• Journal of Aerospace System Engineering
• /
• v.1 no.3
• /
• pp.1-6
• /
• 2007

The COMS(Communication, Ocean & Meteorological Satellite)is the geostationary satellite which will be performing three main objectives such as meteorological service, ocean monitoring and Ka-band satellite communications. This paper presents the analysis of the electromagnetic radiated compatibility between COMS satellite and the ARIANE 5 launch vehicle. As a conclusion, a good level of confidence can be given at present time to demonstrate the compatibility between the spacecraft and the launcher, and vice versa. No threat has been identified regarding the other units powered during launch mode.

• Journal of the Society of Naval Architects of Korea
• /
• v.41 no.6
• /
• pp.140-146
• /
• 2004

This paper presents the structural analysis of the pressure vessels in the unmanned underwater vehicle (UUV) under developing at KORDi, which consists of a ROV, an AUV and a launcher at 6000 m depth in the ocean. Analytical, linear and nonlinear stress and buckling analysis of cylindrical pressure vessels using FEM (ANSYS) are performed to verify the safety of the current design.

• Proceedings of the Korea Committee for Ocean Resources and Engineering Conference
• /
• 2002.05a
• /
• pp.243-250
• /
• 2002

According to Ocean Korea 21, a basic plan established by the Ministry of Maritime Affairs and Fisheries (MOMAF) of Korea in May 2000, Korea Research Institute of Ships and Ocean Engineering (KRISO) proposed a program for the development of a deep-sea unmanned underwater vehicle (UUV) to explore deep sea for scientific purpose. KRISO has launched a project in May 2001 under the support of MOMAF. The deep-sea unmanned underwater vehicle will be applied to scientific researches in deep-sea as well as in shallow water. For operation of underwater vehicles in shallow water near the Korean Peninsula, a special design is required because of strong tidal current. In addition, MOMAF requires the vehicle to be designed for the purpose of long range survey, a long-term observation, and precise works in a specific area. Thus, KRISO has planned to design the system with the functional combination of both ROV and AUV. This paper presents the design of the deep-sea unmanned underwater vehicle.

• Journal of Ocean Engineering and Technology
• /
• v.23 no.5
• /
• pp.61-70
• /
• 2009

An AUV (Autonomous Underwater Vehicle) is an unmanned underwater vessel to investigate sea environments and deep sea resource. To be completely autonomous, AUV must have the ability to home and dock to the launcher. In this paper, we consider a class of homing trajectory planning problem for an AUV with kinematic and tactical constraints in horizontal plane. Since the AUV under consideration has underactuated characteristics, trajectory for this kind of AUV must be designed considering the underactuated characteristics. Otherwise, the AUV cannot follow the trajectory. Proposed homing trajectory panning method that called VGM (Virtual Goal Method) based on visibility graph takes the underactated characteristics into consideration. And it guarantees shortest collision free trajectory. For tracking control, we propose a PD controller by simple guidance law. Finally, we validate the trajectory planning algorithm and tracking controller by numerical simulation and ocean engineering basin experiment in KORDI.

• Aerospace Engineering and Technology
• /
• v.10 no.1
• /
• pp.1-12
• /
• 2011

The error of onboard propellants mass which is mostly occupied in total mass of launch vehicle and The error of residual affect the performance of launch vehicle seriously. In other words, the errors directly cause the error of total impulse. Therefore, optimization of performance of launch vehicle can be achieved by the minimization of the residual. For minimizing the residuals, the active control for completely depleting the propellants and the calculation method using probability for minimizing the residuals have been researched. In this paper, the added fuel was calculated for minimizing the residual and the minimized residual was predicted by the presented method.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.24 no.4
• /
• pp.48-54
• /
• 2020

Low cost launch vehicle for next-generation is underway in advanced space countries such as the United States, Europe, Japan and China. This paper surveys the latest technological trends in avionics system, including ground management system. In the case of on-board equipment, to make short the development period and reduce the cost, the equipment is standardized and modularized for each functions to flexibly respond to changes in system requirements. In addition, a network is applied to all inter-equipment interfaces and a powerful self-diagnostic function is included in the equipment to realize automation/simplification of the interface with the ground system, and it is confirmed that an efficient launcher system is realized.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.40 no.5
• /
• pp.439-445
• /
• 2012

The COMS(Communication, Ocean, and Meteorological Satellite) is subjected to shock loads when the stage or fairing of a launch vehicle is separated and the satellite is separated from the launch vehicle during the launch vehicle flight. And, after the satellite is separated from the launcher, the COMS is subjected to shock loads when the solar array is deployed, Ka-Band communication antenna is deployed, and meteorological imager radiator cover is released. In order to validate the satellite safety against these shock loads on ground, shock tests were performed. In this paper, the shock tests performed in the course of the COMS development are described, and the method to assess the test result is presented with an example of Geostationary Ocean Color Imager(GOCI). In Ariane-5 launch vehicle, the clampband release shock for satellite separation is lower than the fairing or stage separation. In this paper, the extrapolation method to take into account the maximum shock load from the launch vehicle by using the satellite separation shock test result is also introduced.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.40 no.10
• /
• pp.853-861
• /
• 2012

This paper considers one of the explicit guidance algorithms, which has been proposed by Jaggers, to determine the closed-loop guidance algorithm for upper stages of a 3-staged space launch vehicle. Its commanded thrust vector is closer to the optimal solution when compared with that obtained by using the well-known Powered Explicit Guidance (PEG), which has been developed through the Space Shuttle program. Its performance is evaluated here by applying for guidance of the launcher during the second and third stages. Furthermore, to generate more precise guidance commands, it is attempted not to use the approximate formulas for the derivation of the original guidance law, and it is shown that performance is improved in comparison with the original.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2009.11a
• /
• pp.273-277
• /
• 2009

An oxidizer tunnel-type pipe, which shall transport oxidizer from an oxidizer tank to a turbo-pump of an engine, studied is installed through a fuel tank located under an oxidizer tank. A tunnel-type pipe can save weight compared to a detour-type pipe, however may vary the temperature of fuel stored in a fuel tank because of a broad heat transfer area. Hence in this study the characteristics of main oxidizer pipe and thermal propagation from oxidizer to a fuel tank are monitored by a cryogenic performance test with a tunnel-type pipe. In addition, the possibility of adaptation of an oxidizer tunnel-type pipe to launcher system is also analyzed.

• Aerospace Engineering and Technology
• /
• v.11 no.1
• /
• pp.169-177
• /
• 2012

This paper considers the explicit guidance algorithm to determine the closed-loop guidance law applicable to upper stages of a given space launch vehicle. It has the advantage of very simple forms derived from the flat earth assumption, which is appropriate for its on-board application. However the simple time-to-go prediction equation produces the degraded guidance performance of the launcher because of its inaccuracy. To overcome the problem, the elaborate prediction equations, which have been employed in Saturn and H-II, are attempted here. Finally, the simulation results show that the simple guidance approach requires the more accurate time-to-go prediction and gravity integrals for its broad application.