Spacecraft attitude jet control method and system based on delta-sigma modulator

By using a dual-loop attitude control system based on a Δ-Σ modulator, the relative thrust command of the nozzle is modulated into a nozzle switching command with an adjustable duty cycle using a proportional-integral controller and a Δ-Σ modulator. This solves the problem of continuous control of the spacecraft's attitude angle and angular rate, improves attitude control accuracy, and reduces the number of jet ejections.

CN115817854BActive Publication Date: 2026-02-13BEIJING ZHONGKE AEROSPACE TECH CO LTD
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Patent Information

Application Number
CN202211345733.X
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2022-10-31
Publication Date
2026-02-13
Estimated Expiration
2042-10-31

AI Technical Summary

Technical Problem

Existing technologies, while avoiding an increase in the number of times the nozzle ejects air, make it difficult to achieve continuous control of the spacecraft's attitude angle and angular rate, and it is also difficult to improve the accuracy of attitude control.

Method used

A dual-loop attitude control system based on a Δ-Σ modulator is adopted. The attitude angle and attitude angular rate of the spacecraft are fed back through the outer loop and the inner loop respectively. The relative thrust command is generated by the proportional-integral controller and modulated into the nozzle switching command with adjustable duty cycle by the Δ-Σ modulator. Finally, it is converted into the solenoid valve on/off signal to control the nozzle jet.

Benefits of technology

It achieves continuous control of the spacecraft's attitude angle and angular rate without increasing the number of times the nozzle ejects air, thus improving attitude control accuracy and reducing the number of times the nozzle ejects air and the consumption of propellant.

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Abstract

The application provides a spacecraft attitude jet control method and system based on a delta-sigma modulator, which comprises the following steps: collecting the attitude angle and the attitude angular rate of a spacecraft, and feeding back the attitude angle and the attitude angular rate to an outer loop and an inner loop, respectively; in the outer loop, calculating an angular rate command according to the feedback attitude angle and an attitude angle command input into the outer loop, and inputting the angular rate command into the inner loop; in the inner loop, obtaining an angular rate deviation signal according to the angular rate command and the feedback attitude angular rate; in the inner loop, converting the angular rate deviation signal into a jet pipe relative thrust command, modulating the jet pipe relative thrust command into a jet pipe switch command with adjustable duty ratio, and converting the jet pipe switch command into an electromagnetic valve on-off signal of the jet pipe; and controlling the forward jet pipe and the reverse jet pipe to perform jet actions according to the electromagnetic valve on-off signal. The application realizes continuous control of the spacecraft attitude angle and the angular rate and improves the control precision of the spacecraft attitude under the premise of avoiding an increase in the number of jet pipe jet actions.
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