• Current Industrial and Technological Trends in Aerospace
• /
• v.4 no.2
• /
• pp.33-39
• /
• 2006

지난 수년간 중소형 발사체의 부재로 중소형 저궤도 및 정지궤도 위성 발사 시장에서 어려움을 겪어왔던 유럽의 발사 서비스 관련 업체들은 이제 러시아의 소유즈와 새로운 중소형 저궤도 위성 발사체 베가를 도입하여 기존의 아리안-5 발사체로는 지원하기 힘든 중소형 위성 발사 서비스 부문을 집중 육성하려 하고 있다. 기아나 우주센터에서의 소유즈의 발사와 신형 고체로켓 베가의 개발은 2010년 이후를 겨냥한 유럽 발사체 분야의 미래 발전 계획의 한 부분이며, 이러한 계획을 구체화하여 실현하고 있는 기업이 프랑스의 아리안스 페이스사이다. 본 논고에서는 두 발사체 소유즈와 베가의 간략한 역사와 성능을 소개하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.43 no.10
• /
• pp.936-942
• /
• 2015

This paper suggests the significant strategies and their priority to deal with space transportation market trends. First, market trends related with technical improvement and change in demand are analyzed by the literature research. The three key trends are obtained: 'Increasing Demand of High-Performance Launch Vehicles', 'Rising of Low-Price Launch Vehicles', and 'Rising of Dual/Multi-Launch'. And then, strategies for developing the launch vehicle industry in Korea are selected from several studies about commercialization of Korean launch vehicle. The strategies are evaluated by the experts through pairwise comparison matrix and the criteria for this process is how significantly does the strategy effect on the launch vehicle industry through market assessment. As a result, reliable order of priority among the strategies are obtained. Under the three key trends, strategy to enhance reliability is most important. And, strategy to have price competitiveness has secondary priority to deal with 'Rising of Low-Price Launch Vehicles' trend and 'Rising of Dual/Multi-Launch' trend. On the contrary, strategy of government's support is secondary under 'Increasing Demand of High-Performance Launch Vehicles' trend.

• Aerospace Engineering and Technology
• /
• v.6 no.2
• /
• pp.119-125
• /
• 2007

Space launch vehicle development needs many kinds of technologies synthetically. Nowadays, KARI (Korea Aerospace Research Institute) has developed a space launch vehicle, KSLV-I (Korea Space Launch Vehicle-I), that is able to load with an 100kg payload. After that it plans to develop Korean Space Launch Vehicle. As space launch vehicle becomes more complicate and larger, it needs a scientific and analytic development cost estimation. In this paper a cost estimation for KSLV-II using TRANSCOST 7.1 was studied.

• Current Industrial and Technological Trends in Aerospace
• /
• v.4 no.2
• /
• pp.86-97
• /
• 2006

일본은 1954년 도쿄대학의 이도가와 교수가 로켓연구반을 구성하여 연구와 실험을 시작한 후 1955년 8월에 펜슬로켓을 제작하여 수평비행실험을 시작하였다. 이후 베이비 로켓, 카파 로켓, 람다 로켓으로 이어지는 개발과정에서 1970년 람다로켓인 L-4S-5 로켓으로 인공위성 ‘오수미’를 발사하는데 성공하여 자체 위성발사국의 지위를 얻었다. 그러면서 미국으로부터 발사체 기술을 받아 N-1 로켓을 개발하여 1975년에 성공적으로 발사하였다. 이후 자체적으로 기술개발에 성공한 H-I 로켓에 이어 일본의 기간 발사체가 된 H-II A 로켓에 이르기까지 일본은 우주발사체 개발을 지속적으로 꾸준히 발전시켜왔다. 본 논문에서는 일본의 기간 발사체가 된 H-II A 로켓 및 H-II B(H-II A 능력향상형 로켓)에 이르기까지 일본의 로켓 개발과정을 설명하고 또 H-II A 로켓이 어떻게 일본의 기간 로켓이 되었는지 또 H-II A 능력 향상형 로켓, H-II B 로켓의 향후 에 대하여 논의하고자 한다.

