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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 15, Issue 4 - Dec 2014
Volume 15, Issue 3 - Sep 2014
Volume 15, Issue 2 - Jun 2014
Volume 15, Issue 1 - Mar 2014
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Vibration control laws via shunted piezoelectric transducers: A review
Qureshi, Ehtesham Mustafa ; Shen, Xing ; Chen, JinJin ;
International Journal of Aeronautical and Space Sciences, volume 15, issue 1, 2014, Pages 1~19
DOI : 10.5139/IJASS.2014.15.1.1
Attaching a piezoelectric transducer to a vibrating structure, and shunting it with an electric circuit, gives rise to different passive, semi-passive, and semi-active control techniques. This paper attempts to review the research related to structural vibration control, via passive, semi-passive, and semi-active control methods. First, the existing electromechanical modeling is reviewed, along with the modeling methods. These range from lumped parameters, to distributed parameters modeling of piezostructural systems shunted by electrical networks. Vibration control laws are then discussed, covering passive, semi-passive, and semi-active control techniques, which are classified according to whether external power is supplied to the piezoelectric transducers, or not. Emphasis is placed on recent articles covering semi-passive and semi-active control techniques, based upon switched shunt circuits. This review provides the necessary background material for researchers interested in the growing field of vibration damping and control, via shunted piezostructural systems.
Shape Optimization of Damaged Columns Subjected to Conservative and Non-Conservative Forces
Jatav, S.K. ; Datta, P.K. ;
International Journal of Aeronautical and Space Sciences, volume 15, issue 1, 2014, Pages 20~31
DOI : 10.5139/IJASS.2014.15.1.20
This paper deals with the development of a realistic shape optimization of damaged columns that are subjected to conservative and non-conservative forces, using the Genetic Algorithm (GA). The analysis is based on the design of the most optimized shape of the column under the constraint of constant weight, considering the Static, Vibrational, and Flutter characteristics. Under the action of conservative and non-conservative longitudinal forces, an elastic column loses its stability. A numerical analysis based on FEM has been performed on a uniform damaged column, to compute the fundamental buckling load, vibration frequency, and flutter load, under various end restraints. An optimization search based on the Genetic Algorithm is then executed, to find the optimal shape design of the column. The optimized column references the one having the highest buckling load, highest vibration frequency, and highest flutter load, among all the possible shapes of the column, for a given volume. A comparison is then made between the values obtained for the optimized damaged column, and those obtained for the optimized undamaged column. The comparison reveals that the incorporation of damage in the column alters its optimal shape to only a certain extent. Also, the critical load and frequency values for the optimized damaged column are comparatively low, compared with those obtained for the optimized undamaged column. However, these results hold true only for moderate-intensity damage cases. For high intensity damage, the optimal shape may not remain the same, and may vary, according to the severity of damage.
AFP mandrel development for composite aircraft fuselage skin
Kumar, Deepak ; Ko, Myung-Gyun ; Roy, Rene ; Kweon, Jin-Hwe ; Choi, Jin-Ho ; Jeong, Soon-Kwan ; Jeon, Jin-Woo ; Han, Jun-Su ;
International Journal of Aeronautical and Space Sciences, volume 15, issue 1, 2014, Pages 32~43
DOI : 10.5139/IJASS.2014.15.1.32
Automatic fiber placement (AFP) has become a popular processing technique for composites in the aerospace industry, due to its ability to place prepregs or tapes precisely in the exact position when complex parts are being manufactured. This paper presents the design, analysis, and manufacture of an AFP mandrel for composite aircraft fuselage skin fabrication. According to the design requirements, an AFP mandrel was developed and a numerical study was performed through the finite element method. Linear static load analyses were performed considering the mandrel structure self-weight and a 2940 N load from the AFP machine head. Modal analysis was also performed to determine the mandrel's natural frequencies. These analyses confirmed that the proposed mandrel meets the design requirements. A prototype mandrel was then manufactured and used to fabricate a composite fuselage skin. Material load tests were conducted on the AFP fuselage skin curved laminates, equivalent flat AFP, and hand layup laminates. The flat AFP and hand layup laminates showed almost identical strength results in tension and compression. Compared to hand layup, the flat AFP laminate modulus was 5.2% higher in tension and 12.6% lower in compression. The AFP curved laminates had an ultimate compressive strength of 1.6% to 8.7% higher than flat laminates. The FEM simulation predicted strengths were 4% higher in tension and 11% higher in compression than the flat laminate test results.
