Deployment Mechanisms of a Gossamer Satellite Deorbiter

J. M.  Fernandez; Mark Schenk; G.  Prassinos; V. J. Lappas; S. O.  Erb

Deployment Mechanisms of a Gossamer Satellite Deorbiter

J. M. Fernandez, Mark Schenk, G. Prassinos, V. J. Lappas, S. O. Erb

Research output: Contribution to conference › Conference Paper

Abstract

A Gossamer Deorbiter system, comprising a 5×5 m gossamer sail structure and a telescopic deployment system to distance the sail from the host satellite, was tested and qualified to TRL5/6. Two novel deployable boom concepts were developed: lenticular CuBe tape spring booms and bistable CFRP booms. Deployment tests identified the issue of ‘blossoming’ of the coiled booms, resulting in an unpredictable deployment and potential damage to the booms. Modifications to the mechanism design and deployment procedure were introduced to mitigate this issue. The CFRP boom concept was demonstrated to successfully deploy the gossamer sail to its full dimensions, and to be capable of carrying the expected operational loads.

Original language	English
Publication status	Published - 2013
Event	15th European Space Mechanisms and Tribology Symposium 2013 (ESMATS 2013) - Noordwijk, Netherlands Duration: 25 Sept 2013 → 27 Sept 2013

Conference

Conference	15th European Space Mechanisms and Tribology Symposium 2013 (ESMATS 2013)
Country/Territory	Netherlands
City	Noordwijk
Period	25/09/13 → 27/09/13

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title = "Deployment Mechanisms of a Gossamer Satellite Deorbiter",

abstract = "A Gossamer Deorbiter system, comprising a 5×5 m gossamer sail structure and a telescopic deployment system to distance the sail from the host satellite, was tested and qualified to TRL5/6. Two novel deployable boom concepts were developed: lenticular CuBe tape spring booms and bistable CFRP booms. Deployment tests identified the issue of {\textquoteleft}blossoming{\textquoteright} of the coiled booms, resulting in an unpredictable deployment and potential damage to the booms. Modifications to the mechanism design and deployment procedure were introduced to mitigate this issue. The CFRP boom concept was demonstrated to successfully deploy the gossamer sail to its full dimensions, and to be capable of carrying the expected operational loads. ",

author = "Fernandez, {J. M.} and Mark Schenk and G. Prassinos and Lappas, {V. J.} and Erb, {S. O.}",

year = "2013",

language = "English",

note = "15th European Space Mechanisms and Tribology Symposium 2013 (ESMATS 2013) ; Conference date: 25-09-2013 Through 27-09-2013",

}

TY - CONF

T1 - Deployment Mechanisms of a Gossamer Satellite Deorbiter

AU - Fernandez, J. M.

AU - Schenk, Mark

AU - Prassinos, G.

AU - Lappas, V. J.

AU - Erb, S. O.

PY - 2013

Y1 - 2013

N2 - A Gossamer Deorbiter system, comprising a 5×5 m gossamer sail structure and a telescopic deployment system to distance the sail from the host satellite, was tested and qualified to TRL5/6. Two novel deployable boom concepts were developed: lenticular CuBe tape spring booms and bistable CFRP booms. Deployment tests identified the issue of ‘blossoming’ of the coiled booms, resulting in an unpredictable deployment and potential damage to the booms. Modifications to the mechanism design and deployment procedure were introduced to mitigate this issue. The CFRP boom concept was demonstrated to successfully deploy the gossamer sail to its full dimensions, and to be capable of carrying the expected operational loads.

AB - A Gossamer Deorbiter system, comprising a 5×5 m gossamer sail structure and a telescopic deployment system to distance the sail from the host satellite, was tested and qualified to TRL5/6. Two novel deployable boom concepts were developed: lenticular CuBe tape spring booms and bistable CFRP booms. Deployment tests identified the issue of ‘blossoming’ of the coiled booms, resulting in an unpredictable deployment and potential damage to the booms. Modifications to the mechanism design and deployment procedure were introduced to mitigate this issue. The CFRP boom concept was demonstrated to successfully deploy the gossamer sail to its full dimensions, and to be capable of carrying the expected operational loads.

M3 - Conference Paper

T2 - 15th European Space Mechanisms and Tribology Symposium 2013 (ESMATS 2013)

Y2 - 25 September 2013 through 27 September 2013

ER -

Deployment Mechanisms of a Gossamer Satellite Deorbiter

Abstract

Conference

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