End-to-end design of a robust attitude control and vibration suppression system for large space smart structures

Angeletti, Federica; Iannelli, Paolo; Gasbarri, Paolo; Sabatini, Marco

doi:10.1016/j.actaastro.2021.04.007

Cited by 29 publications

(18 citation statements)

References 23 publications

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“…The preceding steering law minimizes the magnitude of the vector ω s , while enforcing the contraint T c = −A ω s . The steering law (15) works only if matrix AA T is nonsingular. This condition is satisfied if at least three columns of A are linearly independent, and this is the case with the ortho-skew arrangement.…”

Section: Actuatorsmentioning

confidence: 99%

“…In particular, actuation dynamics is accurately modeled, through inclusion of all terms that describe the actual torque transferred to the spacecraft. Large satellites use wide solar panels and antennas, and investigating their interaction (as flexible bodies) with the overall rotational dynamics [15] is crucial for the purpose of modeling the spacecraft behavior during a large slewing maneuver. In this paper, the solar panels are modeled as flexural beams that can bend only orthogonally to their plane, and the modal decomposition technique is used.…”

Section: Introductionmentioning

confidence: 99%

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Nonlinear Slewing Control of a Large Flexible Spacecraft Using Reaction Wheels

2022

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Reorientation maneuvers represent a key task for large satellites. This work considers a space vehicle with solar panels and reaction wheels as actuation devices. Solar panels are modeled as flexural beams, using the modal decomposition technique. An inertia-free nonlinear attitude control algorithm, which enjoys quasi-global stability properties, is employed for the numerical simulation of a large reorientation maneuver. Preliminary analysis with ideal actuation allows sizing the control system and identifying the expected elastic displacements. Then, the actuation dynamics is included, and the actual torque transferred to the vehicle no longer coincides with the commanded one, supplied by the nonlinear control algorithm. Moreover, the solar panels are designed to rotate, in order to maximize the power storage during the maneuver. The numerical results prove that the slewing maneuver is successfully completed in reasonable time and without any saturation of the actuation devices, while the elastic displacements remain modest, in spite of the solar panel rotation aimed at pursuing the Sun direction.

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Section: Actuatorsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Nonlinear Slewing Control of a Large Flexible Spacecraft Using Reaction Wheels

2022

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“…Model Replica) of the payload of a realistic space mission. Indeed, a structural model based on available information about the AstroMesh® antenna [18,19] has been realized in a finite element commercial environment [20]. To properly benefit from a distributed active vibration control system, the properties of the developed model have been modified to achieve a mass reduction of up to 30% with respect to the original AstroMesh® reflector.…”

Section: Large Mesh Reflector Structural Modelmentioning

confidence: 99%

“…Their locations have been selected based on a placement procedure that made use of the controllability and observability gramians of the system to attempt to increase-from a control perspective-the relative controllability and observability of the most important system modes. More details about the placement process may be found in Authors' previous work [20]. The final configuration-position and related number of actuators and sensors-is reported in Fig.…”

Section: Distributed Active Vibration Control (Avc) Systemmentioning

confidence: 99%

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Model-Based FDI Applied to a Piezoelectric Active Vibration Suppression System for Smart Flexible Spacecraft

Iannelli

Angeletti

Gasbarri

2021

Aerotec. Missili Spaz.

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Fault Detection and Isolation (FDI) techniques have captured extensive interest and attention in modern autonomous systems; in particular, they are of foremost importance in space applications, due to their scientific relevance, cost and current inability of doing on-orbit maintenance of space systems. In this scenario, FDI strategies are required to counteract possible failure events that, if not properly handled, can reduce system performance or compromise the realization of the mission objectives. In this paper, a model-based FDI strategy is implemented onboard a satellite equipped with a very large mesh reflector on which a distributed network of smart actuators/sensors is mounted to actively counteract undesired elastic vibrations. In particular, the detection and isolation of a possible piezo-actuator failure occurring in the Active Vibration Control (AVC) system of the antenna is addressed by a bank of Unknown Input Observers (UIOs). The design of the proposed UIOs is derived by solving a Linear Matrix Inequality (LMI) problem, which provides the conditions for their existence, and it is based on the linearized 3D state-space model of the controlled spacecraft, under the assumption that all the uncertainties, exogenous disturbances and measurement noises are neglected. Furthermore, pole assignment in the sense of D-stability is integrated in the standard formulation of the UIO to guarantee an adequate transient behaviour of the observers. Finally, an extensive Monte Carlo simulation campaign is conducted to assess the effectiveness of the proposed FDI architecture and its robustness against modelling uncertainties and measurement noise.

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Active vibration control method of a novel on-orbit assembled large-scale two-dimensional planar phased array antenna

Jin,

Liu,

et al. 2024

Acta Mech

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End-to-end design of a robust attitude control and vibration suppression system for large space smart structures

Cited by 29 publications

References 23 publications

Nonlinear Slewing Control of a Large Flexible Spacecraft Using Reaction Wheels

Nonlinear Slewing Control of a Large Flexible Spacecraft Using Reaction Wheels

Model-Based FDI Applied to a Piezoelectric Active Vibration Suppression System for Smart Flexible Spacecraft

Active vibration control method of a novel on-orbit assembled large-scale two-dimensional planar phased array antenna

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