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Enhancing the Resolution of Digital Elevation Models Using Surface Normal from Planetary Images Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-04-09 SungHyun Moon, Oleg Alexandrov, Uland Wong, Han-Lim Choi
A digital elevation model (DEM) can be generated using a gradient of a single image and a stereo image pair from an imaging sensor or laser altimeter sensor on an orbiter. These DEMs are affected by intrinsic problems such as stereo noise in the triangulation process or low spatial resolution from sparse measurement points. Various image-based techniques are presently used to enhance the resolution
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Closed-Form Impact-Angle-Control Guidance of Nose-Dive Missiles for Maximum Terminal Speed Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-04-09 Iksoo Kim, Han-Lim Choi, In-Soo Jeon
This paper addresses an impact angle control guidance problem for nose-dive missiles to achieve the maximum terminal speed against a fixed target in the same vertical plane. By modeling the aerodynamic drag as a drag polar, we set up the nonlinear system equations needed to pursue an analytic closed-form solution. This paper shows that maximizing the terminal speed is equivalent to minimizing a weighted
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Multi-disciplinary Optimization of Wing Sandwich Structure using Proper Orthogonal Decomposition and Automatic Machine Learning Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-04-09 Young Sang Kim, Chanwoo Park
The coupling between different disciplines for multi-disciplinary optimization greatly increases the complexity of a computational framework, while at the same time increasing CPU time and memory usage. To overcome these difficulties, first, proper orthogonal decomposition and radial basis function were used to generate a reduced-order model from the initial experimental points. Second, analysis results
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Improved Modeling Method for 3-Dimensional Woven Composites Using Weaving Parameters Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-04-07 Hiyeop Kim, Jungsun Park
To model 3-Dimensional woven composites, the width and thickness of the yarn are generally used as input parameters. However, since these parameters can only be obtained after the composites are molded, it is not efficient in the initial stages of design using woven composites. Therefore, a geometric modeling method using weaving parameters that can be known before manufacturing is required. In this
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Robust Adaptive Finite-Time Prescribed Performance Attitude Tracking Control of Spacecraft Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-04-07 Qijia Yao
In this paper, a novel adaptive fast nonsingular terminal sliding mode (FNTSM) control approach is proposed for the robust adaptive finite-time prescribed performance attitude tracking control of spacecraft subject to inertia uncertainties, external disturbances, and input saturation. First, a simple error transformation is introduced to guarantee the attitude tracking errors always stay within the
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A Linear Acceleration Control for Precise Trajectory Tracking Flights of a Quadrotor UAV Under High-wind Environments Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-04-07 Dasol Lee
In this paper, a linear acceleration control algorithm is proposed. The proposed algorithm aims to follow a given linear acceleration command accurately to enable precise trajectory tracking flights especially for a quadrotor unmanned aerial vehicle under high-wind environments. Existing linear acceleration control algorithms are based on feedforward control concept only, however the proposed algorithm
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Estimation Technique of Minimum Energy Required for Complete Deployment of Folded Fin Under Gust Requirement (II): Considering Time Constraint Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-04-07 Suk Young Jung
A previously developed estimation technique, of the minimum energy required for complete fin deployment under an operational requirement of gust speed, was modified to consider time consumed for fin unfolding as an additional requirement, which might lead to an increase of the required energy. Some modifications were made such as non-zero kinetic energy of unfolding fin when completely deployed and
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Integrated Framework for Staging and Trajectory Optimization of a Launch Vehicle Considering Range Safety Operations Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-03-25 Byounggyu Cho, Byeong-Un Jo, Jaemyung Ahn
