• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2006년 제4회 한국유체공학학술대회 논문집
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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.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2004년도 한국우주과학회보 제13권2호
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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.

• 한국시뮬레이션학회:학술대회논문집
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• 한국시뮬레이션학회 2005년도 춘계학술대회 논문집
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• pp.106-111
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• 2005

LCC(Launch Control Center) in NARO Space Center perform a data monitoring and control through the interface to the external system of launch vehicle. Launch Control function needs a high reliability and processing speed. Hence, LCC's remote control system configure a real time system. An important role of the Simulation system is discovering a risk element and minimize it When developing a launch control system. Also, secure a development technique to solve the risks. Launch Vehicle simulator is composed of various component at characteristic of the Launch Vehicle. To be like this each function component the developer will be able to develop easily in order, it using the LabVIEW which is a Graphical Program and it programs, The LabVIEW GOOP(Graphical Object-orinted Programming) which supports an Object-orinted programming it uses with the Component it develops will have a strong point which reusability and a unit test, maintenance, size of program and individual developments.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2017년도 제48회 춘계학술대회논문집
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• pp.1006-1010
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• 2017

본 논문은 발사체의 지상대기 및 운용 중 격실 내부의 열제어 및 화재/폭발 방지를 위해서 적용되는 열제어/화재안전계에 대한 설계 및 시험에 대해서 기술한다. 고려된 시스템은 한국형발사체 개발의 일환으로 진행되고 있는 시험발사체의 열제어/화재안전 시스템으로 이 시스템은 나로호의 경험을 토대로 고압 시스템을 적용한다. 고압 및 저압 시스템의 선정은 발사대의 가스공급 설비 및 발사체의 특성을 고려해서 선정하며 이에 따라 시스템의 구성도 달라진다. 결과적으로 개발된 시스템은 시험을 통해서 초기의 설계 조건을 만족하는 결과를 얻을 수 있음이 확인되었으며, 이러한 시스템은 한국형발사체의 개발에 그대로 확장되어 적용될 예정이다.

• 한국추진공학회지
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• 제22권1호
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• pp.80-88
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• 2018

한국형 발사체 지상고정 장치는 발사체 이륙시 엔진 최대 추력에서 고정을 해제 한다. 고정력을 일시에 제거하면 추진체가 탱크 내부에서 상하로 진동하는 Ka Doing a Doing a Doing Mode를 유발할 수 있으므로, 점진적으로 고정력을 제거하는 기능이 필요하다. 본 연구에서는 이를 만족하기 위해 축압기 및 파이로 밸브로 유압구동기를 작동하고 구동기내 오리피스로 속도를 제어하는 지상고정장치 유압시스템의 작동 시험을 수행하였다. 주요 설계변수 변화 의한 유압구동기 운동속도의 영향을 분석하여 이를 바탕으로 구동기 요구속도를 만족시킬 수 있는 유압구동기 설계값들을 도출하였다. 이를 통하여 최대추력에서 동작할 수 있는 발사체 지상고정 장치의 개발을 위한 공학적 기반을 마련하였다.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2009년도 한국우주과학회보 제18권2호
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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.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2003년도 제21회 추계학술대회 논문집
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• pp.20-24
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• 2003

The feasibility of hybrid motor as a first stage of the air launch vehicle is investigated, and the result shows the hybrid motor can replace the solid motor. Optimal design study has been performed for the hybrid motor as a first stage of nanosat air launch vehicle. The first stage hybrid motor of the nanosat air launch vehicle, which uses the F-4E Phantom as a mother plane is designed for given mission requirements. Selected design variables are the number of ports, the initial oxidizer flux, the combustion chamber pressure, and the nozzle expansion ratio. The design results show that a hybrid motor can be successfully applicable to very small air launch vehicles which have severe physical constraints of length and diameter imposed by the mother plane.

• 한국항공우주학회지
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• 제49권2호
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• pp.155-166
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• 2021

본 논문에서는 한국형발사체 2, 3단을 수정하여 500 kg 급 차세대 중형위성(CAS500)을 지구 저궤도(LEO)에 단독 발사할 수 있는 2단형 소형발사체를 설계하였다. 한국형발사체는 3단 발사체이므로 소형발사체로의 활용을 위해서는 단별 속도증분이 새롭게 분배되어야 한다. 이를 위하여 설계 변수로는 단 질량비, 구조비와 1, 2단 엔진 옵션을 고려하였으며, 이에 대한 단 설계 및 궤적해석을 수행하였다. 결과 검토로부터 500 kg 급 위성의 LEO 단독 발사가 가능한 소형발사체 설계변수의 조합을 확인하였다.

• 시스템엔지니어링학술지
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• 제2권1호
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• pp.31-36
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• 2006

Development of launch vehicle needs a large-scale and complicated System Engineering discipline interfacing to small-quantity production with special manufacturing processes. In general, the System Engineering discipline of launch vehicle has its relationship with Production, Operations, Product Assurance and Management disciplines and its internal partitions into the functions of System Engineering Integration & Control, Requirements Engineering, Analysis, Design and Configuration and Verification. As a function of Product Assurance, reliability of launch vehicle plays an significant role in risk management, system safety, flight safety and launch certification through design assurance. Moreover, major functions of systems engineering are integrated by means of reliability in the phases of design and verification. Therefore, derailed identification of system engineering interfaces of reliability, and execution of tasks for reliability assurance is required for successful development of launch vehicle. This paper identifies specific pattern and mechanism of the interfaces between reliability and system engineering.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2004년도 춘계 학술대회논문집
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• pp.17-22
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• 2004

A space launch vehicle departs the ground in a low speed, soon reaches a transonic and a supersonic speed, and then flies in a hypersonic speed into the space. Therefore, the design of a launch vehicle should include the prediction of aerodynamic characteristics for all speed regimes, ranging from subsonic to hypersonic speed. Generally, Empirical and analytical methods and wind tunnel tests are used for the prediction of aerodynamic characteristics. This research presents considerable factors for aerodynamic analysis of a launch vehicle using CFD. This investigation was conducted to determine effects of wake over the base section on the aerodynamic characteristics of a launch vehicle and also performed to determine effects of the sting which exist to support wind tunnel test model.