• Title, Summary, Keyword: Launch Vehicle

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Application of Cost Estimation to Space Launch Vehicle Development Program (우주발사체 개발사업의 비용 추정 현황 및 사례)

  • Yoo, Il-Sang;Seo, Yun-Kyoung;Lee, Joon-Ho;Oh, Bum-Seok
    • Journal of the Society of Korea Industrial and Systems Engineering
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    • v.30 no.3
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    • pp.165-173
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    • 2007
  • A space launch vehicle system represents a typical example of large-scale multi-disciplinary systems, consisting of subsystems such as mechanical structure, electronics, control, telecommunication, propulsion, material engineering etc. A lot of cost is required to develop the launch vehicle system. A precise planning of R&D cost is very essential to make a success of the launch vehicle development program. Especially in the early development phase of a new space launch vehicle system, cost estimation techniques and analogy from past similar development data are very useful methods to estimate a development cost of the launch vehicle system. Now Korea Aerospace Research Institute is in charge of the KSLV-I (Korea Space Launch Vehicle-I) Program that is a part of Korea National Space program. KSLV-I Program is a national undertaking to develop launch capabilities to deliver science satellites of a 100kg-class into a low earth orbit. It is hereafter, going to plan to develop a new korean space launch vehicle. In this paper, first the development costs of well-known launch vehicles in the world are presented to provide a reference to make a development plan of a new launch vehicle. Second this paper introduces the present status of cost estimation applications at NASA. Finally this paper presents the results from application of a TRANSCOST, a parametric cost model, to derive a cost estimate of a new launch vehicle development, as an example.

Operation and Result Analysis of Hydraulic Vehicle Holding Device (발사체 지상고정장치 유압시스템 작동 시험 및 결과 분석)

  • Kim, Dae Rae;Yang, Seong Pil;Lee, Jae Jun;Song, Oh-Seob;Lee, Young-Shin
    • Journal of the Korean Society of Propulsion Engineers
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    • v.22 no.1
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    • pp.80-88
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    • 2018
  • The function of a vehicle holding device (VHD) is to securely hold a launch vehicle on the launch pad and release the launch vehicle at maximum thrust after engine ignition to allow lift-off of the launch vehicle. During the release of the launch vehicle, to prevent the Ka doing a doing a doing mode, which is the vertical oscillation of the entire liquid propellant, the release of the launch vehicle should be gradual. In this study, for the gradual release of a launch vehicle, a hydraulic system comprising an accumulator and pyro valve to operate a hydraulic cylinder and control the speed of the cylinder with an orifice is introduced. Through a test, the influence of design variables on the cylinder speed is analyzed. Based on this, the design values of the hydraulic cylinder are determined. Through this study, the engineering basis for developing a VHD releasing a launch vehicle at maximum thrust is provided.

Launch Site Activities for the Launch of an Earth Observation Satellite

  • Im, Jeong-Heum
    • The Bulletin of The Korean Astronomical Society
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    • v.37 no.2
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    • pp.195.1-195.1
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    • 2012
  • Korea Aerospace Research Institute has developed an earth observation satellite whose primary mission objective is to provide high resolution electro optical earth images for Geographical Information Systems (GIS) establishment and the applications for environmental, agriculture and ocean monitoring. It was successfully launched into its mission orbit by using a commercial launch vehicle on 18th of May, 2012. This paper describes a series of launch activity at the launch site including its transportation to the launch site. Before conducting the launch site operation, satellite operation plane was prepared. Combining the satellite operation plan and launch vehicle activities, an integrated launch site operation plan and schedule have been drawn up. After arrival of the spacecraft at the launch site, post-ship check out has been conducted. And then it was fuel loaded and integrated with launch vehicle hardware. After completion of final electrical check out, count down procedure was executed. on 18th of May, it was launched into the space and was separated from the launch vehicle as planned. About 3 months of early operation and calibration/validation, now the satellite is conducting its normal mission.

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Launch Vehicle Telemetry MUX Test by using the Spacecraft Simulator

  • Won, Young-Jin;Lee, Jin-Ho;Yun, Seok-Teak;Kim, Jin-Hee;Lee, Sang-Ryool
    • Bulletin of the Korean Space Science Society
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    • pp.46.3-46.3
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    • 2009
  • The SAR (Synthetic Aperture Radar) satellite has the advantage of implementing the imaging mission even though it is night time, cloudy weather, and all weather conditions, which is different from the satellite with the optical payload. This is the reason why the SAR satellite comes into the spotlight in the observation satellite field. The Korea Aerospace Research Institute (KARI) has been developing the first Korean SAR satellite and is currently integrating and testing the Flight Model. For the launch vehicle service, KARI finalized the selection of the launch vehicle service provider and finished Critical Design Review (CDR) of the interface between the bus and the launch vehicle. KARI and launch vehicle service provider also finished the test of the telemetry interface between the bus and the launch vehicle. The test of the telemetry interface has the purpose of checking the interface of the telemetry which is the SOH(State-of-Health) of the satellite in an early launch stage. For this test, KARI has finished the development of the spacecraft simulator which is composed of the bus simulator to generate the analog telemetry and the launch vehicle simulator to gather the telemetry. In this research, the result of the hardware implementation and the software implementation for the spacecraft simulator were described. Finally the results of the launch vehicle telemetry MUX test which were performed at the launch vehicle provider's design office by using the spacecraft simulator were summarized. It is expected that this simulator will be used in the next test after the manufacture of the launch vehicle.

