• The Journal of Korea Robotics Society
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• v.12 no.4
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• pp.441-447
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• 2017

Robot arms are being increasingly used in various fields with special attention given to unmanned systems. In this research, we developed a high payload dual-arm robot, in which the forearm module is replaceable to meet the assigned task, such as object handling or lifting humans in a rescue operation. With each forearm module specialized for an assigned task (e.g. safety for rescue and redundant joints for object handling task), the robot can conduct various tasks more effectively than could be done previously. In this paper, the design of the high payload dual-arm robot with replaceable forearm function is described in detail. Two forearms are developed here. Each of forearm has quite a different goal. One of the forearms is specialized for human rescue in human familiar flat aspect and compliance parts. Other is for general heavy objects, more than 30 kg, handling with high degree of freedom more than 7.

• Aerospace Engineering and Technology
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• v.1 no.2
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• pp.149-154
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• 2002

The International Space Station (ISS) is being jointly developed by the following 16 international partners: The United States, Russia, Japan, Canada, Brazil, and the 11 member states of the European Space Agency. Assembly of ISS is a large-scale international program which commenced in November 1998, and is expected to conclude in 2006. Korea Aerospace Research Institute (KARI) is making effort to take part in the development of Payload Support & Interface Module (PSIM) for ISS. When success is achieved with ISS PSIM development project, Korea will have the rights to utilize external attached payload sites and research activities on ISS. Therefore preparation for the utilization of ISS EXPRESS pallet, JEM-EF, and Columbus-EPF need to be made. This paper shows the investigation results of the external attached payload sites for ISS and the application field of space and Earth science.

• Advances in aircraft and spacecraft science
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• v.4 no.4
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• pp.437-448
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• 2017

The problem of flow through the vent is formulated as an unsteady, nonlinear, ordinary differential equation and solved using Runge-Kutta method to obtain pressure inside payload faring. An inverse problem for prediction of the discharge coefficient is presented employing measured internal pressure of the payload fairing during the ascent phase of a satellite launch vehicle. A controlled random search method is used to estimate the discharge coefficient from the measured transient pressure history during the ascent period of the launch vehicle. The algorithm predicts the discharge coefficient stepwise with function of Mach number. The estimated values of the discharge coefficients are in good agreement with differential pressure measured during the flight of typical satellite launch vehicle.

• 제어로봇시스템학회:학술대회논문집
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• 2001.10a
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• pp.177.1-177
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• 2001

This paper describes the design of a NUC(Non-uniformity Correction) module in MSC(Multispectral Camera) which will be a payload on KOMPSAT. This module is required inside a system with data compression module like MSC to minimize the loss of imagery due to non-uniform characteristics between CCD pixels when the imagery is received and processed on a ground station. It comprises Hotlink input/output for imagery data, RS-422 interface with main controller in MSC, a number of SRAMS for storing imagery data and parameters, FPGA controllers which control the entire NUC module under the control of main controller, etc. It inputs 8-channel imagery pixel data which consist of 2-channel MS(Multispectral) band and ...

• Journal of the Korea Institute of Military Science and Technology
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• v.12 no.4
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• pp.452-459
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• 2009

A 6-bit MMIC digital attenuator applicable to X-band TR module has been developed by using $0.5{\mu}m$GaAs pHEMT processes. The Switched-T attenuator scheme and the switched-path attenuator scheme were adopted to obtain low insertion loss and small phase variation, respectively. Resistors and transmission lines are optimized to achieve the digital attenuator with high attenuation accuracy and small phase variation. The digital attenuator has RMS error of 0.4dB, resolution of 0.5dB and dynamic range of 31.5dB. The measurement results show that in-out VSWRs are less than 1.5, phase variation is from -7 to +2 degrees and IIP3 is 36.5dBm.

