• Journal of Astronomy and Space Sciences
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• v.2 no.1
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• pp.1-6
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• 1985

The U.S. Space Shuttle represents the beginning of a new era in transportation and is the critical element in the industrialization of the near-Earth-space. Most of its flights are dedicated to reducing costs launching commercial satellites. However, it provides a microgravity environment for processing unique and improved materials which is generating great interest in both civilian and military sectors. The space shuttle is also the necessary step in establishing a permanent space station which could host materials analysis laboratories and commercial processing facilities. This paper reviews the different elements of the space shuttle transportation system, a typical mission scenario, and discusses current activities in materials processing in space.

• Journal of Astronomy and Space Sciences
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• v.1 no.1
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• pp.35-39
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• 1984

The design of the reusable thermal protection system for the space shuttle orbiter using silica tile played one of key roles in the successful flight of the Columbia and subsequent space shuttles. The basic design goals for this thermal protection system were identified. Manufacturing procedures for the silica tile and the structure of the tile system were also described.

• Journal of the Korean Society of Propulsion Engineers
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• v.20 no.3
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• pp.37-53
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• 2016

This paper deals with an optimal output control for Space Shuttle Main Engine (SSME), a liquid propellant rocket engine using a staged-combustion cycle. For this purpose, we modeled simplified mathematical model of SSME using each SSME component divided into 7 major categories and found trim points called Rated Propulsion Level (RPL). For design the closed-loop system of SSME, we designed optimal output feedback Linear Quadratic Regulation (LQR) control system using SSME linearized model under RPL 104% and demonstrated the performance of the controller through numerical simulation.

• Journal of the Korean Society of Propulsion Engineers
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• v.23 no.4
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• pp.50-60
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• 2019

This paper introduces the development of a toolbox for the Space Shuttle Main Engine(SSME) based on MATLAB/Simulink. A mathematical model of rocket engine creation and validation can be a complex process, the development of a rocket engine toolbox simplifies this process, thereby facilitating engine performance optimization as well as new design development. The mathematical modeling of the SSME dealt with in this paper is formed by 32 first-order differential equations derived from seven governing equations. We develop the toolbox for the SSME classifying each module according to the engine components. Further, we confirm the validity of the toolbox by comparing the results of the simulation obtained using the toolbox with those obtained using the original simulation of the engine.

• International Journal of Aeronautical and Space Sciences
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• v.17 no.4
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• pp.535-550
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• 2016

Securing the safety and the reliability of liquid-propellant rocket engines (LREs) for space vehicles is indispensable as engines consist of many complex components and operate under extremely high energy-dense conditions. Thus, health monitoring has become a mandatory requirement, especially for the reusable LREs that are currently being developed. In this context, a dynamic simulation program based on MATLAB/Simulink was developed in the current research on the Space Shuttle Main Engine (SSME), a partly reusable engine. Then, a series of fault simulations using this program was conducted: at a steady state operating condition (104% Rated Propulsion Level), various simulated fault conditions were artificially injected into the simulation models for the five major valves, the pumps, and the turbines of the SSME. The consequent effects due to each fault were analyzed based on the time responses of the major parameters of the engine. It is believed that this research topic is an essential pre-step for the development of fault detection and diagnosis algorithms for reusable engines in the future.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.4 no.1
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• pp.119-129
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• 1996

이 기술해설은 1989년 7 - 8월호 Journal of Guidance and Control ( Vol. 12, No. 4) 에 실린 William H. Phillips의 "Flying Qualities from Early Airplanes to the Space Shuttle"의 논문을 발췌, 번역한 것이다. 여기서는 비행성 연구에 관한 역사적인 발전과정과 비행성 요구조건의 변천에 대하여 그 내용을 비행성의 영역, 초기의 발전과정, 요구조건에 관한 연구, 지령식 조종계통, 돌풍반응과의 관계, 그리고 비행성의 예측과 양식(format)등으로 구분하여 간단히 소개한다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.213-217
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• 2017

