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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 38, Issue 12 - Dec 2010
Volume 38, Issue 11 - Nov 2010
Volume 38, Issue 10 - Oct 2010
Volume 38, Issue 9 - Sep 2010
Volume 38, Issue 8 - Aug 2010
Volume 38, Issue 7 - Jul 2010
Volume 38, Issue 6 - Jun 2010
Volume 38, Issue 5 - May 2010
Volume 38, Issue 4 - Apr 2010
Volume 38, Issue 3 - Mar 2010
Volume 38, Issue 2 - Feb 2010
Volume 38, Issue 1 - Jan 2010
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Homing Guidance Law and Spiral Descending Path Design for UAV Automatic Landing
Yoon, Seung-Ho ; Kim, H.-Jin ; Kim, You-Dan ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 3, 2010, Pages 207~212
DOI : 10.5139/JKSAS.2010.38.3.207
This paper presents a spiral descending path and a landing guidance law for net-recovery of a fixed-wing unmanned aerial vehicle. The net-recovery landing flight is divided into two phases. In the first phase, a spiral descending path is designed from an arbitrary initial position to a final approaching waypoint toward the recovery net. The flight path angle is controlled to be aligned to the approaching direction at the end of the spiral descent. In the second phase, the aircraft is guided from the approaching waypoint to the recovery net using a pseudo pursuit landing guidance law. Six degree-of-freedom simulation is performed to verify the performance of the proposed landing guidance law.
Trajectory and Attitude Analysis for the 1st Flight Test of KSLV-I Launch Vehicle
Roh, Woong-Rae ; Cho, Sang-Bum ; Ko, Jeong-Hwan ; Sun, Byung-Chan ; Kim, Jeong-Yong ; Park, Jeong-Joo ; Cho, Gwang-Rae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 3, 2010, Pages 213~220
DOI : 10.5139/JKSAS.2010.38.3.213
This paper presents the analysis results of trajectory, performance and attitude control based on the first flight data of the KSLV-I. The KSLV-I had a fairing separation problem and failed to inject spacecraft into the orbit. In this paper, the trajectory, flight performance, and attitude control was analyzed considering the influence of unseparated fairing. Moreover, the flight results and performance of the inertial navigation and guidance system were presented. As a results of post-flight analysis, any other problem besides the fairing separation problem was not happened and onboard equipment functioned normally.
Terminal Homing Guidance of Tactical Missiles with Strapdown Seekers Based on an Unscented Kalman Filter
Oh, Seung-Min ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 3, 2010, Pages 221~227
DOI : 10.5139/JKSAS.2010.38.3.221
Recent development in seeker technology explores a new seeker design in which, with larger field-of-view (FOV), optical parts are strapped down to a body (hence, called as a body-fixed seeker or a strapdown seeker). This design has several advantages such as comparatively easier maintenance and calibration by removing complex mechanical moving parts, increasing reliability, and cost savings. On the other hand, the strapdown seeker involves difficulties in implementing guidance laws since it does not directly provide inertial LOS rates. Instead, information for generating guidance commands should be extracted by estimating missile/target relative motion utilizing target images on the image plane of a strapdown seeker. In this research, a new framework based on an unscented Kalman filter is developed for estimating missile/target relative motion on the simplified assumption of a point source target. Performance of a terminal guidance algorithm, in which guidance command is generated based on the estimated relative motion, is demonstrated by a missile/target engagement simulation.
Flight Control of Tilt-Rotor Airplane In Rotary-Wing Mode Using Adaptive Control Based on Output-Feedback
Ha, Cheol-Keun ; Im, Jae-Hyoung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 3, 2010, Pages 228~235
DOI : 10.5139/JKSAS.2010.38.3.228
This paper deals with an autonomous flight controller design problem for a tilt-rotor aircraft in rotary-wing mode. The inner-loop algorithm is designed using the output-based approximate feedback linearization. The model error originated from the feedback linearization is cancelled within allowable tolerance by using single-hidden-layer neural network. According to Lyapunov direct stability theory, the adaptive update law is derived to run the neural network on-line, which is based on the linear observer dynamics. Moreover, the outer-loop algorithm is designed to track the trajectory generated from way-point guidance. Especially, heading and flight-path angle line-of-sight guidance are applied to the outer-loop to improve accuracy of the landing tracking performance. The 6-DOF nonlinear simulation shows that the overall performance of the flight control algorithm is satisfactory even though the collective input response shows instantaneous actuator saturation for a short time due to the lack of the neural network and the saturation protection logic in that loop.
