Study of Current Femto-Satellite Approches

Tahri, Nizar; Hamrouni, Chafaa; Alimi, Adel M.

doi:10.14569/ijacsa.2013.040520

Cited by 4 publications

(8 citation statements)

References 8 publications

(29 reference statements)

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“…To my loving parents Majid Rahimi and Farideh Farhang, without whose support and endless love, I would not be here. Table 1.1 Satellite program costs by mass [3], [4] 5. 4 Fault prognosis for a normally distributed sample set with 500 particles ..... 120 Table 5.5 Fault prognosis for a normally distributed sample set with 100 particles ..... 120 xii Table 5.6 Fault prognosis for a normally distributed sample set with 1000 particles ... 120 Table 5.…”

Section: Industrial Opportunities At Bombardier Transportation Through Mitacs Programmentioning

confidence: 99%

Fault Diagnosis And Prognosis Of Satellite Attitude Control System With Reaction Wheels and Control Moment Gyros

Rahimi¹

2021

Preprint

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Condition-based maintenance (CBM) and prognostics and health management (PHM), as consisting parts of diagnosis, prognosis, and health monitoring (DPHM) framework, have developed over the past decades to remedy the limitations of the traditional maintenance practices for complex systems. In space, where mass and power budget are restricted, application of CBM and PHM has become more vital to the success of a mission. Reaction wheels (RW) and Control Moment Gyros (CMG), as the most commonly used actuators onboard satellites, are prone to faults and failures. The ability to detect faults, isolate their location and severity, and estimate the remaining useful life (RUL) of the faulty unit can enhance mission success rate and reduce maintenance and damage costs extensively. Therefore, in this thesis, a model-based DPHM framework is developed and evaluated. Firstly, a novel fault detection algorithm is proposed, using Unscented Kalman filters (UKF) in conjunction with residual and innovation sequences, for detecting agile faults in RW/CMG onboard satellites. Secondly, a novel fault isolation algorithm is proposed, using UKF, Bayes’ probability and interacting multiple models (IMM), to isolate the location of the fault and its severity. Finally, a new fault prognosis approach is proposed, using UKF and particle filters (PF) to estimate the RUL of a faulty unit. Extensive simulations were conducted for each phase of the DPHM to verify advantages of the proposed techniques over the available methods in the literature. Extensive simulations were conducted to evaluate the performance of the proposed methods in each module of the framework. Regarding the proposed fault detection scheme, results showed superior performance of the proposed adaptation technique compared to the original UKF and a previously developed AUKF. The proposed fault isolation scheme was able to successfully isolate the faulty unit at multiple levels of isolation including formation level, system level, and actuator level with over 99% success rate for formation level, over 99% success rate for the RW assembly and for up to 90% success rate for the CMG assembly in the system level. For the CMG assembly, due to direct estimation of the fault parameters, it was possible to determine the severity of the faults as well as their location. Finally, the proposed fault prognosis approach provided RUL estimates with errors as low as 1.5% compared to the actual remaining useful life. Overall, the proposed framework can be regarded as a promising tool for fault detection, isolation and identification, and prognosis of the complex nonlinear systems. Furthermore, the proposed framework can be extended to other complex systems in space including multi-agent formation systems and other areas where the model of the system under study is available.

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Section: Industrial Opportunities At Bombardier Transportation Through Mitacs Programmentioning

confidence: 99%

Fault Diagnosis And Prognosis Of Satellite Attitude Control System With Reaction Wheels and Control Moment Gyros

Rahimi¹

2021

Preprint

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“…[2], [3] and [4] discuss the system design, sensors and applications of femto-satellites. PCBsat (70g) and Wikisat (19.7g) are two existing femto-satellites [4] that include a CMOS imager as a payload. PCBsat has two sun sensors, a GPS receiver, and passive aerodynamic attitude control [4].…”

Section: Femto Satellite Surveymentioning

confidence: 99%

“…PCBsat (70g) and Wikisat (19.7g) are two existing femto-satellites [4] that include a CMOS imager as a payload. PCBsat has two sun sensors, a GPS receiver, and passive aerodynamic attitude control [4]. Wikisat has four optic sensors, a 3D accelerometer, a 3D gyrometer and magnetorquers for attitude control [4].…”

Section: Femto Satellite Surveymentioning

confidence: 99%

“…PCBsat has two sun sensors, a GPS receiver, and passive aerodynamic attitude control [4]. Wikisat has four optic sensors, a 3D accelerometer, a 3D gyrometer and magnetorquers for attitude control [4]. Ref.…”

Section: Femto Satellite Surveymentioning

confidence: 99%

“…Next generation sensors for femto-satellites have been studied for use in disaster management missions [3]. Femto-satellites can be based on CMOS (Complementary Metal-Oxide Semiconductor) and MEMS (Micro Electro Mechanical System) technologies [4], but few active control systems have been proposed for femto-satellites. The Control Moment Gyroscope is a space attitude control actuator which acts as torque amplifier [15].…”

Section: Introductionmentioning

confidence: 99%

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Study for femto satellites using micro Control Moment Gyroscope

Post

Bauer

et al. 2016

2016 IEEE Aerospace Conference

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Abstract-Femto-satellites can be used for distributed space missions that can require hundreds to thousands of satellites for real time, distributed, multi-point networks to accomplish remote sensing and science objectives. While suitable sensors are available using micro-electro-mechanical system technology, most femto-satellite designs have no attitude control capability due to the power and size constraints on attitude control actuators. A novel femto-satellite design that uses a micro-electromechanical system Control Moment Gyroscope is studied in this paper. We focus on the principal design, modelling, and discussion of the proposed Control Moment Gyroscope while detailing a controllable femto-satellite design that can make use of attitude control for simple sensing missions.

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