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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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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
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Advanced Computational Dissipative Structural Acoustics and Fluid-Structure Interaction in Low-and Medium-Frequency Domains. Reduced-Order Models and Uncertainty Quantification
Ohayon, R. ; Soize, C. ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 2, 2012, Pages 127~153
DOI : 10.5139/IJASS.2012.13.2.127
This paper presents an advanced computational method for the prediction of the responses in the frequency domain of general linear dissipative structural-acoustic and fluid-structure systems, in the low-and medium-frequency domains and this includes uncertainty quantification. The system under consideration is constituted of a deformable dissipative structure that is coupled with an internal dissipative acoustic fluid. This includes wall acoustic impedances and it is surrounded by an infinite acoustic fluid. The system is submitted to given internal and external acoustic sources and to the prescribed mechanical forces. An efficient reduced-order computational model is constructed by using a finite element discretization for the structure and an internal acoustic fluid. The external acoustic fluid is treated by using an appropriate boundary element method in the frequency domain. All the required modeling aspects for the analysis of the medium-frequency domain have been introduced namely, a viscoelastic behavior for the structure, an appropriate dissipative model for the internal acoustic fluid that includes wall acoustic impedance and a model of uncertainty in particular for the modeling errors. This advanced computational formulation, corresponding to new extensions and complements with respect to the state-of-the-art are well adapted for the development of a new generation of software, in particular for parallel computers.
Spacecraft Guidance Algorithms for Asteroid Intercept and Rendezvous Missions
Hawkins, Matt ; Guo, Yanning ; Wie, Bong ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 2, 2012, Pages 154~169
DOI : 10.5139/IJASS.2012.13.2.154
This paper presents a comprehensive review of spacecraft guidance algorithms for asteroid intercept and rendezvous missions. Classical proportional navigation (PN) guidance is reviewed first, followed by pulsed PN guidance, augmented PN guidance, predictive feedback guidance, Lambert guidance, and other guidance laws based on orbit perturbation theory. Optimal feedback guidance laws satisfying various terminal constraints are also discussed. Finally, the zero-effort-velocity (ZEV) error, analogous to the well-known zero-effort-miss (ZEM) distance, is introduced, leading to a generalized ZEM/ZEV guidance law. These various feedback guidance laws can be easily applied to real asteroid intercept and rendezvous missions. However, differing mission requirements and spacecraft capabilities will require continued research on terminal-phase guidance laws.
Airship Research and Development in the Areas of Design, Structures, Dynamics and Energy Systems
Stockbridge, Casey ; Ceruti, Alessandro ; Marzocca, Pier ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 2, 2012, Pages 170~187
DOI : 10.5139/IJASS.2012.13.2.170
Recent years have seen an outpour of revived interest in the use of airships for a number of applications.Present day developments in materials, propulsion, solar panels, and energy storage systems and the need for a more eco-oriented approach to flight are increasing the curiosity in airships, as the series of new projects deployed in recent years show; moreover, the exploitation of the always mounting simulation capabilities in CAD/CAE, CFD and FEA provided by modern computers allow an accurate design useful to optimize and reduce the development time of these vehicles.The purpose of this contribution is to examine the different aspects of airship development with a review of current modeling techniques for airship dynamics and aerodynamics along withconceptual design and optimization techniques, structural design and manufacturingtechnologies and, energy system technologies. A brief history of airships is presented followed by an analysis of conventional and unconventional airships including current projects and conceptual designs.
Influence of Compressibility Modification to k-ε Turbulence Models for Supersonic Base Flow
Jeon, Sang-Eon ; Park, Soo-Hyung ; Byun, Yung-Hwan ; Kwon, Jang-Hyuk ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 2, 2012, Pages 188~198
DOI : 10.5139/IJASS.2012.13.2.188
An improvement to the k-
turbulence model is presented and is shown to lead to better agreement with data regarding supersonic base flows. The improvement was achieved by imposing a grid-independent realizability constraint in the Launder-Sharma k-
model. The effects of compressibility were also examined. The numerical results show that the modified Launder-Sharma model leads to some improvement in the prediction of the velocity and turbulent kinetic energy profiles. Compressibility corrections also lead to better agreement in both the turbulent kinetic energy and the Reynolds stress profiles with the experimental data.