Observability Analysis of a Vision-INS Integrated Navigation System Using Landmark
Won, Dae-Hee ; Chun, Se-Bum ; Sung, Sang-Kyung ; Cho, Jin-Soo ; Lee, Young-Jae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 3, 2010, Pages 236~242
DOI : 10.5139/JKSAS.2010.38.3.236
A GNSS/INS integration system can not provide navigation solutions if there are no available satellites. To overcome this problem, a vision sensor is integrated with this system. Since generally a vision aided integration system uses only feature point to compute navigation solutions, it has a problem in observability. In this case, additional landmarks, which is priory known points, can improve the observability. In this paper, the observability is evaluated using TOM/SOM matrix and Eigenvalues. There are always the observability problems in the feature-point-only case, but the landmark-use case is fully observable after the
update time. Consequently the landmarks ensure full observability, so the system performance can be improved.
Spacecraft Moment of Inertial Estimation by Modified Rodrigues Parameters
Bang, Hyo-Choong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 3, 2010, Pages 243~248
DOI : 10.5139/JKSAS.2010.38.3.243
This study addresses spacecraft moment of inertial estimation approach using Modified Rodrigues Parameters(MRP). The MRP offer advantage by avoiding singularity in Kalman Filter design for attitude determination caused by the norm constraint of quaternion parameters. Meanwhile, MRP may suffer singularity for large angular displacement, so that we designed appropriate reference attitude motion for accurate estimation. The proposed approach is expected to provide stable error covariance update with accurate spacecraft mass property estimation results.
Development of an Integrated High Fidelity Helicopter and Engine Simulation for Control System Design
Choi, Kee-Young ; Jang, Se-Ah ; Choi, Ki-Young ; Eom, Joo-Sang ; Lee, Beom-Suk ; Son, Young-Chang ; Ryu, Hyeok ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 3, 2010, Pages 249~257
DOI : 10.5139/JKSAS.2010.38.3.249
Full authority digital engine control systems for gas turbine engines are replacing conventional mechanical control units rapidly. However, setting up design processes of controllers for high performance helicopter engines are not well known because of the complexity of the total system. This paper presents a high fidelity helicopter and engine simulation for control system design and analysis. Using this environment, a feedforward schedule was set up for a utility helicopter. The total engine simulation with the new controller showed better or equal performance compared to the total engine simulation with the pre-existing controller.
Real-Time Sound Localization System For Reverberant And Noisy Environment
Kee, Chang-Don ; Kim, Ghang-Ho ; Lee, Taik-Jin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 3, 2010, Pages 258~263
DOI : 10.5139/JKSAS.2010.38.3.258
Sound localization algorithm usually adapts three step process: sampling sound signals, estimating time difference of arrival between microphones, estimate location of sound source. To apply this process in indoor environment, sound localization algorithm must be strong enough against reverberant and noisy condition. Additionally, calculation efficiency must be considered in implementing real-time sound localization system. To implement real-time robust sound localization system we adapt four low cost condenser microphones which reduce the cost and total calculation load. And to get TDOA(Time Differences of Arrival) of microphones we adapt GCC-PHAT(Generalized Cross Correlation-Phase Transform) which is robust algorithm to the reverberant and noise environment. The position of sound source was calculated by using iterative least square algorithm which produce highly accurate position data.
Autonomous Formation Flight Tests of Multiple UAVs
Song, Yong-Kyu ; Heo, Chang-Hwan ; Lee, Sang-Jun ; Kim, Jung-Han ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 3, 2010, Pages 264~273
DOI : 10.5139/JKSAS.2010.38.3.264
In this work, autonomous formation flight tests of multiple UAVs are experimentally studied. After a guidance and control system for a UAV is designed and tested, PID formation controller for follower UAV is tested using longitudinal and lateral distance feedback. It is shown that more stable and efficient formation guidance system is obtained by using position and attitude of the leader aircraft, which is exploited to calculate virtual waypoint for follower. In order to improve transient response during turn, part of roll command of the leader is added to the guidance command. Finally, autonomous formation flight test results of 3 UAVs are shown by using the best guidance algorithm suggested.
