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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 16, Issue 4 - Dec 2015
Volume 16, Issue 3 - Sep 2015
Volume 16, Issue 2 - Jun 2015
Volume 16, Issue 1 - Mar 2015
Selecting the target year
Performance of Contra-Rotating Propellers for Stratospheric Airships
Tang, Zhihao ; Liu, Peiqing ; Sun, Jingwei ; Chen, Yaxi ; Guo, Hao ; Li, Guangchao ;
International Journal of Aeronautical and Space Sciences, volume 16, issue 4, 2015, Pages 485~492
DOI : 10.5139/IJASS.2015.16.4.485
Small advance ratio and low Reynolds number of stratospheric propulsion system bring lots of challenges to the design of propellers. Contra-rotating propeller configuration is proposed to improve the propulsion efficiency. In this paper, the feasibility of contra-rotating propeller for stratospheric airship has been assessed and its performance has been investigated by wind tunnel tests. The experimental results indicate, at relatively low Reynolds number, although the advance ratio is fixed, the performance of propellers is different with variation of Reynolds number. Moreover, at the same Reynolds number, the efficiency of contra-rotating propeller achieved appears to be a few percent greater than that for a standard conventional propulsion system. It can be concluded that contra-rotating propellers would be an efficient means to improve the performance of stratospheric airship propulsion system.
Numerical Analysis of NACA64-418 Airfoil with Blunt Trailing Edge
Yoo, Hong-Seok ; Lee, Jang-Chang ;
International Journal of Aeronautical and Space Sciences, volume 16, issue 4, 2015, Pages 493~499
DOI : 10.5139/IJASS.2015.16.4.493
The aerodynamic performance of blunt trailing edge airfoils was investigated. The flow fields around the modified NACA64-418, which consists of the tip blade of the wind turbine and Mexico model of IEA wind, were analyzed. To imitate the repaired airfoil, the original NACA64-418 airfoil, a cambered airfoil, is modified by the adding thickness method, which is accomplished by adding the thickness symmetrically to both sides of the camber line. The thickness ratio of the blunt trailing edge of the modified airfoil,
, is newly defined to analyze the effects of the blunt trailing edge. The shape functions describing the upper and lower surfaces of the modified NACA64-418 with blunt trailing edge are obtained from the curve fitting of the least square method. To verify the accuracy of the present numerical analysis, the results are first compared with the experimental data of NACA64-418 with high Reynolds number,
, measured in the Langley low-turbulence pressure tunnel. Then, the aerodynamic performance of the modified NACA64-418 is analyzed. The numerical results show that the drag increases, but the lift increases insignificantly, as the trailing edge of the airfoil is thickened. Re-circulation bubbles also develop and increase gradually in size as the thickness ratio of the trailing edge is increased. These re-circulations result in an increase in the drag of the airfoil. The pressure distributions around the modified NACA64-418 are similar, regardless of the thickness ratio of the blunt trailing edge.
Two-Dimensional Moving Blade Row Interactions in a Stratospheric Airship Contra-Rotating Open Propeller Configuration
Tang, Zhihao ; Liu, Peiqing ; Guo, Hao ; Yan, Jie ; Li, Guangchao ;
International Journal of Aeronautical and Space Sciences, volume 16, issue 4, 2015, Pages 500~509
DOI : 10.5139/IJASS.2015.16.4.500
The numerical simulation of two-dimensional moving blade row interactions is conducted by CFD means to investigate the interactions between the front and rear propeller in a stratospheric airship contra-rotating open propeller configuration caused by different rotational speeds. The rotational speed is a main factor to affect the propeller Reynolds number which impact the aerodynamic performance of blade rows significantly. This effect works until the Reynolds number reaches a high enough value beyond which the coefficients become independent. Additionally, the interference on the blade row has been revealed by the investigation. The front blade row moves in the induced-velocity field generated by the rear blade row and the aerodynamic coefficients are influenced when the rear blade row has fast RPMs. The rear blade row moving behind the front one is affected directly by the wake and eddies generated by the front blade row. The aerodynamic coefficients reduce when the front blade row has slow RPMs while increase when the front blade row moves faster than itself. But overall, the interference on the front blade row due to the rear blade row is slight and the interference on the rear blade row due to the front blade row is much more significant.
