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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
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Volume & Issues
Volume 42, Issue 12 - Dec 2014
Volume 42, Issue 11 - Nov 2014
Volume 42, Issue 10 - Oct 2014
Volume 42, Issue 9 - Sep 2014
Volume 42, Issue 8 - Aug 2014
Volume 42, Issue 7 - Jul 2014
Volume 42, Issue 6 - Jun 2014
Volume 42, Issue 5 - May 2014
Volume 42, Issue 4 - Apr 2014
Volume 42, Issue 3 - Mar 2014
Volume 42, Issue 2 - Feb 2014
Volume 42, Issue 1 - Jan 2014
Selecting the target year
Surface Pressure Measurement on a Rotor Blade using Fast-Responding PSP
Kim, Kidong ; Kwon, Kijung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 1, 2014, Pages 1~9
DOI : 10.5139/JKSAS.2014.42.1.1
The present study was conducted by using fast-responding PSP technique to measure the surface pressure on a small-scale rotor blade in hover. Also, the study was performed to verify the accuracy and investigate its possibility of PSP application for rotor blade pressure measurement. Pulsed laser which has 532 nm wavelength was used as a light source. Lifetime measurement technique was applied. Also, the coated paint on a rotor blade was porous PSP which has faster response time than conventional PSP. The blades had NACA0012 airfoils. The length of rotor blade was 340 mm and chord was 40 mm with rectangular shape 1 set, and 4 sets had several tip sweepback angles. The measured results qualitatively showed that the upper surface pressure decreases with increasing the collective pitch angle. Quantitative pressure coefficients of PSP results were higher approximately 0.4 to 0.7 than the pressure tap data of the NASA experiment.
Investigation of Aircraft Plume IR Signature for Various Nozzle Configurations and Atmospheric Conditions
Kang, Dong-Woo ; Kim, In-Deok ; Myong, Rho-Shin ; Kim, Won-Cheol ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 1, 2014, Pages 10~19
DOI : 10.5139/JKSAS.2014.42.1.10
Nozzle configurations and atmospheric conditions play a significant role in the infrared signature level of aircraft propulsion system. Various convergent nozzles of an unmanned aircraft under different atmospheric conditions are considered. An analysis of thermal flow field and nozzle surface temperature distribution is conducted using a compressible CFD code. It is shown that the IR level in rear direction is considerably reduced in deformed nozzles, whereas the IR level in adjacent azimuth angles is increased in aspect ratios around 6 due to the plume spreading effect caused by high aspect ratio of nozzles. In addition, an analysis of atmospheric transmissivity for various seasons and observation distance is conducted using the LOWTRAN 7 code and subsequently plume IR signature is calculated by considering atmospheric effects. It is shown that the IR signature is reduced significantly in summer season and near the band of carbon dioxide in case of relatively close distance.
Composite Guidance Law for Impact Angle Control of Passive Homing Missiles
Park, Bong-Gyun ; Kim, Tae-Hun ; Tahk, Min-Jea ; Kim, Youn-Hwan ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 1, 2014, Pages 20~28
DOI : 10.5139/JKSAS.2014.42.1.20
In this paper, based on the characteristics of proportional navigation, a composite guidance law is proposed for impact angle control of passive homing missiles maintaining the lock-on condition of the seeker. The proposed law is composed of two guidance commands: the first command is to keep the look angle constant after converging to the specific look angle of the seeker, and the second is to impact the target with terminal angle constraint and is implemented after satisfying the specific line of sight(LOS) angle. Because the proposed law considers the seeker`s filed-of-view(FOV) and acceleration limits simultaneously and requires neither time-to-go estimation nor relative range information, it can be easily applied to passive homing missiles. The performance and characteristics of the proposed law are investigated through nonlinear simulations with various engagement conditions.
