FUSE in-orbit attitude control with two reaction wheels and no gyroscopes

Kruk, J. W.; Class, Brian F.; Rovner, Dan; Westphal, Jason J.; Ake, Thomas B.; Moos, H. W.; Roberts, Bryce; Fisher, Landis

doi:10.1117/12.459948

Cited by 14 publications

(6 citation statements)

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“…1. In 2001, Far Ultraviolet Spectroscopic Explorer (FUSE) satellite had a failure with the loss of two of its four reaction wheels required for attitude control [Kruk et al 2002].…”

Section: Faults In Satellite Attitude and Orbit Control Systemmentioning

confidence: 99%

Intelligent Control of Satellite Formation Flying

Li¹

2021

Preprint

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Small satellites flying in formation present a more efficient and affordable way of achieving the same or better performance than a large satellite because of low cost, high density of functionality and a short development cycle. A key technology for achieving mission objectives is the attitude and orbit control system. The overall objective of this dissertation research focuses on developing advanced control strategies and fault tolerant control for satellite formation flying. It is necessary to design and operate the satellite formation flying system to reduce fuel consumption and improve control accuracy. This is a very challenging task due to the nonlinear nature of satellite formation dynamics and the risk of thrusters’ failures and sensors’ faults in the absence of hardware redundancy. A class of nonlinear leader-follower satellite formation flying systems subject to uncertain thrusters’ and sensors’ faults and external J2 disturbances has been studied applying fault detection and identification and second order sliding mode control methodologies. New fault detection and identification and fault tolerant control algorithms were compared with model based fault detection and identification and fault tolerant control algorithms in presence of large initial errors, timevarying external disturbances, and parameter uncertainties. The faults considered were modeled as constant or ramp faults. Numerical results demonstrated the effectiveness of the proposed active fault tolerant control under actuators’ and sensors’ faults. It has been shown that the proposed second order sliding mode control scheme can guarantee local asymptotic stability after system faults. Simulation results confirmed that the suggested control methodologies yield high formation keeping precision and effectiveness for leaderfollower formation flying systems. The tracking errors of the proposed second order sliding mode control, adaptive fuzzy sliding mode control, chattering free sliding mode control and classic sliding mode control resulting from the thruster faults are within 2 m, 4 m, 10 m and 1 m, respectively. The fuel consumption of the proposed second order sliding mode control was the least. It is also necessary to design a fault tolerant satellite attitude control system to reduce fuel consumption and improve control performance accuracy. The proposed fault tolerant attitude control algorithms were based on first order and higher order sliding mode control theory as well as fuzzy logic systems to achieve real time autonomous fault tolerant control. These algorithms were applied to attitude synchronization in both leader-follower formation flying and decentralized formation flying. Attitude synchronization during formation flying was examined considering actuator dynamics while decentralized attitude ynchronization was studied using graph theory with quaternion kinematics. The proposed fault tolerant control algorithm was compared with the existing satellite attitude system controllers in the literature and it was found that the proposed algorithm resulted in three axis attitude stabilization within 0.041◦ in all axes for the fault cases. The reaction wheels’ Coulomb friction, saturations, noise, dead-zones, bias fault and external disturbances are considered. Finally, a nonlinear adaptive fuzzy sliding mode controller was tested using embedded nanosatellite hardware on a frictionless spherical air bearing system. The test results showed attitude errors of 0.8◦ using the proposed controller while a proportional integral derivative controller resulted in 5◦ attitude errors.

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“…1. In 2001, Far Ultraviolet Spectroscopic Explorer (FUSE) satellite had a failure with the loss of two of its four reaction wheels required for attitude control [Kruk et al 2002].…”

Section: Faults In Satellite Attitude and Orbit Control Systemmentioning

confidence: 99%

Intelligent Control of Satellite Formation Flying

Li¹

2021

Preprint

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“…Far Ultraviolet Spectroscopic Explorer (FUSE) satellite was at the peak of its scientific productivity when hardware problems caused the loss of two of its four reaction wheels required for attitude control. The pitch and yaw wheels despun due to excessive friction between the rotors and wheel housings [Kruk et al 2002b]. Engineers reprogrammed the control software by developing a new control law, integrating the Magnetic Torquer Bars in the control loop along with the remaining two reaction wheels, and fine pointing capability was reestablished [Roberts et al 2004].…”

