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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
> Journal Vol & Issue
International Journal of Aeronautical and Space Sciences
Journal Basic Information
Journal DOI :
The Korean Society for Aeronautical & Space Sciences
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Volume & Issues
Volume 13, Issue 4 - Dec 2012
Volume 13, Issue 3 - Sep 2012
Volume 13, Issue 2 - Jun 2012
Volume 13, Issue 1 - Mar 2012
Selecting the target year
A Flight Mechanics-Centric Review of Bird-Scale Flapping Flight
Paranjape, Aditya A. ; Dorothy, Michael R. ; Chung, Soon-Jo ; Lee, Ki-D. ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 3, 2012, Pages 267~281
DOI : 10.5139/IJASS.2012.13.3.267
This paper reviews the flight mechanics and control of birds and bird-size aircraft. It is intended to fill a niche in the current survey literature which focuses primarily on the aerodynamics, flight dynamics and control of insect scale flight. We review the flight mechanics from first principles and summarize some recent results on the stability and control of birds and bird-scale aircraft. Birds spend a considerable portion of their flight in the gliding (i.e., non-flapping) phase. Therefore, we also review the stability and control of gliding flight, and particularly those aspects which are derived from the unique control features of birds.
Fiber-Matrix Interface Characterization through the Microbond Test
Sockalingam, Subramani ; Nilakantan, Gaurav ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 3, 2012, Pages 282~295
DOI : 10.5139/IJASS.2012.13.3.282
Fiber reinforced polymer matrix composites are widely used to provide protection against ballistic impact and blast events. There are several factors that govern the structural response and mechanical properties of a textile composite structure, of which the fiber-matrix interfacial behavior is a crucial determinant. This paper reviews the microbond or microdroplet test methodology that is used to characterize the fiber-matrix interfacial behavior, particularly the interface shear strength (IFSS). The various analytical, experimental, and numerical approaches applied to the microbond test are reviewed in detail.
Effects of Angles of Attack and Throttling Conditions on Supersonic Inlet Buzz
NamKoung, Hyuck-Joon ; Hong, Woo-Ram ; Kim, Jung-Min ; Yi, Jun-Sok ; Kim, Chong-Am ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 3, 2012, Pages 296~306
DOI : 10.5139/IJASS.2012.13.3.296
A series of numerical simulations are carried out to analyze a supersonic inlet buzz, which is an unsteady pressure oscillation phenomenon around a supersonic inlet. A simple but efficient geometry, experimentally adopted by Nagashima, is chosen for the analysis of unsteady flow physics. Among the two sets of simulations considered in this study, the effects of various throttling conditions are firstly examined. It is seen that the major physical characteristic of the inlet buzz can be obtained by inviscid computations only and the computed flow patterns inside and around the inlet are qualitatively consistent with the experimental observations. The dominant frequency of the inlet buzz increases as throttle area decreases, and the computed frequency is approximately 60Hz or 15% lower than the experimental data, but interestingly, this gap is constant for all the test cases and shock structures are similar. Secondly, inviscid calculations are performed to examine the effect regarding angle of attack. It is found that patterns of pressure oscillation histories and distortion due to asymmetric (or three-dimensional) shock structures are substantially affected by angle of attack. The dominant frequency of the inlet buzz, however, does not change noticeably even in regards to a wide range of angle of attacks.
Performance Evaluation of Two-Equation Turbulence Models for 3D Wing-Body Configuration
Kwak, Ein-Keun ; Lee, Nam-Hun ; Lee, Seung-Soo ; Park, Sang-Il ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 3, 2012, Pages 307~316
DOI : 10.5139/IJASS.2012.13.3.307
Numerical simulations of 3D aircraft configurations are performed in order to understand the effects of turbulence models on the prediction of aircraft's aerodynamic characteristics. An in-house CFD code that solves 3D RANS equations and two-equation turbulence model equations are used. The code applies Roe's approximated Riemann solver and an AF-ADI scheme. Van Leer's MUSCL extrapolation with van Albada's limiter is also adopted. Various versions of Menter's
SST turbulence models as well as Coakley's
model are incorporated into the CFD code. Menter's
SST models include the standard model, the 2003 model, the model incorporating the vorticity source term, and the model containing controlled decay. Turbulent flows over a wing are simulated in order to validate the turbulence models contained in the CFD code. The results from these simulations are then compared with computational results from the
AIAA CFD Drag Prediction Workshop. Numerical simulations of the DLR-F6 wing-body and wing-body-nacelle-pylon configurations are conducted and compared with computational results of the
AIAA CFD Drag Prediction Workshop. Aerodynamic characteristics as well as flow features are scrutinized with respect to the turbulence models. The results obtained from each simulation incorporating Menter's
SST turbulence model variations are compared with one another.
