of a various control modes and the procedure was developed, which quickly integrates the HETLAS into HQS(Handling Quality Simulator) and HILS(Hardware In the Loop Simulation) environments. This paper presents a rapid prototyping process using HETLAS that significantly shortens the integration process of the control law into the nonlinear math model, HETLAS, and allows the control law designs to be quickly tested in the piloted simulation and HILS environments.
Human-in-the-Loop Simulation Analysis of Conflict Resolution Maneuvers Using an Air Traffic Control Simulator
Jeong, Se hun ; Oh, Hyeju ; Choi, Keeyoung ; Lee, Hak-Tae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 8, 2015, Pages 739~747
DOI : 10.5139/JKSAS.2015.43.8.739
With rapid growth in the technologies and demand of Remotely Piloted Aircraft Systems (RPASs), integration of such systems into the existing airspace system is becoming an issue in many countries. RPAS have different flight performances, communication characteristics, separation assurance mechanisms, and human machine interfaces from manned aircraft. To establish rules and regulations for RPAS integration, it is important to understand the impacts of RPASs on the airspace system. A simulation system that integrates manned aircraft, air traffic control, and RPASs is developed in Inha University to investigate these impacts through Human-in-The-Loop (HiTL) simulations. Three conflict resolution scenarios between a manned aircraft and a Remotely Piloted Aircraft (RPA) were constructed and tested. Human factors such as the response times of pilots and controllers were measured and analyzed as well as the risk of each maneuver.
A Development of Real Time Video Compression System Based on Embedded Motion JPEG 2000 Using ADV212 and FPGA
Yu, Jae Taeg ; Ra, Sung Woong ; Hyun, Myung Han ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 8, 2015, Pages 748~756
DOI : 10.5139/JKSAS.2015.43.8.748
In this paper, we developed a miniaturized real time video compression system satisfying the military environment using ADV212 and FPGA. We present an efficient hardware design scheme for the weight reduction of the device and also a software solution to deal with noisy image signals. Experimental results show that the frame delay is reduced by a factor of 2 or 3 and the device`s weight is decreased by a factor of 6 to 7. In order to prove the reliability for the military usage of this development, we examine the environmental test (MIL-STD-810G) and EMI test (MIL-STD-461F). Experimental results show that the developed system satisfies the requirements.
On the Experimental Modeling of Focal Plane Compensation Device for Image Stabilization of Small Satellite
Kang, Myoung-Soo ; Hwang, Jai-Hyuk ; Bae, Jae-Sung ; Park, Jean-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 8, 2015, Pages 757~764
DOI : 10.5139/JKSAS.2015.43.8.757
Mathematical modeling of focal plane compensation device in the small earth-observation satellite camera has been conducted experimently for compensation of micro-vibration disturbance. The PZT actuators are used as control actuators for compensation device. It is quite difficult to build up mathematical model because of hysteresis characteristic of PZT actuators. Therefore, the compensation device system is assumed as a
order linear system and modeled by using MATLAB System Identification Toolbox. It has been found that four linear models of compensation device are needed to meet 10% error in the input frequency range of 0~50Hz. These models describe accurately the dynamics of compensation device in the 4 divided domains of the input frequency range of 0~50Hz, respectively. Micro-vibration disturbance can be compensated by feedback control strategy of switching four models appropriately according to the input frequency.