Dynamic modeling and multi-stage integrated control method of ultra-quiet spacecraft

Tang, Liang; Zhang, Kebei; Guan, Xinping; Hao, Renjian; Wang, Youyi

doi:10.1016/j.asr.2019.09.001

Cited by 13 publications

(6 citation statements)

References 20 publications

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“…Moreover, some WD binaries with high accretion rates can be detected by the CSST [ 4 ], which is of great interest to scientists. Because of this, the CSST places a great deal of demands on the installation environment, and even minor disturbance forces from vibration sources might have an impact on its operation [ 5 , 6 ]. This requires ground-based measurements of the disturbance forces generated by the sources and the use of the data to assess the effects of these forces on the telescope in the real environment.…”

Section: Introductionmentioning

confidence: 99%

Prediction Technique and Measuring Device for Coupled Disturbance Forces from Large Equipment in the Spacecraft

Zhou,

Xu,

Xia

2024

Sensors

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To guarantee the accuracy of sophisticated equipment in spacecraft, it is essential to evaluate the dynamic forces of vibration sources. In contrast to conventional rigid-based measuring approaches, a method for predicting the interference of dynamic forces from large sources on spacecraft considering vibration coupling is proposed. In addition, a flexible-based dynamic force measuring platform capable of withstanding large masses and mounting large-volume vibration sources is designed. After that, the experiments for calibrating the platform and acquiring unknown terms in the derived theoretical models are detailed. The principle prototype is then manufactured for feasibility verification. It is demonstrated that despite the low fundamental frequency of the measuring platform of 242.8 Hz, the measurement error of the flexible measuring platform is less than 8% when the coupling is taken into account, which is 29% lower than that without coupling. Additionally, the prediction error of disturbance forces is within 17%. As a result, the accuracy of the proposed dynamic force measurement and prediction of large vibration sources considering coupling is substantially improved, providing a good reference for aerospace applications.

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Section: Introductionmentioning

confidence: 99%

Prediction Technique and Measuring Device for Coupled Disturbance Forces from Large Equipment in the Spacecraft

Zhou,

Xu,

Xia

2024

Sensors

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“…Thus, an accurate dynamic model is needed for predicting microvibration disturbance. In addition, accurate disturbance data from vibration sources should be collected to investigate the characteristics of microvibrations (Tang et al 2020). The main sources of microvibrations in space optical telescopes include the inertial gyroscopes, momentum wheels, cry coolers, and camera shutters (Liu et al 2015).…”

Section: Introductionmentioning

confidence: 99%

Micro-vibration Modeling and Verification of Shutter Mechanism of Survey Space Telescope

姜¹,

文²,

詹³

et al. 2023

Res. Astron. Astrophys.

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The scientific research mission of the Survey Space Telescope (also known as the China Space Station Telescope, CSST) imposes rigorous requirements on the observation precision. However, micro-vibrations generated by the shutter mechanism can seriously affect the performance of the highly-precise and sensitive instruments onboard. This study presents a dynamic model and verifies its performance using experimental results. Indeed, a five-degree-of-freedom nonlinear dynamic model that considers all interference sources and bearing nonlinearity is established. The validity of the proposed model is verified using experimental measurements of the micro-vibration characteristics. The obtained results proved that the proposed dynamic model can accurately predict the characteristics of the micro-vibrations caused by the shutter mechanism in the design stage and provide a theoretical basis for the development of CSST.

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“…Once disturbed, it takes a long time for the solar array to sufficiently attenuate the vibration in free response (Fujii and Suda, 2002; Kalaycioglu and Silva, 2000; Na et al , 2014). The long-time vibration with large amplitude and low frequency makes it challenging to maintain the attitude precision and stability of the satellite (Mao et al , 2019; Zhang et al , 2020; Tang et al , 2020; Angeletti et al , 2021). Therefore, the control approaches for attenuating vibration of the solar array are urgently needed.…”

Section: Introductionmentioning

confidence: 99%

Bending and torsional vibration attenuation of multi-panel deployable solar array using reaction wheel actuators

Wang

Chen²

2022

AEAT

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Purpose This paper aims to present a multi-axis actuating approach to attenuate the bending and torsional vibration of the solar array through the reaction wheel (RW) actuators. Design/methodology/approach The motion equation of the solar array with the RW actuators is derived in modal coordinates for controller design. The reaction torques, induced by the speed change of the RW actuators, are controlled for vibration attenuation through the constraints on the actuators’ rotating speed. The proposed control approach is firstly verified with numerical simulation on the finite element model of a full-scale solar array. Experimental study of a simplified elastic plate model is subsequently performed for feasibility and validity investigation. Findings Both the numerical and experimental studies demonstrated the success of adopting RW as the actuator. Results from numerical simulation reveal that the vibration response peak can be reduced by 80% with 2% of mass increase by using the RW actuators. Practical implications It is demonstrated that the multi-axis actuating method using RW actuators has a great potential in vibration attenuation of the multi-panel deployable solar array. Originality/value An approach to reduce bending and torsional vibration of solar array based on RW actuators is investigated. Theoretical analysis, numerical simulation and experimental study are conducted to demonstrate the validity of the proposed vibration attenuation approach and its potential application in the spacecraft design.

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Dynamic modeling and multi-stage integrated control method of ultra-quiet spacecraft

Cited by 13 publications

References 20 publications

Prediction Technique and Measuring Device for Coupled Disturbance Forces from Large Equipment in the Spacecraft

Prediction Technique and Measuring Device for Coupled Disturbance Forces from Large Equipment in the Spacecraft

Micro-vibration Modeling and Verification of Shutter Mechanism of Survey Space Telescope

Bending and torsional vibration attenuation of multi-panel deployable solar array using reaction wheel actuators

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