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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 14, Issue 4 - Dec 2013
Volume 14, Issue 3 - Sep 2013
Volume 14, Issue 2 - Jun 2013
Volume 14, Issue 1 - Mar 2013
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Numerical Analysis of the Unsteady Subsonic Flow around a Plunging Airfoil
Lee, Kyungwhan ; Kim, Jaesoo ;
International Journal of Aeronautical and Space Sciences, volume 14, issue 3, 2013, Pages 201~209
DOI : 10.5139/IJASS.2013.14.3.201
Much numerical and experimental research has been done for the flow around an oscillating airfoil. The main research topics are vortex shedding, dynamic stall phenomenon, MAV`s lift and thrust generation. Until now, researches mainly have been concentrated on analyzing the wake flow for the variation of frequency and amplitude at a low angle of attack. In this study, wake structures and acoustic wave propagation characteristics were studied for a plunging airfoil at high angle of attack. The governing equations are the Navier-Stokes equation with LES turbulence model. OHOC (Optimized High-Order Compact) scheme and 4th order Runge-Kutta method were used. The Mach number is 0.3, the Reynolds number is, and the angle of attack is from
. The plunging frequency and the amplitude are from 0.05 to 0.15, and from 0.1 to 0.2, respectively. Due to the high resolution numerical method, wake vortex shedding and pressure wave propagation process, as well as the propagation characteristics of acoustic waves can be simulated. The results of frequency analysis show that the flow has the mixed characteristics of the forced plunging frequency and the vortex shedding frequency at high angle of attack.
Transonic flow past a Whitcomb airfoil with a deflected aileron
Kuzmin, Alexander ;
International Journal of Aeronautical and Space Sciences, volume 14, issue 3, 2013, Pages 210~214
DOI : 10.5139/IJASS.2013.14.3.210
The sensitivity of transonic flow past a Whitcomb airfoil to deflections of an aileron is studied at free-stream Mach numbers from 0.81 to 0.86 and vanishing or negative angles of attack. Solutions of the Reynolds-averaged Navier-Stokes equations are obtained with a finite-volume solver using the
SST turbulence model. The numerical study demonstrates the existence of narrow bands of the Mach number and aileron deflection angles that admit abrupt changes of the lift coefficient at small perturbations. In addition, computations reveal free-stream conditions in which the lift coefficient is independent of aileron deflections of up to 5 degrees. The anomalous behavior of the lift is explained by interplay of local supersonic regions on the airfoil. Both stationary and impulse changes of the aileron position are considered.
Aerodynamic Investigation for Prospective Aerospace Vehicle in the Transitional Regime
Ivanovich, Khlopkov Yuri ; Myint, Zay Yar Myo ; Yurievich, Khlopkov Anton ;
International Journal of Aeronautical and Space Sciences, volume 14, issue 3, 2013, Pages 215~221
DOI : 10.5139/IJASS.2013.14.3.215
The basic quantitative tool for the study of hypersonic rarefied flows is the direct simulation Monte Carlo method (DSMC). The DSMC method requires a large amount of computer memory and performance and is unreasonably expensive at the first stage of spacecraft design and trajectory analysis. A possible solution to this problem is approximate engineering methods. However, the Monte Carlo method remains the most reliable approach to compare to the engineering methods that provide good results for the global aerodynamic coefficients of various geometry designs. This paper presents the calculation results of aerodynamic characteristics for spacecraft vehicles in the free molecular, the transitional and the continuum regimes using the local engineering method. Results and methods would be useful to calculate aerodynamics for new-generation hypersonic vehicle designs.
Design Feature-Based Jetfighter Shape Modeling
Zang, Jing ; Liu, Hu ; Liu, Tianping ; Ni, Xianping ;
International Journal of Aeronautical and Space Sciences, volume 14, issue 3, 2013, Pages 222~228
DOI : 10.5139/IJASS.2013.14.3.222
A jetfighter shape modeling method based on design features is researched, to improve the efficiency of shape modeling in the stage of conceptual aircraft design. The aircraft`s general design features and shape parameters, including geometric and position parameters, are described. The coordinate systems of the entire aircraft and its components are defined. As a sample of local shape, a method of inlet intake modeling is introduced. The whole process of the modeling method is proposed. Three examples of different jetfighters are listed, to describe the achievement of basic layout, which includes four main elements. The Fusion of Components can be achieved by regulating the details of the sections of the fuselage. Sample Cases of typical layouts are shown to verify the effectiveness of the proposed method, which provides the basis for further analysis and optimization.
