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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 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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Inverse Problems in Aerodynamics, Heat Transfer, Elasticity and Materials Design
Dulikravich, George S. ; Dennis, Brian H. ; Baker, Daniel P. ; Kennon, Stephen R. ; Orlande, Helcio R.B. ; Colaco, Marcelo J. ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 4, 2012, Pages 405~420
DOI : 10.5139/IJASS.2012.13.4.405
A number of existing and emerging concepts for formulating solution algorithms applicable to multidisciplinary inverse problems involving aerodynamics, heat conduction, elasticity, and material properties of arbitrary three-dimensional objects are briefly surveyed. Certain unique features of these algorithms and their advantages are sketched for use with boundary element and finite element methods.
Solar Sails: Technology And Demonstration Status
Johnson, Les ; Young, Roy ; Barnes, Nathan ; Friedman, Louis ; Lappas, Vaios ; McInnes, Colin ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 4, 2012, Pages 421~427
DOI : 10.5139/IJASS.2012.13.4.421
Solar Sail propulsion has been validated in space (IKAROS, 2010) and soon several more solar-sail propelled spacecraft will be flown. Using sunlight for spacecraft propulsion is not a new idea. First proposed by Frederick Tsander and Konstantin Tsiolkovsky in the 1920's, NASA's Echo 1 balloon, launched in 1960, was the first spacecraft for which the effects of solar photon pressure were measured. Solar sails reflect sunlight to achieve thrust, thus eliminating the need for costly and often very-heavy fuel. Such "propellantless" propulsion will enable whole new classes of space science and exploration missions previously not considered possible due to the propulsive-intense maneuvers and operations required.
Feedback flow control using the POD method on the backward facing step wall model
Cho, Sung-In ; Lee, In ; Lee, Seung-Jun ; Lee, Choong Yun ; Park, Soo Hyung ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 4, 2012, Pages 428~434
DOI : 10.5139/IJASS.2012.13.4.428
Missiles suffer from flight instability problems at high angles of attack, since vortex flow over a fuselage cause lateral force to the body. To overcome this problem at a high angle of attack, the development of a real time vortex controller is needed. In this paper, Proper Orthogonal Decomposition (POD) and feedback controllers are developed for real time vortex control. The POD method is one of the most well known techniques for modeling low order models that represent the original full-order model. An adaptive control algorithm is used for real time control.
Development of Airworthiness Database System with Validation Process for Design Programs of General Aviation Aircraft
Lwin, Tun ; Lee, Jae Woo ; Kim, Sangho ; Lee, Hyojin ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 4, 2012, Pages 435~445
DOI : 10.5139/IJASS.2012.13.4.435
In this paper, a design process is established by integrating aviation safety requirements for the development of general aviation aircraft. An Airworthiness-Design Integration System, which integrates certification requirements with the entire design/analysis process, is developed and presented. For the proposed system, KAS 23/FAR 23/AC 23/CS 23 certification regulations are analyzed to determine design constraints and system compliance checks and to construct an ER&G (Engineering Requirement and Guide) and a Design-Certification Related Table (DCRT). Furthermore, through building a DB (Data Base), the management of design and certification related resources for developing a FAR 23 class aircraft are made. Certification tools and resources are also efficiently managed by the DB. The connection between the certification requirements and the detailed design process is proposed in this system. Tracking of this proposed method is validated by configuring a USE CASE and a system. The Airworthiness-Design Integration system will be constructed based on the system's design plan, certification system, and usage scenarios.
