Optimal Configuration of Four Reaction Wheels in Momentum Management Performance and Reliability Point of View

Kasiri, Ali; Saberi, Farhad Fani

doi:10.1007/s40997-023-00609-1

Cited by 1 publication

(2 citation statements)

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“…Choosing four reaction wheels is actually a trade-off between the satellite’s overall reliability and mass considerations. Four reaction wheels can be arranged in different configurations, and this issue has a direct impact on ACS performance (torque envelope, momentum management, pointing accuracy, power consumption, and so on) 16 . Among various arrangements of the four reaction wheels, the pyramidal arrangement has attracted more attention and has been deeply investigated 17 – 19 .…”

Section: Mathematical Modelingmentioning

confidence: 99%

“…However, many spacecraft benefit from 4 RWs to achieve more reliability and extra maneuverability. Although 4 reaction wheels can be arranged in different configurations known as pyramidal, skew, and tetrahedral 15 , 16 , the pyramidal configuration has attracted more attention and been investigated comprehensively. In this regard, the tilt-angle of RWs in pyramidal configuration has been optimized to achieve minimum power consumption 17 , highest pointing accuracy 18 , highest momentum management performance 19 , and the widest angular-momentum envelope coverage 20 .…”

Section: Introductionmentioning

confidence: 99%

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Nonlinear adaptive pose motion control of a servicer spacecraft in approximation with an accelerated tumbling target

Kasiri,

Fani Saberi

2024

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Removing a limited number of large debris can significantly reduce space debris risks. These bodies are generally exposed to extreme environmental disturbance torques or consecutive accidents due to their large wet area, which causes them to experience accelerated high-rate tumbling motion. The existing literature has adequately explored the approximation operations with non-cooperative targets exhibiting 3-axis tumbling motion. However, the research gap lies in the lack of attention given to addressing this approximation for targets undergoing accelerated motion. Agile, accurate, and large-angle maneuvers are three common necessities for safely capturing such targets. Changes in the moment of inertia brought on by fuel slushing cannot be disregarded during such a maneuver. To deal with nonlinearities, adverse coupling effects, actuator saturation constraints, time-varying moment of inertia, and external disturbances that worsen during accelerated agile large-angle maneuvers, a novel adaptive control approach is developed in this paper. The controller's main advantage is its adjustable desired acceleration, which maintains its performance even when dealing with accelerated motion. The control law is directly synthesized from the nonlinear relative equations of motion, without any linearization or simplification of the system dynamics, making it robust to a variety of orbital elements and target behaviors. Adaptation laws are extracted from the Lyapunov stability theorem in a way that guarantees asymptotic stability. Moreover, control actuator roles (delay, saturation, and allocation) are accounted for in modeling and simulation. Finally, a comprehensive numerical simulation based on three different realistic and strict scenarios is carried out to demonstrate the effectiveness and performance of the proposed control approach. The controller's robustness against time-varying dynamic parameters (sharp and sudden change, smooth and slow change, and periodic change) is extensively demonstrated through simulation.

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Section: Mathematical Modelingmentioning

confidence: 99%