Analysis of the Longitudinal Static Stability and the Drop Trajectory of a Fighter Aircraft`s External Fuel Tank
Kang, Chi-Hang ; Cho, Hwan-Kee ; Jang, Young-Il ; Lee, Sang-Hyun ; Kim, Kwang-Youn ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 3, 2010, Pages 274~279
DOI : 10.5139/JKSAS.2010.38.3.274
The present work is to analyze the longitudinal static stability and the drop trajectory of fighter aircraft`s external fuel tank, of which horizontal fin is modified as the 20% scale down size compared with the original one. The analytical results to the pitching stability of external fuel tank using a thin airfoil`s aerodynamic force data show the corresponding tendency to results of wind tunnel experiment. Results of trajectory simulation by the 6 degree of freedom equations of motion, comparing with drop trajectories of wind tunnel experiment, are shown that aircraft`s attitude affects strongly on horizontal movement but not on the vertical movement. Those results give the reliability to aircraft safety when the external fuel tank with the 20% reduced horizontal fins is released from aircraft based on the flight manual.
Flight Safety Operation for the 1st Flight Test of Naro(KSLV-I)
Ko, Jeong-Hwan ; Choi, Kyu-Sung ; Sim, Hyung-Seok ; Roh, Woong-Rae ; Park, Jeong-Joo ; Cho, Gwang-Rae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 3, 2010, Pages 280~287
DOI : 10.5139/JKSAS.2010.38.3.280
The first Korean satellite launch vehicle, KSLV-I(Korea Space Launch Vehicle-I), was launched for its first flight test on Aug. 25, 2009 from Naro Space Center located in south Jolla province. Because launch vehicles usually fly long range with large amount of propellants aboard, preparation of countermeasures against potential malfunctions during flight is essential in launch operation. In this paper, the flight safety operation, prepared to guarantee flight safety during launch operation of KSLV-I, is presented. Prior to flight test, flight safety analysis is performed to estimate associated risk levels quantitatively, and during flight, flight safety systems are operated to cope with any risky situations. Real-time flight monitoring including computation of instantaneous impact point using tracking data is executed normally and the flight test is completed without activation of flight termination system.
Development of a Air-to-Air Missile Simulation Program for the Lethality Evaluation
Sung, Jae-Min ; Kim, Byoung-Soo ; Shin, Bo-Hyun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 3, 2010, Pages 288~293
DOI : 10.5139/JKSAS.2010.38.3.288
This paper presents to calculate the lethality of missile for the simulation test program and to verify the simulation results. In order to calculate a reliable lethality we need may data and experiments of fuse and warhead, but in reality it is hard to perform a task. Therefore, this paper obtained from the reference paper to analyze the lethality data for the calculation of the lethality. We form the 6 DOF simulation model using the MATLAB/SIMULINK. And formed the autopilot algorithm using the vertical and horizontal acceleration feedback and PNG (Proportional Navigation Guidance) command be used to the guidance algorithm. Finally, we evaluate the results about three cases, front launch, side launch and rear launch to simulate the simulation program, and the target is designed to have a constant speed and direction.
Development and Verification of ELT System Using the MEMS Accelerometer
Lee, Sang-Chul ; Lee, Dong-Kyu ; Kang, Ja-Young ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 3, 2010, Pages 294~299
DOI : 10.5139/JKSAS.2010.38.3.294
ELT(Emergency Locator Transmitter) is used to send distress signal in the event of an aircraft crash. It is very useful but the ELT may transmit wrong signal caused by misjudging between crash and hard-landing. The reason of this problem is the low accuracy of the mechanical G-switch currently in use. To improve the ELT, we developed an ELT system using the MEMS(Micro Electro-Mechanical Sensor) accelerometer. The ELT system consists of acceleration data acquisition/analysis system, program of crash recognition, and GPS receiving system for the position information of an aircraft crash site. A free-drop table was developed for verification of the ELT system. The free-drop table was designed to replicate the acceleration and the pulse duration of the hard landing and the crash. By using the free-drop table, we showed that the ELT system performed well.
Overview of Star Tracker Technology and Its Development Trends
Ju, Gwang-Hyeok ; Lee, Sang-Ryool ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 3, 2010, Pages 300~308
DOI : 10.5139/JKSAS.2010.38.3.300
In order to accelerate the evolution of faster, better, cheaper spacecraft, it is evident that greatly enhanced general-purpose attitude determination methods are needed Currently, star tracker sensors based on charge coupled devices (CCD) or active pixel sensors(APS) enable one to obtain the best spacecraft attitude estimation among the existing sensors for attitude determination. In this paper, basic principles of star tracker technology are explained including major issues arising in design and development of star tracker. Also, an historical overview and worldwide survey associated with various star trackers from star scanner through microelectromechanical system(MEMS)-based star tracker is offered.