• Proceedings of the Korea Society for Simulation Conference
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• 1998.10a
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• pp.182-186
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• 1998

최근 산업체, 공공기관 등 거의 모든 분야에서 인터넷 기술을 이용한 클라이언트/서버환경으로 시스템을 구축하고 있다. 본 논문에서는 이러한 환경에서 DIS와 ADS의 개념을 이용한 전투 시뮬레이션을 수행하여 기존 모델의 비현실적인 가정과 문제의 난이도로 인한 여러 제약을 해결할 수 있으며 시간 및 시스템의 활용면에서 효율의 증가에 대한 모델을 구현하였다. 본 전투 시뮬레이션 모델은 인터넷 프로토콜의 표준으로 자리하고 있는 TCP/IP를 이용한 것이기 때문에 이동통신을 이용한 무선 데이터는 물론, 인터넷 접속이 가능한 곳이라면 어떠한 환경에서도 수행이 가능하다. 노드에서 시뮬레이션이 종료되면 여기서 발생한 생존 대수, 발사시간 분포 등의 정보는 서버에서 적절한 의사결정을 수행한 후 다른 노드로 전달하게 된다.

• Journal of Aerospace System Engineering
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• v.16 no.4
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• pp.28-34
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• 2022

In 2021, Virgin Orbit converted a 747-400 aircraft into an air launch platform, and successfully launched it twice in February and July. Compared to the existing ground launch, interest in the air launch is increasing due to its great utility, such as its independence from the launch location or weather, cost reducing factor, shorter launch preparation time, and its benefit pursuant to altitude and speed. Additionally, as small satellites have similar performance to mid/large satellites in the past due to the miniaturization and precision of electronic equipment, small satellite launches are expected to dominate in the future. In this paper, institutional certification methods such as domestic, overseas, civilian and military airworthiness certification regulations/procedures are reviewed to ensure flight safety of aerial projectiles using large domestic civil aircraft, and applicable civil and military airworthiness certification technology standards are reviewed and analyzed. Additionally, we will review and suggest effective airworthiness certification application plans that reflect the reality, and present airworthiness certification standards (draft) for aerial launch vehicles, by analyzing applicable airworthiness certification technical standards when remodeling aerial launch vehicles.

• Aerospace Engineering and Technology
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• v.2 no.2
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• pp.167-178
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• 2003

The design on the Telemetry Ground System for launch of KSLV(Korea Space Launch Vehicle) in the korean Space center has been conducted in this study. For the optimized system design, first of all, the system deployment plan reflecting the topographic and geographic environments of the space center and launch vehicle characteristics has been developed. The RF link budget analysis for the maximum tracking range, requirement for receiving subsystem including antenna subsystem, requirement for data processing subsystem are also analyzed based on the On-Board Telemetry characteristics and launch vehicle parameters. Based on those analysis, telemetry ground system containing tracking/receiving subsystem, recording subsystem and data processing subsystem, timing subsystem, calibration subsystem and monitoring and control subsystem are designed. Futhermore, the analysis for the maximum permissible data latency and communication protocol between each telemetry station and control center are conducted and the entire system is designed so that the major telemetry parameters selected to the best quality are provided in real time to the control center(RCC, RSC) for the launch mission operation.

• The Journal of the Institute of Internet, Broadcasting and Communication
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• v.19 no.3
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• pp.185-191
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• 2019

During the modern battlefields of multi-batches flight formation attack situation, it is an essential task for a commander to make a proper fire distribution of air defense missile launch platforms for threat targets with effectively and quickly. Pan et al. try to solve this problem using genetic algorithm, but they are fails. This paper gets the initial feasible solution using high threat target first destroying strategy only use 75% available fire of each missile launch platform. Then, the assigned missile is moving to another target in the case of decreasing total threat. As a result of experiment, while the proposed algorithm is polynomial-time complexity greedy algorithm but this can be improve the solution than genetic algorithm.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.1
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• pp.41-52
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• 2021

During atmospheric ascent of a launch vehicle, airborne acoustic loads act on the vehicle and its effect becomes pronounced at transonic speed. In the present study, acoustic loads acting on a hammerhead launch vehicle at a transonic speed have been analyzed using ��-ω SST based IDDES and the results including mean Cp, Cprms, and PSD are compared to available wind-tunnel test data. Mesh dependency of IDDES results has been investigated and it has been concluded that with an appropriate turbulence scale-resolving computational mesh, the characteristic flow features around a transonic hammerhead launch vehicle such as separated shear flow at fairing shoulder and its reattachment on rear body as well as large pressure fluctuation in the region of separated flow behind the boat-tail can be predicted with reasonable accuracy for engineering purposes.