Low Speed Thrust Characteristics of a Modified Sonic Arc Airfoil Rotor through Spin Test Measurement
Lee, Jang-Chang ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 3, 2012, Pages 317~322
DOI : 10.5139/IJASS.2012.13.3.317
The low speed aerodynamic characteristics for a modified sonic arc airfoil which is designed by using the nose shape function of sonic arc, the shape function of NACA four-digit wing sections, and Maple are experimentally investigated. The small rotor blades of a modified sonic arc and NACA0012 airfoil are precisely fabricated with a commercially available light aluminum(Al 6061-T6) and are spin tested over a low speed range (3000rpm-5000rpm). In a consuming power comparison, the consuming powers of NACA0012 are higher than that of modified sonic arcs at each pitch angle. The measured rotor thrust for each pitch angle is used to estimate the rotor thrust coefficient according to momentum theory in the hover state. The value of thrust coefficients for both two airfoils at each pitch angle show almost constant values over the low Mach number range. However, the rotor thrust coefficient of NACA0012 is higher than that of the modified sonic arc at each pitch angle. In conclusion, the aerodynamic performance of NACA0012 is better than that of modified sonic arcs in the low speed regime. This test model will provide a convenient platform for improving the aerodynamic performance of small scale airfoils and for performing design optimization studies.
Vibration Based Structural Damage Detection Technique using Particle Swarm Optimization with Incremental Swarm Size
Nanda, Bharadwaj ; Maity, Damodar ; Maiti, Dipak Kumar ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 3, 2012, Pages 323~331
DOI : 10.5139/IJASS.2012.13.3.323
A simple and robust methodology is presented to determine the location and amount of crack in beam like structures based on the incremental particle swarm optimization technique. A comparison is made for assessing the performance of standard particle swarm optimization and the incremental particle swarm optimization technique for detecting crack in structural members. The objective function is formulated using the measured natural frequency of the intact structure and the frequency obtained from the finite element simulation. The outcomes of the simulated results demonstrate that the developed method is capable of detecting and estimating the extent of damages with satisfactory precision.
Parametric Resonance Characteristics of Laminated Composite Curved Shell Panels in a Hygrothermal Environment
Sahu, S.K. ; Rath, M.K. ; Datta, P.K. ; Sahoo, R. ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 3, 2012, Pages 332~348
DOI : 10.5139/IJASS.2012.13.3.332
The present study deals with the parametric resonance behaviour of laminated composite curved shell panels in a hygrothermal environment using Bolotin's approach. A simple laminated model is developed using first order shear deformation theory (FSDT) for the vibration and dynamic stability analysis of laminated composite shells subjected to hygrothermal conditions. A computer program based on the finite element method (FEM) in a MATLAB environment is developed to perform all necessary computations. Quantitative results are presented to show the effects of curvature, ply-orientations, degree of orthotropy and geometry of laminates on the parametric instability of composite curved shell panels for different temperature and moisture concentrations. The excitation frequencies of laminated composite panels decrease with the increase of temperature and moisture due to reduction of stiffness for all laminates.
Validation of HART II Structural Dynamics Predictions Based on Prescribed Airloads
Sa, Jeong-H. ; You, Young-H. ; Park, Jae-S. ; Park, Soo-H. ; Jung, Sung-N. ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 3, 2012, Pages 349~360
DOI : 10.5139/IJASS.2012.13.3.349
In this study, the accuracy of CSD (Comprehensive Structural Dynamics) analysis on the evaluation of blade aeroelastic responses and structural loads of HART(Higher harmonic Aeroacoustic Rotor Test) II baseline rotor is assessed using a comprehensive rotorcraft dynamics code, CAMRAD II, and a nonlinear flexible multi-body dynamics analysis code, DYMORE. Considering insufficient measurement data for HART II rotor, prescribed airloads computed by a three-dimensional compressible flow solver KFLOW are used to replace the lifting-line airloads and thereby enhance the prediction capability of the comprehensive analyses. The CSD results on blade elastic deflections using the prescribed airloads indicate more oscillatory behavior than those by lifting-line based approaches, but the wave pattern becomes improved by including artificial damping into the rotor system. It is demonstrated that the structural load predictions are improved significantly by the prescribed airloads approach against the measured data, as compared with an isolated CSD analysis.
Nonlinear Adaptive Velocity Controller Design for an Air-breathing Supersonic Engine
Park, Jung-Woo ; Park, Ik-Soo ; Tahk, Min-Jea ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 3, 2012, Pages 361~368
DOI : 10.5139/IJASS.2012.13.3.361
This paper presents an approach on the design of a nonlinear controller to track a reference velocity for an air-breathing supersonic vehicle. The nonlinear control scheme involves an adaptation of propulsive and aerodynamic characteristics in the equations of motion. In this paper, the coefficients of given thrust and drag functions are estimated and they are used to approximate the equations of motion under varying flight conditions. The form of the function of propulsive thrust is extracted from a thrust database which is given by preliminary engine input/output performance analysis. The aerodynamic drag is approximated as a function of angle of attack and fin deflection. The nonlinear controller, designed by using the approximated nonlinear control model equations, provides engine fuel supply command to follow the desired velocity varying with time. On the other hand, the stabilization of altitude, separated from the velocity control scheme, is done by a classical altitude hold autopilot design. Finally, several simulations are performed in order to demonstrate the relevance of the controller design regarding the vehicle.
