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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
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International Journal of Aeronautical and Space Sciences
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Journal DOI :
The Korean Society for Aeronautical & Space Sciences
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Volume & Issues
Volume 11, Issue 4 - Dec 2010
Volume 11, Issue 3 - Sep 2010
Volume 11, Issue 2 - Jun 2010
Volume 11, Issue 1 - Mar 2010
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Finite Volume Analysis of a Supersonic Non-Equilibrium Flow Around an Axisymmetric Blunt Body
Haoui, R. ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 2, 2010, Pages 59~68
DOI : 10.5139/IJASS.2010.11.2.059
The aim of this work is to analyze high temperature flows around an axisymmetric blunt body taking into account chemical and vibrational non-equilibrium state for air mixture species. For this purpose, a finite volume methodology is employed to determine the supersonic flow parameters around the axisymmetric blunt body. This allows the capture of a shock wave before a blunt body placed in supersonic free stream. The numerical technique uses the flux vector splitting method of Van Leer. Here, adequate time stepping parameters, along with Courant, Friedrich, Lewis coefficient and mesh size level are selected to ensure numerical convergence, sought with an order of
Experimental Framework for Controller Design of a Rotorcraft Unmanned Aerial Vehicle Using Multi-Camera System
Oh, Hyon-Dong ; Won, Dae-Yeon ; Huh, Sung-Sik ; Shim, David Hyun-Chul ; Tahk, Min-Jea ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 2, 2010, Pages 69~79
DOI : 10.5139/IJASS.2010.11.2.069
This paper describes the experimental framework for the control system design and validation of a rotorcraft unmanned aerial vehicle (UAV). Our approach follows the general procedure of nonlinear modeling, linear controller design, nonlinear simulation and flight test but uses an indoor-installed multi-camera system, which can provide full 6-degree of freedom (DOF) navigation information with high accuracy, to overcome the limitation of an outdoor flight experiment. In addition, a 3-DOF flying mill is used for the performance validation of the attitude control, which considers the characteristics of the multi-rotor type rotorcraft UAV. Our framework is applied to the design and mathematical modeling of the control system for a quad-rotor UAV, which was selected as the test-bed vehicle, and the controller design using the classical proportional-integral-derivative control method is explained. The experimental results showed that the proposed approach can be viewed as a successful tool in developing the controller of new rotorcraft UAVs with reduced cost and time.
Attitude Estimation for Satellite Fault Tolerant System Using Federated Unscented Kalman Filter
Bae, Jong-Hee ; Kim, You-Dan ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 2, 2010, Pages 80~86
DOI : 10.5139/IJASS.2010.11.2.080
We propose a spacecraft attitude estimation algorithm using a federated unscented Kalman filter. For nonlinear spacecraft systems, the unscented Kalman filter provides better performance than the extended Kalman filter. Also, the decentralized scheme in the federated configuration makes a robust system because a sensor fault can be easily detected and isolated by the fault detection and isolation algorithm through a sensitivity factor. Using the proposed algorithm, the spacecraft can continuously perform a given mission despite navigation sensor faults. Numerical simulation is performed to verify the performance of the proposed attitude estimation algorithm.
Satellite Attitude Control with a Modified Iterative Learning Law for the Decrease in the Effectiveness of the Actuator
Lee, Ho-Jin ; Kim, You-Dan ; Kim, Hee-Seob ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 2, 2010, Pages 87~97
DOI : 10.5139/IJASS.2010.11.2.087
A fault tolerant satellite attitude control scheme with a modified iterative learning law is proposed for dealing with actuator faults. The actuator fault is modeled to reflect the degradation of actuation effectiveness, and the solar array-induced disturbance is considered as an external disturbance. To estimate the magnitudes of the actuator fault and the external disturbance, a modified iterative learning law using only the information associated with the state error is applied. Stability analysis is performed to obtain the gain matrices of the modified iterative learning law using the Lyapunov theorem. The proposed fault tolerant control scheme is applied to the rest-to-rest maneuver of a large satellite system, and numerical simulations are performed to verify the performance of the proposed scheme.
Unmanned Aerial Vehicle Recovery Using a Simultaneous Localization and Mapping Algorithm without the Aid of Global Positioning System
Lee, Chang-Hun ; Tahk, Min-Jea ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 2, 2010, Pages 98~109
DOI : 10.5139/IJASS.2010.11.2.098
This paper deals with a new method of unmanned aerial vehicle (UAV) recovery when a UAV fails to get a global positioning system (GPS) signal at an unprepared site. The proposed method is based on the simultaneous localization and mapping (SLAM) algorithm. It is a process by which a vehicle can build a map of an unknown environment and simultaneously use this map to determine its position. Extensive research on SLAM algorithms proves that the error in the map reaches a lower limit, which is a function of the error that existed when the first observation was made. For this reason, the proposed method can help an inertial navigation system to prevent its error of divergence with regard to the vehicle position. In other words, it is possible that a UAV can navigate with reasonable positional accuracy in an unknown environment without the aid of GPS. This is the main idea of the present paper. Especially, this paper focuses on path planning that maximizes the discussed ability of a SLAM algorithm. In this work, a SLAM algorithm based on extended Kalman filter is used. For simplicity's sake, a blimp-type of UAV model is discussed and three-dimensional pointed-shape landmarks are considered. Finally, the proposed method is evaluated by a number of simulations.
