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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
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Journal of the Korean Society for Aeronautical & Space Sciences
Journal Basic Information
Journal DOI :
The Korean Society for Aeronautical & Space Sciences
Editor in Chief :
Volume & Issues
Volume 25, Issue 6 - Dec 1997
Volume 25, Issue 5 - Oct 1997
Volume 25, Issue 4 - Aug 1997
Volume 25, Issue 3 - Jun 1997
Volume 25, Issue 2 - Apr 1997
Volume 25, Issue 1 - Feb 1997
Selecting the target year
A Small Scale Wind Tunnel Test for High AOA Stability Study of High Maneuver Aircraft
Chung, In-Jae ; Reu, Tae-Kyu ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 25, issue 5, 1997, Pages 1~1
During the conceptual design phase of a high maneuvering jet trainer class aircraft, the aerodynamic characteristics of the aircraft nose and vertical tail have been studied to investigate the high angle-of-attack static stability of the aircraft, by using the low speed-small scale wind tunnel with 1/50 scale generic wing-body-tail model. For the aerodynamic characteristic analysis of the aircraft nose shape and vortex effects, the nose chine effects have been studied. Also, the vertical tail effects have been studied at high angle-of-attack. Through the study of the aerodynamic characteristics of the nose chine and the vertical tail shape, practical high angle-of-attack aerodynamic anaylsis procedure has been developed for the purpose of selecting the nose chine and the vortical tail combinations.
A Study on the Design and Application of Spin Recovery System for the Trainer Aircraft
Byun, Jin-Ku ; Lee, Sang-Jik ; Shin, Yoong-Hyun ; Lee, Dae-Yearl ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 25, issue 5, 1997, Pages 7~7
This paper presents a design and application of spin recovery system for the trainer aircraft which consists of anti-spin chute, chute box, chute support structure, chute deployment device, chute disconnect device(explosive bolt). It especially focuses on the design of anti-spin chute, and aircraft structural criteria under an ultimate operational condition and explains the entire spin recovery system and it's operational procedure. Before the spin flight test, ground functional test and on-board high taxing test were carried out for checking it's applicability and reliability, and then the results are also briefly described.
Numerical Computation of Flows about an Aircraft with Flow-through Inlet
Lee, Seung-Soo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 25, issue 5, 1997, Pages 16~16
An Euler solver which can use arbitrary multi-block grid systems has been developed. This solver uses MUSCL approach for the higher order of spatial discretization error. Furthermore, it has the exit boundary condition given in terms of mass flow rate so that it can simulate the flows through engine inlet. The flow-through exit boundary condition, unlike Murman's method, does not have to regenerate inlet duct grid for the different mass flow rates. The solver has been tested on a generic missile and its results have been compared with the experimental and computational results. Mixed internal and external flows around a jet trainer with a pitot type inlet have been computed.
A study on the Development of General Purpose Program for the Analysis of Flows in the High Performance Combustor of a Gas Turbine
Shin, Dong-Sin ; Lee, Hyeong-Rae ; Hur, Nam-Keon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 25, issue 5, 1997, Pages 24~24
We developed a general purpose program for the analysis of flows in a gas turbine combustor. The program uses non-staggered grids based on finite volume method and the cartesian velocities as primitive variables. The combustion model is irreversible one step reaction with infinite chemistry. We considered the Favre averaged governing equations and the clipped gaussian distribution as a probability density function of the conserved scalar. We calculated n flow inside the C-type diffuser to check the boundary fitted coordinate. The velocity vector and kinetic energy distribution show the effect of curvature. The cross section where the curvature ends shows the secondary flow and vortex. The velocity profiles at cross section agree well with experimental results. We calculated turbulent diffusion flame behind a bluff body for the combustion simulation. Simulation shows two recirculating region like experimental results. Simulated velocity, turbulent kinetic energy, temperature and concentration distribution agree well with experimental data.