This paper proposes an integrated framework for staging and trajectory optimization of a launch vehicle under a constraint on the instantaneous impact point (IIP) of the separated stage. The proposed framework iterates between the optimal staging module and the trajectory optimization module to minimize the lift-off mass of a launch vehicle for a given payload mass. The trajectory optimization module
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Aerodynamic Performance Enhancement of Tiltrotor Aircraft Wings Using Double-Row Vortex Generators Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-03-25 Hao Chen, Bo Chen
To improve the aerodynamic performance of tiltrotor aircraft, the flow characteristics of the V-22 airfoil without and with one, two parallel rows of vortex generators (VGs) were investigated using numerical simulation methods. The results were obtained with three-dimensional compressible Reynolds-averaged Navier–Stokes equations, and the turbulence was simulated with the SA-based DES model. The influence
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A New Method of Reducing the Vibration Localization of the Multi-packet Whole Mistuned Bladed Disk System Using Bladed Packets Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-03-25 Xuanen Kan, Bo Zhao
Multi-packet whole bladed disks are found in some turbo engines. At the same time, mistuning of blades is inevitable and it will lead to the vibration localization in which vibration energy mainly locates in some blades in the bladed disk system. It can accelerate the high cycle fatigue of the bladed disk. It is critical to search for an efficient way to control the level of vibration localization
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Dynamics and Adaptive Sliding Mode Control of a Mass-Actuated Fixed-Wing UAV Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-03-05 Xiaoqi Qiu, Mingen Zhang, Wuxing Jing, Changsheng Gao
Compared with UAVs controlled by aerodynamic surfaces, mass-actuated UAVs have higher aerodynamic efficiency and better stealth performance. This paper focuses on the dynamics and attitude control of a mass-actuated fixed-wing UAV (MFUAV) with an internal slider. Based on the derived mathematical model of the MFUAV, the influence of the slider parameters on the dynamical behavior is analyzed, and the
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Directional Axis Estimation including Wind Velocity for Fixed Wing UAV Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-03-10 Chanhong Park, Sanghyuk Park
A new method to estimate the aircraft heading angle, wind velocity, and airspeed bias error is proposed without relying on the magnetometer. A GPS, rate-gyro, pitot-static tube, and sideslip angle sensor are combined through a design of an extended Kalman filter based on a vectorial geometric relation among the ground, air, and wind velocity. The feasibility of the method is validated through a desktop
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A New Study on the Gap Effect of an Airfoil with Active Flap Control Based on the Overset Grid Method Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-03-05 Zhiyuan Hu, Guohua Xu, Yongjie Shi
Rotors with active flap control have considerable potential in reducing vibration and noise and improving aerodynamic performance. However, due to the movement of the flap, there are unavoidable gaps between the components that will lead to significant changes in the aerodynamic characteristics. Moreover, considering the difficulties in motion modeling and the accuracy of the simulation of the flow
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Experimental Investigation of Wing Rock Phenomenon of a Fighter Aircraft with Conical Forebody Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-03-05 Hyoung-Seog Chung, Donghyurn Cho, Jongbum Kim, Young Il Jang
To achieve supermaneuverability, the flight envelope for modern fighter aircraft should be extended beyond 40 \(\sim \)60° angles of attack region, where unstable and undesirable flight characteristics such as wing rock may occur. This paper investigates the wing rock phenomenon of a fighter configuration having conventional conical forebody through free-to-roll (FTR) wind tunnel tests. The time history
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Development of a Vision-Based Recognition and Position Measurement System for Cooperative Missions of Multiple Heterogeneous Unmanned Vehicles Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-03-05 Sukkeun Kim, Jihoon Park, Dongin Han, Eunsoo Kim, Daewoo Lee
Research on cooperation missions of multiple unmanned vehicles (UVs) is growing to overcome the limitations of conventional missions and to increase the variety of missions. In this study, a vision-based recognition and position measurement system was developed to cooperate with an unmanned aerial vehicle (UAV) in case an unmanned ground vehicle (UGV) is unable to drive due to terrain obstacles. Phase