The hybrid uncertain neural network method for mechanical reliability analysis
Peng, Wensheng ; Zhang, Jianguo ; You, Lingfei ;
International Journal of Aeronautical and Space Sciences, volume 16, issue 4, 2015, Pages 510~519
DOI : 10.5139/IJASS.2015.16.4.510
Concerning the issue of high-dimensions, hybrid uncertainties of randomness and intervals including implicit and highly nonlinear limit state function, reliability analysis based on the hybrid uncertainty reliability mode combining with back propagation neural network (HU-BP neural network) is proposed in this paper. Random variables and interval variables are as input layer of the neural network, after the training and approximation of the neural network, the response variables are obtained through the output layer. Reliability index is calculated by solving the optimization model of the most probable point (MPP) searching in the limit state band. Two numerical cases are used to demonstrate the method proposed in this paper, and finally the method is employed to solving an engineering problem of the aerospace friction plate. For this high nonlinear, small failure probability problem with interval variables, this method could achieve a good analysis result.
Experimental Study on the Performance of a Bidirectional Hybrid Piezoelectric-Hydraulic Actuator
Jin, Xiao Long ; Ha, Ngoc San ; Li, Yong Zhe ; Goo, Nam Seo ; Woo, Jangmi ; Ko, Han Seo ; Kim, Tae Heun ; Lee, Chang Seop ;
International Journal of Aeronautical and Space Sciences, volume 16, issue 4, 2015, Pages 520~528
DOI : 10.5139/IJASS.2015.16.4.520
The piezoelectric-hydraulic actuator is a hybrid device that consists of a hydraulic pump driven by a piezo-stack coupled to a conventional hydraulic cylinder. The actuator is of compact size, but can produce a moderate energy output. Such hybrid actuators are currently being researched and developed in many industrialized countries due to the requirement for high performance and compact flight systems. In a previous study, we designed and manufactured a unidirectional hybrid actuator. However, the blocking force was not as high as expected. Therefore, in this study, we redesigned the pump chamber and hydraulic cylinder and also improved the system by removing the air bubbles. Two different types of piezo-stacks were used. In order to achieve bidirectional capabilities in the actuator, commercial solenoid valves were used to control the direction of the output cylinder. Experimental testing of the actuator in unidirectional and bidirectional modes was performed to examine performance issues related to driving frequency, bias pressure, reed valve thickness, etc. The results showed that the maximum blocking force was measured as 970.2N when the frequency was 185Hz.
A Preliminary Design of Flight Test Conditions for a Sub-scale RBCC Engine using a Sounding Rocket
Kim, Hye-Sung ; Kim, Kui-Soon ; Oh, Se-Jong ; Choi, Jeong-Yeol ; Yang, Won-Seok ;
International Journal of Aeronautical and Space Sciences, volume 16, issue 4, 2015, Pages 529~536
DOI : 10.5139/IJASS.2015.16.4.529
Various R&D programs for rocket-based combined cycle (RBCC) engines have progressed worldwide for the space development and the defense applications. As a way toward indigenous domestic RBCC program, a preliminary design of flight test conditions was studied in this study for a sub-scale RBCC engine using a sounding rocket. Launch and flight profiles were calculated for several booster options and compared with that of HyShot II program. The result shows that the Korea Sounding Rocket-II (KSR-II) is a proper candidate to perform the flight test available in Korea. The recommend flight test conditions with KSR-II are Mach 6.0 with a test vehicle of 230 kg and Mach 7.4 with 50 kg. Present study will soon be followed by a design of sub-scale RBCC for a flight test using a sounding rocket.
Reliability Evaluation of a Pin Puller via Monte Carlo Simulation
Lee, Hyo-Nam ; Jang, Seung-gyo ;
International Journal of Aeronautical and Space Sciences, volume 16, issue 4, 2015, Pages 537~547
DOI : 10.5139/IJASS.2015.16.4.537
A Monte Carlo (MC) simulation was conducted to predict the reliability of a newly developed pyrotechnic pin puller. The reliability model is based on the stress-strength interference model that states that failure occurs if the stress exceeds the strength. In this study, the stress is considered to be the energy consumed by movement of a pin shaft, and the strength is considered to be the energy generated by pyrotechnic combustion for driving the pin shaft. Failure of the pin puller can thus be defined as the consumed energy being greater than the generated energy. These energies were calculated using a performance model formulated in the previous study of the present authors. The MC method was used to synthesize the probability densities of the two energies and evaluate the reliability of the pin puller. From a probabilistic perspective, the calculated reliability was compared to a deterministic safety factor. A sensitivity analysis was also conducted to determine which design parameters most affect the reliability.
