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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
Study on Reflected Pressure in a Shock Tunnel According to the Size of a Nozzle Throat
Lee, Jong Kook ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 6, 2015, Pages 479~487
DOI : 10.5139/JKSAS.2015.43.6.479
In a reflected shock tunnel, stagnation conditions of a nozzle are determined by the flow behind a reflected shock. When calculating the flow behind the reflected shock, unlike a shock tube, the flow leakage through the nozzle is to be considered. The analytical studies were done to find out the characteristics of the stagnation conditions of the nozzle with various nozzle throat size. Experiments and numerical simulations were also carried out for further understanding of the flow leakage effects. It was found that the nozzle stagnation pressure was diminished by the increase of the size of the nozzle throat. It was also found that the steady pressure in the stagnation were maintained well at the area ratio of the driven tube to the nozzle throat is 4.5.
Optimal path planning and analysis for the maximization of multi UAVs survivability for missions involving multiple threats and locations
Jeong, Seongsik ; Jang, Dae-Sung ; Park, Hyunjin ; Seong, Taehyun ; Ahn, Jaemyung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 6, 2015, Pages 488~496
DOI : 10.5139/JKSAS.2015.43.6.488
This paper proposes a framework to determine the routes of multiple unmanned aerial vehicles (UAVs) to conduct multiple tasks in different locations considering the survivability of the vehicles. The routing problem can be formulated as the vehicle routing problem (VRP) with different cost matrices representing the trade-off between the safety of the UAVs and the mission completion time. The threat level for a UAV at a certain location was modeled considering the detection probability and the shoot-down probability. The minimal-cost path connecting two locations considering the threat level and the flight distance was obtained using the Dijkstra algorithm in hexagonal cells. A case study for determining the optimal routes for a persistent multi-UAVs surveillance and reconnaissance missions given multiple enemy bases was conducted and its results were discussed.
Composite Guidance Law for Impact Angle Control Against Moving Targets Under Physical Constraints
Park, Bong-Gyun ; Kim, Tae-Hun ; Kim, Youn-Hwan ; Kwon, Hyuck-Hoon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 6, 2015, Pages 497~506
DOI : 10.5139/JKSAS.2015.43.6.497
A composite guidance law for impact angle control against nonstationary nonmaneuvering targets is proposed. The proposed law is based on the characteristics of proportional navigation and generates two kinds of guidance commands during the homing phase. The first command is to keep the desired look angle, and the second is to attack the target with impact angle constraint. The switch of guidance phases occurs when the specific light-of-sight(LOS) angle determined from the engagement information is satisfied. The calculation method of the maximum achievable impact angle is also proposed to design easily the desired impact angle within the missile capability. Numerical simulations are performed to investigate the performance and characteristics of the proposed law.
Extended Target State Vector Estimation using AKF
Cho, Doo-Hyun ; Choi, Han-Lim ; Lee, Jin-Ik ; Jeong, Ki-Hwan ; Go, Il-Seok ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 6, 2015, Pages 507~515
DOI : 10.5139/JKSAS.2015.43.6.507
This paper proposes a filtering method for effective state vector estimation of highly maneuvering target. It is needed to hit the point called `sweet spot` to increase the kill probability in missile interception. In paper, a filtering method estimates the length of a moving target tracked by a frequency modulated continuous wave (FMCW) radar. High resolution range profiles (HRRPs) is generated from the radar echo signal and then it`s integrated into proposed filtering method. To simulate the radar measurement which is close to real, the study on the properties of scattering point of the missile-like target has been conducted with ISAR image for different angle. Also, it is hard to track the target efficiently with existing Kalman filters which has fixed measurement noise covariance matrix R. Therefore the proposed method continuously updates the covariance matrix R with sensor measurements and tracks the target. Numerical simulations on the proposed method shows reliable results under reasonable assumptions on the missile interception scenario.
Validation of Rotor Aeroacoustic Noise in Hovering and Low Speed Descent Flight
You, Younghyun ; Jung, Sung Nam ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 6, 2015, Pages 516~525
DOI : 10.5139/JKSAS.2015.43.6.516
In this paper, the acoustic pressure of a helicopter rotor in hovering and low speed descent flight is predicted and compared with experimental data. Ffowcs Williams-Hawkings equation is used to predict the acoustic pressure. Two different wind tunnel test data are used to validate the predicted results. Boeing 360 model rotor test results are used for the low-frequency noise in hover, and HART II test results are employed for the mid-frequency noise, especially BVI noise, in low speed descent flight. A simple free-wake model as well as the state-of-the-art CFD/CSD coupling method are adopted to perform the analysis. Numerical results show good agreement against the measured data for both low-frequency and mid-frequency harmonic noise signal. The noise carpet results predicted using the FFT(Fast Fourier Transform) shows also reasonable correlation with the measured data.