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Inverse Design of Flow Distortion Dominated by Shock Wave Interaction with Experimental Verification Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-03-03 Kaikai Yu, Peng Su, Yile Chen, Jinglei Xu
With the development of supersonic/hypersonic vehicles, the influence of non-uniform flow has attracted increasing attention. Non-uniform flow exists everywhere in a scramjet, which is a potent engine for supersonic/hypersonic vehicles. Most flows entering the isolator, combustor, and nozzle exhibit high non-uniformity. Thus, several design methods for generating non-uniform flow have been proposed
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Approach Control Concepts and Optimal Vertiport Airspace Design for Urban Air Mobility (UAM) Operation Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-03-01 Kyowon Song, Hwasoo Yeo, Jung-Ho Moon
In this study, we proposed concepts of a vertiport airspace design that must precede for the practical operation of urban air mobility, an emerging new urban mobility solution. We developed algorithms to find the optimal radius of airspace for each concept and, through simulations, derived comparisons among them. We also introduced the concept of a vertiport terminal control area where an personal
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Numerical Simulation of Streamer Physics in Nanosecond Pulsed Surface Discharges Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-02-26 Sangjun Ahn, Jeongheon Chae, Hyung-Jin Kim, Kyu Hong Kim
Two-dimensional numerical simulations of a nanosecond pulsed single dielectric barrier discharge (SDBD) are performed in air. Streamers produced in nanosecond SDBDs have filamentary properties and generate a strong electric field and high-density gradient of charged particles. This results in non-equilibrium effects of electrons, which makes analysis of the plasma physics challenging. To simulate the
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Aerodynamic Performance of the Three-Dimensional Lumped Flexibility Wing Under Wind Fluctuating Condition Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-02-26 Mingkang Zhu, Jianyang Zhu, Tao Zhang
Understanding the effect of fluctuating wind on the aerodynamic performance of the wing is important for designing practical using flapping-wing micro air vehicles (FMAV). This paper aims at providing a systematic synthesis on the fluctuating wind influence on the performance of the three dimensional lumped flexibility wing based on the numerical analysis approach. The fluctuating wind is simplified
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Integrated Adaptive Control for Spacecraft Attitude and Orbit Tracking Using Disturbance Observer Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-02-26 Kewei Xia, Youngho Eun, Taeyang Lee, Sang-Young Park
This paper addresses the control issue of the integrated attitude and orbit tracking of spacecraft in the presence of inertia parameter uncertainty and spatial disturbance. By considering thruster as the control actuator, the 6-degree-of-freedom integrated model consisting of attitude and orbit dynamics is formulated. Based on the backstepping design, an adaptive control strategy is developed by exploiting
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Bi-criteria Aircraft Trajectory Optimization in Implementing the Area Navigation Concept Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-02-23 Vyacheslav Erokhin, Boris Lezhankin, Tatyana Portnova
To solve a problem of bi-criteria optimization of an aircraft flight trajectory using the data of satellite navigation systems, the authors suggest an approach based on the game theory methods. The target was set to organize trajectory control with two partial criteria of optimality (desired track deviation and position-fixing error) minimized simultaneously. It is shown that the minima of individual
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Numerical Investigation of Fixed and Non-fixed Separation with Shear Layer Adapted Delayed Detached Eddy Simulation Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-02-23 Li Hao, Liu Wei, Wang Shengye
Delayed detached eddy simulation (DDES) has been proved to be suitable for the numerical simulation of massively separated flow. Whereas, there are still some drawbacks in the treatment of gray area, which is the transition zone between Reynolds-Averaged Navier–Stokes (RANS) and large eddy simulation (LES). In this paper, a modified DDES with shear layer adapted (SLA) subgrid length scale was employed
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Design Optimization and Investigation of Aerodynamic Characteristics of Low Reynolds Number Airfoils Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-02-23 Ali Arshad, Lucas Brandão Rodrigues, Iñigo Martínez López