Quasi-steady State Simulation of Rotating Detonation Engine
Niyasdeen, Mohammed ; Oh, Sejong ; Kim, Kui Soon ; Choi, Jeong-Yeol ;
International Journal of Aeronautical and Space Sciences, volume 16, issue 4, 2015, Pages 548~559
DOI : 10.5139/IJASS.2015.16.4.548
We performed a numerical simulation based on the two-dimensional (2-D) unsteady Euler's equation with a single-step Arrhenius reaction model in order to investigate the detonation wave front propagation of an Argon (Ar) diluted oxy-hydrogen mixture (
). This simulation operates in the detonation frame of reference. We examine the effect of grid size and the performance impact of integrated quantities such as mass flow. For a given set of baseline conditions, the minimal and maximum grid resolutions required to simulate the respective detonation waves and the detonation cell structures are determined. Tertiary shock wave behavior for various grids and pre-exponential factors are analyzed. We found that particle fluctuation can be weakened by controlling the mass flow going through the oblique shock waves.
Numerical Studies of Supersonic Planar Mixing and Turbulent Combustion using a Detached Eddy Simulation (DES) Model
Vyasaprasath, Krithika ; Oh, Sejong ; Kim, Kui-Soon ; Choi, Jeong-Yeol ;
International Journal of Aeronautical and Space Sciences, volume 16, issue 4, 2015, Pages 560~570
DOI : 10.5139/IJASS.2015.16.4.560
We present a simulation of a hybrid Reynolds-averaged Navier Stokes / Large Eddy Simulation (RANS/LES) based on detached eddy simulation (DES) for a Burrows and Kurkov supersonic planar mixing experiment. The preliminary simulation results are checked in order to validate the numerical computing capability of the current code. Mesh refinement studies are performed to identify the minimum grid size required to accurately capture the flow physics. A detailed investigation of the turbulence/chemistry interaction is carried out for a nine species 19-step hydrogen-air reaction mechanism. In contrast to the instantaneous value, the simulated time-averaged result inside the reactive shear layer underpredicts the maximum rise in
concentration and total temperature relative to the experimental data. The reason for the discrepancy is described in detail. Combustion parameters such as OH mass fraction, flame index, scalar dissipation rate, and mixture fraction are analyzed in order to study the flame structure.
Rotor Blade Sweep Effect on the Performance of a Small Axial Supersonic Impulse Turbine
Jeong, Sooin ; Choi, Byoungik ; Kim, Kuisoon ;
International Journal of Aeronautical and Space Sciences, volume 16, issue 4, 2015, Pages 571~580
DOI : 10.5139/IJASS.2015.16.4.571
In this paper, a computational study was conducted in order to investigate the rotor blade sweep effect on the aerodynamics of a small axial supersonic impulse turbine stage. For this purpose, three-dimensional unsteady RANS simulations have been performed with three different rotor blade sweep angles (
) and the results were compared with each other. Both NTG (No tip gap) and WTG (With tip gap) models were applied to examine the effect on tip leakage flow. As a result of the simulation, the positive sweep model (
) showed better performance in relative flow angle, Mach number distribution, entropy rise, and tip leakage mass flow rate compared with no sweep model. With the blade static pressure distribution result, the positive sweep model showed that hub and tip loading was increased and midspan loading was reduced compared with no sweep model while the negative sweep model (
) showed the opposite result. The positive sweep model also showed a good aerodynamic performance around the hub region compared with other models. Overall, the positive sweep angle enhanced the turbine efficiency.
Monocular Vision-Based Guidance and Control for a Formation Flight
Cheon, Bong-kyu ; Kim, Jeong-ho ; Min, Chan-oh ; Han, Dong-in ; Cho, Kyeum-rae ; Lee, Dae-woo ; Seong, kie-jeong ;
International Journal of Aeronautical and Space Sciences, volume 16, issue 4, 2015, Pages 581~589
DOI : 10.5139/IJASS.2015.16.4.581
This paper describes a monocular vision-based formation flight technology using two fixed wing unmanned aerial vehicles. To measuring relative position and attitude of a leader aircraft, a monocular camera installed in the front of the follower aircraft captures an image of the leader, and position and attitude are measured from the image using the KLT feature point tracker and POSIT algorithm. To verify the feasibility of this vision processing algorithm, a field test was performed using two light sports aircraft, and our experimental results show that the proposed monocular vision-based measurement algorithm is feasible. Performance verification for the proposed formation flight technology was carried out using the X-Plane flight simulator. The formation flight simulation system consists of two PCs playing the role of leader and follower. When the leader flies by the command of user, the follower aircraft tracks the leader by designed guidance and a PI control law, and all the information about leader was measured using monocular vision. This simulation shows that guidance using relative attitude information tracks the leader aircraft better than not using attitude information. This simulation shows absolute average errors for the relative position as follows: X-axis: 2.88 m, Y-axis: 2.09 m, and Z-axis: 0.44 m.