Advanced 1D Structural Models for Flutter Analysis of Lifting Surfaces
Petrolo, Marco ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 2, 2012, Pages 199~209
DOI : 10.5139/IJASS.2012.13.2.199
An advanced aeroelastic formulation for flutter analyses is presented in this paper. Refined 1D structural models were coupled with the doublet lattice method, and the g-method was used for flutter analyses. Structural models were developed in the framework of the Carrera Unified Formulation (CUF). Higher-order 1D structural models were obtained by using Taylor-like expansions of the cross-section displacement field of the structure. The order (N) of the expansion was considered as a free parameter since it can be arbitrarily chosen as an input of the analysis. Convergence studies on the order of the structural model can be straightforwardly conducted in order to establish the proper 1D structural model for a given problem. Flutter analyses were conducted on several wing configurations and the results were compared to those from literature. Results show the enhanced capabilities of CUF 1D in dealing with the flutter analysis of typical wing structures with high accuracy and low computational costs.
A Continuous Robust Control Strategy for the Active Aeroelastic Vibration Suppression of Supersonic Lifting Surfaces
Zhang, K. ; Wang, Z. ; Behal, A. ; Marzocca, P. ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 2, 2012, Pages 210~220
DOI : 10.5139/IJASS.2012.13.2.210
The model-free control of aeroelastic vibrations of a non-linear 2-D wing-flap system operating in supersonic flight speed regimes is discussed in this paper. A novel continuous robust controller design yields asymptotically stable vibration suppression in both the pitching and plunging degrees of freedom using the flap deflection as a control input. The controller also ensures that all system states remain bounded at all times during closed-loop operation. A Lyapunov method is used to obtain the global asymptotic stability result. The unsteady aerodynamic load is considered by resourcing to the non-linear Piston Theory Aerodynamics (PTA) modified to account for the effect of the flap deflection. Simulation results demonstrate the performance of the robust control strategy in suppressing dynamic aeroelastic instabilities, such as non-linear flutter and limit cycle oscillations.
Feasibility Study to Actively Compensate Deformations of Composite Structure in a Space Environment
Farinelli, Ciro ; Kim, Hong-Il ; Han, Jae-Hung ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 2, 2012, Pages 221~228
DOI : 10.5139/IJASS.2012.13.2.221
An active compensation method for the deformation of composite structures using additional controllable metal parts is proposed, and its feasibility is experimentally investigated in a simulated space environment. Composite specimens are tested in a vacuum chamber, which is able to maintain pressure on the order of 10-3 torr and interior temperature in the range of
. The displacement-measuring interferometer system, which consists of a heterodyne HeNe laser and an interferometer, is used to measure the displacement of the whole structure. Meanwhile, the strain of the composite part and temperature of both parts are measured by fiber Bragg grating sensors and thermistors, respectively. The displacement of the composite structure is maintained within a tolerance of
by controlling the elongation of the metal part, which is bonded to the end of the composite part. Also, the possibility of fiber Bragg grating sensors as control input sensors is successfully demonstrated using a proper corrective factor based on the specimen temperature gradient data.
Experimental and numerical study on the failure of sandwich T-joints under pull-off loading
Nguyen, Khanh-Hung ; Park, Yong-Bin ; Kweon, Jin-Hwe ; Choi, Jin-Ho ; Shul, Chang-Won ; Yang, Myung-Seog ; Jun, Seung-Moon ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 2, 2012, Pages 229~237
DOI : 10.5139/IJASS.2012.13.2.229
In this study, the failure mechanism of sandwich-to-laminate T-joints under pull-off loading was investigated by experiment and the finite element method. A total of 26 T-joint specimens were manufactured and tested in order to investigate the effects of both adhesive thickness (0.4, 2.0, and 4.0 mm) and environmental conditions on the failure of the joints. The results showed that failure occurred mainly as intralaminar failure in the first layer of the sandwich face, which was contacted to the paste adhesive. The failure load did not significantly change with increasing adhesive thickness in both RTD (Room Temperature and Dry) and ETW (Elevated Temperature and Wet) conditions. In the case of ETW conditions, however, the failure load increased slightly with an increase in adhesive thickness. The joints tested in ETW conditions had higher failure loads than those tested in RTD conditions. In addition to the experiment, a finite element analysis was also conducted to investigate the failure of the joint. The stress inside the first ply of the sandwich face was of interest because during the experiment, failure always occurred there. The analysis results showed good agreement with the trend of experimental results, except for the case of the smallest adhesive thickness. The highest stress was predicted in the regions where initial failure was observed in the experiment. The maximum stress was almost constant when the adhesive thickness was beyond 2 mm.
