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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 41, Issue 12 - Dec 2013
Volume 41, Issue 11 - Nov 2013
Volume 41, Issue 10 - Oct 2013
Volume 41, Issue 9 - Sep 2013
Volume 41, Issue 8 - Aug 2013
Volume 41, Issue 7 - Jul 2013
Volume 41, Issue 6 - Jun 2013
Volume 41, Issue 5 - May 2013
Volume 41, Issue 4 - Apr 2013
Volume 41, Issue 3 - Mar 2013
Volume 41, Issue 2 - Feb 2013
Volume 41, Issue 1 - Jan 2013
Selecting the target year
The Performance Estimation of Rotor in Wind Fence by Rotor Analysis Solver based on Actuator Disk Model
Kim, Taewoo ; Oh, Sejong ; Kang, Hee Jung ; Yee, Kwanjung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 6, 2013, Pages 429~439
DOI : 10.5139/JKSAS.2013.41.6.429
The purpose of current study is to develop the rotor analysis solver and perform a rotor aerodynamic analysis in the wind fence. To this end, the rotor analysis solver based on actuator disk model was employed. To consider the asymmetric effect of the rotor in the wind fence, the flapping motion analysis was conducted with blade element theory for the effective angle of attack calculation. The validation cases which are the rotor with wall and ground were accomplished by developed solver. The decrease of rotor performance by wind fence was confirmed. The wind fence configuration was suggested which guarantees more than 95% rotor performance compared with the no fence case.
Vibratory Loads Reduction of a Rotor in Slow Descent using Higher Harmonic Control Technology
You, Younghyun ; Jung, Sung Nam ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 6, 2013, Pages 440~447
DOI : 10.5139/JKSAS.2013.41.6.440
In this paper, a higher harmonic control (HHC) methodology is applied to find the optimum input scenario for the vibratory hub loads reduction. A comprehensive aeroelastic analysis code, CAMRAD II, is used to model the HART (Higher-harmonic-control Aeroacoustic Rotor Test) II rotor, and parametric study is conducted for the best HHC inputs leading to a minimum vibration (MV) condition. The resulting outcomes are compared with the earlier HART II test results. It is indicated that the control input adopted in the MV condition showed less satisfactory results. The new MV condition obtained in the present investigation can achieve 45% lower vibration level than the baseline uncontrolled condition. The optimum HHC input results lead to 3/rev harmonic input having
phase angle. About 5% reduction in the required power is possible but accompanies with the increase of vibration level.
Flutter Suppression of a Flexible Wing using Sliding Mode Control
Lee, Sang-Wook ; Suk, Jinyoung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 6, 2013, Pages 448~457
DOI : 10.5139/JKSAS.2013.41.6.448
This paper presents the design of an active flutter suppression system for flexible wing using sliding mode control method. The aerodynamic force generated by the motion of a flexible wing control surface is utilized as control force. For this purpose, aeroservoelastic model is formulated by blending aeroelastic model, control surface actuator model, and gust model. A sliding mode controller is designed for active flutter suppression on the aeroservoelastic model in conjunction with Kalman filter that estimates the system states based on the measured output. The performance of the designed controller is demonstrated via numerical simulation for the representative flexible wing model.
Design and Flight Test of Autonomous Landing Approach Algorithm for UAV
Jeong, Minjeong ; Ryu, Han-Seok ; Park, Sanghyuk ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 6, 2013, Pages 458~464
DOI : 10.5139/JKSAS.2013.41.6.458
This paper presents an algorithm for autonomous landing approach of a unmanned aerial vehicle. The main purpose of the autonomous landing approach in this study is to help a safe landing at night. From any initial position of the aircraft when this function is engaged, a flight path command is generated from the initial position. The shortest combination of an initial circular arc, a straight line segment, and a final circular arc is chosen for the flight path that will lead the aircraft to one end of runway for a landing. The algorithm is initially validated through numerous simulations with various initial conditions of aircraft. Then it is successfully validated through a number of flight tests.
Deploy Position Determination for Accurate Parachute Landing of a UAV
Kim, Inhan ; Park, Sanghyuk ; Park, Woosung ; Ryoo, Chang-Kyung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 6, 2013, Pages 465~472
DOI : 10.5139/JKSAS.2013.41.6.465
In this paper, we suggest how to determine the parachute deploy position for accurate landing of a UAV at a desired position. The 9-DOF dynamic modeling of UAV-parachute system is required to construct the proposed algorithm based on neural network nonlinear function approximation technique. The input and output data sets to train the neural network are obtained from simulation results using UAV-parachute 9-DOF model. The input data consist of the deploy position, UAV`s velocity, and wind velocity. The output data consist of the cross range and down range of landing positions. So we predict the relative landing position from the current UAV position. The deploy position is then determined through distance compensations for the relative landing positions from the desired landing position. The deploy position is consistently calculated and updated.