This study aims to develop a simple and efficient design optimization methodology for the low Reynolds number airfoils. XFOIL is used as an aerodynamic solver while modeFRONTIER workflow is employed for the design optimization purpose. The airfoil SG6043 is used as the reference airfoil for optimization due to its common applications when long-endurance characteristics are desired. A simple design
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A Practical Optimal Guidance Scheme Under Impact Angle and Terminal Acceleration Constraints Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-02-22 Hyo-Seon Chi, Yong-In Lee, Chang-Hun Lee, Han-Lim Choi
This paper proposes a practical optimal guidance law that can handle terminal angle and acceleration constraints while providing robustness against uncertainty in autopilot dynamics. Building upon a well-established linear-quadratic optimal guidance framework, we first derive an energy-minimizing guidance scheme that nullifies terminal acceleration called optimal guidance law with impact angle and
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Flight Simulation Training Devices: Application, Classification, and Research Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-02-17 Jelena Vidakovic, Mihailo Lazarevic, Vladimir Kvrgic, Ivana Vasovic Maksimovic, Aleksandar Rakic
Safe and efficient training using flight simulation training devices (FSTD) is one of the fundamental components of training in the commercial, military, and general aviation. When compared with the live training, the most significant benefits of ground trainers include improved safety and the reduced cost of a pilot training process. Flight simulation is a multidisciplinary subject that relies on
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Effect of Stringer Design on the Stability of Stiffened Composite Panel Under In-plane Shear: An Experimental Study Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-02-17 Yuequan Wang, Shuhua Zhu
The safe exploitation of the buckling and post-bulking region of stiffened composite panels is of prime interest in aerospace engineering. Experiments were carried out to investigate the effects of stringer design on the buckling and post-buckling behavior of stiffened composite panels subjected to in-plane shear loading in this study. Three configurations of I-shape stringers were designed with the
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Development and Verification of a Fuel System to Meet Impact Resistance Performance of Rotorcraft External Auxiliary Fuel Tanks Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-02-12 Won Choi, Hyunbum Park
In the event of an aircraft crash, the impact resistance performance of the fuel tank is essential to maximize the survivability of the crew. Damage caused by excessive load on the fuel cell and interference between the fuel cell and the surrounding structure is a main cause in case of an aircraft accident. The fuel system of fuel tank for aircraft should be designed to prevent fuel cell damage by
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Study of Separation Mechanism and Characteristics of Ridge-Cut Explosive Bolts Using Numerical Analysis Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2020-11-24 Juho Lee, Yong-Seok Kim, Seung-Ju Baek, Hyeon Su Jeong
Ridge-cut explosive bolts are a type of pyrotechnic release devices in which two connected structures are separated by explosives. They are designed such that shock waves can interact with and cut their body. Furthermore, they provide a clean separation surface and require a smaller explosive amount compared with other types of explosive bolts. In this study, ridge-cut explosive bolts of various diameters
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A New Guidance Algorithm Against High-Speed Maneuvering Target Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-01-22 Kyoung-Rok Song, Tae-Hun Kim, Chang-Hun Lee, Min-Jea Tahk
This paper aims to propose a new guidance algorithm for intercepting a high-speed maneuvering target, such as a tactical ballistic missile that flies in a quasi-ballistic trajectory. The motivation of this study lies in the fact that the classical proportional navigation guidance (PNG) undergoes the performance degradation under the above engagement scenario due to its intrinsic property. To deal with
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HCF Weak Link Optimization for Wide-Chord Fan Blades Based on Circumferential Stacking Line Design Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-01-18 Yong Chen, Zhonglin Wang, Xiaopu Zhang
