Structural design for deployable optical telescopes

Huybrechts, Steven; Wegner, Peter; Maji, Arup; Kozola, Brian D.; Griffin, Steven; Meink, Troy

doi:10.1109/aero.2000.878448

Cited by 4 publications

(4 citation statements)

References 1 publication

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“…Ultralightweight Telescope (UltraLITE), 115 also called deployable optical telescope (DOT), 116 is a deployable TMA telescope developed mainly by the Air Force Research Laboratories. This proposed design spawned a series of structure experiments to validate several elements of its architecture.…”

Section: Ultralitementioning

confidence: 99%

“…46 This development program focused extensively on active vibration controllers 117 and the design of a very stiff deployment structure through the use of hybrid CFRP, including high and intermediate modulus fibers. 115 Several effective apertures of the telescope were reported throughout the technology development program, with a testbed of 1.7 m being built. 117 More system design options are discussed by Powers et al 118 for a baseline size of 5 to 6 m apertures flying on high altitudes, in the order of 15,000 km.…”

Section: Ultralitementioning

confidence: 99%

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Review on thermal and mechanical challenges in the development of deployable space optics

Villalba

Kuiper

Gill

2020

J. Astron. Telesc. Instrum. Syst.

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Deployable optics promise a revolution in the capability of observing the universe by delivering drastically reduced mass and volume needs for a desired level of performance compared to their conventional counterparts. However, this places new demands on the mechanical and thermal designs of new telescopes, essentially trading mass and volume for structural and control complexity. We compile the thermomechanical challenges that should be taken into consideration when designing optical space systems, as well as summarize 14 projects proposed to address them. Stringent deployment repeatability requirements demand low hysteresis, whereas stability requirements require high stiffness, proper thermal management, and active optics.

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Section: Ultralitementioning

confidence: 99%

Section: Ultralitementioning

confidence: 99%

Review on thermal and mechanical challenges in the development of deployable space optics

Villalba

Kuiper

Gill

2020

J. Astron. Telesc. Instrum. Syst.

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“…However, due to low vibration tolerances, the support structure must be stiff. 66 As a result, small, otherwise unnoticed nonlinearities (called microdynamics) of the structure become large problems. One important nonlinearity called microlurch has been identified and is believed to be caused by a sudden release of strain energy built up due to frictional effects in joints and latches of a structure.…”

Section: Space Telescopesmentioning

confidence: 99%

<title>Survey of state-of-the-art vibration isolation research and technology for space applications</title>

Winthrop¹,

Cobb²

2003

SPIE Proceedings

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A broad survey of the literature detailing the state-of-the-art and future research trends in vibration isolation for current and proposed space systems is presented. Terminology for vibration control is first defined. Next, the vibration isolation problem is discussed taking into account nonlinearities associated with variable parameters. It is followed by a discussion of some current space specific applications, illustrating the tremendous importance of vibration control technology for space and the challenges these applications present. Next, a discussion of vibration control elements is provided. Finally, a summary of semi-active control strategies is presented and conclusions are drawn about the state of the art.

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“…In total, there are 10 actuators (three for each primary mirror and one for the secondary mirror support tower) and 9 sensors (three for each primary mirror). More information on the experiment design, construction, and control can be found in [1,4,5,7,[13][14][15]. The Large Deployable Optics team has focused on collecting input-output data in the time and frequency domain for system identification.…”

Section: Experiments Description and Approachmentioning

confidence: 99%

System identification of space structures

Lacy

Babuška²,

Schrader³

et al.

Proceedings of the 2005, American Control Conference, 2005.

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Large precision spacecraft present a challenging control problem. They are modally dense, have a very large frequency bandwidth over which disturbances can affect payload performance, and are lightly damped. The performance of passive vibration isolation systems will be limited by the constraints of physics and mechanical components, particularly at low frequencies. This motivates the need for an active isolation system. High fidelity system models are required to obtain the high performance control. Developing these high fidelity system models of large space structures is a challenge for experiments, algorithms, and computational resources.

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Structural design for deployable optical telescopes

Cited by 4 publications

References 1 publication

Review on thermal and mechanical challenges in the development of deployable space optics

Review on thermal and mechanical challenges in the development of deployable space optics

<title>Survey of state-of-the-art vibration isolation research and technology for space applications</title>

System identification of space structures

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