• Aerospace Engineering and Technology
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• v.13 no.1
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• pp.37-43
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• 2014

The ground station which operates the LEO satellite performs monitoring state of health of the satellite, sending the commands for the imaging mission of receiving the images during about 10 minutes of contact time. To finish the planned procedure in limited contact time, specific level of autonomy is applied in the satellite and the ground system. For example, the attitude and orbit control logic has high level of autonomy because it must be operated alone for long period without operator intervention. On the other hand, the fault management logic has relatively low level of autonomy because of that failure detection and safing operation are performed on-board, whereas failure identification and recovery are on-ground operation. The level of autonomy of the satellite affects also the ground operation. The command set for mission operation is generated by ground system. If the satellite has higher level of autonomy, some of operation currently done on-ground can be performed on-board, so the ground operation can be simplified. In this paper, we discuss the level of autonomy and propose a concept for improving the level of autonomy of an LEO satellite.

• Journal of Korean Society for Geospatial Information Science
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• v.20 no.3
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• pp.49-56
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• 2012

Performance analysis on RAIM, which is one of the techniques for monitoring integrity to ensure the reliability of GPS, was conducted in this study. RAIM is such a method which allows its user to monitor integrity in the stand-alone mode. Among the existing RAIM procedures, the representative methods including the RCM (Range Comparison Method), LSRM (Least Square Residual Method), Parity approach and WRAIM (Weighted RAIM) were evaluated, and their performance was analyzed. To validate the performance of the implemented algorithms, fault detection was tried on the clock malfunctioning event of PRN 23 occurred on January 1st, 2004. As a result, it was identified that the LSRM and the WRAIM detected all the faults happened in the event. In the case of RCM, all the states of fault were detected except for the error which occurred as a false alarm at one epoch. Furthermore, simulated biases were added for each satellite to analyze the sensitivity of each algorithm. Consequently, when biases of the 9-13 meters range were simulated for the RCM and LSRM algorithm, all the malfunctions were detected. For the WRAIM method, it could detect range biases greater than 15 meters.

• Proceedings of the KIEE Conference
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• 2005.07d
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• pp.2573-2575
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• 2005

본 논문에서는 원자 시계를 이용한 위성 시계 고장 판단 기법을 제안한다. GPS 측정치 중 위성 시계 오차 성분을 제외한 위성 궤도 오차, 이온층 지연 오차, 대류층 지연 오차, 수신기 시계 오차를 제거하여 위성 시계 오차에 의한 영향만을 검사하도록 한다. 특히 TCXO와 같은 일반적인 수신기 시계를 사용할 경우 정확한 수신기 시계 오차 크기를 추정하기 어렵기 때문에 원자 시계와 같은 정밀 신호 발생기를 이용하여 수신기 시계 오차에 의한 영향을 제거하는 방법을 제시한다. 제시한 방법은 실제 위성 시계에 이상이 발생 했을 때 수집한 데이터를 이용한 실험을 통하여 검증하도록 한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.6
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• pp.570-576
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• 2010

This paper can be used for GPS air navigation study on integrity monitoring algorithm as, the projected horizontal plane using GPS pseudorange residuals for fault detection satellites were suspected. Failure to remove the detected suspicious satellite, compare with threshold which is calculated using satellite deployment (PDOP) and determine whether the failure is presented. The theory that horizontal projection of the satellite failure residuals greater than residual of normal satellite is proved mathematically. Comparison with horizontal projection residuals are likely to malfunction in the satellite were presented. To evaluate the proposed algorithm, bias fault insert into GPS pseudorange, and compare with conventional parity space method about fault detection and isolation capability.

• Journal of Astronomy and Space Sciences
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• v.15 no.2
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• pp.499-508
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• 1998

Satellite Operations Subsystem in the Mission Control Element provides real-time monitoring of the satellite status and transmits telecommands to control the satellite during the contact time. This paper presents the dynamic fault management strategy of Satellite Operations Subsystem designed to minimize data loss using software and hardware redundancy for upgrade safety and reliability of Satellite Operations Subsystem. Also this paper describes the performance test method to prove justification of implementation and analyzes the results.

