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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 15, Issue 4 - Dec 2014
Volume 15, Issue 3 - Sep 2014
Volume 15, Issue 2 - Jun 2014
Volume 15, Issue 1 - Mar 2014
Selecting the target year
Clarification about Component Mode Synthesis Methods for Substructures with Physical Flexible Interfaces
Ohayon, R. ; Soize, C. ;
International Journal of Aeronautical and Space Sciences, volume 15, issue 2, 2014, Pages 113~122
DOI : 10.5139/IJASS.2014.15.2.113
The objective of the paper is to clarify a methodology based on the use of the existing component mode synthesis methods for the case of two damped substructures which are coupled through a linking viscoelastic flexible substructure and for which the structural modes with free geometrical interface are used for each main substructure. The proposed methodology corresponds to a convenient alternative to the direct use either of the Craig-Bampton method applied to the three substructures (using the fixed geometric interface modes) or of the flexibility residual approaches initiated by MacNeal (using the free geometric interface modes). In opposite to a geometrical interface which is a topological interface on which there is a direct linkage between the degrees of freedom of substructures, we consider a physical flexible interface which exists in certain present technologies and for which the general framework linear viscoelasticity is used and yields a frequency-dependent damping and stiffness matrices of the physical flexible interface.
Review on Advanced Health Monitoring Methods for Aero Gas Turbines using Model Based Methods and Artificial Intelligent Methods
Kong, Changduk ;
International Journal of Aeronautical and Space Sciences, volume 15, issue 2, 2014, Pages 123~137
DOI : 10.5139/IJASS.2014.15.2.123
The aviation gas turbine is composed of many expensive and highly precise parts and operated in high pressure and temperature gas. When breakdown or performance deterioration occurs due to the hostile environment and component degradation, it severely influences the aircraft operation. Recently to minimize this problem the third generation of predictive maintenance known as condition based maintenance has been developed. This method not only monitors the engine condition and diagnoses the engine faults but also gives proper maintenance advice. Therefore it can maximize the availability and minimize the maintenance cost. The advanced gas turbine health monitoring method is classified into model based diagnosis (such as observers, parity equations, parameter estimation and Gas Path Analysis (GPA)) and soft computing diagnosis (such as expert system, fuzzy logic, Neural Networks (NNs) and Genetic Algorithms (GA)). The overview shows an introduction, advantages, and disadvantages of each advanced engine health monitoring method. In addition, some practical gas turbine health monitoring application examples using the GPA methods and the artificial intelligent methods including fuzzy logic, NNs and GA developed by the author are presented.
Initial Configuration Layout Design for 95-Seat Regional Turboprop Aircraft
Hwang, In Seong ; Chung, Jindeog ; Kang, Wanggu ; Lee, Hae-Chang ;
International Journal of Aeronautical and Space Sciences, volume 15, issue 2, 2014, Pages 138~145
DOI : 10.5139/IJASS.2014.15.2.138
The initial configuration for 95-seat passenger regional turboprop aircraft, the so called KC950, was designed to meet the market requirements. This paper prescribes the initial design based upon aircraft design guidelines and compared the competitive aircraft configurations after considering the related FAR 25 regulations. More specifically, results of design describe how to select the fuselage cross-sectional area, how to layout the cabin, and how to determine the overall shape and physical dimension of the fuselage. Sizing of wing and empennage areas is estimated using empirical equations and tail volume coefficients in this design. Some design guidelines to determine wing sweep angle, taper ratio, incidence angle and location are also introduced.
Adaptive nonsingular sliding mode based guidance law with terminal angular constraint
He, Shaoming ; Lin, Defu ;
International Journal of Aeronautical and Space Sciences, volume 15, issue 2, 2014, Pages 146~152
DOI : 10.5139/IJASS.2014.15.2.146
In this paper, a new adaptive nonsingular terminal sliding mode control theory based impact angle guidance law for intercepting maneuvering targets was documented. In the design procedure, a new adaptive law for target acceleration bound estimation was presented, which allowed the proposed guidance law to be used without the requirement of the information on the target maneuvering profiles. With the aid of Lyapunov stability criteria, the finite-time convergent characteristics of the line-of-sight angle and its derivative were proven in theory. Numerical simulations were also performed under various conditions to demonstrate the effectiveness of the proposed guidance law.
