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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
Selecting the target year
Multi-Objective Design Exploration and its Applications
Obayashi, Shigeru ; Jeong, Shin-Kyu ; Shimoyama, Koji ; Chiba, Kazuhisa ; Morino, Hiroyuki ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 4, 2010, Pages 247~265
DOI : 10.5139/IJASS.2010.11.4.247
Multi-objective design exploration (MODE) and its applications are reviewed as an attempt to utilize numerical simulation in aerospace engineering design. MODE reveals the structure of the design space based on trade-off information. A self-organizing map (SOM) is incorporated into MODE as a visual data mining tool for the design space. SOM divides the design space into clusters with specific design features. This article reviews existing visual data mining techniques applied to engineering problems. Then, we discuss three applications of MODE: multidisciplinary design optimization for a regional-jet wing, silent supersonic technology demonstrator and centrifugal diffusers.
The Application of Piezoelectric Materials in Smart Structures in China
Qiu, Jinhao ; Ji, Hongli ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 4, 2010, Pages 266~284
DOI : 10.5139/IJASS.2010.11.4.266
Piezoelectric materials have become the most attractive functional materials for sensors and actuators in smart structures because they can directly convert mechanical energy to electrical energy and vise versa. They have excellent electromechanical coupling characteristics and excellent frequency response. In this article, the research activities and achievements on the applications of piezoelectric materials in smart structures in China, including vibration control, noise control, energy harvesting, structural health monitoring, and hysteresis control, are introduced. Special attention is given to the introduction of semi-active vibration suppression based on a synchronized switching technique and piezoelectric fibers with metal cores for health monitoring. Such mechanisms are relatively new and possess great potential for future applications in aerospace engineering.
Adaptive and Robust Aeroelastic Control of Nonlinear Lifting Surfaces with Single/Multiple Control Surfaces: A Review
Wang, Z. ; Behal, A. ; Marzocca, P. ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 4, 2010, Pages 285~302
DOI : 10.5139/IJASS.2010.11.4.285
Active aeroelastic control is an emerging technology aimed at providing solutions to structural systems that under the action of aerodynamic loads are prone to instability and catastrophic failures, and to oscillations that can yield structural failure by fatigue. The purpose of the aeroelastic control among others is to alleviate and even suppress the vibrations appearing in the flight vehicle subcritical flight regimes, to expand its flight envelope by increasing the flutter speed, and to enhance the post-flutter behavior usually characterized by the presence of limit cycle oscillations. Recently adaptive and robust control strategies have demonstrated their superiority to classical feedback strategies. This review paper discusses the latest development on the topic by the authors. First, the available control techniques with focus on adaptive control schemes are reviewed, then the attention is focused on the advanced single-input and multi-input multi-output adaptive feedback control strategies developed for lifting surfaces operating at subsonic and supersonic flight speeds. A number of concepts involving various adaptive control methodologies, as well as results obtained with such controls are presented. Emphasis is placed on theoretical and numerical results obtained with the various control strategies.
Attitude Controller Design and Test of Korea Space Launch Vehicle-I Upper Stage
Sun, Byung-Chan ; Park, Yong-Kyu ; Roh, Woong-Rae ; Cho, Gwang-Rae ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 4, 2010, Pages 303~312
DOI : 10.5139/IJASS.2010.11.4.303
This paper introduces the upper stage attitude control system of KSLV-I, which is the first space launch vehicle in Korea. The KSLV-I upper stage attitude control system consists of two electro-hydraulic actuators and a reaction control system using cold nitrogen gas. A proportional, derivative, and integral controller is designed for the electro-hydraulic thrust vectoring system, and Schmidt trigger ON/OFF controllers are designed for the reaction control system. Each attitude controller is designed to have enough stability margins. The stability and performance of KSLV-I upper stage attitude control system is verified via hardware in the loop tests. Hardware in the loop tests are accomplished for perturbed flight conditions as well as nominal flight condition. The test results show that the attitude control loop of KSLV-I upper stage is very stable and the attitude controllers perform well for all flight conditions. Attitude controllers designed in this paper have been successfully applied to the first flight of KSLV-I on August 25, 2009. The flight test results show that all attitude controllers of the KSLV-I upper stage performed well and satisfied the accuracy specifications even during abnormal flight conditions.
