Quaternion versus Rotation Matrix Feedback for Spacecraft Attitude Stabilization Using Magnetorquers

Celani, Fabio

doi:10.3390/aerospace9010024

Cited by 3 publications

(1 citation statement)

References 20 publications

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“…Furthermore, quaternion‐based attitude systems may cause an undesired behaviour known as the unwinding phenomenon because one of the two quaternions that stand for the desired attitude is unstable. Consequently, if the feedback quaternion becomes very close to the unstable one during the attitude evolution, the multirotor attitude pushes away from it rather than converging to the desired attitude [33, 34]. Compared with Refs.…”

Section: Stability Analysismentioning

confidence: 99%

Robust optimal attitude control for hexarotors with disturbances, uncertainties, and delays

Abdollahi

Salehfard

2022

IET Cyber-Phy Sys Theory & Ap

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A robust optimal attitude controller for hexarotor helicopters is proposed. Compared to the previous research studies on hexarotors, the current study takes account of the influences of non‐linear and coupling dynamics, structured and unstructured uncertainties, external time‐varying disturbances, and input time delays. A linear time‐invariant system is derived for each Euler angle by considering the actual rotational dynamic model as a nominal non‐linear system plus an equivalent perturbation, including non‐linear and coupling dynamics, uncertainties, disturbances, and time delays. Using this approach, a Linear Quadratic Regulation controller is first designed for the nominal linear system of each angle to accomplish the desired tracking performances. Then, a robust compensator based on the robust compensation method is proposed to counteract the effects of the equivalent perturbation on the system. Moreover, the robust attitude tracking property and uniform asymptotical stability of the closed‐loop hexarotor system are proved using Lyapunov stability theory. Several simulations have been performed to demonstrate the effectiveness and robustness of the proposed controller. Finally, experimental results are provided to confirm the robust performance of the proposed controller.

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Section: Stability Analysismentioning

confidence: 99%

Robust optimal attitude control for hexarotors with disturbances, uncertainties, and delays

Abdollahi

Salehfard

2022

IET Cyber-Phy Sys Theory & Ap

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Contactless attitude control of an uncooperative satellite by laser ablation

et al. 2022

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Power Saving in Magnetorquers by Operating in Cryogenic Environments

et al. 2023

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Satellites with cryogenic instrumentation have great potential for military, commercial, and scientific space missions due to the increased sensitivity of their sensors, even for Low Earth Orbit (LEO) missions. For these missions, magnetorquers are a common electromagnetic actuation solution for controlling the attitude and orientation of the satellite. As for any other component of a satellite, the optimization of power consumption and weight is always beneficial for the design. In this work, we propose a novel idea to reduce power consumption during magnetorquer operation: installing the magnetorquer in the cryogenic area of the satellite, instead of installing an actuator in the hot area. As the electric resistivity of the wire is greatly reduced, power consumption is also reduced. However, the heat generated in the magnetorquer, even if lower, must still be dissipated by the cryocooling system, which has an additional energetic cost. The cryogenic temperature range where this effect is beneficial, and the amount of power saved, was determined as a function of different cryocooler technologies’ efficiency and the purity of the copper wire material. It is analytically demonstrated that the operation of the magnetorquer in a temperature range from 10 to 40 K could save energy with respect to operation at 300 K if the copper wires have a residual resistance ratio larger than 200 RRR. A prototype magnetorquer suitable for cryogenic temperatures was manufactured and tested at liquid nitrogen temperature, 77 K, to experimentally demonstrate the variation in the energy consumption. The magnetorquer comprised an iron core with copper wire winding that achieved 1.42 Am2 by applying 0.565 W at 0.5 A. When operating submerged in liquid nitrogen at a temperature of 77 K, the power used by the magnetorquer was reduced by eight times due to the change in electrical resistivity.

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Quaternion versus Rotation Matrix Feedback for Spacecraft Attitude Stabilization Using Magnetorquers

Cited by 3 publications

References 20 publications

Robust optimal attitude control for hexarotors with disturbances, uncertainties, and delays

Robust optimal attitude control for hexarotors with disturbances, uncertainties, and delays

Contactless attitude control of an uncooperative satellite by laser ablation

Power Saving in Magnetorquers by Operating in Cryogenic Environments

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