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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
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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 16, Issue 4 - Dec 2015
Volume 16, Issue 3 - Sep 2015
Volume 16, Issue 2 - Jun 2015
Volume 16, Issue 1 - Mar 2015
Selecting the target year
Analysis of the Flow Field of Carrier-Based Aircraft Exhaust Jets Impact on the Flight Deck
Yue, Kuizhi ; Sun, Yicheng ; Liu, Hu ; Guo, Weigang ;
International Journal of Aeronautical and Space Sciences, volume 16, issue 1, 2015, Pages 1~7
DOI : 10.5139/IJASS.2015.16.1.1
In order to provide some references for suitability of carrier-based aircrafts, this paper studies the flow field of exhaust jets and its impact on the flight deck. The geometrical models of aircraft carrier and carrier-based aircrafts are firstly built, on which unstructured tetrahedral meshes are generated for numerical analysis. Then, this paper simulates the flow field of exhaust jets to evaluate its impact on the Jet Blast Deflector (JBD) and the flight deck, when four carrier-based aircrafts are ready to start off in the bow. The standard k-
equations, three-dimension N-S equations and the Computational Fluid Dynamics (CFD) theory are used in the analysis process. To solve the equations, the thermal coupling of the wind and the jet flow are also considered. The velocity and temperature distributions are provided with the simulation of the CFD software, FLUENT. The results indicate that: (1) this analytical method can be used to simulate aerodynamic problems with complex geometrical models, and the results are of high reliability; (2) the safety working area, the installation scheme of the JBD and the arrangement of the take-off position can be optimized through analysis.
Numerical simulation of aerodynamic characteristics of a BWB UCAV configuration with transition models
Jo, Young-Hee ; Chang, Kyoungsik ; Sheen, Dong-Jin ; Park, Soo Hyung ;
International Journal of Aeronautical and Space Sciences, volume 16, issue 1, 2015, Pages 8~18
DOI : 10.5139/IJASS.2015.16.1.8
A numerical simulation for a nonslender BWB UCAV configuration with a rounded leading edge and span of 1.0 m was performed to analyze its aerodynamic characteristics. Numerical results were compared with experimental data obtained at a free stream velocity of 50 m/s and at angles of attack from -4 to
. The Reynolds number, based on the mean chord length, is
. 3D multi-block hexahedral grids are used to guarantee good grid quality and to efficiently resolve the boundary layer. Menter`s shear stress transport model and two transition models (
model) were used to assess the effect of the laminar/turbulent transition on the flow characteristics. Aerodynamic coefficients, such as drag, lift, and the pitching moment, were compared with experimental data. Drag and lift coefficients of the UCAV were predicted well while the pitching moment coefficient was underpredicted at high angles of attack and influenced strongly by the selected turbulent models. After assessing the pressure distribution, skin friction lines and velocity field around UCAV configuration, it was found that the transition effect should be considered in the prediction of aerodynamic characteristics of vortical flow fields.
Aeroacoustic Investigation of a Cavity with and without Doors by Delayed Detached Eddy Simulation
Liu, Yu ; Tong, Mingbo ;
International Journal of Aeronautical and Space Sciences, volume 16, issue 1, 2015, Pages 19~27
DOI : 10.5139/IJASS.2015.16.1.19
In the present study, an effort was made to numerically investigate rectangular cavity aeroacoustics with and without doors. The simulation was performed on an open cavity with an aspect ratio of 5:1:1 at Mach 0.85 using the delayed detached eddy simulation (DDES) approach based on the Spalart-Allmaras model. Two cavity configurations, a clean cavity and a cavity with doors, were modeled. The results obtained from the clean cavity were compared with the experimental sound pressure levels (SPL) and the root mean square for the pressures applied. Furthermore, comparisons of frequencies were made using a modified semi-empirical Rossiter formula. The simulation using DDES precisely predicted the pressure fluctuation and the results matched the experiment quite well. The SPLs at the rear of the cavity were much higher than those in the front due to the instability of the shear layer impinging on the rear wall. Comparisons of DDES for the clean cavity and the doors-on cavity revealed that the SPLs inside the cavity as well as the magnitude of tones are amplified by the side doors. The main focus of this investigation was to obtain a better understanding of the open cavity acoustic resonance phenomenon and investigate the effects of cavity doors on the SPL.