Ironbird Ground Test for Tilt Rotor Unmanned Aerial Vehicle
Hwang, Soo-Jung ; Choi, Seong-Wook ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 4, 2010, Pages 313~318
DOI : 10.5139/IJASS.2010.11.4.313
The power plant system of a tilt rotor unmanned aerial vehicle (UAV) was verified by the Ironbird ground test, which considerably reduces cost and risk during the developmental stages. The function and performance of the engine, drive line, nacelle conversion, and rotor systems were evaluated using a building block test approach. The Ironbird test concept facilitates the discovery of potential faults in earlier stages of the testing period. As a result, the developmental testing period could effectively be shortened. The measured test data acquired through a ground control and data acquisition system exhibited satisfactory results which meet the developmental specifications of a tilt rotor UAV.
Numerical Analysis of the Three-Dimensional Wake Flow and Acoustic Field around a Circular Cylinder
Kim, Tae-Su ; Kim, Jae-Soo ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 4, 2010, Pages 319~325
DOI : 10.5139/IJASS.2010.11.4.319
For decades, researchers have rigorously studied the characteristics of flow traveling around blunt objects in order to gain greater understanding of the flow around aircraft, vehicles or vessels. Many different types of flow exist, such as boundary layer flow, flow separation, laminar and turbulent flow, vortex and vortex shedding; such types are especially observed around circular cylinders. Vortex shedding around a circular cylinder exhibits a two-dimensional flow structure possessing a Reynolds number within the range of 47 and 180. As the Reynolds number increases, the Karman vortex changes into a three-dimensional flow structure. In this paper, a numerical analysis was performed examining the flow and aero-acoustic field characteristics around a circular cylinder using an optimized high-order compact scheme, which is a high order scheme. The analysis was conducted with a Reynolds number ranging between 300 and 1,000, which belongs to B-mode flow around a circular cylinder. For a B-mode Reynolds number, a proper spanwise length is analyzed in order to obtain the characteristics of three-dimensional flow. The numerical results of the Strouhal number as well as the lift and drag coefficients according to Reynolds numbers are coincident with the other experimental results. Basic research has been conducted studying the effects an unstable three-dimensional wake flow on an aero-acoustic field.
Learning the Covariance Dynamics of a Large-Scale Environment for Informative Path Planning of Unmanned Aerial Vehicle Sensors
Park, Soo-Ho ; Choi, Han-Lim ; Roy, Nicholas ; How, Jonathan P. ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 4, 2010, Pages 326~337
DOI : 10.5139/IJASS.2010.11.4.326
This work addresses problems regarding trajectory planning for unmanned aerial vehicle sensors. Such sensors are used for taking measurements of large nonlinear systems. The sensor investigations presented here entails methods for improving estimations and predictions of large nonlinear systems. Thoroughly understanding the global system state typically requires probabilistic state estimation. Thus, in order to meet this requirement, the goal is to find trajectories such that the measurements along each trajectory minimize the expected error of the predicted state of the system. The considerable nonlinearity of the dynamics governing these systems necessitates the use of computationally costly Monte-Carlo estimation techniques, which are needed to update the state distribution over time. This computational burden renders planning to be infeasible since the search process must calculate the covariance of the posterior state estimate for each candidate path. To resolve this challenge, this work proposes to replace the computationally intensive numerical prediction process with an approximate covariance dynamics model learned using a nonlinear time-series regression. The use of autoregressive time-series featuring a regularized least squares algorithm facilitates the learning of accurate and efficient parametric models. The learned covariance dynamics are demonstrated to outperform other approximation strategies, such as linearization and partial ensemble propagation, when used for trajectory optimization, in terms of accuracy and speed, with examples of simplified weather forecasting.
