• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
• /
• 2017.10a
• /
• pp.536-538
• /
• 2017

UHD high speed digital camera system will be installed around launch pad and launch complex tower to acquire high speed image for motion analysis of integral parts of launch vehicle during the lift-off of KSLV-II in the Naro space center. In this paper, We compared configuration of high speed digital camera system operating in the Naro space center with UHD high speed digital camera system for mission of KSLV-II.

• Journal of the Korea Academia-Industrial cooperation Society
• /
• v.21 no.5
• /
• pp.443-450
• /
• 2020

This paper reports a design improvement study to solve the stoppage phenomenon caused by the launch-support device applied to K105A1. The K105A1 is a weapon system equipped with an old 105 mm towed howitzer in a wheeled vehicle, which provides superior maneuverability compared to track equipment. The launch support device serves to withstand fire impact and load. In this way, this device is fixed firmly to the ground in preparation for the shooting mission and is responsible for the critical performance, such as fixing the position of the vehicle. On the other hand, during the field test, a temporary stoppage of the launch support occurred, which caused a problem of not being fixed to the ground. To solve this problem, the cause of failure was analyzed by a replay test and parts inspection. In addition, the operating concept, method, and design were analyzed to derive the cause and solve the problem by changing the parts design. Finally, the performance and firing missions were performed normally by applying the changed design to K105A1. The performance stability and reliability of the launch support device were confirmed, which are expected to be of great assistance in the development of military equipment in the future.

• Journal of the Korea Institute of Military Science and Technology
• /
• v.18 no.3
• /
• pp.316-325
• /
• 2015

This paper describes the design guide and its assessment process to be applied to the launcher vehicle exterior design. A launcher vehicle design is required to meet three kinds of design attributes; symbolic quality, usability, and aesthetic quality. The launcher vehicles referred to in this paper are assessed by the elements in the guidelines. A set of assessment process and methods is derived to evaluate how well the three design attributes are applied in the actual launch vehicle design. An example of assessment is shown at the last part of this paper. By this way designers can take various criteria into account integratively and select the final design. High design satisfaction and pride of the operators and the nation can be assured in the end.

• Journal of the Korea Institute of Military Science and Technology
• /
• v.16 no.5
• /
• pp.590-597
• /
• 2013

For a lower tier defense, the distance between a launcher and an engagement control station is quite important to estimate the proper defense area and to effectively arrange missile launchers. In this paper, we have analyzed an effectiveness of anti-ballistic missile launcher arrangement for the lower tier defense against the ballistic missile. The operation concept, specific configuration and aerodynamic characteristics of the ballistic missile such as SCUD-B/C, Nodong are considered in order to develop a realistic engagement simulation. The diverse engagement results through numerical simulations are provided to conduct the effectiveness analysis of anti-ballistic missiles.

• Proceedings of the KSME Conference
• /
• 2007.05a
• /
• pp.718-723
• /
• 2007

A three dimensional multibody modeling of a launcher system was developed and dynamic characteristics of the system was carried out. All the components were modeled as rigid bodies, All the components of system, ie; chassis, turret, cage and suspension parts, are modeled as rigid. The force interaction between the ground and tire was modeled as a point contact model. The factors were selected as cause and effect diagram of the MINITAB. To see effect of the stiffness, damping, mass at the launcher system, several cases of suspension parameters were compared and optimal values were selected. The stiffness and the damping coefficient were selected as design variables to minimize the required time for the next fire. The dynamic simulation was carried out using the ADAMS, and the MINITAB was employed for data analysis.

• Current Industrial and Technological Trends in Aerospace
• /
• v.4 no.2
• /
• pp.49-54
• /
• 2006

현재 전라남도 고흥 외나로도에서는 발사체를 발사하기 위한 우주센터를 건립 중에 있다. 우주센터 내에는 추적레이다, 발사대, 발사통제시스템, 기상 장비 등 발사를 위한 그리고 발사 후의 발사체 추적을 위한 장비가 건설 중이다. 본 글에서는 우주센터 기상장비 중에서 낙뢰현상을 감지할 수 있고 낙뢰의 이동방향을 추적할 수 있는 종합낙뢰감지시스템에 대하여 낙뢰의 관측방법과 국내외에서 낙뢰를 감지하여 실제 기상청이나 Launch Site에서 사용하고 있는 실례를 소개하고 우주센터에 설치 중인 종합낙뢰감지시스템의 성능과 앞으로의 활용가능성에 대하여 알아보기로 하겠다.

• Aerospace Engineering and Technology
• /
• v.3 no.2
• /
• pp.98-103
• /
• 2004

This paper describes a system design of Launch Ground Complex for the Korea Space Launch Vehicle-I which will play so important roles of successful execution for Korea National Space Development Program. Launch Ground Complex has to supply safe work space, construction and equipments for assembling, check-out and launching of the space launch vehicle, and it consists of Mechanical, Electrical, Fluid Ground Support Equipment and Infrastructure. Mechanical Ground Support Equipment consists of Launch Pad, Mobile Assembly Tower, Umbilical Tower, Lightning Tower, Theodolite Building and Auxiliary.

• Proceedings of the Korean Society For Composite Materials Conference
• /
• 2004.10a
• /
• pp.56-60
• /
• 2004

2단 또는 3단형으로 설계되고 있는 KSLV-I 발사체의 단연결부는 직경의 변화에 따라 원뿔대(Truncated cone) 구조물이 필요하다. 원뿔대형 구조물이 발사체의 외피일 경우에는 일반적인 실린더형 동체와는 다르게 공력에 의한 버페팅(buffeting)과 공력가열 등이 추가적인 설계인자로 고려되어야 한다. 복합재료 샌드위치 구조물은 외피의 굽힘 강성이 크고, 일체성형으로 실린더형 혹은 원뿔대형 구좁물을 쉽게 제작할 수 있어 단연결부에 적용되고 있다. 또한 위성어댑터(Payload Adapter)등에도 사용되어 우주발사체에는 매우 일반적인 구조물이다. 복합재료 샌드위치 구조물의 제작과 정적시험을 통하여 구조 특성을 알아보았다. 일체형 샌드위치 구조물의 효율을 높이기 위해서는 프레임과의 체결부를 효율적으로 설계하여야 하며 하중의 종류에 따라서 면재의 적층각도가 중요함을 알 수 있었다.

• Proceedings of the Korean Society of Precision Engineering Conference
• /
• 2012.10a
• /
• pp.693-694
• /
• 2012

• Bulletin of the Korean Space Science Society
• /
• 2006.04a
• /
• pp.110-110
• /
• 2006