Experimental Study of Adaptive Sliding Mode Control for Vibration of a Flexible Rectangular Plate
Yang, Jingyu ; Liu, Zhiqi ; Cui, Xuanming ; Qu, Shiying ; Wang, Chu ; Lanwei, Zhou ; Chen, Guoping ;
International Journal of Aeronautical and Space Sciences, volume 16, issue 1, 2015, Pages 28~40
DOI : 10.5139/IJASS.2015.16.1.28
This paper aims to address the intelligent active vibration control problem of a flexible rectangular plate vibration involving parameter variation and external disturbance. An adaptive sliding mode (ASM) MIMO control strategy and smart piezoelectric materials are proposed as a solution, where the controller design can deal with problems of an external disturbance and parametric uncertainty in system. Compared with the current `classical` control design, the proposed ASM MIMO control strategy design has two advantages. First, unlike existing classical control algorithms, where only low intelligence of the vibration control system is achieved, this paper shows that high intelligent of the vibration control system can be realized by the ASM MIMO control strategy and smart piezoelectric materials. Second, the system performance is improved due to two additional terms obtained in the active vibration control system. Detailed design principle and rigorous stability analysis are provided. Finally, experiments and simulations were used to verify the effectiveness of the proposed strategy using a hardware prototype based on NI instruments, a MATLAB/SIMULINK platform, and smart piezoelectric materials.
Analysis and Test of Hydrodynamic Ram in Welded Metallic Water Tanks
Kim, Jong Heon ; Kim, Chun-Gon ; Jun, Seungmoon ;
International Journal of Aeronautical and Space Sciences, volume 16, issue 1, 2015, Pages 41~49
DOI : 10.5139/IJASS.2015.16.1.41
Analysis and test of hydrodynamic ram in welded metallic tanks containing water were performed to investigate the phenomena and to understand the effects on the resulting structural behavior. Arbitrary Lagrange-Euler coupling method was used for the analysis of the fluid-structure interaction occurring in the hydrodynamic ram, where the projectile, tank, and water are exchanging load, momentum, and energy during the traveling of the projectile through the water of the tank. For a better representation of the physical phenomena, modeling of the welded edges is added to the analysis to simulate the earlier weld line fracture and its influence on the resulting hydrodynamic ram behavior. Corresponding hydrodynamic tests were performed in a modified gas gun facility, and the following panel-based examinations of various parameters, such as displacement, velocity, stress, and energy, as well as hydrodynamic ram pressure show that the analysis and test are well correlated, and thus the results of the study reasonably explain the characteristics of the hydrodynamic ram. The methodology and procedures of the present study are applicable to the hydrodynamic ram assessment of airframe survivability design concepts.
A Parametric Study of Ridge-cut Explosive Bolts using Hydrocodes
Lee, Juho ; Han, Jae-Hung ; Lee, YeungJo ; Lee, Hyoungjin ;
International Journal of Aeronautical and Space Sciences, volume 16, issue 1, 2015, Pages 50~63
DOI : 10.5139/IJASS.2015.16.1.50
Explosive bolts are one of pyrotechnic release devices, which are highly reliable and efficient for a built-in release. Among them, ridge-cut explosive bolts which utilize shock wave generated by detonation to separate bolt body produce minimal fragments, little swelling and clean breaks. In this study, separation phenomena of ridge-cut explosive bolts or ridge-cut mechanism are computationally analyzed using Hydrocodes. To analyze separation mechanism of ridge-cut explosive bolts, fluid-structure interactions with complex material modeling are essential. For modeling of high explosives (RDX and PETN), Euler elements with Jones-Wilkins-Lee E.O.S. are utilized. For Lagrange elements of bolt body structures, shock E.O.S., Johnson-Cook strength model, and principal stress failure criteria are used. From the computational analysis of the author`s explosive bolt model, computational analysis framework is verified and perfected with tuned failure criteria. Practical design improvements are also suggested based on a parametric study. Some design parameters, such as explosive weights, ridge angle, and ridge position, are chosen that might affect the separation reliability; and analysis is carried out for several designs. The results of this study provide useful information to avoid unnecessary separation experiments related with design parameters.
Pseudospectral Model Predictive Control for Exo-atmospheric Guidance
Rahman, Tawfiqur ; Zhou, Hao ; Yang, Liang ; Chen, Wanchun ;
International Journal of Aeronautical and Space Sciences, volume 16, issue 1, 2015, Pages 64~76
DOI : 10.5139/IJASS.2015.16.1.64
This paper suggests applying pseudospectral model predictive method for exo-atmospheric guidance. The method is a fusion of pseudospectral law and model predictive control, in which a two point boundary value problem is formulated using model predictive approach and solved by applying pseudospectral law. In this work, the method is applied to exo-atmospheric guidance with specific target requirement. The existing exo-atmospheric guidance methods suffice general requirements for guidance, but cannot ensure specific target constraints; whereas, the presented method is able to do so. The proposed guidance law is assessed through simulation of perturbed cases, and the tests suggest that the method is able to operate semi-autonomously under control and thrust vector perturbations.
