Long-distance, drag-free, low-thrust, low-Earth-orbit formation control

Canuto, Enrico; Massotti, Luca; Molano-Jimenez, Andres; Perez, Carlos

doi:10.3182/20100906-5-jp-2022.00051

Cited by 3 publications

(5 citation statements)

References 9 publications

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“…Lemma 1 shows (3) is unstable. Formation state predictor and control are designed and implemented around a discrete-time version of (3) as in Canuto, 2010b, where the wide-band noise vectors , a d w w become discrete-time white noise with bounded variance, and the time unit T is designed such that 1 T ω << .…”

Section: Formation Dynamics and Perturbationsmentioning

confidence: 99%

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Formation control for the next generation Earth-gravimetry missions

Canuto

Molano-Jimenez

Montenegro

et al. 2011

IFAC Proceedings Volumes

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The formation control of a long-distance, drag-free, low-thrust, low-Earth orbit satellite is outlined, in view of future Earth-gravity monitoring missions employing long baseline interferometry (> 10 km) and lasting at least six years. To this purpose, a formation consisting of two drag-free satellites, orbiting at a fixed distance in a sun-synchronous orbit, has been proposed as a baseline. Formation fluctuations are bounded by a box 500x50x50 m. Although at first sight not demanding, the formation control induces non-gravitational accelerations, that are obliged to respect tight drag-free requirements, and are constrained by millinewton thrust bounds. In addition formation fluctuations due to tide forces should not be impaired as their measurement is the mission goal. Requirements are formulated as four time and frequency-domain inequalities, to be suitably parameterized by control gains. Exploiting closeloop Hill's equation properties and asymptotic approximations, explicit design inequalities are obtained leading to a first-trial control design. Simulated runs through a fine spacecraft and low-Earth-orbit simulation dominated by the highly variable thermosphere drag show the first-trial design meets the tight control requirements, and demonstrates mission feasibility.

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Section: Formation Dynamics and Perturbationsmentioning

confidence: 99%

“…Cross-track gains derive from a well-known result, which is stated without proof (see Canuto, 2010b).…”

Section: 4mentioning

confidence: 99%

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Formation control for the next generation Earth-gravimetry missions

Canuto

Molano-Jimenez

Montenegro

et al. 2011

IFAC Proceedings Volumes

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“…This control method utilizes external actuation to counteract relative motion deviations between the external and internal spacecraft, thereby achieving compensation for interference from the external spacecraft. Due to its significant developmental potential, scholars have conducted extensive research on the inner-formation system [14][15][16][17][18] and drag-free spacecraft [19][20][21][22][23][24][25][26][27][28][29][30][31][32].…”

Section: Introductionmentioning

confidence: 99%

Event-Triggered Disturbance Estimation and Output Feedback Control Design for Inner-Formation Systems

Hao,

Zhang

2024

Applied Sciences

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This study investigates an event-triggered disturbance estimation approach for the inner-formation system. An extended state observer is designed using an event-based sampling scheme, which offers advantages over traditional estimation methods by reducing information transmission and unnecessary output information exchange while ensuring accurate system estimation performance. Additionally, a method for designing output-feedback control is proposed. The separation of feedback control and event-based observation in the design of output feedback allows us to apply existing optimal control algorithms to the targeted plant without compromising our established event-triggered sampling methods. A numerical simulation is presented, and we demonstrate the effectiveness of our proposed approach for the inner-formation system.

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“…Due to the shared actuators between spacecrafts and test masses, the drag-free and attitude controllers for a spacecraft with internal test masses are designed as an integrated system, commonly referred to as drag-free and attitude control (DFAC) systems. The design details of DFAC systems have garnered significant attention from scholars [32][33][34][35][36][37][38][39][40]. Here are some typical designs: E. Canuto addressed the issue of system model accuracy by establishing noise estimators, constructed a new digital model, and proposed a feasible control system for the GOCE satellite based on EMC theory [32].…”

Section: Introductionmentioning

confidence: 99%

Design and Analysis of the Integrated Drag-Free and Attitude Control System for TianQin Mission: A Preliminary Result

Hao,

Zhang

2024

Aerospace

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This article explores novel in-orbit drag-free technology that can be utilized for deep space detection scientific missions. In this study, we considered a two-test-mass drag-free method and analyzed the design of the drag-free and attitude control system for the TianQin mission. The entire control system was comprehensively designed, including an actuator allocation design and controllers for two test masses and one spacecraft, with a total of 18 degrees of freedom. Furthermore, stability analysis was conducted. Based on our design, numerical analysis and simulations were performed assuming geocentric orbit conditions in the TianQin mission, confirming the feasibility of this aerospace engineering concept. The versatility of the design allows for its application to scientific observations across various disciplines by modifying the structure of the simulation environment, and consequently, the approach discussed in this study holds significant practical implications for effectively accomplishing deep space observation tasks.

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Long-distance, drag-free, low-thrust, low-Earth-orbit formation control

Cited by 3 publications

References 9 publications

Formation control for the next generation Earth-gravimetry missions

Formation control for the next generation Earth-gravimetry missions

Event-Triggered Disturbance Estimation and Output Feedback Control Design for Inner-Formation Systems

Design and Analysis of the Integrated Drag-Free and Attitude Control System for TianQin Mission: A Preliminary Result

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