Various Structural Approaches to Analyze an Aircraft with High Aspect Ratio Wings
El Arras, Anas ; Chung, Chan Hoon ; Na, Young-Ho ; Shin, SangJoon ; Jang, SeYong ; Kim, SangYong ; Cho, Changmin ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 4, 2012, Pages 446~457
DOI : 10.5139/IJASS.2012.13.4.446
Aeroelastic analysis of an aircraft with a high aspect ratio wing for medium altitude and long endurance capability was attempted in this paper. In order to achieve such an objective, various structural models were adopted. The traditional approach has been based on a one-dimensional Euler-Bernoulli beam model. The structural analysis results of the present beam model were compared with those by the three-dimensional NASTRAN finite element model. In it, a taper ratio of 0.5 was applied; it was comprised of 21 ribs and 3 spars, and included two control surfaces. The relevant unsteady aerodynamic forces were obtained by using ZAERO, which is based on the doublet lattice method that considers flow compressibility. To obtain the unsteady aerodynamic force, the structural mode shapes and natural frequencies were transferred to ZAERO. Two types of unsteady aerodynamic forces were considered. The first was the unsteady aerodynamic forces which were based on the one-dimensional beam shape; the other was based on the three-dimensional FEM model shape. These two types of aerodynamic forces were compared, and applied to the foregoing flutter analysis. The ultimate goal of the present research is to analyze the possible interaction between the rigid-body degrees of freedom and the aeroelastic modes. This will be achieved after the development of a reliable nonlinear beam formulation that would validate the current results as well as enable a thorough investigation of the nonlinearity. Moreover, such analysis will allow for an examination of the above-mentioned interaction between the flight dynamics and aeroelastic modes with the inclusion of the rigid body degrees of freedom.
Application of the Laplace transformation for the analysis of viscoelastic composite laminates based on equivalent single-layer theories
Sy, Ngoc Nguyen ; Lee, Jaehun ; Cho, Maenghyo ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 4, 2012, Pages 458~467
DOI : 10.5139/IJASS.2012.13.4.458
In this study, the linear viscoelastic response of a rectangular laminated plate is investigated. The viscoelastic properties, expressed by two basic spring-dashpot models, that is Kelvin and Maxwell models, is assumed in the range to investigate the influence of viscoelastic coefficients to mechanical behavior. In the present study, viscoelastic responses are performed for two popular equivalent single-layered theories, such as the first-order shear deformation theory (FSDT) and third-order shear deformation theory (TSDT). Compliance and relaxation modulus of time-dependent viscoelastic behavior are approximately determined by Prony series. The constitutive equation for linear viscoelastic material as the Boltzmann superposition integral equation is simplified by the convolution theorem of Laplace transformation to avoid direct time integration as well as to improve both accuracy and computational efficiency. The viscoelastic responses of composite laminates in the real time domain are obtained by applying the inverse Laplace transformation. The numerical results of viscoelastic phenomena such as creep, cyclic creep and recovery creep are presented.
Autopilot Design for a Target Drone using Rate Gyros and GPS
Rhee, Ihnseok ; Cho, Sangook ; Park, Sanghyuk ; Choi, Keeyoung ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 4, 2012, Pages 468~473
DOI : 10.5139/IJASS.2012.13.4.468
Cost is an important aspect in designing a target drone, however the poor performance of low cost IMU, GPS, and microcontrollers prevents the use of complex algorithms, such as ARS, or INS/GPS to estimate attitude angles. We propose an autopilot which uses rate gyro and GPS only for a target drone to follow a prescribed path for anti-aircraft training. The autopilot consists of an altitude hold, roll hold, and path following controller. The altitude hold controller uses vertical speed output from a GPS to improve phugoid damping. The roll hold controller feeds back yaw rate after filtering the dutch roll oscillation to estimate the roll angle. The path following controller operates as an outer loop of the altitude and roll hold controllers. A 6-DOF simulation showed that the proposed autopilot guides the target drone to follow a prescribed path well from the view point of anti-aircraft gun training.
Collision Avoidance Maneuver Planning Using GA for LEO and GEO Satellite Maintained in Keeping Area
Lee, Sang-Cherl ; Kim, Hae-Dong ; Suk, Jinyoung ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 4, 2012, Pages 474~483
DOI : 10.5139/IJASS.2012.13.4.474
In this paper, a collision avoidance maneuver was sought for low Earth orbit (LEO) and geostationary Earth orbit (GEO) satellites maintained in a keeping area. A genetic algorithm was used to obtain both the maneuver start time and the delta-V to reduce the probability of collision with uncontrolled space objects or debris. Numerical simulations demonstrated the feasibility of the proposed algorithm for both LEO satellites and GEO satellites.