A Study on Real Time Linear Simulation and Control for Aircraft Gas Turbine Engine
Kong, Chang-Duk ; Kim, Sog-Kyun ; Ki, Ja-Young ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 25, issue 5, 1997, Pages 36~36
The performance of aero gab turbine engine should be optimized because it is directly related to overall aircraft performance. In this study, by using the dynamic simulation program DYNGEN with modifying the block data component maps into new maps of an aero gas turbine engine, a nonlinear dynamic simulation was performed to predict the overall engine performance at two cases of flight conditions such as M=0, sea lever=0, and M=0.6, altitude=1.5km. Also by using an interpolation scheme for sampling data about several operating points, a real time linear simulation was derived for nonlinear gas turbine engine and was compared with other cases such as the 3% rpm step model, the 5% rpm step model, and the 6% rpm step model within operating range. Finally control schemes such as the PI (Proportional-Integral) and the optimal LQR(Linear Quadratic Regulator) compensator were applied to improve an engine dynamic performance with step fuel flow rate. Comparing the results, it was proven that the LQR controller can suppress the overshoot of turbine inlet temperature more effectively than the PI controller.
Characteristics of Reduced Models for the Control of a Turbojet Engine
Boo, Joon-Hong ; Seo, Jong-Bae ; Kim, Jin-Gon ; Min, Sung-Ki ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 25, issue 5, 1997, Pages 46~46
Linear system models of a turbojet engine based on actual performance maps were constructed and investigated for their characteristic behavior, Various reduced models were compared with a nonlinear simulation result, in which the fuel flow is the only control input and is given as a function of time. The reduced models were consisted of 2 to 5 state variables with different combinations. As long as the engine RPM is considered as one of the state variables, only minor deviations from the full model were observed during a simulation of the transient operation. Furthermore, the models generated by 5 different magnitude of perturbations were compared. The result of this study can be utilized in constructing more dependable and economic linear model for electronic turbojet engine controller.
A Study on Stress Analysis of Tire Tread Block
Kim, Doo-Man ; Kwon, Young-Chan ; Shin, Dong-Yeop ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 25, issue 5, 1997, Pages 55~55
The deformation behavior of a tire tread rubber in contact with the roadway is complicated under the traction and breaking conditions. Because it is closely connected with running conditions and wear of tire, its proper analysis is difficult in theoretical and experimental method though many studies have been proceeded. In this paper, distributions of contact pressure and the shearing stress of a tread rubber block of truck tire subjected to compressive load P and lateral load Q are obtained. This analysis calculation predicts markedly different contact pressure distribution from those given previously by this analysis for a wide range of shape factor variation. Futher, we gave two kind of analysis by the energy method and the finite element method (ABAQUS code) on the contact pressure and the shearing stress of a tread block under P and Q. These analytical results are compared with each other and the previous ones and then show that the highest contact pressure remains moderate]y finite but not to be considerably large as predicted by the previous FEM analysis.
Effects of Volume Fraction and Porosity on the Unsteady Thermal Stress of F G M Plate
Kim, Kui-Seob ; Choi, Deok-Kee ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 25, issue 5, 1997, Pages 62~62
The material properties of a heterogeneous material such as the functionally graded materials is given as a function of location. Therefore, the heat conduction equation on such the herterogeneous material become nonlinear and it is found to be difficult to solve such problems analytically. In order to solve the unsteady heat conduction equation, the perturbation theory and a modified Green's function are employed. Applying the modified Green's function makes it easy to build the perturbation solution to the problem without carrying out the difficult inverse Laplace transformation. Using the temperature distribution and the transient thermal stresses obtained by the perturbation theory and the modified Green's function, the effects of the volume fraction and the porosity on the unsteady thermal stresses of the functionally graded materials is studied in this paper. A one-dimensional infinite plate composed of the functionally graded materials is considered to illustrate the validation of the present method.