• Journal of Advanced Navigation Technology
• /
• v.25 no.4
• /
• pp.267-272
• /
• 2021

The end of the ROK-U.S. missile guidelines opened up the possibility of developing space launch vehicles for various platforms based on air and sea. In particular, the air-based space launch vehicle is an essential space power projection capability compared to the ground-based space launch vehicle in consideration of the geographical location of the Korean Peninsula, such as the deployment of various satellite orbits and the timely launch of satellite. In addition, compared to the ground-based launch vehicle, the cost reduction effect is large, and it has the merit of energy gain because it can be launched with the advantage of the aircraft's altitude and speed. Therefore, in this paper, the necessity of air-based space launch vehicle in the strategic environment of the Korean Peninsula is clearly presented, and through technology trend analysis of various air launch vehicle, the three methods are proposed to have the most efficient air-based space launch vehicle capability in the Korean situation.

• Journal of Korea Society of Industrial Information Systems
• /
• v.22 no.5
• /
• pp.39-49
• /
• 2017

A Space Launch Vehicle (SLV) for Launching Satellites Consists of Multi-stage Rockets for the Purpose of Efficient Flight and Accomplishes the Launch Mission through Flight Events such as Stage Separation, Engine Start and Stop. In this Process, the SLV is Supposed to Undergo the Processes of the Powered Flight Section in which the Engine Generates Thrust and the Ballistic Flight Section in which there is no Thrust Repeatedly. Because it is Difficult to Express these Flight Characteristics of the SLV as a Single Dynamics Model, much Research on Tracking Algorithms using Multiple Models has been Undertaken. In case of using the Multiple Model Tracking Algorithm, it is Expected to Improve the Tracking Performance of the SLV. However, it is Difficult to Select Proper Dynamics Models to be used and the Calculation Amount Increases due to the use of Multiple Models. In this Paper, we Propose a Method to Track the SLV with Diverse Flight Characteristics Efficiently by only Two Kalman Filters using Constant Acceleration Model and Adaptive Singer Model.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.22 no.2
• /
• pp.138-151
• /
• 2018

In this study, development information and technologies for reusable launch vehicles were surveyed. We investigated the reusable launch vehicles developed in various countries and analyzed their recovery technologies. In particular, we focus on the technologies of the Falcon 9 of SpaceX and the New Shepard of Blue Origin, which have succeeded in several flight experiments. Moreover, we explain the control algorithms for each flight condition. Finally, we discuss the reusable technologies that can be applied to the Korean Space Launch Vehicle to reduce the launch cost.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2017.05a
• /
• pp.21-25
• /
• 2017

The umbilical system used for launch vehicle is to connect all ground supply lines (Pneumatic, hydraulic and electrical) to launch vehicle and disconnect those at few second before launch vehicle lift-off (or simultaneously with launch vehicle lift-off). During launch preparation stage, all umbilical shall be securely connected and also at separation stage, separation of all umbilical line shall be guaranteed. Therefore finding an appropriate connection force is a key factor on development of umbilical system. According to these design requirement, various kind of umbilical system has been developed from early stage of space development till today. In this paper, various kind of umbilical system developed so far is introduced according to its feature and operational concept. Also, umbilical system used for KSLV-II is introduced

• Journal of the Korean Society of Propulsion Engineers
• /
• v.26 no.5
• /
• pp.52-62
• /
• 2022

A launch vehicle is a one of the biggest hardware among the products of human technology. For huge size launch vehicles, to transport to Launch Complex and to erect on launch pad precisely and safely is very critical issue. Therefore, a final assembly, transportation, erection and holding in vertical position in launch pad requires very precise operational technology, processes and related aggregates. Those operational concept has been developed to comply with the requirement of each launch vehicle and technology level at that time. In this paper, a progress of operational methodology in global launch vehicles are described. In addition, methodologies used on the KSLV-1 Naro and the KSLV-II Nuri launch vehicle are introduced.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.31 no.3
• /
• pp.72-78
• /
• 2003

In this paper, the feasibility study and the parametric design of hybrid motor with HTPB/LOX were conducted for micro air launch system. Design results were compared with 1st stage of Pegasus XL for verification of hybrid motor. Results showed that hybrid motor replace solid booster if Isp of hybrid motor reaches 330sec. In addition, mission analysis was established for micro air launch system, and parametric design was conducted with design variables: number of port, initial oxidizer flux, and chamber pressure. And the region of Isp was identified by parametric study which satisfied design constraints and mission analysis.