Fault Detector and Fault Detection Method for Attitude Control System of Spacecraft
First Claim
1. A fault detector for an attitude control system (ACS) of a spacecraft including a plurality of actuators, comprising:
- a first interacting multiple model (IMM) fault detection block for generating a normal model filter of the plurality of actuators and a plurality of upper level filters including fault model filters corresponding to the respective actuators, and detecting faults of the plurality of actuators using an IMM estimation technique from the plurality of upper level filters; and
a second IMM fault detection block for generating a plurality of lower level filters each including a fault type model filter of the fault-detected actuator in the first IMM fault detection block, and detecting a fault type of the failed actuator using the IMM estimation technique.
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Abstract
Provided are a fault detector and a fault detection method for an attitude control system (ACS) of a spacecraft. The fault detector includes a first interacting multiple model (IMM) fault detection block for generating a normal model filter of the plurality of actuators and a plurality of upper level filters including fault model filters corresponding to the respective actuators, and detecting faults of the plurality of actuators using an IMM estimation technique from the plurality of upper level filters, and a second IMM fault detection block for generating a plurality of lower level filters each including a fault type model filter of the fault-detected actuator in the first IMM fault detection block, and detecting a fault type of the failed actuator using the IMM estimation technique.
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Citations
11 Claims
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1. A fault detector for an attitude control system (ACS) of a spacecraft including a plurality of actuators, comprising:
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a first interacting multiple model (IMM) fault detection block for generating a normal model filter of the plurality of actuators and a plurality of upper level filters including fault model filters corresponding to the respective actuators, and detecting faults of the plurality of actuators using an IMM estimation technique from the plurality of upper level filters; and a second IMM fault detection block for generating a plurality of lower level filters each including a fault type model filter of the fault-detected actuator in the first IMM fault detection block, and detecting a fault type of the failed actuator using the IMM estimation technique. - View Dependent Claims (2, 3, 4, 5, 6, 7)
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8. A fault detection method for an attitude control system (ACS) of a spacecraft including a plurality of actuators, comprising:
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a first actuator-fault detection operation of generating a normal model filter of the plurality of actuators and a plurality of upper level filters including fault model filters corresponding to the respective actuators, and detecting faults of the plurality of actuators using an interacting multiple model (IMM) estimation technique; and a second actuator-fault detection operation of generating a plurality of lower level filters corresponding to fault types of the fault-detected actuators in the first actuator-fault detection operation, and detecting the fault type of the failed actuator using the IMM estimation technique. - View Dependent Claims (9, 10, 11)
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Specification