• The Korea Journal of Herbology
• /
• v.34 no.1
• /
• pp.109-116
• /
• 2019

Objectives : This study aimed to analyze contents of chlorogenic acid among major ingredients and determine the optimal solvent for the antioxidant activity from Solidago virga-aurea var. gigantea(SV) aerial part. Methods : Mature aerial part of extracted SV at the first crop on June 2018 was used. SV was mixed with each at the ethanol concentrate rates of water, 10, 30, 50, 70, and 100% and extracted them for three times for eight hours at $70^{\circ}C$. The contents of chlorogenic acid and seven kinds of antioxidant activities were measured in SV extracts. Results : The highest the contents of chlorogenic acid was from 10% ethanol extracts showed. Total polyphenol and flavonoids of SV extracts were 126.16 mg/g and 105.84 mg/g, respectively. Scavenging activities of DPPH, ABTS, and hydroxyl radical significantly increased in a dose-dependent in SV extracts, while it was almost similar with control at the concentration of $500{\mu}g/mL$. $Fe^{2+}$ chelating activity significantly increase in a dose-dependent in SV extract, it was lower than control. Nitrite scavenging activity increased, dose-dependent in the sequence of pH 1.2> pH 3.0 > pH 6.0 in SV extracts, while it was almost similar with control at the concentration of $500{\mu}g/mL$, pH 1.2, and pH 3.0. Conclusions : Thus, this study found that higher contents of chlorogenic acid and excellent antioxidant activity were contained in 10% ethanol extracts in mature aerial part of SV. It is expected to be used as basic data as natural antioxidant materials.

• Spatial Information Research
• /
• v.17 no.2
• /
• pp.191-200
• /
• 2009

Aerial digital camera was used in outside since 2000 because of technical development & improvement of it. In korea, line type or frame type digital camera introduced since 2006 was used in manufacture and Correction of National base map appling the number and distribution of control point of analogue aerial triangulation from 2008. The main objective of the study is to compare and analyze the effects of the number and distribution of control points in accuracy of results, when we execute aerial triangulation with images from ADS40, line type sensored aerial digital camera available in korea. The result of RMSE can be concluded that accuracy of all the case are meet the aerial photograph surveying work regulation of NGI as to horizontal of control point ${\pm}0.068m$, ${\pm}0.073m$, ${\pm}0.071m$, height ${\pm}0.041m$, ${\pm}0.055m$, ${\pm}0.055m$, ${\pm}0.041m$, as to horizontal of check point ${\pm}0.167m$, ${\pm}0.113m$, ${\pm}0.110m$, height ${\pm}0.128m$, ${\pm}0.086m$, ${\pm}0.081m$. We have confirmed that it is possible to make out large scale digital topographic map.

• Journal of Advanced Navigation Technology
• /
• v.21 no.5
• /
• pp.450-458
• /
• 2017

This paper presents dynamic modelling and simulation study on attitude/altitude control of an insect-mimicking flapping micro aerial vehicle during hovering. Mathematical modelling consists of three parts: simplified flapping kinematics, flapping-wing aerodynamics, and six degree of freedom dynamics. Attitude stabilization is accomplished through linear quadratic regulator based on the linearized model of the time-varying nonlinear system, and altitude control is designed in the outer loop using PID control. The performance of the proposed controller is verified through numerical simulation where attitude stabilization and altitude control is done for hovering. In addition, it is confirmed that the attitude channel by periodic control is marginally stable against periodic pitching moment caused by flapping.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.49 no.12
• /
• pp.971-980
• /
• 2021

Recently popularized drone technologies have revealed that low-cost small unmanned aerial vehicles(UAVs) can be a significant threat to prevailing power by operating in group or in swarms. Researchers in many countries have tried to utilize integrated swarm unmanned aerial system(SUAS) in the battlefield. Agency for Defense Development also identified four core technologies in developing SUAS: swarm control, swarm network, swarm information, and swarm collaboration, and the authors started researches on swarm control and network technologies in order to be able to operate vehicle platforms as the first stage. This paper introduces design and integration of SUAS consisting of small fixed-wing UAVs, swarm control and network algorithms, a ground control system, and a launcher, with which swarm control and network technologies have been verified by flight tests. 19 fixed-wing UAVs succeeded in swarm flight in the final flight test for the first time as a domestic research.