Integrated Simulation of Descent Phase using the RCS jet for a Lunar Lander
Min, Chan-Oh ; Jeong, Seun-Woo ; Lee, Dae-Woo ; Cho, Keum-Rae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 6, 2013, Pages 473~480
DOI : 10.5139/JKSAS.2013.41.6.473
Researches for various lunar landing technologies are in progress for the lunar exploration program planned for early 2020s in Korea. This paper shows the integrated simulation for safe lunar landing guidance/control system in powered descent phase. Generally, the lunar lander uses on/off(bang-bang) controller to control the RCS jet thrusters instead of proportional controller. In this paper, the on/off controller using phase-plane switching function, and thruster selection algorithm to control sixteen thrusters are applied. Also additional guidance commands are calculated by a proposed fuzzy logic guidance algorithm. The simulation results show that lunar lander can follow a reference trajectory which is generated by optimization method, then land on the surface safely.
Lever Arm Error Compensation of GPS/INS Integrated Navigation by Velocity Measurements
Park, Je Doo ; Kim, Minwoo ; Kim, Hee Sung ; Lee, Je Young ; Lee, Hyung Keun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 6, 2013, Pages 481~487
DOI : 10.5139/JKSAS.2013.41.6.481
In GPS(Global Positioning System)/INS(Inertial Navigation System) integrated navigation systems, GPS antennas and an inertial measurement units are usually installed outside and inside of the vehicle, respectively. By the difference of installed locations, performance of GPS/INS integrated navigation systems is affected by lever arm errors. For more accurate navigation, lever arm errors need to be compensated correctly since it directly affects the accuracy of navigation states. This paper proposes an effective lever arm error compensation method that utilizes velocity measurements of GPS and INS. By an experiment, feasibility of the proposed algorithm is verified. It is also shown that lever arm compensation is especially important when vehicles are experiencing rotational movements.
A Development and Verification Process of Auto Generated Code for Fly-By-Wire Helicopter Control Law
Ahn, Seong-Jun ; Kim, Chong-Sup ; Cho, In-Je ; Heo, Jin-Goo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 6, 2013, Pages 488~494
DOI : 10.5139/JKSAS.2013.41.6.488
The control law design and analysis environment of the FBW helicopter system have been developed using model base design method. The model based design is generally used in a aircraft, unmanned aerial system and automobile as well as rotorcraft development. The model based design provides many advantages such as development risk and schedule reduction using simulation and autocode generation. This paper describes a development of process for verification and validation of auto generated code for FBW helicopter flight control law. And this process is applied for Fly-By-Wire Helicopter Development Project. The results of functional test for auto generated code meet several specific requirements.
Ground Vibration Test for Korean Utility Helicopter
Kim, Se-Hee ; Kwak, Dong-Il ; Jung, Se-Un ; Choi, Jong-Ho ; Kim, Joung-Hun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 6, 2013, Pages 495~501
DOI : 10.5139/JKSAS.2013.41.6.495
Korean Utility Helicopter (KUH) has been designed to avoid the blade passing frequency and any instability due to a coupling of dynamic characteristics between the main rotor and the airframe in ground operation. For these design objectives, the vibration analysis and the ground resonance analysis were performed to analyze the dynamic characteristics of the airframe and the main rotor. Then, the whirl-tower test was conducted to identify the dynamic characteristics of the main rotor and the ground vibration test (GVT) was conducted to identify the dynamic characteristics of the airframe. The GVT for KUH was conducted with the test conditions and test articles established in consideration of each flight and ground condition. This paper shows the method and technique for performing the GVT for KUH and presents the correlation technique and the results for the correlated analysis model.
Ground Ejection Tests for the Safe Separation Analysis of a Gliding Bomb
Lee, Kidu ; Lee, Inwon ; Park, Youngkun ; Baek, Seungwoock ; Jung, Nahyeon ; Jung, Sangjun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 6, 2013, Pages 502~508
DOI : 10.5139/JKSAS.2013.41.6.502
Various combinations of cartridge and orifice were applied for ground ejection tests of a gliding bomb model equipped with a new guidance kit. Larger diameter of orifice made larger ejection force at each of bomb racks. Normal operations of the wing deploying mechanism and the devices inside of the bomb model were confirmed. Also high speed video data showed that pitch angle of the gliding bomb varied due to the ejection force.