• Journal of Space Technology and Applications
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• v.1 no.1
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• pp.85-103
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• 2021

Environmental Control & Life Support System (ECLSS) technology is essential for humans to live safely in space other than on Earth and celestial bodies (ex, Moon, Mars etc.) in our solar system. Life support systems generally consist of Air Management System (AMS), Water Recovery System (WRS), and Waste Management System (WMS), and it can enable humans to breathe and live in enclosed dwellings in outer space. First, this paper described the development trends of life support systems that have been developed under the leadership of NASA. In addition, we introduced the current development status of life support system in operation on the International Space Station (ISS) and prospected the development trends in Korea.

• Journal of the Korean Society of Manufacturing Process Engineers
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• v.21 no.8
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• pp.72-78
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• 2022

Bending using high-frequency induction heating is used to bend pipes and sections, and is currently widely applied in industrial fields such as power generation facilities, ships, onshore plants, and offshore plants. The purpose of this study is to study the manufacturing process and design technology of high-frequency bending of pipe to make the best pipe design arrangement. Although various studies are being conducted in the field of high-frequency bending, more research is needed on high-frequency bending of pipes for ship building and offshore plants. The purpose of this study is to review the feasibility of production design using 3D model tool of S3D and AM(PDMS), and to review and improve bending thickness reduction, reduction rate, and roundness.

• The Korean Journal of Air & Space Law and Policy
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• v.19 no.1
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• pp.165-182
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• 2004

According to the Annex 17 to the Convention on International Civil Aviation, an appropriate authority of each contracting state has to define and allocate tasks and coordinate activities between the departments, agencies and other organizations of the State, airport and aircraft operators and other entities concerned with or responsible for the implementation of various aspects of the national civil aviation security programme. It is generally recognized that the three major parties responsible for the aviation security at an airport are appropriate government departments, airport operator and airlines. The airlines are the beneficiaries of security activities as well as the provider of security activities. So, their responsibilities have been critical in protecting civil aviation from unlawful interferences. The airport has to take leading role in implementing security tasks at airport area because the airport operator is the provider of airport facilities and services to its customer and the security activities belong to its services. The government has the responsibilities not only for establishing regulatory system but also for oversighting the implementation of aviation security activities. The paper is to review the revision of aviation security regulation and the changes of aviation security responsibilities, and costs and task assignment in Republic of Korea after September 11 event. The responsibilities, tasks and costs assigned to airlines, airport operators and government are introduced and evaluated in terms of economic fairness, effectiveness and efficiency of aviation security activities. The drawbacks of new legal system are pointed out and the suggestions to remedy them are proposed as conclusions.

• Journal of Aerospace System Engineering
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• v.13 no.5
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• pp.49-56
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• 2019

The Long-Term Sustainability (LTS) guidelines have attracted the most attention in the recent formation of international norms of behavior regarding outer space activities. The discussion began at the U.N. COPUOS in 2010. In June 2019, the 21 guidelines were finally adopted. The guidelines include international cooperation to promote and support the observation of the situation of orbiting objects, including space debris, for the purpose of preserving the space environment indefinitely, sharing data and forecasts on space weather, and announcing each country's space policy in accordance with international law. Some guidelines have failed to reach a consensus as the mitigation of space debris is often difficult to separate from space weapons tests. As plans for small satellites and Rendezvous and Proximity Operations have been projected for the future, it is expected that each countries' position on preserving the space environment will become more acute.