A Novel Nonlinear Robust Guidance Law Design Based On SDRE Technique
Moosapour, Seyyed Sajjad ; Alizadeh, Ghasem ; Khanmohammadi, Sohrab ; Moosapour, Seyyed Hamzeh ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 3, 2012, Pages 369~376
DOI : 10.5139/IJASS.2012.13.3.369
A nonlinear robust guidance law is designed for missiles against a maneuvering target by incorporating sliding-mode and optimal control theories based on the state dependent Riccati equation (SDRE) to achieve robustness against target accelerations. The guidance law is derived based on three-dimensional nonlinear engagement kinematics and its robustness against disturbances is proved by the second method of Lyapunov. A new switching surface is considered in the sliding-mode control design. The proposed guidance law requires the maximum value of the target maneuver, and therefore opposed to the conventional augmented proportional navigation guidance (APNG) law, complete information about the target maneuver is not necessary, and hence it is simple to implement in practical applications. Considering different types of target maneuvers, several scenario simulations are performed. Simulation results confirm that the proposed guidance law has much better robustness, faster convergence, and smaller final time and control effort in comparison to the sliding-mode guidance (SMG) and APNG laws.
ADS-B based Trajectory Prediction and Conflict Detection for Air Traffic Management
Baek, Kwang-Yul ; Bang, Hyo-Choong ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 3, 2012, Pages 377~385
DOI : 10.5139/IJASS.2012.13.3.377
The Automatic Dependent Surveillance Broadcast (ADS-B) system is a key component of CNS/ATM recommended by the International Civil Aviation Organization (ICAO) as the next generation air traffic control system. ADS-B broadcasts identification, positional data, and operation information of an aircraft to other aircraft, ground vehicles and ground stations in the nearby region. This paper explores the ADS-B based trajectory prediction and the conflict detection algorithm. The multiple-model based trajectory prediction algorithm leads accurate predicted conflict probability at a future forecast time. We propose an efficient and accurate algorithm to calculate conflict probability based on approximation of the conflict zone by a set of blocks. The performance of proposed algorithms is demonstrated by a numerical simulation of two aircraft encounter scenarios.
The Characteristic Modes and Structures of Bluff-Body Stabilized Flames in Supersonic Coflow Air
Kim, Ji-Ho ; Yoon, Young-Bin ; Park, Chul-Woung ; Hahn, Jae-Won ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 3, 2012, Pages 386~397
DOI : 10.5139/IJASS.2012.13.3.386
The stability and structure of bluff-body stabilized hydrogen flames were investigated numerically and experimentally. The velocity of coflowing air was varied from subsonic velocity to a supersonic velocity of Mach 1.8. OH PLIF images and Schlieren images were used for analysis. Flame regimes were used to classify the characteristic flame modes according to the variation of the fuel-air velocity ratio, into jet-like flame, central-jet-dominated flame, and recirculation zone flame. Stability curves were drawn to find the blowout regimes and to show the improvement in flame stability with increasing lip thickness of the fuel tube, which acts as a bluff-body. These curves collapse to a single line when the blowout curves are normalized by the size of the bluff-body. The variation of flame length with the increase in air flow rate was also investigated. In the subsonic coflow condition, the flame length decreased significantly, but in the supersonic coflow condition, the flame length increased slowly and finally reached a near-constant value. This phenomenon is attributed to the air-entrainment of subsonic flow and the compressibility effect of supersonic flow. The closed-tip recirculation zone flames in supersonic coflow had a reacting core in the partially premixed zone, where the fuel jet lost its momentum due to the high-pressure zone and followed the recirculation zone; this behavior resulted in the long characteristic time for the fuel-air mixing.
A Fault Detection Method of Redundant IMU Using Modified Principal Component Analysis
Lee, Won-Hee ; Park, Chan-Gook ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 3, 2012, Pages 398~404
DOI : 10.5139/IJASS.2012.13.3.398
A fault detection process is necessary for high integrity systems like satellites, missiles and aircrafts. Especially, the satellite has to be expected to detect faults autonomously because it cannot be fixed by an expert in the space. Faults can cause critical errors to the entire system and the satellite does not have sufficient computation power to operate a large scale fault management system. Thus, a fault detection method, which has less computational burden, is required. In this paper, we proposed a modified PCA (Principal Component Analysis) as a powerful fault detection method of redundant IMU (Inertial Measurement Unit). The proposed method combines PCA with the parity space approach and it is much more efficient than the others. The proposed fault detection algorithm, modified PCA, is shown to outperform fault detection through a simulation example.