• Journal of Aerospace System Engineering
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• v.13 no.3
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• pp.64-69
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• 2019

The purpose of this study is to explore the current status and challenges of the space development system in Korea following the successful launch of test vehicle, the Korean space launch vehicle II on the 30th anniversary of space development and seek an alternative to the government organizations for efficient space development future. The study investigates the space development system of leading countries such as USA, France, and Japan with keen focus on the administrative organizations and thereafter draw implications for Korea. The analysis of the existing situation in Korea focuses on governance, such as space-related government organizations, space development agency, and specialized research funding agency. As a result, this study proposes the need for full-scale discussion on building a space agency.

• Science of Emotion and Sensibility
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• v.21 no.1
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• pp.17-34
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• 2018

The era of fully autonomous vehicles which can travel to their destination completely, is expected to arrive in the near future. The automobile industry will face a huge change in the near future. It makes the industry in the midst of a major turning point, since the automobile was born in the late 1800s. It is expected that the fully autonomous vehicle will be defined as a part of a living space beyond the concept of transportation. However, the existing research on the interior design of the fully autonomous vehicle is insufficient. The purpose of this study is to propose a design method of interior space through analyzing in-vehicle activities, which is a fundamental design element that can satisfy user's emotional experience suitable the concept of living space. For this purpose, the consumer's consciousness about the in-vehicle activity of fully autonomous vehicle was investigated. As a result, domestic consumers perceived the needs of in-vehicle activities related to resting, listening and watching activities such as 'sleeping and resting', 'watching TV and movie', 'listening to music' among 'self - centered' activities. Based on the results of the investigation, this study will suggest a design method of interior design of the fully autonomous vehicle. This study is meaningful, because it is a leading research that suggests new ways of designing interior space by analyzing consumer's needs in a quantitative method.

• Transactions of the Korean Society of Automotive Engineers
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• v.10 no.1
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• pp.216-233
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• 2002

Due to the environmental problems of fuel consumption and vehicle emission, etc., automotive makers are trying to reduce the weight of vehicles. The most effective way to reduce a vehicle weight is to use lighter materials, such as aluminum and plastics. Aluminum Intensive Vehicle(AIV) has many advantages in the aspects of weight reduction, body stiffness and model change. So, most of automotive manufacturers are attempting to develop AIV using Aluminum Space Frame(ASF). The weight of AIV can be generally reduced to about 30% than that of conventional steel vehicle without the loss of impact energy absorbing capability. And the body stiffness of AIV is higher than that of conventional steel monocoque body. In this study, Aluminum Intensive Vehicle is developed and analyzed on the basis of steel monocoque body. The energy absorbing characteristics of aluminum extrusion components are investigated from the test and simulation results. The crush and crash characteristics of AIV based on the FMVSS 208 regulations are evaluated in comparison with steel monocoque. Using these results, the design concepts of the effective energy absorbing members and the design guide line to improve crashworthiness for AIV are suggested.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.9
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• pp.72-79
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• 2004

A method for thruster fault diagnosis for launch vehicle upper stage was developed. In order to protect the launch vehicle against the occurrence of faults, it is necessary to detect and identify the fault, as well as to reconfigure the controller of the vehicle. Considering the upper stage launch vehicle using reaction control system, an analytical method was adopted in order to detect the fault occurred in thruster. The fault detection scheme can be applied to the system regardless of the form of thruster fault occurred - leakage or lock-out. Results from processor-in-the-loop simulation are provided to demonstrate the validity of this fault detection and isolation scheme for the upper stage launch vehicle.

• Aerospace Engineering and Technology
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• v.6 no.1
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• pp.165-172
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• 2007

A space launch vehicle is a very complex system composed of many kinds of components. It is necessary for even a small piece of components in it to be free of defects, malfunctions and to operate normally for the sake of the mission success. For these reasous, a variety of tests are carried out. Burn-in test is to detect latent material and workmanship defects which occurs early in the components use. Developed countries for the space technology have considered the burn-in test for flight vehicles in the standard test documents and performed it. Referred to the documents, application methods of burn-in test will be considered for the components of domestic space launch vehicles such as KSLV-I in this document.

• Journal of Aerospace System Engineering
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• v.10 no.2
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• pp.14-21
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• 2016

In this study, we proposed a water rocket CULV-1 (Chosun University Launch Vehicle-1). Unlike a conventional water rocket, CULV-1 can perform the booster rocket, fairing, and payload separation like an actual launch vehicle and also the imaging data acquisition. The conceptual and critical design of the proposed CULV-1 have been performed considering the operation characteristics. The verification tests have been performed from subsystem to system level in accordance with the established test specifications and verification procedures. Through the final launch test of the flight model, we have verified the design effectiveness of the proposed separation mechanisms for water rocket applications and the mission requirements of the CULV-1 also have been complied.

• International Journal of Aeronautical and Space Sciences
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• v.11 no.4
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• pp.303-312
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• 2010

This paper introduces the upper stage attitude control system of KSLV-I, which is the first space launch vehicle in Korea. The KSLV-I upper stage attitude control system consists of two electro-hydraulic actuators and a reaction control system using cold nitrogen gas. A proportional, derivative, and integral controller is designed for the electro-hydraulic thrust vectoring system, and Schmidt trigger ON/OFF controllers are designed for the reaction control system. Each attitude controller is designed to have enough stability margins. The stability and performance of KSLV-I upper stage attitude control system is verified via hardware in the loop tests. Hardware in the loop tests are accomplished for perturbed flight conditions as well as nominal flight condition. The test results show that the attitude control loop of KSLV-I upper stage is very stable and the attitude controllers perform well for all flight conditions. Attitude controllers designed in this paper have been successfully applied to the first flight of KSLV-I on August 25, 2009. The flight test results show that all attitude controllers of the KSLV-I upper stage performed well and satisfied the accuracy specifications even during abnormal flight conditions.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.179-182
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• 2011

A practical application of flight-axes/attitude control thrusters to the space launch vehicle and their design development localization are investigated and analyzed. Hydrazine thrusters are mostly used in a final stage of space launch vehicles on account of its higher specific impulse and reliability necessary for the precise attitude control attaining the orbit insertion with higher accuracy.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.8
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• pp.574-581
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• 2019

This paper investigates the effects of thrust misalignments and offsets of the lateral center of gravity of a space launch vehicle on its guidance performance. Sensitivity analysis and Monte Carlo simulations are applied to analyze their effects by computing changes in orbit injection errors when including the error sources. To compensate their effects, the attitude controller including an integrator additionally and the Steering Misalignment Correction (SMC) routine of the Saturn V are considered, and then Monte Carlo simulations are performed to evaluate their performances.

• Transactions of the Korean Society of Automotive Engineers
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• v.18 no.5
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• pp.56-61
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• 2010

This paper presents dynamic clearance verification considering engine movement for vehicle engine room package and validates through physical vehicle test. Traditionally, static clearance guide has been used for engine room package, but it's only 2-dimension criteria that results in requiring unnecessary space and it's not possible to conduct engine movement with real driving conditions. Thus, the dynamic DMU considers engine movement based on 28 load cases that are Roll Data analyzed by CAE for maximum engine movement and visualizes part-to-part dynamic clearance into virtual space. The dynamic DMU enables to develop compact engine room package without unnecessary space. The result of comparison between simulation and physical test has 0.892 correlation coefficient.