Performance Analysis of Pursuit-Evasion Game-Based Guidance Laws
Kim, Young-Sam ; Kim, Tae-Hun ; Tahk, Min-Jea ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 2, 2010, Pages 110~117
DOI : 10.5139/IJASS.2010.11.2.0110
We propose guidance laws based on a pursuit-evasion game. The game solutions are obtained from a pursuit-evasion game solver developed by the authors. We introduce a direct method to solve planar pursuit-evasion games with control variable constraints in which the game solution is sought by iteration of the update and correction steps. The initial value of the game solution is used for guidance of the evader and the pursuer, and then the pursuit-evasion game is solved again at the next time step. In this respect, the proposed guidance laws are similar to the approach of model predictive control. The proposed guidance method is compared to proportional navigation guidance for a pursuit-evasion scenario in which the evader always tries to maximize the capture time. The capture sets of the two guidance methods are demonstrated.
Earliest Intercept Geometry Guidance to Improve Mid-Course Guidance in Area Air-Defence
Shin, Hyo-Sang ; Tahk, Min-Jea ; Tsourdos, A. ; White, B.A. ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 2, 2010, Pages 118~125
DOI : 10.5139/IJASS.2010.11.2.118
This paper describes a mid-course guidance strategy based on the earliest intercept geometry (EIG) guidance. An analytical solution and performance validation will be addressed for generalized mid-course guidance problems in area air-defence in order to improve reachability and performance. The EIG is generated for a wide range of possible manoeuvres of the challenging missile based on the guidance algorithm using differential geometry concepts. The main idea is that a mid-course guidance law can defend the area as long as it assures that the depending area and objects are always within the defended area defined by EIG. The velocity of Intercept Point in EIG is analytically derived to control the Intercept Geometry and the defended area. The proposed method can be applied in deciding a missile launch window and launch point for the launch phase.
Conceptual Design of a Multi-Rotor Unmanned Aerial Vehicle based on an Axiomatic Design
Yoo, Dong-Wan ; Won, Dae-Yeon ; Tahk, Min-Jea ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 2, 2010, Pages 126~130
DOI : 10.5139/IJASS.2010.11.2.126
This paper presents the conceptual design of a multi-rotor unmanned aerial vehicle (UAV) based on an axiomatic design. In most aerial vehicle design approaches, design configurations are affected by past and current design tendencies as well as an engineer's preferences. In order to design a systematic design framework and provide fruitful design configurations for a new type of rotorcraft, the axiomatic design theory is applied to the conceptual design process. Axiomatic design is a design methodology of a system that uses two design axioms by applying matrix methods to systematically analyze the transformation of customer needs into functional requirements (FRs), design parameters (DPs), and process variables. This paper deals with two conceptual rotary wing UAV designs, and the evaluations of tri-rotor and quad-rotor UAVs with proposed axiomatic approach. In this design methodology, design configurations are mainly affected by the selection of FRs, constraints, and DPs.
Three-Axis Autopilot Design for a High Angle-Of-Attack Missile Using Mixed H
Won, Dae-Yeon ; Tahk, Min-Jea ; Kim, Yoon-Hwan ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 2, 2010, Pages 131~135
DOI : 10.5139/JASS.2010.11.2.131
We report on the design of a three-axis missile autopilot using multi-objective control synthesis via linear matrix inequality techniques. This autopilot design guarantees
performance criteria for a set of finite linear models. These models are linearized at different aerodynamic roll angle conditions over the flight envelope to capture uncertainties that occur in the high-angle-of-attack regime. Simulation results are presented for different aerodynamic roll angle variations and show that the performance of the controller is very satisfactory.
Waypoint Planning Algorithm Using Cost Functions for Surveillance
Lim, Seung-Han ; Bang, Hyo-Choong ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 2, 2010, Pages 136~144
DOI : 10.5139/JASS.2010.11.2.136
This paper presents an algorithm for planning waypoints for the operation of a surveillance mission using cooperative unmanned aerial vehicles (UAVs) in a given map. This algorithm is rather simple and intuitive; therefore, this algorithm is easily applied to actual scenarios as well as easily handled by operators. It is assumed that UAVs do not possess complete information about targets; therefore, kinematics, intelligence, and so forth of the targets are not considered when the algorithm is in operation. This assumption is reasonable since the algorithm is solely focused on a surveillance mission. Various parameters are introduced to make the algorithm flexible and adjustable. They are related to various cost functions, which is the main idea of this algorithm. These cost functions consist of certainty of map, waypoints of co-worker UAVs, their own current positions, and a level of interest. Each cost function is formed by simple and intuitive equations, and features are handled using the aforementioned parameters.
Comprehensive Code Validation on Airloads and Aeroelastic Responses of the HART II Rotor
You, Young-Hyun ; Park, Jae-Sang ; Jung, Sung-Nam ; Kim, Do-Hyung ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 2, 2010, Pages 145~153
DOI : 10.5139/IJASS.2010.11.2.145
In this work, the comprehensive structural dynamics codes including DYMORE and CAMRAD II are used to validate the higher harmonic control aeroacoustic rotor test (HART) II data in descending flight condition. A total of 16 finite elements along with 17 aerodynamic panels are used for the CAMRAD II analysis; whereas, in the DYMORE analysis, 10 finite elements with 31 equally-spaced aerodynamic panels are utilized. To improve the prediction capability of the DYMORE analysis, the finite state dynamic inflow model is upgraded with a free vortex wake model comprised of near shed wake and trailed tip vortices. The predicted results on aerodynamic loads and blade motions are correlated with the HART II measurement data for the baseline, minimum noise and minimum vibration cases. It is found that an improvement of solution, especially for blade vortex interaction airloads, is achieved with the free wake method employed in the DYMORE analysis. Overall, fair to good correlation is achieved for the test cases considered in this study.