• Journal of Astronomy and Space Sciences
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• v.14 no.1
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• pp.166-178
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• 1997

Many research works are on going to monitor and diagnose diverse malfunctions of satellite systems as the complexity and number of satellites increase. Currently, many works on monitoring and diagnosis are carried out by human experts but there are needs to automate much of the routine works of them. Hence, it is necessary to study on using expert systems which can assist human experts routine work by doing automatically, thereby allow human experts devote their expertise more critical and important areas of monitoring and diagnosis. In this paper, we are employing artificial intelligence techniques to model human expert's knowledge and inference the constructed knowledge. Especially, case-based approaches are used to construct a knowledge base to model human expert capabilities which use previous typical exemplars. We have designed and implemented a prototype case-based system for diagnosing satellite malfunctions using cases. Our system remembers typical failure cases and diagnoses a current malfunction by indexing the case base. Diverse methods are used to build a more user friendly interface which allows human experts can build a knowledge base in an easy way.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.1
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• pp.42-47
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• 2010

This paper considers a fault tolerant control problem for a spacecraft using wheels which are momentum exchanging devices. The control of a satellite with only two healthy wheels has been studied and its result has been presented. Two different configurations have been considered. When the yaw rate cannot be controlled directly by any control input, the desired yaw rate can be obtained by using the roll rate as a pseudo control. As a result, all three angular speeds have been stabilized, and two attitude angles including pitch and yaw have been controlled to converge to the desired values.

• Journal of Satellite, Information and Communications
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• v.12 no.4
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• pp.67-71
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• 2017

A solar array is main electrical energy source for Low-Earth-Orbit(LEO) satellite. The solar array cannot generate electrical energy during eclipse period, a battery supply electrical energy to the satellite. The electrical power of the solar array is changed in accordance with operating voltage and the solar array has the maximum power point. The solar array regulator makes the solar array supply electrical energy to the satellite and charge the battery. The solar array is connected to the solar array regulator input and the battery is connected to the solar array regulator output. The solar array regulator consists 2 of 3 hot redundant. One solar array regulator contains 3 DC-DC converters, and the solar array regulator operates stably even if the failure occur in one DC-DC converter. In this paper, the solar array regulator, the battery and the solar array operation is analyzed when the failure occur in one DC-DC converter.

• Journal of Aerospace System Engineering
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• v.13 no.2
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• pp.26-33
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• 2019

Control moment gyro (CMG) employed as satellite actuators, generates a large torque through the steering of its gimbals. Although each gimbal holds a high-speed rotating wheel, the wheel imbalances induces disturbance and degrades the satellite control quality. Therefore, the disturbances ought to be detected and identified as a precaution against actuator faults. Among the method used in detecting disturbances is the state observers. In this paper, we apply a continuous second order sliding mode observer to detect single disturbances/faults in CMGs. Verification of the algorithm is also done on the hardware satellite simulator where four CMGs are installed.

• Journal of Satellite, Information and Communications
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• v.11 no.3
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• pp.51-57
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• 2016

Many kinds of telemetry should be monitored to check the state of spacecraft and it leads the time consumption. However, it is very important to define the status of satellite in short time because the contact number and time of low earth orbit satellite is limited. Also, on-board fault management should be prepared for non-contact operation because of the sever space environment. In this paper, on-board and ground autonomous operation method for the safety enhancement is described. Immediate fault detection and response is possible in ground by explicit anomaly detection through satellite event and error information. Also, satellite operation assistant system is proposed for ground autonomy that collect event sequence in accordance with related telemetry and recommend or execute an appropriate action for abnormal state. Critical parameter monitoring method with checking rate, mode and threshold is developed for on-board autonomous fault management. If the value exceeds the limit, pre-defined command sequence is executed.