Since more than 30% of the liquid rocket engine failures occur during the start-up process, and the Space Shuttle Main Engine (SSME) is especially sensitive to small changes in propellant conditions, a 2% error in the valve position or a 0.1sec timing error could lead to significant damage of the engine, simulation modeling of start-up process is important. However, there are many difficulties associated with engine start-up process caused by nonlinear mass flow and heat transfer characteristics associated with filling an unconditioned engine system with cryogenic propellants. In this paper, we modelled a SSME simulation model using partially Computational Fluid Dynamics (CFD) method to solve these problems and checked the performance by comparing with the performance of the simulation model using the lumped method under the state of normal condition.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.12
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• pp.1069-1075
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• 2017

With the recent development of space technology, the satellite market, especially the small satellite market, is growing globally. As the satellite market continues to grow, the launch vehicle market is also growing, and demand for low-cost launches is increasing. There are a number of options for low-cost launches, including development of engine that uses low-cost propellants, product and transportation cost savings, but the most effective way to reduce launch costs is to reuse the used launch vehicles. USA's Space Shuttle, a famous rocket as manned spacecraft, could be referred as the start of reusable launch vehicle. However, Space Shuttle had limited reusable parts and it was very expensive even though it is a reusable launch vehicle because of its low efficiency. In recent years, aiming at a real reusable launch vehicle, reusable launch vehicle for commercial purposes have been developed around USA's SpaceX and Blue Origin, and re-landing tests were successfully accomplished. In addition, SpaceX successfully did the re-using of first-stage launch vehicle that had been succeeded in re-landing already. In accordance with this trend, countries such as Europe and India are also concentrating on the study of reusable launch vehicles. Including Blue Origin, companies like Virgin Galactic and XCOR in the United States, are also trying to commercialize the same reusable technology as the private manned space tourism. Confirmation of these technology trends is essential, because the re-use technology could change the landscape of the global launch vehicle market.

• International Journal of Aeronautical and Space Sciences
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• v.18 no.4
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• pp.807-815
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• 2017

For liquid rocket engine(LRE)-based space launch vehicles, longitudinal instability, often referred to as the pogo phenomenon in the literature is predicted. In the building block of system-level task, accurate dynamic modeling of a fluid-filled tank is an essential. This paper attempts to apply the virtual mass method that accounts for the interaction of the vehicle structure and the enclosed liquid oxygen to LOX-filled tanks. The virtual mass method is applied in a modal analysis considering the hydroelastic effect of the launch vehicle tank. This method involves an analysis of the fluid in the tank in the form of mass matrix. To verify the accuracy of this method, the experimental modal data of a small hemispherical tank is used. Finally, the virtual mass method is applied to a 1/8-scale space shuttle external tank. In addition, the LOX tank bottom pressure in the external tank model is estimated. The LOX tank bottom pressure is the factor required for the coupling of the LOX tank with the propulsion system. The small hemispherical tank analysis provides relatively accurate results, and the 1/8-scale space shuttle external tank provides reasonable results. The LOX tank bottom pressure is also similar to that in the numerical results of a previous analysis.

• Korean Institute of Interior Design Journal
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• v.27 no.1
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• pp.156-164
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• 2018

This study analyzed the characteristics of Physical Environment of existing free shuttle bus Interior centered on elderly people who frequently use free shuttle buses. The purpose of this study is to provide basic data that can be used for improvement of existing free shuttle buses. In the case of the old type, in terms of accessible design, the middle entrance is not normally opened except the wheelchair occupant, so that the entrance of the front wheel is always used. Therefore, most elderly people go to the back seat and travel distance is twice longer. In addition, many stairs caused frequent inconveniences for boarding. In the case of the new type, it is planned to be a low-floor type, and various types of safety rods and handles, pictograms for enhancing the information convenience are well-equipped, and the measured value of the overall design characteristic is high. However, in the case of mental stability, it was confirmed that the seat of the bus is colored with a cold color system and is in a different relationship with the warm color which can feel mental stability. Overall, both old and new shuttle buses lack audiovisual feedback on bus routes and route guidance in terms of Supportive design. Also, since the cleaning tools and other miscellaneous items were left in the room, it became an obstacle to space utilization in terms of adaptable design. In terms of safety, both shuttle buses did not come into view with fire extinguishers shaded by miscellaneous items. Therefore, immediate action is unlikely in case of emergency. This problem should be resolved quickly.