Modeling and collision avoidance control for the Disturbance-Free Payload spacecraft

Hongjie, Yang; Liu, Lei; Yun, Hai; Xin-guo, LI

doi:10.1016/j.actaastro.2019.07.025

Cited by 14 publications

(6 citation statements)

References 20 publications

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“…Our research group has previously conducted flow calibration on the differential pressure system [25]. The pressure calibration was carried out in the pressure range of 2600-80500 Pa, with the results shown in figure 5 [26,27]. The calibration results indicate that the smaller the pressure difference, the smaller the difference between the theoretical flow rate and the actual flow rate, which remains below 10%.…”

Section: Ac High-voltage Power Supply Systemmentioning

confidence: 99%

Experimental investigation of the polarity-switching process with different bipolar ionic liquid thruster operating frequencies

WU 吴,

YANG 杨,

LUO 罗

et al. 2024

Plasma Sci. Technol.

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The bipolar ionic liquid thruster employ ionic liquid as propellant to discharge positively and negatively charged high-energy particles under an alternating current(AC) power source, effectively suppressing electrochemical reaction and ensuring charge neutrality. Determining an optimal AC supply power source frequency is critical for sustained stable thruster operation. This study focuses on the emission characteristics of the ionic liquid thruster under varied AC conditions. The AC power supply was set within the frequency range of 0.5 to 64 Hz, with eight specific frequency conditions selected experimentation. The experimental results indicate that the thruster operate steadily within a voltage range of ±1470 to ±1920 V, with corresponding positive polarity current ranging from 0.41 to 4.91 μA and negative polarity current ranging from -0.49 to -4.10 μA. During voltage polarity switching, an emission delay occurs, manifested as a prominent peak signal caused by circuit capacitance characteristics and a minor peak signal resulting from liquid droplets. Extended emission test were conducted at 16 Hz demonstrating approximately 1 hour and 50 minutes of consistent emission before intermittent discharge. These findings underscore the favorable impact of alternating current conditions within the 8 to 16 Hz range on the self-neutralization capability of the ionic liquid thruster.

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Section: Ac High-voltage Power Supply Systemmentioning

confidence: 99%

Experimental investigation of the polarity-switching process with different bipolar ionic liquid thruster operating frequencies

WU 吴,

YANG 杨,

LUO 罗

et al. 2024

Plasma Sci. Technol.

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“…At present, the main method for attenuating the disturbances caused by flexible cables is to establish a disturbance model and conduct feedforward compensation. The equating of the flexible cables connection between the two modules into a spring system is an accepted modeling method [9], and the equivalent stiffness matrix can be obtained through experiments [10]. However, due to the difficulty in measuring the rotational motion of the flexible cables, only the stiffness associated with linear motion can be obtained, resulting in the equivalent spring model not being able to reflect the rotational dynamics of the flexible cables.…”

Section: Introductionmentioning

confidence: 99%

Disturbance Attenuation and Pointing Control System Design for an Improved Disturbance-Free Payload Spacecraft

et al. 2023

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The low-frequency disturbances transmitted by flexible cables are difficult to be attenuated for a novel disturbance-free payload spacecraft, which decreases the payload’s pointing accuracy and stability. In this research, a new spacecraft configuration with a high-precision inertial reference unit composed of capacitive sensors and a spherical test mass is proposed. The disturbance attenuation and pointing control system is subdivided into four interconnected control loops. The payload can be isolated from disturbances in the all-frequency band by the active vibration isolation control loop and the drag-free control loops, and its high-precision pointing requirement can be satisfied with the attitude pointing control loop and the attitude tracking control loop. An integrated control strategy is proposed, and the control system is decoupled into 12 single-input single-output control loops by pre-compensating, which lays the foundation for feedback design. Through the amplitude-frequency response analysis, the control bandwidth is designed according to the Proportional-Integral-Differentive control algorithm. The numerical simulations show that the disturbance attenuation performance is better than −20 dB in the all-frequency band, and the pointing accuracy and the pointing stability are better than 10−6 deg and 10−7 deg/s, respectively. The new spacecraft configuration and the disturbance attenuation and pointing control system provide a general technical solution for payloads with high-precision and high-stability requirements.

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“…By taking the advantages of the noncontact Lorentz actuator, the advanced control algorithms, such as twistor-based synchronous sliding model control, and model predictive control, have been proposed to guarantee a good performance of the stability control. The development of the noncontact closeproximity formation satellite has been greatly promoted through the above-mentioned researches [19][20][21][22][23][24]. Also, due to the advantage of the noncontact close-proximity formation satellite, the payload module can be considered the conventional satellite and there are many related researches on controller design [25,26].…”

Section: Introductionmentioning

confidence: 99%

“…(1) Compared with the previous researches on the noncontact close-proximity formation satellite in [19][20][21][22][23][24], this paper extends its advantage into the attitude maneuver operation by using compound control strategy…”

Section: Introductionmentioning

confidence: 99%

Compound Attitude Maneuver and Collision Avoiding Control for a Novel Noncontact Close-Proximity Formation Satellite Architecture

Liao

Xie²,

Zhou³

et al. 2022

International Journal of Aerospace Engineering

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In order to achieve the attitude maneuver performance of the noncontact close-proximity formation satellite architecture, this paper presents a compound control strategy with variable-parameter sliding mode control and disturbance observer-based feedforward compensation. Firstly, the variable-parameter sliding mode control is proposed to guarantee the attitude maneuver performance of the payload module. Secondly, the collision avoiding control with disturbance observer-based feedforward compensation is proposed to guarantee the synchronization of the two separated modules within the small air clearance constraint of the noncontact Lorentz actuator. Finally, a physical air-floating platform is established to verify the effectiveness of the proposed approach.

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Modeling and collision avoidance control for the Disturbance-Free Payload spacecraft

Cited by 14 publications

References 20 publications

Experimental investigation of the polarity-switching process with different bipolar ionic liquid thruster operating frequencies

Experimental investigation of the polarity-switching process with different bipolar ionic liquid thruster operating frequencies

Disturbance Attenuation and Pointing Control System Design for an Improved Disturbance-Free Payload Spacecraft

Compound Attitude Maneuver and Collision Avoiding Control for a Novel Noncontact Close-Proximity Formation Satellite Architecture

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