• Aerospace Engineering and Technology
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• v.7 no.2
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• pp.144-150
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• 2008

Bogie(The Launch vehicle transporter) is the special land transportation vehicle for the LV (Launch vehicle) which is used for not only the transportation-means of LV from LVAB(Launch Vehicle Assembly Building) to LP(Launch Pad) but also one of principal tools for launch operation sequence. Due to the multi-role of Bogie, The technical requirements of bogie are very complicated. Especially launch operation has performed with not only bogie but also many ground support equipments. So, it is impossible to establish technical requirements of bogie without whole understanding of launch operation. This paper was made for arranging whole launch operation sequence and technical requirements of bogie based on the this sequence.

• Journal of Aerospace System Engineering
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• v.10 no.2
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• pp.14-21
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• 2016

In this study, we proposed a water rocket CULV-1 (Chosun University Launch Vehicle-1). Unlike a conventional water rocket, CULV-1 can perform the booster rocket, fairing, and payload separation like an actual launch vehicle and also the imaging data acquisition. The conceptual and critical design of the proposed CULV-1 have been performed considering the operation characteristics. The verification tests have been performed from subsystem to system level in accordance with the established test specifications and verification procedures. Through the final launch test of the flight model, we have verified the design effectiveness of the proposed separation mechanisms for water rocket applications and the mission requirements of the CULV-1 also have been complied.

• Aerospace Engineering and Technology
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• v.11 no.1
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• pp.135-144
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• 2012

The NARO is South Korea's first carrier launch vehicle, which made its flights from NARO Space Center on 25 August 2009 and 10 June 2010. LV PACS(Preparation Automated Control System) is a electrical ground support system to monitor and control the integrated launch vehicle during the launch preparation and operation in Launch Complex. As a subsystem of LV PACS, LV PACS-II was developed for launch preparation and operation of the NARO upper stage, and all the functions and requirements were verified successfully through NARO flight tests. In this paper the core technology and characteristics applied to LV PACS-II are described.

• Aerospace Engineering and Technology
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• v.2 no.1
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• pp.140-152
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• 2003

Scenario is a guiding principle of launch operation and control for rocket and ground support system. Therefore, developing a scenario is the first step to prepare for rocket launch, which is a critical task for success of KSR-III flight test. The launch scenario for KSR-III flight test is a procedural sequence of command and control signals to be given to rocket and ground support systems. In this paper, the UML object modeling method is applied to development of a launch scenario. First, the subsystems of the launch system are modeled by objects, and then the interfaces between each two subsystems are modeled by association links. The finally obtained object diagram of KSR-III launch system is used to analyzing flow of data and commands and control signals, and interactions. The scenario includes the sequences of pre-launch/launch operations and emergency operations.

• Journal of the Korean Society for Nondestructive Testing
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• v.29 no.4
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• pp.331-337
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• 2009

Space launch vehicles require highly reliable, lightweight structures. It is thus important to monitor the structural health of these components with nondestructive inspections. In this paper, we studied an example of a nondestructive inspection that was partially applied to the manufacture and inspection of a launch vehicle. Ultrasonic tests, X-rays, tapping, and acoustic emissions comprised the inspection method. A payload fairing, high pressure tank, fastener part, and bonding part were used as hardware to be inspected. We proposed a quantitative standard for debonding inspection of the payload fairing and acoustic emission data for the proof test of the high pressure tank. We analyzed the fracture mode of the sandwich fastener part according to frequency changes. We also proposed a standard specimen for ultrasonic inspection of bonds of different materials. The present analyses and results provide data for evaluation of the launch operation sequence to ensure launch vehicles afford high reliability.

• Proceedings of the Korean Society For Composite Materials Conference
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• 2005.11a
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• pp.161-164
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• 2005

This paper finds the optimal staking sequence of the satellite composite structures to minimize severe thermal deformations during their orbital operation using GAs and finite element analyses. Then, the optimal design is reinforced to endure the launch loads like high inertia and vibratory loads that are, usually, smaller than orbital loads induced by space environments. The thermal deformation of sandwich panels was minimized at the staking sequence of [$0_2$/90]s and that of composite strut was lowest at the angle of [0/${\pm}45$]s Also there was no buckling in the compressive loading. By vibration analysis, the natural frequencies of the composite components are much higher than aluminum structures and the expected stiffness condition is satisfied. Then, a composite optical bench was fabricated for tests and all analyses results were verified by structural testing. There were good correlations between two results.

• Journal of Space Technology and Applications
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• v.3 no.1
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• pp.72-85
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• 2023

Most Nanosatellites are launched in nanosatellite deployers. Nanosatellites in the deployer are turned off during launch, and they start boot sequence after deploying at their mission orbit. For this reason, nanosatellites must have deployment switch. Most of the nanosatellite deployment switch has two part, first is electric switch to boot the satellite system and second is mechanical assembly to push the switch. In most cases, electric switches are installed in the satellite main body, and the switch operations are translated via the mechanical assembly. These implementations are mechanically complicated and hard to guarantee the appropriate operation without the problems due to friction between pusher and satellite structure. This paper proposes the another implementation method of deployment switch for nanosatellites by installing the electric switch outside the main body without any kind of mechanical parts.

• Journal of The Korean Astronomical Society
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• v.54 no.1
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• pp.9-16
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• 2021

The Ozone Dynamics Investigation Nano-Satellite (ODIN) is a CubeSat design proposed by Chungnam National University as contribution to the CubeSat Competition 2019 sponsored by the Korean Aerospace Research Institute (KARI). The main objectives of ODIN are (1) to observe the polar ozone column density (latitude range of 60° to 80° in both hemispheres) and (2) to investigate the chemical dynamics between stratospheric ozone and ozone depleting substances (ODSs) through spectroscopy of the terrestrial atmosphere. For the operation of ODIN, a highly efficient power system designed for the specific orbit is required. We present the conceptual structural design of ODIN and an analysis of power generation in a sun synchronous orbit (SSO) using two different configurations of 3U solar panels (a deployed model and a non-deployed model). The deployed solar panel model generates 189.7 W through one day which consists of 14 orbit cycles, while the non-deployed solar panel model generates 152.6 W. Both models generate enough power for ODIN and the calculation suggests that the deployed solar panel model can generate slightly more power than the non-deployed solar panel model in a single orbit cycle. We eventually selected the non-deployed solar panel model for our design because of its robustness against vibration during the launch sequence and the capability of stable power generation through a whole day cycle.