Parametric Studies and Performance Analysis of a Biplane Micro Air Vehicle
Maqsood, Adnan ; Go, Tiauw Hiong ;
International Journal of Aeronautical and Space Sciences, volume 14, issue 3, 2013, Pages 229~236
DOI : 10.5139/IJASS.2013.14.3.229
This paper presents the experimental investigation of a biplane micro air vehicle. The effects of geometric parameters, gap, stagger, and decalage angle are investigated at low Reynolds number (~150,000) in a low-speed wind tunnel. A rigid flat plate with an aspect ratio of one and square planform shape is used to evaluate all three geometric parameters. The side dimension of the single flat plate is 0.15 m. The goal is to find an optimal biplane configuration that should exceed monoplane performance by generating high lift and flying as slow as possible, in order to capture high-quality visual recordings. This configuration will directly help to fly at a lower velocity and to make tighter turns that are advantageous in restricted environments. The results show that the aerodynamic performance of the biplane MAV is significantly enhanced through the combination of gap and stagger effects. A performance comparison demonstrates the superiority of the optimal biplane configuration compared to a monoplane in cruise and glide phases. Moreover, no significant compromise is found for the range, endurance, and climb performance.
Landing Dynamic and Key Parameter Estimations of a Landing Mechanism to Asteroid with Soft Surface
Zhao, Zhijun ; Zhao, JingDong ; Liu, Hong ;
International Journal of Aeronautical and Space Sciences, volume 14, issue 3, 2013, Pages 237~246
DOI : 10.5139/IJASS.2013.14.3.237
It is of great significance to utilize a landing mechanism to explore an asteroid. A landing mechanism named ALISE (Asteroid Landing and In Situ Exploring) for asteroid with soft surface is presented. The landing dynamic in the first turning stage, which represents the landing performance of the landing mechanism, is built by a Lagrange equation. Three key parameters can be found influencing the landing performance: the retro-rocket thrust T, damping element damping
, and cardan element damping
. In this paper, the retro-rocket thrust T is solved with considering that the landing mechanism has no overturning in extreme landing conditions. The damping element damping c1 is solved by a simplified dynamic model. After solving the parameters T and
, the cardan element damping
is calculated using the landing dynamic model, which is built by Lagrange equation. The validities of these three key parameters are tested by simulation. The results show a stable landing, when landing with the three estimated parameters T,
. Therefore, the landing dynamic model and methods to estimate key parameters are reasonable, and are useful for guiding the design of the landing mechanism.
Moving Mass Actuated Reentry Vehicle Control Based on Trajectory Linearization
Su, Xiao-Long ; Yu, Jian-Qiao ; Wang, Ya-Fei ; Wang, Lin-lin ;
International Journal of Aeronautical and Space Sciences, volume 14, issue 3, 2013, Pages 247~255
DOI : 10.5139/IJASS.2013.14.3.247
The flight control of re-entry vehicles poses a challenge to conventional gain-scheduled flight controllers due to the widely spread aerodynamic coefficients. In addition, a wide range of uncertainties in disturbances must be accommodated by the control system. This paper presents the design of a roll channel controller for a non-axisymmetric reentry vehicle model using the trajectory linearization control (TLC) method. The dynamic equations of a moving mass system and roll control model are established using the Lagrange method. Nonlinear tracking and decoupling control by trajectory linearization can be viewed as the ideal gain-scheduling controller designed at every point along the flight trajectory. It provides robust stability and performance at all stages of the flight without adjusting controller gains. It is this "plug-and-play" feature that is highly preferred for developing, testing and routine operating of the re-entry vehicles. Although the controller is designed only for nominal aerodynamic coefficients, excellent performance is verified by simulation for wind disturbances and variations from -30% to +30% of the aerodynamic coefficients.