This paper describes the combination of a Kriging surrogate model with a micro-genetic algorithm for studying the influence of circumferential perturbations from the stack line on the high-cycle fatigue (HCF) weak link of a fan blade in a high-bypass-ratio turbofan engine. Based on the circumferential perturbations of the fan blade stack line, an automated system is developed for the parameterized
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Design and Stability Analysis of High-Speed Unmanned Aerial Vehicle Electric Anti-Skid Braking System Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-01-18 Qiaozhi Yin, Hong Nie, Xiaohui Wei
A new combined electric anti-skid braking system of a high-speed unmanned aerial vehicle is designed to improve the stability and to reduce the system sensor noise. An electric anti-skid braking mechanism model considering the sensor noise effect is built in MATLAB/Simulink. The stability of a slip ratio braking system and a deceleration braking system is analyzed using the Routh criterion and Lyapunov
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Vibration Fatigue Analysis for Structural Durability Evaluation Under Vibratory Loads Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-01-12 Young-Sik Joo, Jong-Cheon Lee
The structural integrity of aircraft structures under vibratory loads is primarily evaluated through vibration tests, but it is necessary to predict the design life through vibration fatigue analysis at the design stage. Vibratory loads affect the durability of aircrafts by combining with the dynamic characteristics of their structures. The generation of stress spectrum in the vibratory loads, which
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Fault and Failure Tolerant Model Predictive Control of Quadrotor UAV Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-01-12 Wooyoung Jung, Hyochoong Bang
This paper presents fault tolerance control (FTC) of a quadrotor under actuator faults. A complete FTC design approach with fault detection and diagnosis (FDD) is addressed. The proposed FTC is based on the model predictive control, which can be applied to nonlinear systems using the so-called successive convexification algorithm, which converts a nonconvex function to a convex function in a successive
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Correction to: An LES for the Effects of Particle Size and Velocity Ratio on the Flow Structure in the Secondary Combustor Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-01-04 Jong-Chan Kim, Hanyoung Choi, Hong-Gye Sung
Due to an unfortunate oversight the acknowledgment section has been omitted.
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Effect of Atomic Oxygen on LEO CubeSat Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-01-04 W. M. Mahmoud, D. Elfiky, S. M. Robaa, M. S. Elnawawy, S. M. Yousef
Atomic oxygen (AO) is a major threat to satellites in Low Earth Orbits (LEO). AO causes serious damage to satellites such as erosion, corrosion and damage to almost all satellites surfaces. This study presents numerical prediction for the space environment effects on NARSSCube satellite using ATOMOX module in Space ENVironment Information System (SPENVIS) online simulation tools. Indeed, the prediction
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Optimization of Discrete Cavities with Guide Vanes in A Centrifugal Compressor based on A Comparative Analysis of Optimization Techniques Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-01-04 Sang-Bum Ma, Min-Su Roh, Kwang-Yong Kim
Discrete cavities with guide vanes were developed and optimized to improve the operating stability of a centrifugal compressor. Various combinations of search algorithms and surrogate models were tested to find the best optimization methods. Aerodynamic analysis was performed using three-dimensional Reynolds-averaged Navier–Stokes equations. The numerical results obtained for the total pressure ratio
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Enhanced Pressure Based Coupled Algorithm to Combine with Pressure–Velocity-Enthalpy for all Mach Number Flow Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-01-04 J. R. Shin, T. W. Kim
In this paper, a pressure-based coupled computational fluid dynamics algorithm for numerical analysis of all Mach number region flow is developed. For this purpose, an enhanced pressure based coupled algorithm was developed through the pressure–velocity coupled algorithm and the pressure-enthalpy coupled algorithm were combined. In additional, the Kurganov–Tadmor flux splitting scheme, which is mainly
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Efficient Methodology with Grid Configurations for HSI Noise Prediction in Hover Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2021-01-04 K. Kim, S. H. Park, M. J. Park, S. N. Jung, C. J. Kim