• Proceedings of the KSRS Conference
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• v.2
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• pp.797-799
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• 2006

The Electro-optical camera subsystem as a payload of a satellite system consists of OM (optical module) and CEU(camera electronics unit), and most performances of the camera subsystem depend a lot on the CEU in which TDI CCDs(Time Delayed Integration Charge Coupled Device) take the main role of imaging by converting the light intensity into measurable voltage signal. Therefore it is required to specify and design the CEU very carefully at the early stage of development with overall specifications, design considerations, calibration definition, test methods for key performance parameters. This paper describes the overview of CEU development. It lists key requirement characteristics of CEU hardware and design considerations. It also describes what kinds of calibration are required for the CEU and defines the test and evaluation conditions in verifying requirement specifications of the CEU, which are used during acceptance test, considering the fact that CEU performance results change a lot depending on test and evaluation conditions such as operational line rate, TDI level, and light intensity level, so on.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2005.05a
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• pp.250-253
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• 2005

This paper is investigates the separation shock of payload fairing. Separation test of subscale PLF using half separation device and half PLA is performed. Resulting shock loads at equipment bay and fairing joint are measured. Pyroshock estimation is performed using AUTOSEA Pyroshock Module. Input data to analysis model is obtained from the separation test results of subscale PLF. And model of AUTOSEA is updated comparing results between tests and analysis.. This enables us to validate the AUTOSEA model. Tuned model of subscale PLF and separation device is used to update full scale model, and the shock analysis result of full scale model is estimated in this paper. This paper also discusses the results regarding the difficulty of structural modeling and its numerical implementation in AutoSEA2 Software.

• Proceedings of the Korea Electromagnetic Engineering Society Conference
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• 2002.11a
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• pp.86-90
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• 2002

본 논문에서는 Ka-band 위성중계기에 사용되어지는 수신하향변환기(Receiver-Downconverter) 모듈의 설계 및 제작 그리고 시험 결과에 대하여 기술하였다. 개발된 수신하향변환기는 30.6~31㎓ 대역의 신호를 입력으로 받아들여 20.8~21.2㎓ 대역의 신호를 출력하는 일종의 Downconverter 이지만, 모듈의 입력단에 저잡음 증폭부가 포함된 수신기의 역할도 하고 있다. 개발된 모듈은 제작과정 및 시험과정에 있어 위성중계기 부품 제작 규정을 준수하였으며, 그 개발된 성능은 현재까지 알려진 국내외 유사 부품중의 최고의 성능을 보여주고 있다. 측정된 모듈의 성능은 상온에서 1.9㏈의 잡음지수, 55㏈ 이득, 58dBc의 C/l3 값을 보여주고 있다. 제작된 모듈의 크기는 93mm$\times$84mm$\times$26mm이며 무게는 240g으로서 국내외 유사 제품에 비해 소형이다.

• Journal of Astronomy and Space Sciences
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• v.17 no.2
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• pp.309-316
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• 2000

KOMPSAT-2 will carry MSC(Multi-Spectral Camera) which provides 1m resolution panchromatic and 4m resolution multi-spectral images at the altitude of 685km sun-synchronous mission orbit. The mission operation of KOMSPAT-2 is to provide the earth observation using MSC with nadir pointing. KOMPSAT-2 will also have the capability of roll/pitch tilt maneuver using reaction wheel of satellite as required. In order to protect MSC from thermal distortion as well as direct sunlight, MSC shall be operated within the constraint of sun incidence angle. It is expected that the sunlight will not violate the constraint of sun incidence angle for normal mission operations without roll/pitch maneuver. However, during roll/pitch tilt operations, optical module of MSC may be damaged by the sunlight. This study analyzed sun incidence angle of payload using KOMPSAT-2 AOCS (Attitude and Orbit Control Subsystem) Design and Performance Analysis Soft ware for KOMPSAT-2 normal mission operations.

• Aerospace Engineering and Technology
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• v.1 no.1
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• pp.42-54
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• 2002

In December of 1997, Korea Aerospace Research Institute begin to develope the conceptual design of Kompsat2 as the Kompsat1 design is nearly completed. Basic direction of this design was set up to utilized the heritage of Kompsat1 and modify the payload module to accommodate the new high resolution space borne camera. And in the early stage of this design, total system configuration design study was conducted based on 1st level payload information. In this paper, mechanical system design at various stage is documented and this will be used as a path finder or guidelines in the future feasibility study or conceptual design.