Ground Base Laser Torque Applied on LEO Satellites of Various Geometries
Khalifa, N.S. ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 4, 2012, Pages 484~490
DOI : 10.5139/IJASS.2012.13.4.484
This paper is devoted to investigate the feasibility of using a medium power ground-based laser to produce a torque on LEO satellites of various shapes. The laser intensity delivered to a satellite is calculated using a simple model of laser propagation in which a standard atmospheric condition and linear atmospheric interaction mechanism is assumed. The laser force is formulated using a geocentric equatorial system in which the Earth is an oblate spheroid. The torque is formulated for a cylindrical satellite, spherical satellites and for satellites of complex shape. The torque algorithm is implemented for some sun synchronous low Earth orbit cubesats. Based on satellites perigee height, the results demonstrate that laser torque affecting on a cubesat has a maximum value in the order of
which is comparable with that of solar radiation. However, it has a minimum value in the order of
which is comparable with that of gravity gradient. Moreover, the results clarify the dependency of the laser torque on the orbital eccentricity. As the orbit becomes more circular it will experience less torque. So, we can conclude that the ground based laser torque has a significant contribution on the low Earth orbit cubesats. It can be adjusted to obtain the required control torque and it can be used as an active attitude control system for cubesats.
Intentional GNSS Interference Detection and Characterization Algorithm Using AGC and Adaptive IIR Notch Filter
Yang, Jeong Hwan ; Kang, Chang Ho ; Kim, Sun Young ; Park, Chan Gook ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 4, 2012, Pages 491~498
DOI : 10.5139/IJASS.2012.13.4.491
A Ground Based Augmentation System (GBAS) is an enabling technology for an aircraft's precision approach based on a Global Navigation Satellite System (GNSS). However, GBAS is vulnerable to interference, so effective GNSS interference detection and mitigation methods need to be employed. In this paper, an intentional GNSS interference detection and characterization algorithm is proposed. The algorithm uses Automatic Gain Control (AGC) gain and adaptive notch filter parameters to classify types of incoming interference and to characterize them. The AGC gain and adaptive lattice IIR notch filter parameter values in GNSS receivers are examined according to interference types and power levels. Based on those data, the interference detection and characterization algorithm is developed and Monte Carlo simulations are carried out for performance analysis of the proposed method. Here, the proposed algorithm is used to detect and characterize single-tone continuous wave interference, swept continuous wave interference, and band-limited white Gaussian noise. The algorithm can be used for GNSS interference monitoring in an excessive Radio Frequency Interference environment which causes loss of receiver tracking. This interference detection and characterization algorithm will be used to enhance the interference mitigation algorithm.
GPS Output Signal Processing considering both Correlated/White Measurement Noise for Optimal Navigation Filtering
Kim, Do-Myung ; Suk, Jinyoung ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 4, 2012, Pages 499~506
DOI : 10.5139/IJASS.2012.13.4.499
In this paper, a dynamic modeling for the velocity and position information of a single frequency stand-alone GPS(Global Positioning System) receiver is described. In static condition, the position error dynamic model is identified as a first/second order transfer function, and the velocity error model is identified as a band-limited Gaussian white noise via non-parametric method of a PSD(Power Spectrum Density) estimation in continuous time domain. A Kalman filter is proposed considering both correlated/white measurements noise based on identified GPS error model. The performance of the proposed Kalman filtering method is verified via numerical simulation.
Internal Flow Dynamics and Regression Rate in Hybrid Rocket Combustion
Lee, Changjin ;
International Journal of Aeronautical and Space Sciences, volume 13, issue 4, 2012, Pages 507~514
DOI : 10.5139/IJASS.2012.13.4.507
The present study is the analyses of what has been attempted and what was understood in terms of improving the regression rate and enlarging the basic understanding of internal flow dynamics. The first part is mainly intended to assess the role of helical grain configuration in the regression rate inside the hybrid rocket motor. To improve the regression rate, a combination of swirl (which is an active method) and helical grain (which is a passive method) was adopted. The second part is devoted to the internal flow dynamics of hybrid rocket combustion. A large eddy simulation was also performed with an objective of understanding the origin of isolated surface roughness patterns seen in several recent experiments. Several turbulent statistics and correlations indicate that the wall injection drastically changes the characteristics of the near-wall turbulence. Contours of instantaneous streamwise velocity in the plane close to the wall clearly show that the structural feature has been significantly altered by the application of wall injection, which is reminiscent of the isolated roughness patterns found in several experiments.