Complex and unsteady flow patterns occur around rotating rotor blades owing to the generation of shock waves at the blade tip and interference between the blade and tip wake when the blade rotates at high speeds, thereby resulting in specific noise characteristics. Furthermore, these noise characteristics cause noise pollution in private areas and degrade detectability of helicopters in military applications
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UAV Path Planning with Derivative of the Heuristic Angle Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2020-12-08 Daehee Lim, Jihoon Park, Dongin Han, Hwanchol Jang, Wontae Park, Daewoo Lee
This paper introduces improved weighted A* (WA*DH), an advanced version of the weighted A* (WA*). To increase the performance of WA*, we suggest a new parameter, the heuristic angle, which is defined as the angle between the direction of an nth node to the target and the direction of the heading from the (n−1)th node to the nth node on the path. The process of WA*DH involves searching nodes that degrade
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A Telemetry-Based Post-flight Wind Profile Estimation Method for Air-to-Surface Missiles Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2020-12-04 Seok-Woo Kim, Han-Lim Choi
This paper presents a wind profile estimation method for test flight of a short-range air-to-surface missile. The method integrates the telemetry data (e.g., navigation data, fin control history), empirical regional wind profile data, and a high-fidelity flight dynamics simulator to infer on the vertical wind profile that the missile has experienced during the flight. The inference procedure works
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An Improved Weight Optimization AAIM Method Aided by Barometric Altimeter Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2020-10-19 Xiaowei Xu, Jizhou Lai, Min Liu, Zhiming Zheng, Yuting Dai, Kai Huang
Aiming at the problem of insufficient availability in the satellite receiver autonomous integrity monitoring (RAIM) method, an improved aircraft autonomous integrity monitoring (AAIM) method aided by barometric altimeter based on weight optimization is proposed under the actual configuration of the airborne navigation system. The information of satellite navigation system and barometric altimeter is
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In-Flight Strain Monitoring of Aircraft Tail Boom Structure Using a Fiber Bragg Grating Sensor Based Health and Usage Monitoring System Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2020-10-19 Hyunseok Kwon, Yurim Park, Changkyo Shin, Jin-Hyuk Kim, Chun-Gon Kim
With the increased use of composite materials in aircraft structures, continuous and thorough monitoring of structural conditions is highly required for the assurance of safety and reliability. In this study, as part of the fiber Bragg grating (FBG) sensor-based aircraft health and usage monitoring system (HUMS) development research, in-flight strain monitoring of an aircraft tail boom structure using
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Performance Analysis and Mass Estimation of a Small-Sized Liquid Rocket Engine with Electric-Pump Cycle Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2020-09-29 Juyeon Lee, Tae-Seong Roh, Hwanil Huh, Hyoung Jin Lee
The propellant supply system of a liquid rocket engine using an electric pump has high reliability because of the relatively small number of components. The system also has the merit of a quick response and ease of control owing to its simple configuration. Recently, the rocket lab developed the Rutherford engine, which has an electric pump cycle, because of the improved technology in the electric
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Comparative Study for Inspection Planning of Aircraft Structural Components Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2020-09-23 Sung Jin Kim, Joo-Ho Choi
In the aircraft operation, the metallic airframes are usually exposed to the extreme loading conditions during the flights due to which the risk of failure should be assessed and held to an allowed level to prevent the associated loss. If the components are inspectable, the components should be inspected routinely so that the fatigue damage can be detected before failure, which usually requires non-destructive
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Effects of the O/F Ratio on the Performance of a Low Thrust LO X /Methane Rocket Engine with an ElecPump-fed Cycle Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2020-09-16 Byungil Yu, Hyun-Duck Kwak, Hong Jip Kim
Recently, electrically driven pump-fed cycle rocket engines (i.e., ElecPump engines) have received considerable attention. ElecPump engines are superior to pressure-fed engines and will likely replace gas generator cycle engines under a 100 kN thrust level. This study focuses on LOX/methane ElecPump engines with a low-thrust level and estimates the nominal operation point of the engine. The objective
