• Journal of the Korean Crystal Growth and Crystal Technology
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• v.7 no.3
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• pp.504-513
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• 1997

Ideal candidates for the thermal-protection system of advanced spacecraft like Space Shuttle, are FRCI(Fibrous Refractory Composite Insulation) and AETB(Alumina-Enhanced Thermal Barrier). In the present work, we carried out the mathematical modeling and computer simulation of the thermal response of FRCI to heat, pulse, comparing with that of silica. Also, we calculated the conductivity of FRCI as various variables at the temperature range of 100~2000 K.

• Aerospace Engineering and Technology
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• v.13 no.2
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• pp.47-53
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• 2014

This paper cites that reaction wheel which is widely used on precisely controling a spacecraft is designed with Simulink as a software model. Electrical Characteristics and Mechanical ones of reaction wheels are applied to the simulation model and those equations are summarized for helping understanding. Moreover, results of numerical simulations with rigid body model show that the designed software model of reaction wheels is known to be well operated under its set parameter values.

• 제어로봇시스템학회:학술대회논문집
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• 1996.10a
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• pp.4-12
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• 1996

This keynote presentation covers the subject of intelligent systems development for monitoring and control in various NASA space applications. Similar intelligent systems technology also has applications in terrestrial commercial applications. Discussion will be given of the general approach of intelligent systems and description given of intelligent systems under prototype development for possible use in Space Shuttle Upgrade, in the Experimental Crew Return. Vehicle, and in free-flying space robotic cameras to provide autonomy to these spacecraft with flexible human intervention, if desired or needed. Development of intelligent system monitoring and control for regenerative life support subsystems such as NASA's human rated Bio-PLEX test facility is also described. A video showing two recent world's firsts in real-time vision-guided robotic arm and hand grasping of tumbling and translating complex shaped objects in micro-gravity will also be shown.

• International Journal of Aerospace System Engineering
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• v.1 no.1
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• pp.16-20
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• 2014

Recently, various kinds of study on light weight structure are performing in the world. The Al honeycomb sandwich structural type adopt for improvement of lightness and structural stability to major part structure of aircraft or spacecraft. Adhesion badness properties of adhesive and adhesion properties of fillet mainly studied about al honeycomb structure. But study for adhesive properties of sandwich construction with surface treatment of Aluminum alloy barely performed. In this study, adhesive film was used between Al and honeycomb core of honeycomb panel[1]. The study for adhesive properties of sandwich construction with surface treatment of AA 5052 skin was performed.

• Aerospace Engineering and Technology
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• v.7 no.2
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• pp.53-57
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• 2008

In this article, we discuss steering laws for control moment gyro cluster, which have been studied on the project, "Development of control moment gyro engineering model for middle-size spacecraft", supported by Ministry of Knowledge Economy, Korea. We compare performance of MP, SR, SR Escape/Avoidance steering laws and check each law's performance by simulations and experiments.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.20 no.4
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• pp.1-6
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• 2012

The accurate information of mass properties is required for the precise control of the spacecraft. The mass properties, mass and inertia, are changeable by some reasons such as consumption of propellant, deployment of solar panel, sloshing, environmental effect, etc. The gyro-based attitude data including noise and bias reduces the control accuracy so it needs to be compensated for improvement. This paper introduces a real-time inertia estimation method for the attitude determination of STSAT-3, Korea Science Technology Satellite. In this method we first filter the gyro noise with the Extended Kalman Filter(EKF), and then estimate the moment of inertia by using the filtered data from the EKF based on the Recursive Least Square(RLS).

• Proceedings of the Korean Institute of Electrical and Electronic Material Engineers Conference
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• 2008.04c
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• pp.62-66
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• 2008

Spacecrafts such as most of commercial satellites that are operating in the geostationary orbit can be subjected to intense irradiation by charged particles. The surface made of dielectric materials can therefore become probable sites for damaging electrostatic discharges. Thanks to a specially equipped chamber, the spatial environment can be reproduced experimentally in the laboratory. In this paper, the behavior of high energy electrons injected in polymers such as PolyMethylMetaAcrylate (PMMA) and Kapton is studied. Results obtained by surface potential technique, pulse-electro acoustic device and a cell based on the split Faraday cup system are analyzed and discussed.

• International Journal of Aeronautical and Space Sciences
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• v.4 no.2
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• pp.61-68
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• 2003

The space systems are being operated in a uncertain space environment and are desired to have autonomous capability for long periods of time without frequent telecommunications with the ground station. At the same time, requirements for new set of satellite system set of projects/systems calling for "autonomous" operations for long unattended periods of time are emerging. Since, by the nature of space systems, it is desired to perform its mission flawlessly and also it is of extreme importance to have fault-tolerant sensors and actuators for the purpose of validating science measurement data for the mission success. This studies focused on the identification/demonstration of critical technology innovations that will be applied to the Validation Control System.

• Journal of the Korean Society of Propulsion Engineers
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• v.8 no.2
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• pp.54-61
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• 2004

Miniaturization of subsystems including propulsion systems is recent trends in spacecraft technology. Small space vehicle propulsion is not only a technological challenge of a scaling system down, but also a combination of fundamental flow/combustion constraints. In this paper, physical constraints of micronozzle for cold gas micro-thruster are reviewed and discussed. Method to measure small thrust are also described.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.17-22
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• 2006

Anhydrous hydrazine and its methyl derivatives MMH and UDMH have been safety used as monopropellant and bipropellant fuels in thousands of satellites and expendable launch vehicles. Since KOMPSAT program, We have been developing skills on the hydrazine propulsion system for several years. This paper presents an overview of the hydrazine for the space application - propellant overview, material compatibility, handling cautions and the future of hydrazine systems.