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Aerodynamic Design Techniques in The Launch Vehicle (발사체 개발에서의 공력설계 기법)

  • Ahn, Chang-Soo;Sun, Chul;Kang, Kyoung-Tai
    • 유체기계공업학회:학술대회논문집
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    • pp.41-44
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    • 2006
  • In the field of launch vehicle development, aerodynamic design means an overall management about external appearances. At least, related to outer figures of the launch vehicle, aerodynamic design has the initiative activities. For that reason, in this report, aerodynamic design techniques and application methods will be introduced.

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The Launch of the COMS by Ariane-5 Launch Vechicle (아리안-5 발사체를 이용한 통신해양기상위성 발사)

  • Lee, Ho-Hyung;Kim, Bang-Yeop;Choi, Jung-Su;Han, Cho-Young
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.36 no.3
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    • pp.291-297
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    • 2008
  • The launch of the COMS by using Ariane-5 launch vehicle is introduced. First, the COMS is introduced briefly, and then, the Ariane-5 launch vehicle is introduced including detail description of the improvement of Vulcain-1 engine of Ariane-5G to Vulcain-2 engine of Ariane-5ECA for 20% increase of thrust. Then, the launch process of the COMS is introduced. The COMS will be launched from the Guiana Space Center in Kourou, French Guiana. After the final check at PPF the COMS is transferred to HPF in the same building for fueling, and it is integrated to the launch vehicle adaptor at HPF, too. Then, this assembly is transferred to Final Assembly Building. After the satellites to be launched together are integrated to the launch vehicle on the launch table in the Final Assembly Building, the launch table loaded with the launch vehicle is moved to the launch pad for launch. The events during the launch vehicle flight is also introduced.

A CONCEPTUAL DESIGN FOR ELECTRICAL GROUNDING ARCHITECTURE OF KOREAN SPACE LAUNCH VEHICLE

  • Kim Kwang-Soo;Lee Soo-Jin;Ma Keun-Soo;Shin Myoung-Ho;Hwang Seung-Hyun;Ji Ki-Man;Chung Eui-Seung
    • Bulletin of the Korean Space Science Society
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    • pp.231-234
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    • 2004
  • Electrical grounding is defined as referencing an electrical circuit or a common reference plane for preventing shock hazards and for enhancing operability of the circuit and EMI control. In order to realize the best electrical grounding system of korean space launch vehicle, we should design the electrical grounding architecture of korean space launch vehicle of system-level at the earliest point in design procedure. To minimize the electrical grounding loop and the unnecessary electromagnetic interference or radiation among the electronic subsystems, we should establish the electrical grounding rules of the all electrical interfaces. The electrical interfaces among the electronic subsystems are generally classified into the electrical power and signal interfaces. Because of using the primary and secondary power system architecture in the korean space launch vehicle system such as the common space launch vehicle systems, we need to establish the electrical grounding rules between the primary and secondary power system. We also need to establish the electrical signal grounding interface rules among the electronic subsystems. In this paper, we will describe the grounding schemes of the common space launch vehicle system and propose a conceptual design for the electrical grounding architecture of korean space launch vehicle system.

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A Study on the Life Cycle for Launch Vehicle in NASA (NASA의 발사체 수명주기에 대한 연구)

  • Jung, Dong-Ho;Kim, Ji-Hoon;Lee, Han-Ju;Oh, Seung-Hyub
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.99-105
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    • 2006
  • A Launch vehicle which consists of many sub-systems is one sophisticated huge system. A lot of experience and system integration technique are needed for the launch vehicle to accomplish a mission successfully. The characteristics and complexity in the development of the launch vehicle depend on the size of that. However the systematic work flow is similar to each other. This paper introduces a standardized development process which is based on the whole program life cycles and experiences of NASA on the development of the launch vehicle. The development process can be categorized into 10 phases through the life cycle of the launch vehicle.

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Design and Test of Thermal Control and Fire Safety System for Space Launch Vehicle (발사체 열제어/화재안전 시스템 설계 및 시험)

  • Ko, Ju Yong;Oh, Taek Hyun;Lee, Joon-Ho
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.1006-1010
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    • 2017
  • This paper describes the design and test of the thermal control and fire safety system for thermal control and the fire/explosion prevention of inside the compartment during the preparation and operation of the space launch vehicle at the launch pad. The system considered here is for the test launch vehicle which is being developed as part of the development of the Korean Space launch vehicle-II. This system applies the high pressure system based on the heritage of Naro launch vehicle. The selection of thermal control and fire safety system from high pressure and low pressure system is done in consideration of the characteristics of the launch pad gas supply system and the characteristics of launch vehicle, and the system configuration is also changed accordingly. As a result, it has been confirmed that the developed system satisfies the initial design conditions through the test. Moreover the system will be applied to the development of the Korean launch vehicle in the future.

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