Optimal Controller for Near-Space Interceptor with Actuator Saturation
Fan, Guo-Long ; Liang, Xiao-Geng ; Hou, Zhen-Qian ; Yang, Jun ;
International Journal of Aeronautical and Space Sciences, volume 14, issue 3, 2013, Pages 256~263
DOI : 10.5139/IJASS.2013.14.3.256
The saturation of the actuator impairs the response performance of the near space interceptor control system. A control system based on the properties of linear tracking system is designed for this problem. The properties are that the maximum value of the pseudo-Lyapunov function of the linear tracking control system do not present at the initial state but at the steady state, based on which the bounded stability problem is converted into linear tracking problem. The pseudo-Lyapunov function of the linear tracking system contain the input variables; the amplitude and frequency of the input variables affect the stability of the nonlinear control system. Designate expected closed-loop poles area for different input commands and obtain a controller which is function of input variables. The coupling between variables and linear matrices make the control system design problem non-convex. The non-convex problem is converted into a convex LMI according to the Shur complement lemma and iterative algorithm. Finally the simulation shows that the designed optimal control system is quick and accurate; the rationality of the presented design techniques is validated.
Object-Oriented Mission Modeling for Multiple Transport Aircraft
Zang, Jing ; Liu, Hu ; Liu, Tianping ; Ni, Xianping ;
International Journal of Aeronautical and Space Sciences, volume 14, issue 3, 2013, Pages 264~271
DOI : 10.5139/IJASS.2013.14.3.264
A method of multiple transport-aircraft mission modeling is proposed in order to improve the efficiency of evaluating and optimizing pre-mission plans. To deal with the challenge of multiple transport-aircraft missions, the object-oriented modeling method is utilized. The elements of the mission are decomposed into objects and businesses, And the major mission objects and their important properties are summarized. A complex mission can be broken down into basic business modules such as the ground section and flight section. The business models of loading and fueling services in the ground section are described. The business model of the flight section is composed of an air route and flight profile with the flight equation and the fuel consumption model. The logical relationship of objects and business modules is introduced. The architecture of the simulation system, which includes a database, computation module, graphical user interface (GUI) module, and a result analysis module, is established. A sample case that includes two different plans is provided to verify the model`s ability to achieve multi-aircraft composite mission simulation.
A Development of 3-D Resolution Algorithm for Aircraft Collision Avoidance
Kim, Youngrae ; Lee, Sangchul ; Lee, Keumjin ; Kang, Ja-Young ;
International Journal of Aeronautical and Space Sciences, volume 14, issue 3, 2013, Pages 272~281
DOI : 10.5139/IJASS.2013.14.3.272
Traffic Collision Avoidance System (TCAS) is designed to enhance safety in aircraft operations, by reducing the incidences of mid-air collision between aircraft. The current version of TCAS provides only vertical resolution advisory to the pilots, if an aircraft`s collision with another is predicted to be imminent, while efforts to include horizontal resolution advisory have been made, as well. This paper introduces a collision resolution algorithm, which includes both vertical and horizontal avoidance maneuvers of aircraft. Also, the paper compares between the performance of the proposed algorithm and that of algorithms with only vertical or horizontal avoidance maneuver of aircraft.
An Antenna Tracking Profile Design for Communication with a Ground station
Lee, Donghun ; Lee, Kyung-Min ; Rashed, Mohammed Irfan ; Bang, Hyochoong ;
International Journal of Aeronautical and Space Sciences, volume 14, issue 3, 2013, Pages 282~295
DOI : 10.5139/IJASS.2013.14.3.282
In order to communicate with a ground station, the tracking profile design problem for a directional antenna system is considered. Because the motions of the gimbal angles in the antenna system affect the image quality, the main object is to minimize the motion of the gimbal angles during the satellite`s imaging phase. For this goal, parameter optimization problems in the imaging and maneuver phases are formulated separately in the body-frame, and solved sequentially. Also, several mechanical constraints, such as the limitation of the gimbal angle and rate, are considered in the problems. The tracking profiles of the gimbal angles in the maneuver phases are designed with N-th order polynomials, to continuously connect the tracking profiles between two imaging phases. The results confirm that if the vector trace of the desired antenna-pointing vector is within the antenna`s beam-width angle, motions of the gimbal angles are not required in the corresponding imaging phase. Also, through numerical examples, it is shown that motion of the gimbal angles in the imaging phase can be minimized by the proposed design process.