Low frequency Instability in Hybrid Rocket Post-chamber Configuration
Park, Kyungsu ; Lee, Changjin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 1, 2014, Pages 29~36
DOI : 10.5139/JKSAS.2014.42.1.29
Hybrid rocket displays many different low frequency pressure oscillations during combustion. Thermal lag between solid and gas phase is the primary mechanism to trigger low frequency pressure oscillations of around 10Hz, and Helmholtz or
mode also produces other types of low frequency oscillations above 10 Hz which is associated with the change in combustion volume. Since the flow characteristics in hybrid rocket is very similar to those in solid rocket combustion, it is not surprising to observe similar pressure oscillation behaviors. Experimental test shows that combustion pressure suddenly turns into to a big amplitude oscillation around 10Hz then followed by returning to an original pressure level after a short period combustion. Further investigations show that this instability is independent of the change in O/F ratio at all. One of the possible candidates is the vortex shedding dynamics over the backward step in the post combustion chamber. It is required to investigate the low frequency oscillation mechanism in the future study.
Conceptual Design and Development Test of an Unmanned Scaled-down Quad Tilt Prop PAV
Byun, Young-Seop ; Song, Jun-Beom ; Kim, Jae-Nam ; Jeong, Jin-Suk ; Song, Woo-Jin ; Kang, Beom-Soo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 1, 2014, Pages 37~46
DOI : 10.5139/JKSAS.2014.42.1.37
This paper describes the conceptual design and development test procedure of a unmanned scaled-down personal air vehicle(PAV) with drive and flight dual mode capability. Trade studies on operational requirements led to the suggestion of a quad tilt prop platform which has nacelle tilt capability with multi rotor configuration. Motors for propeller propulsion and driving mechanism were integrated into a single nacelle, then they were implemented by nacelle tilt mechanism for conversion between the drive and the flight modes. Primary design parameters and initial specifications were confirmed through conceptual design, then functional tests were performed with the test platforms for the drive and the flight modes.
Initial Sizing of a Glider Type High Altitude Long Endurance Unmanned Aerial Vehicle Using Alternative Energy
Han, Hye-Sun ; Kim, Chan-Eol ; Hwang, Ho-Yon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 1, 2014, Pages 47~58
DOI : 10.5139/JKSAS.2014.42.1.47
In this research, the initial sizing of a HALE(High Altitude Long Endurance) UAV which uses solar power and hydrogen fuel cell as an alternative energy was performed. Instead of a wing box type, a glider type was chosen since it is relatively easy to get a data thanks to many researches abroad. Maximum takeoff weight is around 150Kg and the propulsion system is composed of motor, propeller, solar cell, and hydrogen fuel cell which can be recharged through electrolysis. Maximum takeoff weight was estimated as aspect ratio, wing span, wing area change while considering energy balance of required energy which is necessary for flight during the entire day and available energy which can be taken from the solar cell.
Numerical Study on the Power-on Effect of a Pusher-propeller Aircraft using CFD
Cho, Jeong-Hyun ; Cho, Jin-Soo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 1, 2014, Pages 59~66
DOI : 10.5139/JKSAS.2014.42.1.59
In the case of a propeller-driven aircraft, power-on effect generated by the propeller has a strong influence on the performance and the stability of an aircraft directly and indirectly. A numerical study on the power-on effect has been performed using the CFD based on the multiple reference frame and sliding mesh model. The power-on effect increases the overall lift and the maximum lift of the aircraft. In addition to lift increment, power-on effect delays the stall of the aircraft. On the other hand, the power-on effect increases the drag significantly and consequently decreases the lift-to-drag ratio of the aircraft. Furthermore, the power-on effect decreases the nose-down pitching moment and consequently decreases the longitudinal static stability of the aircraft. It is expected that the analysis results presented and discussed in this report will be used as an important material for analyzing the aircraft performance and stability and will contribute the development of the propeller-driven aircraft with the pusher propeller.