A Study on the Parameters for Icing Airworthiness Flight Tests of Surion Military Helicopter
Hur, Jang-Wook ; Kim, Chan-Dong ; Jang, Jae-Sang ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 6, 2015, Pages 526~532
DOI : 10.5139/JKSAS.2015.43.6.526
In order to relieve limitation of flight operation under icing condition and verify its operation in adverse weather condition for Surion, military helicopter developed in Korea, airworthiness certification in icing condition is required. The process of Surion icing certification should be considered by implementation of four methods by step such as CFD analysis, simulated flight tests, artificial icing flight tests, and natural icing flight tests. For Surion icing flight tests, these are required 20~30 sorties and 20~23 hours in artificial icing condition; 20~30 sorties and 20~22 hours in natural icing condition. In addition, to proceed with efficient flight tests, it is necessary to implement artificial icing flight tests in LWC
natural icing flight tests in less than LWC
Analysis of Folding Wing Deployment with Aero and Restraint Effects
Kim, Seung-il ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 6, 2015, Pages 533~539
DOI : 10.5139/JKSAS.2015.43.6.533
Recently, guided missiles applies folding wings to save space. During wing deployment, aero force acting on wing effects significantly on deployment performance, usually aerodynamic coefficient are calculated by CFD analysis. However, Missile Datcom can calculates estimated aerodynamic coefficient very quickly by assuming wing deployment motions as dihedral angle of wing. If missile has external store, wings may need to be folded on top of each other. In this case, one of wing help or interrupt other wing deployment, locking effect. In this study, both effects were included on wing deployment performance analysis to criteria for wings locked condition and formulated wing deploy performance, and compared with wind tunnel test data. Analysis predicted vulnerable wind direction of wing deployment very well.
Development of an ACMI Simulator Based on LVC Integrating Architecture
Jang, Youngchan ; Oh, Jihyun ; Myung, Hyunsam ; Kim, Cheonyoung ; Hong, Youngseok ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 6, 2015, Pages 540~547
DOI : 10.5139/JKSAS.2015.43.6.540
This paper describes development contents and flight tests of an ACMI simulator based on LVC integrating architecture. ACMI is the system that provides air combat training and ground bombing training for improving fighting efficiency, that is the live simulation involving real people to operate real systems. ACMI simulator was developed for technic acquisition of LVC interoperability by using data link communication. ACMI simulator simulated maneuvering of a fighter by operating an UAV, a fighter can be distinguished from an UAV by maneuvering characteristics. This study proposes maneuvering simulation method by using flight data of the UAV, and performed its flight test for verifying similarity of fighter maneuvering.
Development of a Control Law to Pneumatic Control for an Anti-G Suit
Kim, Chong-sup ; Hwang, Byung-moon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 6, 2015, Pages 548~556
DOI : 10.5139/JKSAS.2015.43.6.548
The highly maneuverable fighter aircraft such as F-22, F-16 and F-15have the high maneuverability to maximize the combat performance, whereas the high maneuver characteristics might degrade the pilot`s mission efficiency due to fatigue`s increase by exposing him to the high gravity and, in the worst case, the pilot could face GLOC (Gravity-induced Loss Of Consciousness). The advanced aerospace company has applied the various technologies to improve the pilot`s tolerance to the gravity acceleration, in order to prevent the pilot from entering the situation of the loss of consciousness. Especially, the Anti-G Suit(AGS) equipment to protect the pilot against the high gravity in flight could improve the mission success rate by decreasing the pilot`s fatigue in the combat maneuver as well as prevent the pilot from facing GLOC. In this paper, a control algorithm is developed and verified to provide an optimal air pressure to AGS according to the gravity increase during the high performance maneuver. This result is expected, as the key technology, to contribute to the KF-X(Korean Fighter eXperimental), project in the near future.
Application and Performance Evaluation of Helicopter Active Vibration Control System for Surion
Kim, Do-Hyung ; Kim, Tae-Joo ; Paek, Seung-Kil ; Kwak, Dong-Il ; Jung, Se-Un ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 6, 2015, Pages 557~567
DOI : 10.5139/JKSAS.2015.43.6.557
The most decisive factor of major sources of a helicopter is the main rotor system and the rotor-induced vibration is one of the technical challenges which should be resolved to ensure comfort for crews and passengers. Passive vibration reduction devices are adopted in conventional helicopters and several types of passive devices are also used in Surion. In recent years, foreign helicopter manufactures have increasingly applied the application of AVCS (active vibration control system) because of their superior performance with lower weight compared to passive device. In addition to weight reduction, AVCS has advantages maintaining its performance over aircraft configuration changes and flight condition changes. The technology demonstration program was performed in order to validate the performance of AVCS when applied to Surion, and optimization process for finding optimal configuration of sensors and actuators. Optimal configuration was produced using ground and flight test data, and its performance was evaluated and compared with flight test result.
Multidisciplinary Design Optimization of Earth Observation Satellite Conceptual Design using Collaborative Optimization
Kim, Hongrae ; Chang, Young-Keun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 6, 2015, Pages 568~583
DOI : 10.5139/JKSAS.2015.43.6.568
In this paper, the conceptual design procedure and results of Earth observation satellite through Multidisciplinary Design Optimization (MDO) are described. The conceptual design equations for major parameters are developed based on the established database of Earth observation satellite so far. The MDO conceptual design tool for Earth observation satellite was developed by applying the Collaborative Optimization (CO) architecture amongst several MDO architecture techniques available today. The objective for this research was set to minimize the total mass of satellite as well as satisfy all design constraints by utilizing the Sequential Quadratic Programming (SQP) algorithm. Eventually the effectiveness of MDO conceptual design tool was verified through proposing a comparison between the conceptual design results with MDO applied and the design specification of ASNARO-1 & IKONOS-2 Earth observation satellite.