Modeling, Dynamics and Control of Spacecraft Relative Motion in a Perturbed Keplerian Orbit
Okasha, Mohamed ; Newman, Brett ;
International Journal of Aeronautical and Space Sciences, volume 16, issue 1, 2015, Pages 77~88
DOI : 10.5139/IJASS.2015.16.1.77
The dynamics of relative motion in a perturbed orbital environment are exploited based on Gauss` and Cowell`s variational equations. The inertial coordinate frame and relative coordinate frame (Hill frame) are used, and a linear high fidelity model is developed to describe the relative motion. This model takes into account the primary gravitational and atmospheric drag perturbations. Then, this model is used in the design of a navigation, guidance, and control system of a chaser vehicle to approach towards and to depart from a target vehicle in proximity operations. Relative navigation uses an extended Kalman filter based on this relative model to estimate the relative position/velocity of the chaser vehicle with respect to the target vehicle. This filter uses the range and angle measurements of the target relative to the chaser from a simulated LIDAR system. The corresponding measurement models, process noise matrix, and other filter parameters are provided. Numerical simulations are performed to assess the precision of this model with respect to the full nonlinear model. The analyses include the navigation errors and trajectory dispersions.
Orbit Ephemeris Failure Detection in a GNSS Regional Application
Ahn, Jongsun ; Lee, Young Jae ; Won, Dae Hee ; Jun, Hyang-Sig ; Yeom, Chanhong ; Sung, Sangkyung ; Lee, Jeong-Oog ;
International Journal of Aeronautical and Space Sciences, volume 16, issue 1, 2015, Pages 89~101
DOI : 10.5139/IJASS.2015.16.1.89
To satisfy civil aviation requirements using the Global Navigation Satellite System (GNSS), it is important to guarantee system integrity. In this work, we propose a fault detection algorithm for GNSS ephemeris anomalies. The basic principle concerns baseline length estimation with GNSS measurements (pseudorange, broadcasted ephemerides). The estimated baseline length is subtracted from the true baseline length, computed using the exact surveyed ground antenna positions. If this subtracted value differs by more than a given threshold, this indicates that an ephemeris anomaly has been detected. This algorithm is suitable for detecting Type A ephemeris failure, and more advantageous for use with multiple stations with various long baseline vectors. The principles of the algorithm, sensitivity analysis, minimum detectable error (MDE), and protection level derivation are described and we verify the sensitivity analysis and algorithm availability based on real GPS data in Korea. Consequently, this algorithm is appropriate for GNSS regional implementation.
Path Tracking Controller Design and Simulation for Korean Lunar Lander Demonstrator
Yang, Sungwook ; Son, Jongjun ; Lee, Sangchul ;
International Journal of Aeronautical and Space Sciences, volume 16, issue 1, 2015, Pages 102~109
DOI : 10.5139/IJASS.2015.16.1.102
In Korea, Lunar exploration program has been prepared with the aim of launching in the 2020`s. As a part of it, a lunar lander demonstrator was developed, which was the model for verifying the system such as structure, propulsion, and control system, before launching into the deep space. This paper deals with the path tracking performance of the lunar lander demonstrator with respect to the thruster controller based on Pulse Width Pulse Frequency Modulator (PWPFM) and Pulse Width Modulator (PWM). First, we derived equations of motion, considering the allocation of the thrusters, and designed the path tracking controller based on Euler angle. The signal generated from the path tracking controller is continuous, so PWPFM and PWM modulator are adopted for generating ON/OFF signal. Finally, MATLAB simulation is performed for evaluating the path tracking ability. We compared the path tracking performances of PWPFM and PWM based thrust controller, using performance measures such as the total impulse and the position error with respect to the desired path.
Predictions on the Internal Loads and Structural Deflection in a Full-scale Experimental Bearingless Rotor
Eun, WongJong ; Ryu, HanYeol ; Shin, SangJoon ; Kee, YoungJung ; Kim, Deog-Kwan ;
International Journal of Aeronautical and Space Sciences, volume 16, issue 1, 2015, Pages 110~122
DOI : 10.5139/IJASS.2015.16.1.110
In this paper, the unsteady aerodynamics and blade structural dynamics of an experimental bearingless rotor were analyzed. Due to the multiple load path and nonlinear behavior of a bearingless rotor, sophisticated structural modeling and structural-aerodynamic coupled analysis is required. To predict the internal load and deformation of an experimental bearingless rotor, trim analysis was implemented. The results showed good agreement when compared with those predicted by CAMRAD II the rotorcraft comprehensive analysis. It is possible to extend the present structural-aerodynamic combined analysis to further advanced configurations of the bearingless rotor in the future.