Computational Investigation of Lightning Strike Effects on Aircraft Components
Ranjith, Ravichandran ; Myong, Rho Shin ; Lee, Sangwook ;
International Journal of Aeronautical and Space Sciences, volume 15, issue 1, 2014, Pages 44~53
DOI : 10.5139/IJASS.2014.15.1.44
A lightning strike to the aircraft seriously affects the aircraft and its components in various ways. As one of the most critical threats to the flight safety of an aircraft, fuel vapour ignition by lightning can occur through various means, notably through hot spot formation on the fuel tank skins. In this study, a coupled thermal-electrical approach using the commercial software ABAQUS is used to study the effects of a lightning strike on aircraft fuel tanks. This approach assumes that the electrical conductivity of a material depends on temperature, and that a temperature rise in a material due to Joule heat generation depends on electrical current. The inter-dependence of thermal and electrical properties-the thermal-electrical coupling-is analyzed by a coupled thermal-electrical analysis module. The analysis elucidates the effects of different material properties and thicknesses of tank skins and identifies the worst case of lightning zones.
Mutual Recognition of National Military Airworthiness Authorities: A Streamlined Assessment Process
Purton, Leon ; Kourousis, Kyriakos I. ; Clothier, Reece ; Massey, Kevin ;
International Journal of Aeronautical and Space Sciences, volume 15, issue 1, 2014, Pages 54~62
DOI : 10.5139/IJASS.2014.15.1.54
The Air and Space Interoperability Council (ASIC) has adopted the European Defence Agency (EDA) process for inter-regulatory military airworthiness authority recognition. However, there are gaps in the application of this process to nations outside of the European Union. This paper proposes a model that can effectively map diverse technical airworthiness regulatory frameworks. This model, referred to as the Product-Behaviour-Process (PBP) Bow-Tie model, provides the systematic structure needed to represent and compare regulatory frameworks. The PBP Bow-Tie model identifies key points of difference that need to be addressed, during inter-agency recognition between the two regulatory authorities. With the intention to adopt global use of the EDA process, the proposed PBP Bow-Tie model can be used as a basis for the successful recognition of regulatory frameworks outside of the European Union. Iris plots produced from the implementation of this model are presented, and proposed as a suitable means of illustrating the outcome of an assessment, and of supporting the comparisons of results. A comparative analysis of the Australian Defence Force and New Zealand Defence Force airworthiness regulatory frameworks is used as a case study. The case study clearly illustrates the effectiveness of the model in discerning regulatory framework differences; moreover, it has offered an opportunity to explore the limitations of the Iris plot.
Research on Robust Stability Analysis and Worst Case Identification Methods for Parameters Uncertain Missiles
Hou, Zhenqian ; Liang, Xiaogeng ; Wang, Wenzheng ;
International Journal of Aeronautical and Space Sciences, volume 15, issue 1, 2014, Pages 63~73
DOI : 10.5139/IJASS.2014.15.1.63
For robust stability analysis of parameters uncertainty missiles, the traditional frequency domain method can only analyze each respective channel at several interval points within uncertain parameter space. Discontinuous calculation and couplings between channels will lead to inaccurate analysis results. A method based on the
-gap metric is proposed, which is able to comprehensively evaluate the robust stability of missiles with uncertain parameters; and then a genetic-simulated annealing hybrid optimization algorithm, which has global and local searching ability, is used to search for a parameters combination that leads to the worst stability within the space of uncertain parameters. Finally, the proposed method is used to analyze the robust stability of a re-entry missile with uncertain parameters; the results verify the feasibility and accuracy of the method.
Missile two-loop acceleration autopilot design based on 𝓛
adaptive output feedback control
He, Shao-Ming ; Lin, De-Fu ;
International Journal of Aeronautical and Space Sciences, volume 15, issue 1, 2014, Pages 74~81
DOI : 10.5139/IJASS.2014.15.1.74
This article documents the design of a novel two-loop acceleration autopilot based on
adaptive output feedback control for tail-controlled missiles. The inner loop is an adaptive angle-of-attack tracking loop and the outer loop is the traditional PI controller for error compensation. A systematic low-pass filter design procedure is provided for minimum phase system and is applied to the inner loop design while the parameters of the outer loop are obtained from the multi-objective optimization problem. The effectiveness of the proposed autopilot is verified through numerical simulations under various conditions.