Disturbance-Observer-Based Robust H
Switching Tracking Control for Near Space Interceptor
Guo, Chao ; Liang, Xiao-Geng ;
International Journal of Aeronautical and Space Sciences, volume 15, issue 2, 2014, Pages 153~162
DOI : 10.5139/IJASS.2014.15.2.153
A novel robust
switching tracking control design method with disturbance observer is proposed for the near space interceptor (NSI) with aerodynamic fins and reaction jets. Initially, the flight envelop of the NSI is divided into small subregions, and a slow-fast loop polytopic linear parameter varying (LPV) model is proposed, to approximate the nonlinear dynamic of the NSI, based on the Jacobian linearization and Tensor-Product (T-P) model transformation approach. A disturbance observer is then constructed, to estimate the modeled disturbance. Subsequently, based on the descriptor system method, a robust switching controller is developed, to ensure that the closed-loop descriptor system is stable with a desired
disturbance attenuation level. Furthermore, the outcome of the proposed switching tracking control problem is formulated as a set of linear matrix inequalities (LMIs). Finally, simulation results demonstrate the effectiveness of the proposed design method.
Guidance Law for Near Space Interceptor based on Block Backstepping Sliding Mode and Extended State Observer
Guo, Chao ; Liang, Xiao-Geng ;
International Journal of Aeronautical and Space Sciences, volume 15, issue 2, 2014, Pages 163~172
DOI : 10.5139/IJASS.2014.15.2.163
This paper proposes a novel guidance law based on the block backstepping sliding mode control and extended state observer (ESO), which also takes into account the autopilot dynamic characteristics of the near space interceptor (NSI), and the impact angle constraint of attacking the maneuvering target. Based on the backstepping control approach, the target maneuvers and the parameter uncertainties of the autopilot are regarded as disturbances of the outer loop and inner loop, respectively. Then, the ESO is constructed to estimate the target acceleration and the inner loop disturbance, and the block backstepping sliding model guidance law is employed, based on the estimated disturbance value. Furthermore, in order to avoid the "explosion of complexity" problem, first-order low-pass filters are also introduced, to obtain differentiations of the virtual control variables. The stability of the closed-loop guidance system is also proven, based on the Lyapunov theory. Finally, simulation results demonstrate that the proposed guidance law can not only overcome the influence of the autopilot dynamic delay and target maneuvers, but also obtain a small miss distance.
LFT Modeling and Robust Stability Analysis of Missiles with Uncertain Parameters
Hou, Zhen-Qian ; Liang, Xiao-Geng ; Wang, Wen-Zheng ; Li, Rui ;
International Journal of Aeronautical and Space Sciences, volume 15, issue 2, 2014, Pages 173~182
DOI : 10.5139/IJASS.2014.15.2.173
The structured singular value (
) analysis based method has many advantages for the robust stability analysis of missiles with uncertain parameters. Nevertheless, the present linear fractional transformation (LFT) modeling process, which is the basis of
analysis, is complex, and not suitable for automatic implementation; on the other hand,
analysis requires a large amount of computation, which is a burden for large-scale application. A constructive procedure, which is computationally more efficient, and which may lead to a lower order realization than existing algorithms, is proposed for LFT modeling. To reduce the calculation burden, an analysis method is developed, based on skew
. On this basis, calculation of the supremum of
over a fixed frequency range converts into a single skew
value calculation. Two algorithms are given, to calculate the upper and lower bounds of skew
, respectively. The validity of the proposed method is verified through robust stability analysis of a missile with real uncertain parameters.
Generalized Computational Nodes for Pseudospectral Methods
Kim, Chang-Joo ; Park, Soo Hyung ; Jung, Sung-Nam ; Sung, Sangkyung ;
International Journal of Aeronautical and Space Sciences, volume 15, issue 2, 2014, Pages 183~189
DOI : 10.5139/IJASS.2014.15.2.183
Pseudo-spectral method typically converges at an exponential rate. However, it requires a special set of fixed collocation points (CPs) to get highly accurate formulas for partial integration and differentiation. In this study, computational nodes for defining the discrete variables of states and controls are built independently of the CPs. The state and control variables at each CP, which are required to transcribe an NOCP into the corresponding NLP, are interpolated, using those variables allocated at each node. Additionally, Lagrange interpolation and spline interpolation are investigated, to provide a guideline for selecting a favorable interpolation method. The proposed techniques are applied to the solution of an NOCP using equally spaced nodes, and the computed results are compared to those using the standard PS approach, to validate the usefulness of the proposed methods.