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Optimal Task Assignment for UAV Swarm Operations in Hostile Environments Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2020-09-02 Jongyun Kim, Hyondong Oh, Beomyeol Yu, Seungkeun Kim
This paper proposes the engagement model and optimal task assignment algorithm for small-UAV swarm operations in hostile maritime environments. To alleviate the complexity of a real engagement environment, several assumptions are made: in the proposed engagement model, a vessel can attack the UAV within a certain range with a constant kill probability rate; and the ability of a vessel to attack UAVs
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Investigation and Improvement of Pusher-Propeller Installation Effect for Flying Wing UAV Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2020-08-18 Wenbo Shi, Jie Li, Shuai Zhao, Zhao Yang
This paper presents a collaborative experimental and numerical research to investigate the influences of the installation of propeller on aircraft aerodynamic performance, and two approaches to mitigate the propeller installation effect are also analyzed. The configuration under investigation is based on a real flying wing unmanned aerial vehicle with a two-bladed pusher-propeller mounted on the aft
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Development of Flight Control Law for Improvement of Uncommanded Lateral Motion of the Fighter Aircraft Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2020-08-18 Chong-Sup Kim, Chang-Ho Ji, Byoung Soo Kim
The Abrupt Wing Stall (AWS) at moderate Angle-of-Attacks (AoA) and transonic flight conditions can result in uncommanded lateral motions such as heavy wing, wing drop and wing rock that degrade handling qualities, mission performance and safety of flight for the aircraft. This phenomenon caused by asymmetric wing flows makes it difficult to perform precision tracking or maneuvering in the transonic
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Study on Thermal Properties of Epoxy-Adhesive Film for Aluminum Sandwich Composite Structure Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2020-08-13 Kyoungwon Oh, Hyunbum Park
Among many composite material structures, honeycomb sandwich composites have been used in various ways. The honeycomb sandwich is adhered by polymer resin adhesive and the stiffness of honeycomb sandwich structures is determined by adhesive characteristics. This study is intended to evaluate adhesive characteristics after surface treatment and lateral compressive characteristics before and after thermal
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Application of Weibull Parameter Estimation Methods for Fatigue Evaluation of Composite Materials Scatter Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2020-08-13 Changbae Lee, Duhyun Gong, SangJoon Shin
Rotorcraft composite structures are required to satisfy desired reliability levels when analyzing the scatter of material properties at coupon and element levels in accordance with the Federal Aviation Regulations “FAR 29.573” and the Advisory Circular “AC 29.573”. By estimating the strength and life shape parameters from static and fatigue test results, load enhancement factors can be obtained. Thus
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Gyroless Spin-Stabilization Controller and Deorbiting Algorithm for CubeSats Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2020-08-13 Jose E. Morales, Jongrae Kim, Robert R. Richardson
CubeSats are becoming increasingly popular in the scientific community. While they provide a whole new range of opportunities for space exploration, they also come with their own challenges. One of the main concerns is the negative impact which they can have in the space debris problem. Commonly lacking from attitude determination and propulsion capabilities, it has been difficult to provide CubeSats
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A Study on Airworthiness for Fuel System of Unmanned Air Vehicle Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2020-08-05 Nakgon Baek
This paper presents a study on airworthiness of fuel system for an unmanned air vehicle. The presented contents consist of network modeling for analysis and flight test results on fuel system airworthiness. First, performance prediction of fuel system for unmanned air vehicle was achieved using software tool based on theoretical analysis and empirical data. And also flight tests were performed for
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Numerical Study about Aerodynamic Interaction for Coaxial Rotor Blades Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2020-08-04 Sang Hyun Park, Oh Joon Kwon