• International Journal of Aeronautical and Space Sciences
• /
• v.11 no.3
• /
• pp.167-174
• /
• 2010

The design, dynamics, and control allocation of tri-rotor unmanned aerial vehicles (UAVs) are introduced in this paper. A trirotor UAV has three rotor axes that are equidistant from its center of gravity. Two designs of tri-rotor UAV are introduced in this paper. The single tri-rotor UAV has a servo-motor that is installed on one of the three rotors, which enables rapid control of its motion and its various attitude changes-unlike a quad-rotor UAV that depends only on the angular velocities of four rotors for control. The other design is called 'coaxial tri-rotor UAV,' which has two rotors installed on each rotor axis. Since the tri-rotor type of UAV has the yawing problem induced from an unpaired rotor's reaction torque, it is necessary to derive accurate dynamic and design control logic for both single and coaxial tri-rotors. For that reason, a control strategy is proposed for each type of tri-rotor, and nonlinear simulations of the altitude, Euler angle, and angular velocity responses are conducted by using a classical proportional-integral-derivative controller. Simulation results show that the proposed control strategies are appropriate for the control of single and coaxial tri-rotor UAVs.

• International Journal of Aeronautical and Space Sciences
• /
• v.2 no.2
• /
• pp.95-107
• /
• 2001

This paper is devoted to the parameter optimization of unmanned aerial vehicle's (UAV) flight control laws. Optimization procedure is based on the ideas of mixed $H_2/H_{\infty}$ control of multi-model plants. By using this approach, some partial $H_2$-terms defining the performance of nominal and parametrically perturbed Flight Control System (FCS) responses to deterministic command signals in stochastic atmosphere as well as $H_{\infty}$-terms defining robustness of the FCS can be incorporated in the composite cost function. Special penalty function imposed on the location of closed-loop system's poles keeps the speed of response and oscillatory properties for both nominal and perturbed FCS in reasonable limits. That is the reason why this procedure may provide reasonable trade-off between the performance and robustness of FCS that are very important especially for UAV. Its practical importance is illustrated by case studies of lateral and longitudinal control of small UAV.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.47 no.3
• /
• pp.212-219
• /
• 2019

As unmanned aerial vehicle (UAV) has been utilized for military operation, efficient ways for controlling UAV has been necessary. In particular, instead of conventional approach using console control, speech recognition based UAV control is essential for military environments in which rapid command operation is required. But research on this novel approach is not actively studied yet. In this study, we introduce efficient ways of speech recognition system operation for voice-driven UAV control, focusing on mission command control from manned aircraft rather than ground control center. We propose an efficient way of system operation for UAV control in cooperation of aircraft and UAV, and verify its efficiency via speech recognition experiment.

• Journal of the Korean Society for Aviation and Aeronautics
• /
• v.19 no.2
• /
• pp.16-22
• /
• 2011

It is recognized that the control surface fault is detected by monitoring the value of the coefficients due to the control surface deviation. It is found out the control surface stuck position by comparing the trim value with the reference value. To detect and isolate the fault, two mixed methods apply to the real-time parameter estimation and similarity measure. If the scatter of aerodynamic coefficients for the fault and normal are closing nearly, fault decision is difficult. Applying similarity measure to decide for fault or not, it makes a clear and easy distinction between fault and normal. Low power processor is applied to the real-time parameter estimator and computation of similarity measure.

• Korean Journal of Cognitive Science
• /
• v.2 no.2
• /
• pp.359-403
• /
• 1990

This paper introduces a blackboard system which extracts imbedded road and building structures irom aerial photograph images. The role of three major component(blackboard, knowledge source, and control module)in blackboard system will be illustrated in terms of knowledge representation and control strategies. The hypothesis on a blackboard will be organized in a hierarchical form, the knowledge sources which generate hypothesis and verify them will be shown in detail, and the control module will describe how the knowledge sources can dervie solutions. Especially this paper shows that searching image strutures can be greatly simplified by the use of a mapping image.

• International Journal of Aeronautical and Space Sciences
• /
• v.10 no.2
• /
• pp.148-160
• /
• 2009

By the development of recent technology, a new variant of rotorcrafts having four rotors start drawing attention from aerial-robotics engineers more than before. Its potential spans from just being control device test bed to performing difficult task such as carrying surveillance device to unreachable places. In this regards, modeling a quad-rotor is significant in analyzing its dynamic behavior and in synthesizing control system for such a vehicle. This paper summarizes the modeling of a mini quad-rotor aerial vehicle. A first principle approach is considered for deriving the model based on Euler-Newton equations of motion. The result of the modeling is a simulation platform that is expected to acceptably predict the dynamic behavior of the quad-rotor in various flight conditions. Linear models associated with different flight condition can be extracted for the purpose of control synthesis.