• Journal of Advanced Navigation Technology
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• v.27 no.5
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• pp.666-673
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• 2023

The runway occupancy time of landing aircraft is an important factor in determining runway capacity. The purpose of this study is to suggest improvement measures for runway occupancy time to improve the operation of existing airports. In order to derive improvement measures, a comparative analysis was conducted on the effectiveness of improvement using aircraft operation status data for specific days at the case airport. The FAA REDIM model was used to analyze the improvement plan, and the improvement application function of the model was used to confirm the effect of improving runway capacity by adding a rapid escape taxiway to an airport without a rapid escape taxiway. This study's approach can be applied to the derivation of runway improvement measures and preliminary prediction of effectiveness, and it presents cases that can be applied to future airport construction projects or airport improvement projects.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.4
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• pp.383-391
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• 2009

The detonation wave characteristics of JP-7 and oxygen mixture is investigated by one-step induction parameter model (IPM) obtained from a detailed chemistry mechanism. A general procedure of obtaining reliable one-step kinetics IPM for hydrocarbon mixture from the fully detailed chemistry is described in this study. The IPM is obtained by the reconstruction of the induction time database obtained from a detailed kinetics library. The IPM was confirmed by the comparison of the induction time calculations with that from detailed kinetics. The IPM is later implemented to a fluid dynamics code and applied for the numerical simulation of detonation wave propagation. The numerical results show the detailed characteristics of the detonation wave propagation in JP-7 and oxygen mixture at affordable computing time, which is not be possible by the direct application of the detailed chemical kinetics mechanism of hydrocarbon fuel combustion.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.10
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• pp.954-961
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• 2008

An experimental study has been conducted to investigate the flow field around the wing having a circular damage hole. The damage was represented by a circular hole passing through the model with 10% airfoil chord diameter and normal to the chord. The hole was centered at quarter or half chord. The PIV flow fields and static pressure measurements on the wing upper and lower surface were carried out at Rec=2.85×105 based on the chord length. The PIV results showed the two types of flow structures around a damage hole were formed. The first one was a weak jet that formed an attached wake behind the damage hole. The second one resulted from increased incidence; this was a strong jet where the flow through the hole penetrates into the free-stream resulting in extensive separation of oncoming boundary layer flow and development of a separated wake with reverse flow. The surface pressure data showed a big pressure alteration near the circular damage hole. The severity of pressure alteration was increased as a damage hole located nearer to the leading edge.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.10
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• pp.842-850
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• 2014

This paper presents a trajectory tracking controller for rotorcraft UAVs to improve the tracking performances in the presence of various uncertainties. The proposed tracking method consists of a velocity guidance law based on the relative distance and L1 adaptive augmentation loop for tracking the velocity commands. In the proposed structure, the desired velocity generated by the guidance law is the reference value of the adaptive controller for accurate path tracking. In the guidance law, the desired acceleration is generated based on the relative distance and its derivatives, and then the velocity command of the inner control loop is calculated by integrating the accelerations. $L_1$ augmentation loop supplements the linear controller to guarantee the flight performances such as a tracking accuracy in the presence of the uncertainties. The proposed controller was validated in actual flight tests to successfully demonstrate its capability using a quadrotor UAV.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.9
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• pp.839-847
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• 2011

This paper proposes a new guidance law for increasing the lethality of munitions. The well known PNG (Proportional Navigation Guidance) is inadequate for the munitions because of some weaknesses. Even if the munition does not have the impact point error, the acceleration command is non zero because the line-of-sight changes at all times in flight. Therefore, we use a difference between a target and an impact point. This proposed guidance law is similar to PNG in the form, but this guidance law concentrates a correction rate of flight path angle instead of the LOS (Line of Sight) rate. The correction of flight path angle is defined as the amount of impact point error. This impact point error can be calculated by neural networks rapidly. Finally, we show that the simulation results prove the suitability of this law.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.7
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• pp.508-516
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• 2019

In this paper, we propose a guidance law to control Impact Angle in consideration of look angle limit of the missile with strapdown seeker on the non-maneuvering target. The proposed law is based on sliding mode algorithm and generates acceleration commands using look angle and line of sight information provided by the strapdown seeker and navigation system. And, target velocity and target path angle are provided by like TADS (Target Acquisition and Designation System) at launch time. We can confirm that the target interception and impact angle control are possible through the convergence of the proposed sliding surface. In addition, it is possible to confirm that the sign of derivative result of the look angle at the maximum and minimum look angle is opposite to the sign of the look angle, so the look angle limit is not exceeded.