Pyramidal reaction wheel arrangement optimization of satellite attitude control subsystem for minimizing power consumption
Shirazi, Abolfazl ; Mirshams, Mehran ;
International Journal of Aeronautical and Space Sciences, volume 15, issue 2, 2014, Pages 190~198
DOI : 10.5139/IJASS.2014.15.2.190
The pyramidal reaction wheel arrangement is one of the configurations that can be used in attitude control simulators for evaluation of attitude control performance in satellites. In this arrangement, the wheels are oriented in a pyramidal configuration with a tilt angle. In this paper, a study of pyramidal reaction wheel arrangement is carried out in order to find the optimum tilt angle that minimizes total power consumption of the system. The attitude control system is analyzed and the pyramidal configuration is implemented in numerical simulation. Optimization is carried out by using an iterative process and the optimum tilt angle that provides minimum system power consumption is obtained. Simulation results show that the system requires the least power by using optimum tilt angle in reaction wheels arrangement.
Rheological Characterization of Hydrogen Peroxide Gel Propellant
Jyoti, B.V.S. ; Baek, Seung Wook ;
International Journal of Aeronautical and Space Sciences, volume 15, issue 2, 2014, Pages 199~204
DOI : 10.5139/IJASS.2014.15.2.199
An experimental investigation on the rheological behavior of gelled hydrogen peroxide at different ambient temperature (283.15, 293.15 and 303.15 K) was carried out in this study. The gel propellant was rheologically characterized using a rheometer, in the shear rate ranges of 1 to
, and 1 to
. Hydrogen peroxide gel was found to be thixotropic in nature. The apparent viscosity value with some yield stress (in-case of shear rate 1 to
) drastically fell with the shear rate. In the case of the shear rate range of 1 to
, the apparent viscosity and yield stress of gel were significantly reduced at higher ambient temperatures. In the case of the shear rate range of 1 to
, no significant effect of varying the ambient temperature on the gel apparent viscosity was observed. The up and down shear rate curves for hydrogen peroxide gel formed a hysteresis loop that showed no significant change with variation in temperature for both the 1 to
and the 1 to
shear rate ranges. No significant change in the thixotropic index of gel was observed for different ambient temperatures, for both low and high shear rates. The gel in the 1 to
shear rate range did not lead to a complete breakdown of gel structure, in comparison to that in the 1 to
shear rate range.
Parametric Study on Performance of Inertance Pulse Tube Cryocooler
Lee, K.H. ; Rhee, J. ; Kim, J.S. ;
International Journal of Aeronautical and Space Sciences, volume 15, issue 2, 2014, Pages 205~211
DOI : 10.5139/IJASS.2014.15.2.205
The design parameters to affect the cooling capacity of a cryocooler were examined with the application of numerical modeling to optimize an inertance pulse tube cryocooler. This modeling includes the regenerator, pulse tube, inertance tube, gas reservoir, and heat exchangers. One-dimensional modeling on strings of acoustic and thermoacoustic elements was applied to compare the design parameters. The diameter and length of the pulse tube can significantly affect the cooling capacity and efficiency. The aftercooler was optimized by maintaining a certain size. The efficiency also improved as the length of inertance tube and volume of gas reservoir are increased. It was confirmed that effective design parameters are critical to the performance of an inertance pulse tube cryocooler considering the comparison of the dimensions of each part to optimize its cooling power and efficiency.
Increasing Flight Endurance of MAVs using Multiple Quantum Well Solar Cells
Hassanalian, Mostafa ; Radmanesh, Mohammadreza ; Sedaghat, Ahmad ;
International Journal of Aeronautical and Space Sciences, volume 15, issue 2, 2014, Pages 212~217
DOI : 10.5139/IJASS.2014.15.2.212
Micro Aerial Vehicles (MAVs) are useful devices to assess new features that may be utilized in a full size aircraft to enhance performance or to increase endurance. In this article, sources for energy saving in the micro air vehicles are initially addressed. Then, by specifying the important parameters on energy consumption of an aircraft, a feasibility study is conducted to assess the benefit of using solar cells to increase flight endurance. Next, a new solar cell has been designed and optimized for MAVs. This cell consists of a multiple quantum wells for which the quantum factor and the absorption coefficient are calculated by solving the Shrodinger equation using MATLAB software. Then, the manner and influence of MAVs parameters using the solar cells are examined to suggest optimal planform for different purposes. In order to increase flight endurance, it is noted that by using appropriate planform and the optimized solar cells, flight endurance can be increased by more than 30 percent.