A Study on the Stability of Spinning Free-Free Beam Subjected to Follower Forces
Lee, Won-Cheol ; Kim, Ji-Hwan ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 25, issue 5, 1997, Pages 69~69
It is studied the critical spinning speed of a spinning isotropic Timoshenko beam with free-free boundary condition under a tip follower force. The critical speeds are computed for various non-dimensional parameters. Isoparametric
element is used to analyze the two dimensional Timoshenko beam. For a beam with free-free end condition, a convergence test of critical spinning speed is performed. The effects of follower force, shear deformation and rotary inertia on critical spinning speed of beam are studied.
Active Vibration Control of Composite Grid Structure by Piezoceramic Sensors and Actuators
Ra, Wan-Kyu ; Kwak, Moon-Kyu ; Yoon, Kwang-Joon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 25, issue 5, 1997, Pages 76~76
This paper is concerned with the active vibration control of grid structures by means of piezoceramic actuators and sensors. The vibration control technique for the grid structure used in this paper is based on the positive position feedback control, which has been successfully used for the vibration control of beam structures. The decentralized and centralized positive position feedback control methodologies are developed using the symmetric and anti-symmetric properties of bending and torsional modes of the grid structure. Electronic circuits for the realization of control schemes are explained in detail. The control techniques prove its effectiveness by experiments.
Design of Overlapping Decentralized Kalman Filter for Initial Rapid Alignment of Strapdown Inertial Navigation System
Park, Chan-Gook ; Kim, Kwang-Jin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 25, issue 5, 1997, Pages 86~86
In this paper, a decentralized filtering with the overlapping decomposition is performed for improving alignment time of strapdown inertial navigation systems(SDINS). To apply the overlapping decentralized Kalman filter to the initial alignment, we investigate the SDINS error model and suggest the good overlapping subsystem. Based on the SDINS error model, a correlation between attitude errors and velocity and sensor errors is analyzed. Using the correlation the overlapping states are determined so that velocity errors are included, off-diagonal blocks are close to zero, and the each subsystem with the overlapping decomposition is completely observable. Also the error model in accordance with the conditions is reordered. Through the covariance analysis, it is shown that the performance of the proposed model is similar to that of the optimal model but the calculation burden is reduced to one-third.
Dynamic Response of Landing Gear Taxiing on Uneven Runways
Nie, H. ; Lim, Kyeong-Ho ; Hwang, Jae-Hyeok ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 25, issue 5, 1997, Pages 96~96
An analytical landing gear model of simulating actual aircraft taxiing behavior by the power spectral density method is formulated. The dynamic model deals with not only shock-absorber non-linear damping and air-spring stiffness, but also tire non-linear damping and stiffness. The validity of this model is demonstrated with a comparison of frequency-domain and time-domain analytical results of dynamic response for two aircrafts, Boeing 707 and Boeing 737-94. The equivalent linearization technique in probabilistic method is introduced to treat landing gear non-linear parameters such as shock-absorber air-spring force, hydraulic damping and Coulomb friction, and tire stiffness. It is concluded that the air-spring stiffness and damping of shock-absorber have a great effect on root-mean-square of sprung-mass overload. The decrease of air-spring stiffness and increase of shock-absorber damping cause on obvious reduction in vibration level. An approach for determining the lower limit of air-spring stiffness and the upper limit of shock-absorber damping is presented, which is useful to assess and improve dynamic properties of aircraft as well as landing gears. For instance, it may give 43% and 60% reduction in root-mean-square sprung-mass overload(i.e., aircraft gravity overload) respectively for Boeing 707 and Boeing 737-94 aircraft by selecting the presented air-spring stiffness and shock-absorber damping.
Design of a Robust Force Controller of Control Loading System of a Flight Simulator using Adaptive Algorithm
Hwang, Jai-Hyuk ; Lee, Seong-Choon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 25, issue 5, 1997, Pages 108~108
In this paper, a robust force control algorithm, which provides the same wheel forces in real time to the student pilot in a flight simulator as those occurred during real flight, has been suggested. The novel force controller is designed using STC(self-tuning controller) that estimates the unknown parameters of force generating system and updates the control forces appropriately in real time. The force controller consists of feedback and feedforward parts. Feedback part is designed to reduce the effect of disturbance using inverse dynamics, PI control, and STC. Feedforward part is to improve the command following ability. It has been found by a series of simulation that the force controller suggested in this study has excellent command following ability and robustness to parameter errors.
