Abstract
This paper presents a fault detection and isolation (FDI) approach in order to detect and isolate actuators (thrusters and reaction wheels) faults of an autonomous spacecraft involved in the rendez-vous phase of the Mars Sample Return (MSR) mission. The principal component analysis (PCA) has been adopted to estimate the relationships between the various variables of the process. To ensure the feasibility of the proposed FDI approach, a set of data provided by the industrial “high-fidelity” simulator of the MSR and representing the opening (resp., the rotation) rates of the spacecraft thrusters (resp., reaction wheels) has been considered. The test results demonstrate that the fault detection and isolation are successfully accomplished.
Highlights
In industry, an embedded system can be subjected to various promptings that may significantly affect the performance and the security of the system in question
This paper presents a fault detection and isolation (FDI) approach in order to detect and isolate actuators faults of an autonomous spacecraft involved in the rendez-vous phase of the Mars Sample Return (MSR) mission
In this paper, we will present a diagnosis approach for spacecraft actuators based on the principal component analysis (PCA) technique analyzing their performance during the rendez-vous phase of the MSR mission
Summary
An embedded system can be subjected to various promptings that may significantly affect the performance and the security of the system in question. The primary purpose of fault protection is to ensure that anomalies or operational problems encountered during the operation of the spacecraft do not result in a permanent reduction in the spacecraft’s capabilities or loss of the mission itself To avoid these risks and any deviation from the nominal orbits, it is indispensable to provide a system with a fault detection and isolation (FDI) functionality and an automatic reconfiguration onboard a spacecraft. Numerous fault diagnosis systems have been developed to detect and isolate the thrusters’ failures Most of these systems have been based on an analytic method using a mathematical model [6, 14]. In this paper, we will present a diagnosis approach for spacecraft actuators (thrusters and reaction wheels) based on the PCA technique analyzing their performance during the rendez-vous phase of the MSR mission.
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