Numerical analysis of the attitude stability of a charged spacecraft in the Pitch-Roll-Yaw directions
Abdel-Aziz, Yehia A. ; Shoaib, Muhammad ;
International Journal of Aeronautical and Space Sciences, volume 15, issue 1, 2014, Pages 82~90
DOI : 10.5139/IJASS.2014.15.1.82
In this paper, the effect of Lorentz force on the stability of attitude orientation of a charged spacecraft moving in an elliptic orbit in the geomagnetic field is considered. Euler equations are used to derive the equations of attitude motion of a charged spacecraft. The equilibrium positions and its stability are investigated separately in the pitch, roll and yaw directions. In each direction, we use the Lorentz force to identify an attitude stabilization parameter. The analytical methods confirm that we can use the Lorentz force as a stabilization method. The charge-to-mass ratio is the main key of control, in addition to the components of the radius vector of the charged center of the spacecraft, relative to the center of mass of the spacecraft. The numerical results determine stable and unstable equilibrium positions. Therefore, in order to generate optimum charge, which may stabilize the attitude motion of a spacecraft, the amount of charge on the surface of spacecraft will need to be monitored for passive control.
Design of the propelling nozzles for the launchers and satellites
Haoui, Rabah ;
International Journal of Aeronautical and Space Sciences, volume 15, issue 1, 2014, Pages 91~96
DOI : 10.5139/IJASS.2014.15.1.91
The aim of this work is to determine supersonic nozzle profiles that are used in propulsion, for launchers or embarked with satellites. This design has the role of firstly, providing important propulsion, i.e. with uniform and parallel flow at exit; and secondly, to find short length profiles, without modification of the flow in the nozzle. The first elaborate program is used to determine the profile of the divergent, by using the characteristics method for an axisymmetric flow. The second program is conceived by using the finite volume method, to determine and test the profile found connected to a convergent.
Using Acoustic Liner for Fan Noise Reduction in Modern Turbofan Engines
Azimi, Mohammadreza ; Ommi, Fathollah ; Alashti, Naghmeh Jamshidi ;
International Journal of Aeronautical and Space Sciences, volume 15, issue 1, 2014, Pages 97~101
DOI : 10.5139/IJASS.2014.15.1.97
With the increase in global air travel, aircraft noise has become a major public issue. In modern aircraft engines, only a small proportion of the air that passes through the whole engine actually goes through the core of the engine, the rest passes around it down the bypass duct. A successful method of reducing noise further, even in ultra-high bypass ratio engines, is to absorb the sound created within the engine. Acoustically absorbent material or acoustic liners have desirable acoustic attenuation properties and thus are commonly used to reduce noise in jet engines. The liners typically are placed upstream and downstream of the rotors (fans) to absorb sound before it propagates out of the inlet and exhaust ducts. Noise attenuation can be dramatically improved by increasing the area over which a noise reducing material is applied and by placing the material closer to the noise source. In this paper we will briefly discuss acoustic liner applications in modern turbofan engines.
Performance Modeling of a Pyrotechnically Actuated Pin Puller
Jang, Seung-Gyo ; Lee, Hyo-Nam ; Oh, Jong-Yun ;
International Journal of Aeronautical and Space Sciences, volume 15, issue 1, 2014, Pages 102~111
DOI : 10.5139/IJASS.2014.15.1.102
An analytical model was developed to understand the physics and predict the functional performance of a pin puller. The formulated model is based on one-dimensional gas dynamics for an ideal gas. Resistive forces against pin shaft movement were measured in quasi-static mechanical tests, the results of which were incorporated into the model. The expansion chamber pressure and the pin shaft displacement were measured from an actual firing test and compared to the model prediction. The gas generation rate was adjusted by a correction factor, and the heat transfer rate was obtained through parametric analysis. The validity of the model is assessed for additional firing tests with different amounts of pyrotechnic charge. This model can provide knowledge on how the pin puller functions, and on which design parameters contribute the most to the actuation of the pin puller. Using this model, we estimate the functional safety factor by comparing the energy generated by the pyrotechnic charge to the energy required to accomplish the function.