KC-100 Full-scale Airframe Static Test
Shim, Jae-Yeul ; Jung, Keunwan ; Lee, Hanyong ; Lee, Sang Keun ; Hwang, Gui-Chul ; Ahn, Seokmin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 1, 2014, Pages 67~75
DOI : 10.5139/JKSAS.2014.42.1.67
A full-scale static test for a composite structure small aircraft (KC-100) was conducted in the KARI. The test includes 15 full-scale test and 7 local test conditions. Test requirements with test schedule, test article with dummy structures, test load generation, test system, and equipment are introduced for the test. Test load data of the 1st test condition(U1) was analyzed to evaluate an accuracy of load control for the test. The analysis results show that load data obtained during test were within tolerance of Static Null Pacing Error(SNPE) and the error value of load control was 8.6N. The error of load controls for the full-scale static test using dozens of actuators was calculated by a method suggested by authors. Test data for all other test conditions is also shown in this paper. Finally, reactions measured from restraint system of the U1 test condition show that the reaction changes as load increment. The factors which may change the change of reactions for a full-scale static test are introduced in this study.
Design Improvement of Vent System for Korean Utility Helicopter`s Anti-Explosion Fuel Tank
Kim, Joung-Hun ; Kim, Chang-Young ; Chang, Joong-Jin ; Lee, Mal-Young ; Shim, Dai-Sung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 1, 2014, Pages 76~81
DOI : 10.5139/JKSAS.2014.42.1.76
Military helicopter is exposed to the enemy gun firing due to the low altitude flight of contour flight, hovering & nap of the Earth flight, therefore it has the high possibility to be exploded by the gun firing. Recently the Anti-ballistic requirement is required to get the high level of safety from gun firing in required operational capability. The first military utility helicopter of SURION has the Anti-ballistic requirement and explosion proof. In order to meet the requirement, OBIGGS is adopted for the first time in KUH. It is proven that Anti-Explosion capability is satisfied to requirement for improving vent system which was insufficiently designed in development period and related to Anti-explosion.
Double Demodulation of a Ring Laser Dither Signal for Reducing the Dynamic Error of an Inertial Navigation System
Shim, Kyu-Min ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 1, 2014, Pages 82~89
DOI : 10.5139/JKSAS.2014.42.1.82
This paper discusses the methods for reducing the sampling time quantization errors of the body dither type ring laser gyroscope. A ring laser gyroscope has the angle quantization error which is generated by the frequency counting method of the laser beat signal and sampling time quantization error which is generated by the demodulation method for eliminating the body dithering in which the sampling periods are fitted to the dither periods. Generally, because the dither periods are longer than the calculation periods of the inertial navigation system, vehicle navigation errors are produced by long time attitude update missing during the vehicle move with a high dynamical motion. In this paper, the double demodulation method is proposed for reducing the sampling time quantization error and its effects under the dynamic situation are confirmed by simulation.
The Antenna Design for Korea SAT-5 Satellite Communication in Ka-band
Kim, Chun-Won ; Cheong, Chi-Hyun ; Kim, Kun-Woo ; Lee, Seong-Jae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 1, 2014, Pages 90~97
DOI : 10.5139/JKSAS.2014.42.1.90
In this paper, we have designed the antenna for Korea SAT-5 Satellite Communication which can use Ka band in the earth station. The antenna structure consist of the the dual-offset gregorian reflector that has high gain and efficiency, the corrugated horn that has symmetric radiation patterns and low side lobe levels, the iris polarizer that make circular polarization and the OrthoMode Transducer that separate transmitting and receiving signals. The designed antenna gain is more than 45.7dBi in Tx-band which use LHCP and 42.0dBi in Rx-band which use RHCP. The co-polarized and cross-polarized radiation pattern comply with ITU-R S.580-6 and S.731-1 that are recommended by International Telecommunication Union in the geostationary satellite. The Axial ratio is less than 1.0dB in Tx-band and 1.5dB in Rx-band that meet MIL-STD-188-164A.