Design of an Autonomous Hover Control System for a Small Quadrotor
Raharja, Gilar B. ; Kim, Gyu-Beom ; Yoon, K.J. ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 4, 2010, Pages 338~344
DOI : 10.5139/IJASS.2010.11.4.338
This paper discusses the development of the control system of a mini quadrotor in Konkuk University for indoor applications. The attitude control system consists of a stability augmentation system, which acts as the inner loop control, and a modern control approach based on modeling will be implemented as the outer loop. The inner loop control was experimentally satisfied by a proportional-derivative controller; this was used to support the flight test in order to validate the modeling. This paper introduces the mathematical model for the simulation and design of the optimal control on the outer loop control. To perform the experimental tests, basic electronic hardware was developed using simple configurations; a microcontroller used as the embedded controller, a low-cost 100 Hz inertial sensors used for the inertial sensing, infra-red sensors were employed for horizontal ranging, an ultrasonic sensor was used for ground ranging and a high performance propeller system built on an quadrotor airframe was also employed. The results acquired from this compilation of hardware produced an automatic hovering ability of the system with ground control system support for the monitoring and fail-safe system.
Store Separation Analysis of a Fighter Aircraft`s External Fuel Tank
Cho, Hwan-Kee ; Kang, Chi-Hang ; Jang, Young-Il ; Lee, Sang-Hyun ; Kim, Kwang-Yeon ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 4, 2010, Pages 345~350
DOI : 10.5139/IJASS.2010.11.4.345
The repetitive vibrating action of an aerodynamic load causes an external fuel tank`s horizontal fin to experience a shorter life cycle than its originally predicted one. Store separation analysis is needed to redesign the fin of an external fuel tank. In this research, free-drop tests were conducted using 15% scaled models in a subsonic wind tunnel in order to analyze the store separation characteristics of an external fuel tank. The store separation trajectory based on grid tests was also obtained to verify the results of the free-drop tests. The results acquired from the free-drop tests correlated well with the grid tests in regards to the trajectories and behavior of the stores separated from the aircraft. This agreement was especially noted in the early stages of the store separation.
Collision Avoidance Using Linear Quadratic Control in Satellite Formation Flying
Mok, Sung-Hoon ; Choi, Yoon-Hyuk ; Bang, Hyo-Choong ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 4, 2010, Pages 351~359
DOI : 10.5139/IJASS.2010.11.4.351
This paper proposes a linear system control algorithm with collision avoidance in multiple satellites. Consideration of collision avoidance is augmented by adding a weighting term in the cost function of the original tracking problem in linear quadratic control (LQC). Because the proposed algorithm relies on a similar solution procedure to the original LQC, its inherent advantages, including gain-robustness and optimality, are preserved. To confirm and visualize the derived algorithm, a simple example of two-vehicle motion in the two-dimensional plane is illustrated. In addition, the proposed collision avoidance control is applied to satellite formation flying, and verified by numerical simulations.
The Bending Analysis of Three Phase Polymer Composite Plate Reinforced by Glass Fiber and Titanium Oxide Particles Including Creep Effect
Duc, Nguyen Dinh ; Minh, Dinh Khac ; VanThu, Pham ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 4, 2010, Pages 360~365
DOI : 10.5139/IJASS.2010.11.4.360
Three phase composite materials are widely used in the shipbuilding industry. When reinforced with fiber and particle, the physical and mechanical properties of polymer composite materials are improved. This paper presents the bending analysis of a three phase composite plate with an epoxy matrix, reinforced glass fiber and titanium oxide particles including creep effect when shear stress is taken into account. The obtained results indicate that creep strains lead to compression in the composite material. Introducing reinforced fibers and particles reduces the plate`s deflection, when increasing the stretch coefficient allows the calculation of creep deflection during a long loading period.