Integrated modeling activities for the James Webb Space Telescope: optical jitter analysis

Hyde, T. Tupper; Ha, Kong Q.; Johnston, John D.; Howard, Joseph M.; Mosier, Gary E.

doi:10.1117/12.551806

Cited by 31 publications

(17 citation statements)

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“…The James Webb Space Telescope [1], the Solar Observatory Solar-C [2] but also the low-cost end market (e.g. SSTL300-S1 platform [3,4] and Skybox [5]), all carry vibration sensitive instruments on-board (e.g.…”

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confidence: 99%

Dynamic Mass of a Reaction Wheel Including Gyroscopic Effects: An Experimental Approach

2017

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In the recent years, driven by the increasingly stringent stability requirements imposed by some satellites' payloads (e.g. the new generation of optical instruments), the issue of accurate on-board spacecraft microvibration modelling has attracted signicant interest from engineers and scientists. This paper investigates the microvibrationinduced phenomenon on a cantilever congured reaction wheel assembly including sub and higher harmonic amplications due to modal resonances and broadband noise. A mathematical model of the reaction wheel assembly is developed and validated against experimental test results. The model is capable to represent each conguration in which the reaction wheel assembly will operate whether it is hard-mounted on a dynamometric platform or suspended free-free. The outcomes of this analysis are used to establish a novel methodology to retrieve the dynamic mass of the reaction wheel assembly in its operative range of speeds. An alternative measurement procedure has been developed for this purpose, showing to produce good estimates over a wide range of frequency using a less complex test campaign compared to typical dynamic mass setups. Furthermore, the gyroscopic eect inuence in the reaction wheel assembly response is thoroughly examined both analytically and experimentally. Finally, to what extent the noise aects the convergence of the novel approach is investigated.

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confidence: 99%

Dynamic Mass of a Reaction Wheel Including Gyroscopic Effects: An Experimental Approach

2017

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“…They are used to keep parts of the spacecraft within the desired temperature. [7] shows the disturbances generated by these components on the James Webb Space Telescope and their effect on the mission design. Last but not least, Reaction Wheels (RW) have been extensively studied and analysed.…”

Section: Introductionmentioning

confidence: 99%

A semiempirical methodology to characterise a family of microvibration sources

Lellis

Stabile

Aglietti

et al. 2019

Journal of Sound and Vibration

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“…Flywheels commonly used as attitude control execution units in modern high stability and high precision spacecraft [4][5][6]. Due to the rotor dynamic, static unbalance, driving motor error, bearing defects and other factors, the flywheel components will produce complex harmonic disturbance and noise in its normal spinning, which makes the flywheel become one of the main disturbance sources [7][8][9].…”

Section: Introductionmentioning

confidence: 99%

“…[13]. However, there is no systematic reports on the disturbance mechanism of the flywheel components up to now [4,6,9,11,14].…”

Section: Introductionmentioning

confidence: 99%

Flywheel micro-vibration characters of a high resolution optical satellite

Li¹,

Tan²,

Kong³

et al. 2017

J. vibroeng.

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According to the pictures of a sub-meter resolution optical satellite which were acquired on orbit, there is a phenomenon of jitter in the process of taking pictures. As the main attitude control component of the satellite, the flywheel will produce the disturbance in its normal work, which has great influence on the high resolution optical satellite. This paper has respectively researched the flywheel components' disturbance mechanism from four parts, including uneven rotator, rotator friction, bearing disturbance, foundation loose, and builds the mathematical model of disturbance to analyze the characteristics of disturbance. We have simulated and tested the flywheel components' disturbance. The disturbance force of flywheel components is 2 N magnitude and the torque of disturbance is 1.5 N•m magnitude in time domain. The flywheel's infrastructure should be more inflexible especially around 90-100 Hz. For this target high resolution optical satellite, there should be effective damping measures around 48.6 Hz, 190.4 Hz and 285.4 Hz to decrease the flywheel disturbance to guarantee the high precision of the satellite. The result would offer guidance for system optimization design and vibration isolation compensation of the later type of improved satellite or other same type of satellites.

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Integrated modeling activities for the James Webb Space Telescope: optical jitter analysis

Cited by 31 publications

References 0 publications

Dynamic Mass of a Reaction Wheel Including Gyroscopic Effects: An Experimental Approach

Dynamic Mass of a Reaction Wheel Including Gyroscopic Effects: An Experimental Approach

A semiempirical methodology to characterise a family of microvibration sources

Flywheel micro-vibration characters of a high resolution optical satellite

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