Landing Gear Modelling for a Real-time Simulation
Rhee, In-Seok ; Cho, Byeong-Kwan ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 25, issue 5, 1997, Pages 117~117
Airplane landing gear system is modelled for a simulation of an airplane on runway. Each landing gear is considered as spring-damper system with 1 degree of freedom, and tires are modelled as three directional nonlinear spring-dampers. Two landing simulations and a taxing simulation are performed for verification of these modelling.
Fabrication and Evaluation of a Silicon Servo Accelerometer
Seo, Jae-Beom ; Shim, Kyu-Min ; Moon, Hong-Key ; Oh, Moon-Su ; Lee, Kwan-Sup ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 25, issue 5, 1997, Pages 126~126
This paper presents the initial results of development of a inertial navigation grade silicon pendulous servo accelerometer. This effort focused on the developing a bulk-micro-machined silicon pendulum, characteristics of pendulum and a testing methods of accelerometer. The performance data presented in this paper includes threshold, bias short term stability and nonlinerity of scale factor. This silicon accelerometer developed is demonstrated the feasibility of meeting 1NM/hr accuracy.
Analysis of Random Drift Characteristics for a Single Degree-of-Freedom Rate Integrating Gyroscope
Moon, Hong-Key ; Choi, Young-Whan ; Kim, Nyun-Ook ; Oh, Moon-Su ; Lee, Young-Shin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 25, issue 5, 1997, Pages 132~132
This paper presents an error equation for a single degree of freedom rate integrating gyroscope. It is demonstrated that the power variation of a motor is a dominant source of gyroscope random drift, if the gyro temperature is controlled precisely and the other error sources are isolated properly. Stability test for motors and gyros are performed by using two types of motor power supplies which are made of highly stable quartz oscillators. Using the sine wave motor supply which is designed to minimize higher harmonic terms of output voltage, the gyroscope random drift can be reduced significantly.
The Damage Tolerance Analysis Techniques of an Aircraft Wing
Joo, Young-Sik ; Kim, Min-Sung ; Jung, Byung-Woo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 25, issue 5, 1997, Pages 141~141
This paper delineates the requirements and analysis procedure of the damage tolerance analysis for the aircraft safety and structural life prediction. The U.S. military specification (MIL-A-83444) describes the damage tolerance analysis requirements in terms of initial crack assumption, residual strength standard, and inspection periods, etc. Those are applied in appropriate manner in accordance with the structure types and inspectabilities. In this paper, damage tolerance analysis procedures according to the structure types and inspectabilities are briefly summarized. A damage tolerance analysis result of a small aircraft is also shown as an example.
The First Wind Tunnel in Korea
Hahn, Man-Sop ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 25, issue 5, 1997, Pages 147~147
Development of a Dry Low Emission Combustor for the ASE120 Industrial Gas Turbine Engine
Woo, Yoo-Cheol ; Ki, Kwan-No ; Ahn, Byung-Jae ; Kim, Joong-Shin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 25, issue 5, 1997, Pages 151~151
Performance Analysis and Installation Design of Various Propulsion Integrations
Chin, Kwang-Seok ; Park, Ji-Wan ; Kong, Chang-Deok ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 25, issue 5, 1997, Pages 159~159
Structural Design and Test/Evaluation of Small Gas Turbine Engine
Kim, Gyeong-Su ; Kim, Seung-U ; Kim, U-Hyeong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 25, issue 5, 1997, Pages 170~170
Combustion Instability in Liquid Rocket Engines
Yoon, Myeong-Won ; Yoon, Jae-Keon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 25, issue 5, 1997, Pages 183~183