Flight Test Measurement and Assessment of a Flapping Micro Air Vehicle
Kim, Jong-Heon ; Park, Chan-Yik ; Jun, Seung-Moon ; Chung, Dae-Keun ; Kim, Jong-Rok ; Hwang, Hee-Chul ; Stanford, Bret ; Beran, Philip ; Parker, Gregory ; Mrozinski, Denny ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 2, 2012, Pages 238~249
DOI : 10.5139/IJASS.2012.13.2.238
Flight test of flapping micro air vehicles (FMAVs) is carried out using an instrumented measurement system to obtain various engineering parameters and hence to assess the flight performance of the vehicles through the data investigation. An indoor flight test facility equipped with a motion capture system and tracking cameras is used for the work presented in this paper. Maneuvers including straight-level flight, ground flapping, takeoff and landing are tested. Spatial position and orientation data are obtained from the retro-reflective tracking markers attached to the vehicles. Subsequent test analysis is carried out by generating performance parameters from raw data and then assessing the flight performance by comparison of the vehicles. The main findings of this work confirm that the test method and procedures presented here enable the systematic numerical data measurement and assessment of the flying performances of these vehicles, and show the applicability for the test and evaluation of general flapping MAVs.
Pseudolite Antenna Calibration Algorithm using a Multi-Antenna Receiver
Kim, Chong-Won ; Jeon, Sang-Hoon ; Kim, Ghang-Ho ; Kee, Chang-Don ; Lee, Taik-Jin ; So, Hyoung-Min ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 2, 2012, Pages 250~259
DOI : 10.5139/IJASS.2012.13.2.250
The need for position information in indoor environments has been growing lately. Several indoor navigation systems have been studied. Among them, pseudolite-based indoor positioning systems are one of the best systems to obtain precise position measurements. However, the installation of such systems is very difficult because the calibration of pseudolite antenna position is complicated. For precise calibration, the use of carrier phase measurements is necessary, and whenever carrier phase measurements are considered, problems with cycle ambiguity appear. In this paper, a new approach to calibrate the positions of pseudolite antennas is proposed. By using a multi-antenna, the ambiguity can be eliminated, epoch by epoch, for every single carrier phase measurement. Moreover, the number of calibration points can be reduced down to 3 by use of measurements collected at unknown positions. Using the proposed methods, the process of the collection of carrier phase measurements becomes considerably simple and convenient. Simulation results are presented to verify the proposed algorithms.
Development of a Fine Digital Sun Sensor for STSAT-2
Rhee, Sung-Ho ; Lyou, Joon ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 2, 2012, Pages 260~265
DOI : 10.5139/IJASS.2012.13.2.260
Satellite devices for fine attitude control of the Science & Technology Satellite-2 (STSAT-2). Based on the mission requirements of STSAT-2, the conventional analog-type sun sensors were found to be inadequate, motivating the development of a compact, fast and fine digital sun sensor (FDSS). The FDSS uses a CMOS image sensor and has an accuracy of less than 0.03degrees, an update rate of 5Hz and a weight of less than 800g. A pinhole-type aperture is substituted for the optical lens to minimize its weight. The target process speed is obtained by utilizing the Field Programmable Gate Array (FPGA), which acquires images from the CMOS sensor, and stores and processes the image data. The sensor accuracy is maintained by a rigorous centroid algorithm. This paper describes the FDSS designs, realizations, tests and calibration results.