Section: Rationale Behind Fault Tolerant Control Designmentioning

confidence: 99%

“…Loss of critical control actuators like reaction wheels can lead to spacecraft pointing control accuracy degradation and for some cases, the spacecraft may completely lose its stabilization capability. The ability of the spacecraft to attain sufficient degree of attitude dexterity after losing two reaction wheels has been practically demonstrated for several missions like TOPEX [Lam et al 2001], and FUSE [Kruk et al 2002a]. Three-axis stabilization using two remaining reaction wheels was accomplished by integrating other torque generating actuators like reaction control thrusters and magnetic torquer bars (MTB).…”

Section: Chaptermentioning

confidence: 99%

Fault Tolerant Control Of Spacecraft

Godard¹

2021

Preprint

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Autonomous multiple spacecraft formation flying missions demand the development of reliable control systems to ensure rapid, accurate, and effective response to various attitude and formation reconfiguration commands. Keeping in mind the complexities involved in the technology development to enable spacecraft formation flying, this thesis presents the development and validation of a fault tolerant control algorithm that augments the AOCS on-board a spacecraft to ensure that these challenging formation flying missions will fly successfully. Taking inspiration from the existing theory on nonlinear control, a fault-tolerant control system for the RyePicoSat missions is designed to cope with actuator faults whilst maintaining the desirable degree of overall stability and performance. Autonomous fault tolerant adaptive control scheme for spacecraft equipped with redundant actuators and robust control of spacecraft in underactuated configuration, represent the two central themes of this thesis. The developed algorithms are validated using a hardware-in-the-loop simulation. A reaction wheel testbed is used to validate the proposed fault tolerant attitude control scheme. A spacecraft formation flying experimental testbed is used to verify the performance of the proposed robust control scheme for underactuated spacecraft configurations. The proposed underactuated formation flying concept leads to more than 60% savings in fuel consumption when compared to a fully actuated spacecraft formation configuration. We also developed a novel attitude control methodology that requires only a single thruster to stabilize three axis attitude and angular velocity components of a spacecraft. Numerical simulations and hardware-in-the-loop experimental results along with rigorous analytical stability analysis shows that the proposed methodology will greatly enhance the reliability of the spacecraft, while allowing for potentially significant overall mission cost reduction.

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“…FUSE had four reaction wheels, two sets of three degree of freedom gyroscopes, three magnetic torqueing bars, three-axis magnetometers, course sun sensors, a fine error sensor, and a payload of 4 co-aligned prime focus telescopes and Rowland spectrographs with micro-channel plate detectors to observe light rays in the ultraviolet spectrum ranging 905 to 1187 Angstroms. FUSE suffered failures in three out of four reaction wheels and both of its sets of gyroscopes also failed 6,7 , offering a compelling real-world example to study with our fault reconfiguration framework. In response to the failures, FUSE's control laws and gyroscopes were reconfigured to re-establish acceptable operational performance, but since these reconfigurations were performed manually from the ground station, substantial mission time was sacrificed with the spacecraft in safe mode while awaiting reconfiguration instructions.…”

Section: Baseline Spacecraft Case Studymentioning

confidence: 99%

A Mission Based Fault Reconfiguration Framework for Spacecraft Applications

Nasir

Atkins

Kolmanovsky

2012

Infotech@Aerospace 2012

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We present a Markov Decision Process (MDP) framework for computing post-fault reconfiguration policies that are optimal with respect to a discounted cost. Our cost function penalizes states that are unsuitable to achieve the remaining objectives of the given mission. The cost function also penalizes states where the necessary goal achievement actions cannot be executed. We incorporate probabilities of missed detections and false alarms for a given fault condition into our cost to encourage the selection of policies that minimize the likelihood of incorrect reconfiguration. To illustrate the implementation of our proposed framework, we present an example inspired by the Far Ultraviolet Spectroscopic Explorer (FUSE) spacecraft with a mission to collect scientific data from 5 targets. Using this example, we also demonstrate that there is a design tradeoff between safe operation and mission completion. Simulation results are presented to illustrate and manage this tradeoff through the selection of optimization parameters.

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FUSE in-orbit attitude control with two reaction wheels and no gyroscopes

Cited by 14 publications

References 0 publications

Intelligent Control of Satellite Formation Flying

Intelligent Control of Satellite Formation Flying

Fault Tolerant Control Of Spacecraft

A Mission Based Fault Reconfiguration Framework for Spacecraft Applications

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