• Journal of Space Technology and Applications
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• v.4 no.2
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• pp.137-152
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• 2024

Currently, investigations in microgravity environments are carried out in a variety of applications, including drop towers, where experiments can be performed for short periods of time, and space stations, where time is not limited. However, producing a microgravity environment for long-term scientific research requires huge development expenditures and efforts. As a result, if the microgravity experiment is carried out on a cubesat, the variety of scientific studies will likely increase even more due to its low cost. The Korea Microgravity Science Laboratory (KMSL) cubesat, which has these features, is a satellite that has carried out microgravity science missions. On March 22, 2021, the KMSL satellite was launched by a Soyuz2.1a from Baikonur in Kazakhstan and operated normally for nearly two months. This article presents results and lessons gained for successfully completing science missions in microgravity based on the KMSL satellite's operational experience.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 1992.10a
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• pp.3-7
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• 1992

포는 대체로 정확도와 최대 발사거리 및 최대 발사속도 등에 의해 그 성능 이 표현된다. 그 중에서도 최대 발사속도는 매우 중요한 인자로서 포의 주퇴 복좌 장치의 성능에 의해 직접적으로 영향을 받게 된다. 따라서 포의 최대 발사속도 향상을 위해서는 주퇴복좌 장치의 동특성 해석 능력을 확보하고, 그로부터 주퇴 장치의 설계 변경이 가능하도록 해야 한다. 한편, 주퇴복좌기 의 주퇴특성은 주퇴시 총주퇴저항력이 전주퇴장에 대해서 거의 일정해야만 포신에 전달되는 힘을 최소로 하면서 주퇴시간을 최소로 할 수 있으며 이러 한 설계 개념으로 주퇴복좌기를 설계한다. 그에 따라 주퇴복좌기는 그 내부 가 가변 오리피스 및 조절 로드로 이루어져 주퇴복좌기의 주퇴 저항력을 주 퇴속도 및 주퇴변위에 따라 변화시키도록 되어 있다. 따라서 주퇴복좌기는 필연적으로 강한 비선형 특성을 나타낸다. 이러한 주퇴복좌기를 모델링할 때 에 기존에는 주퇴복좌기내의 모든 유체역학적 요소를 고려하여 모델링하는 기법이 통용되어왔다. 그러나 이러한 모델링은 각 요소의 모델링 오차가 누 적될 위험이 있으므로 정확한 모델링을 보장할 수 없으며, 매우 복잡한 과정 을 거쳐야 한다. 따라서 본 연구에서는 주퇴 완충기 시뮬레이터를 이용한 실 험에 따른 계의 파라미터 예측을 통하여 모델링하는 기법을 시도하여 보았 다.

• Journal of the Korean Society of Propulsion Engineers
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• v.23 no.2
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• pp.95-103
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• 2019

Control systems of compressed gas supply facility are responsible for storing and supplying compressed gases required for launch complex qualification test and launch operation. Most of the facilities that make up the launch complex require compressed gas for their operation. Therefore, such control systems should be developed and verified earlier rather than the other systems that constitute the launch complex. Each verification for hardware and software is performed separately. In particular, software verification of control algorithms loaded on the controller takes a lot of time and man power during the development period of the control system. Thus, specific test procedures and methods should be prepared in advance for efficient development. This paper introduces the configuration of a compressed gas supply facility and its control system with the verification procedure and results of major algorithms.

• Journal of the Korean Society of Propulsion Engineers
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• v.25 no.3
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• pp.127-137
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• 2021

The launch complex(LC) is composed of various facilities. The launch control system that operates remotely those of LC spends much time and labor for developing and verifying its control algorithms. The verification of algorithms is performed by the software developer entering simulated state values based on the test procedure and checking the output result according to the algorithm flow. These verification processes should be performed repeatedly, thus the human errors are easily occurred. In this paper, an efficient automated verification method with a script test procedure is proposed to minimize human errors and shorten the verification duration. We also present the results of the algorithm verification tests for the cases of the compressed gases supply system and the electro pneumatic panel system of LC.

• Bulletin of the Korean Space Science Society
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• 2009.10a
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• pp.42.2-42.2
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• 2009

한국천문연구원에서 개발 중인 KHz급 Satellite Laser Ranging(SLR) 시스템인 ARGO-M 의 운영시스템 중의 하나인 Interface Control System 은 현재 시각에서의 위성의 위치를 개산하여 추적마운트부에 Tracking 정보를 제공하고, 주기적으로 발사되는 레이저의 귀환 시간을 계산하여 수신광검출기 게이트를 열어야 하는 시간을 FPGA 보드에 전달하는 기능 등을 수행하게 된다. 이러한 일련의 작업은 각각 필요한 시점에 정확하게 실행되어야 하며 이를 위해 실시간 운영체계가 사용될 예정이다. 실시간 운영체계 하에서 Ranging 에 관련한 프로세스를 수행할 경우에 발생될 수 있는 문제점을 검토하기 위해서 기존에 Austria Graz SLR 관측소에서 사용하고 있는 DOS용 테스트 프로그램을 실시간 운영체계로 검토되고 있는 INtime 환경으로 이식하여 성능을 기존의 DOS 프로그램과 비교하여 보았다. Controller 역할을 담당하고 있는 FPGA 보드와의 데이터 통신의 주기성을 확인하는 시험 결과 실시간 운영체계를 사용하는 경우가 USB 사용 등 외적인 교란에 의한 영향을 적게 받는 것을 확인 할 수 있었다. 또한 500피코초 단위의 해상도를 갖는 내부 이벤트 타이머와의 연계, 레이저 발사 명령, 광검출기의 게이트 여닫기 등의 프로세스가 실시간 환경에서 문제점 없이 구현 가능함을 확인하였다.