In the present study, the interaction effect by inter-rotor spacing of coaxial rotor blades in hovering and forward flight is studied by using a Reynolds-averaged Navier–Stokes CFD flow solver based on mixed meshes. The meshes were composed of unstructured near-body region and Cartesian off-body region. The flux-difference splitting scheme of Roe was used for computing inviscid fluxes on the near-body
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Axial Turbine Performance Estimation During Dynamic Operations Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2020-08-04 Razvan Nicoara, Valeriu Vilag, Jeni Vilag, Zoltan Kolozvary
During service, a turbine engine undergoes frequently dynamic operations. Because of the changes in mass flow, temperature, pressure, as well as the different reaction of the components of turbine to these changes, the turbine performances may vary significantly. It is critical to understand and quantify these variations to design and integrate the turbine to the engine. This paper presents a study
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Analysis of Interaction Between Oscillating Jet Issuing from a Fluidic Oscillator and a Crossflow Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2020-07-31 Raunak Jung Pandey, Sang-Hyuk Kim, Kwang-Yong Kim
In the present study, numerical simulation was conducted to study both the internal and external flows of a fluidic oscillator in a quiescent environment and with a crossflow. Unsteady Reynolds-averaged Navier–Stokes analysis was used to evaluate the flow field. The blowing ratio was varied to understand the interaction between the free stream and the oscillating jet. Results for the time-averaged
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Numerical Investigation of Supersonic Lateral Jet Interaction for Subsonic Projectiles with Different Fins at Large Angle of Attack Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2020-07-31 Xiao Wang, Ruyi Tao, Wenjun Ruan, Hao Wang, Dongjian Su, Xinggan Lu
Detached Eddy Simulation is used to study the interaction flowfields of a supersonic lateral jet penetrating into the crossflow of projectiles with cruciform or X-type fin configurations at \({\text{Ma}} = 0.3\) and \(\alpha = 0^\circ ,30^\circ \sim 60^\circ\). For \(\alpha = 0^\circ\), typical flow structures such as barrel shock, Mach disk and counter-rotating vortex pair(CVP) induced from the jet
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Numerical Investigation on Aero-optical Reduction for Supersonic Turbulent Mixing Layer Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2020-07-23 Xi-wan Sun, Xiao-liang Yang, Wei Liu
The tangential injection flow commingled with the mainstream could be abstracted as mixing layer, and profound importance is attached to aero-optical reduction for film-cooling target-seeking vehicles in engineering application. Leveraging the in-house code based on explicit fifth-order Weighted Compact Nonlinear Scheme and ray-tracing method, the supersonic mixing layer is numerically simulated to
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CFDP PDU Tunneling Service over DTN Between Heterogeneous Deep Space Communication Assets Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2020-07-20 Cheol Hea Koo, Hyungshin Kim
In space exploration missions, the spacecraft have limited computing resources. In particular, the communications environments for these spacecraft, whether in deep space or the cislunar region, are characterized by intermittent connectivity loss, long signal-propagation delay, and high bit-error rates between spacecraft and their ground stations. Delay-Tolerant Network (DTN) has been introduced to
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An LES for the Effects of Particle Size and Velocity Ratio on the Flow Structure in the Secondary Combustor Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2020-07-20 Jong-Chan Kim, Hanyoung Choi, Hong-Gye Sung
The effects of flow structure and particle size in the secondary combustor of a ducted rocket on mixing are investigated using a two-phase large eddy simulation analysis. The corner recirculation zone and central recirculation area appear in the combustor. Vortexes are generated mainly by the axial inlet flow. The stretched eddies along the axial direction appear on the rear section of the combustor
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A New Cooperative Homing Guidance of Anti-ship Missiles for Survivability Enhancement Int. J. Aeronaut. Space Sci. (IF 0.509) Pub Date : 2020-07-15 Yeong-Cheol Kim, Chang-Hun Lee, Tae-Hun Kim, Min-Jea Tahk
This paper proposes a new cooperative homing guidance to enhance the survivability of multiple anti-ship missiles against a high-value target such a frigate or a battleship when prior information on the target is unknown. In this paper, the survivability enhancement for the multiple anti-ship missiles against the battleship with no preliminary information on its current heading direction and weak spot