Research Progress of the Structure Vibration-Attitude Coordinated Control of Spacecraft
Yang, Jingyu ; Qu, Shiying ; Lin, Jiahui ; Liu, Zhiqi ; Cui, Xuanming ; Wang, Chu ; Zhang, Dujiang ; gu, Mingcheng ; Sun, Zhongrui ; Yang, Kang ; Zhou, Lanwei ; Chen, Guoping ;
International Journal of Aeronautical and Space Sciences, volume 16, issue 4, 2015, Pages 590~601
DOI : 10.5139/IJASS.2015.16.4.590
This paper gives an overview of research on the field of structure vibration-attitude coordinated control of spacecraft. First of all, the importance of the technology has been given an introduction, and then later the research progress of space structure dynamics modeling, research progress of structure vibration-attitude coordinated control of flexible spacecraft have been discussed respectively. Finally, future research on application of structure vibration-attitude coordinated control of spacecraft has been recommended.
Performance Evaluation of Hinge Driving Separation Nut-type Holding and Releasing Mechanism Triggered by Nichrome Burn Wire
LEE, Myeong-Jae ; LEE, Yong-Keun ; OH, Hyun-Ung ;
International Journal of Aeronautical and Space Sciences, volume 16, issue 4, 2015, Pages 602~613
DOI : 10.5139/IJASS.2015.16.4.602
As one of the mission payloads to be verified through the cube satellite mission of Cube Laboratory for Space Technology Experimental Project (STEP Cube Lab), we developed a hinge driving separation nut-type holding and releasing mechanism. The mechanism offers advantages, such as a large holding capacity and negligible induced shock, although its activation principle is based on a nylon cable cutting mechanism triggered by a nichrome burn wire generally used for cube satellite applications for the purpose of holding and releasing onboard appendages owing to its simplicity and low cost. The basic characteristics of the mechanism have been measured through a release function test, static load test under qualification temperature limits, and shock measurement test. In addition, the structural safety and operational functionality of the mechanism module under launch and on-orbit environments have been successfully demonstrated through a vibration test and thermal vacuum test.
Inflow Prediction and First Principles Modeling of a Coaxial Rotor Unmanned Aerial Vehicle in Forward Flight
Harun-Or-Rashid, Mohammad ; Song, Jun-Beom ; Byun, Young-Seop ; Kang, Beom-Soo ;
International Journal of Aeronautical and Space Sciences, volume 16, issue 4, 2015, Pages 614~623
DOI : 10.5139/IJASS.2015.16.4.614
When the speed of a coaxial rotor helicopter in forward flight increases, the wake skew angle of the rotor increases and consequently the position of the vena contracta of the upper rotor with respect to the lower rotor changes. Considering ambient air and the effect of the upper rotor, this study proposes a nonuniform inflow model for the lower rotor of a coaxial rotor helicopter in forward flight. The total required power of the coaxial rotor system was compared against Dingeldein's experimental data, and the results of the proposed model were well matched. A plant model was also developed from first principles for flight simulation, unknown parameter estimation and control analysis. The coaxial rotor helicopter used for this study was manufactured for surveillance and reconnaissance and does not have any stabilizer bar. Therefore, a feedback controller was included during flight test and parameter estimation to overcome unstable situations. Predicted responses of parameter estimation and validation show good agreement with experimental data. Therefore, the methodology described in this paper can be used to develop numerical plant model, study non-uniform inflow model, conduct performance analysis and parameter estimation of coaxial rotor as well as other rotorcrafts in forward flight.
Design space exploration in aircraft conceptual design phase based on system-of-systems simulation
Tian, Yifeng ; Liu, Hu ; Huang, Jun ;
International Journal of Aeronautical and Space Sciences, volume 16, issue 4, 2015, Pages 624~635
DOI : 10.5139/IJASS.2015.16.4.624
Design space exploration has been much neglected in aircraft conceptual design phase, which often leads to a waste of time and cost in design, manufacture and operation process. It is necessary to explore design space based on operational system-of-systems (SoS) simulation during the early phase for a competitive design. This paper proposes a methodology to analyze aircraft performance parameters in four steps: combination of parameters, object analysis, operational simulation, and key-parameters analysis. Meanwhile, the design space of an unmanned aerial vehicle applied in earthquake search and rescue SoS is explored based on this methodology. The results show that applying SoS simulation into design phase has important reference value for designers on aircraft conceptual design.