Dual stage passive vibration isolation for optical interferometer missions

Bronowicki, Allen J.; MacDonald, Rhonda; Gürsel, Yekta; Goullioud, Renaud; Neville, Timothy; Platus, David L.

doi:10.1117/12.460731

Cited by 20 publications

(17 citation statements)

References 6 publications

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“…It is noted that real micro-vibration sources produce disturbances in all six degrees of freedom whereas the proposed isolator counteracts a disturbance only along a single degree of freedom (since the strut's two degrees of freedom are collinear). However, the evaluation of the damper performance of a single strut allows it to be compared with other damping solutions [1,31]. EMSDs provide a damping force due to the combination of two different physics phenomena that are described by the Faraday-Lenz law and the Lorentz force law (see [31] for more details).…”

Section: Analytical Modelmentioning

confidence: 99%

“…The reaction wheel used for this test belongs to the 10SP series made by Surrey Satellite Technology Ltd (this reaction wheel was chosen in place of the one from the 100SP series due to availability issues at the time of the tests). The 10SP reaction wheel has a mass of approximately 1 kg and in order to compensate for the increased mass one of the with the TF of a 1-DoF system with EMSD [31] and the one of a passive isolator that uses viscoelastic materials [1]. In particular, the 2-collinear-DoF system is capable of Figure 13: Experimental results for the test with the reaction wheel.…”

Section: Broadband Signal With Reaction Wheelmentioning

confidence: 99%

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A 2-collinear-DoF strut with embedded negative-resistance electromagnetic shunt dampers for spacecraft micro-vibration

Stabile

Aglietti

Richardson

et al. 2017

Smart Mater. Struct.

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Micro-vibration on board a spacecraft is an important issue that affects payloads requiring high pointing accuracy. Although isolators have been extensively studied and implemented to tackle this issue, their application is far from being ideal due to the several drawbacks that they present, such as limited low-frequency attenuation for passive systems or high power consumption and reliability issues for active systems. In the present study, a novel 2-collinear-DoF strut with embedded Electromagnetic Shunt Dampers (EMSD) is modelled, analysed and the concept is physically tested. The combination of high-inductance components and negative-resistance circuits is used in the two shunt circuits to improve the EMSD micro-vibration mitigation and to achieve an overall strut damping performance that is characterised by the elimination of the resonance peaks and a remarkable FRF final decay rate of −80 dB/dec. The EMSD operates without requiring any control algorithm and can be comfortably integrated on a satellite due to the low power required, the simplified electronics and the small mass. This work demonstrates, both analytically and experimentally, that the proposed 2-collinear-DoF strut with embedded EMSD 2 strut is capable of producing better isolation performance than other well-established damping solutions over the whole temperature range of interest.

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Section: Analytical Modelmentioning

confidence: 99%

Section: Broadband Signal With Reaction Wheelmentioning

confidence: 99%

A 2-collinear-DoF strut with embedded negative-resistance electromagnetic shunt dampers for spacecraft micro-vibration

Stabile

Aglietti

Richardson

et al. 2017

Smart Mater. Struct.

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show abstract

“…This paper will focus on results achieved with the phase 1 setup. Bronowicki et al 5 describes initial dynamics testing of the Phase 2 structure. Phase 1 is a simpler version of the STB3 phase 2 with the following differences: -Test-article mounted on top of a rigid table (instead of the flight-like structure).…”

Section: Introductionmentioning

confidence: 99%

Dim star fringe stabilization demonstration using pathlength feed-forward on the SIM testbed 3 (STB3)

2003

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Future space-based optical interferometers such as the Space Interferometer Mission require fringe stabilization to the level of nanometers in order to produce astrometric data at the micro-arc-second level. Even the best attitude control system available to date will not be able to stabilize the attitude of a several thousand pound spacecraft to a few milli-arc-seconds. Active pathlength control is usually implemented to compensate for attitude drift of the spacecraft. This issue has been addressed in previous experiments while tracking bright stars. In the case of dim stars, as the sensor bandwidth falls below one hertz, feedback control will not provide sufficient rejection. However, stabilization of the fringes from a dim-star down to the nanometer level can be done open loop using information from additional interferometers looking at bright guide stars.The STB3 testbed developed at the Jet Propulsion Laboratory features three optical interferometers sharing a common baseline, dynamically representative to the SIM interferometer. An artificial star feeding the interferometers is installed on a separate optics bench. Voice coils are used to simulate the attitude motion of the spacecraft by moving the entire bench. Data measured on STB3 show that fringe motion of a dim star due to spacecraft attitude changes can be attenuated by 80 dB at 0.1Hz without feedback control, using only information from two guide stars. This paper describes the STB3 setup, the pathlength feed-forward architecture, implementation issues and data collected with the system.

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“…There are two ways to counter this trend. The first is to employ dual-stage passive isolation as is planned for the Space Interferometer Mission (SIM) [5]. Neither isolator frequency needs to be quite as low, since the isoation effect from the two is multiplicative.…”

Section: Introductionmentioning

confidence: 99%

A layered vibration control strategy for space telescopes

Bronowicki

2003

SPIE Proceedings

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An approach for achieving a several order of magnitude reduction of vibration in space telescopes is described. The building blocks encompass: active damping in the payload, passive and active vibration isolation in the payload mount, and active steering of the entire payload using feedback from optical sensors to the actuators in the isolator. The layers of control sequentially mitigate vibrations emanating from the disturbance source.This strategy is especially applicable to large space-based optical systems, such as deployable telescopes. A dynamically scaled test bed has been developed to demonstrate this. The test bed incorporates a full-telescope isolator based on passive isolation technology demonstrated on the Chandra X-ray Observatory. A PZT force sensor and a voice coil actuator have been incorporated to provide additional active isolation at low to mid frequencies. The active isolation is implemented in a stable manner using independent modal space control (IMSC). Residual vibrations in the telescope secondary mirror supports are damped using PZT actuator/sensor patches and local analog feedback. Finally, signals from line-of-sight sensors in the two tilt directions are fed to the tilt states in the IMSC controller to effect payload pointing control.

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Dual stage passive vibration isolation for optical interferometer missions

Cited by 20 publications

References 6 publications

A 2-collinear-DoF strut with embedded negative-resistance electromagnetic shunt dampers for spacecraft micro-vibration

A 2-collinear-DoF strut with embedded negative-resistance electromagnetic shunt dampers for spacecraft micro-vibration

Dim star fringe stabilization demonstration using pathlength feed-forward on the SIM testbed 3 (STB3)

A layered vibration control strategy for space telescopes

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