A micro-fabricated colloidal thruster array

Paine, Mark D.; Gabriel, S.B.

doi:10.2514/6.2001-3329

Cited by 22 publications

(16 citation statements)

References 4 publications

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“…The results were documented in two M.S. Theses, by M. Paine [12] and L.F. Velasquez [13, respectivley. The concept proposed by Paine involved micro-capillary channels oriented perpendicular to the face of a silicon wafer.…”

Section: Ir-a %V-hired (From -mentioning

confidence: 80%

Colloid Thrusters, Physics, Fabrication and Performance

Martı́nez-Sánchez¹,

Akinwande²

2005

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'ublic reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing in. tata needed, and completing and reviewing this collection of information. Send comments regarding this burden estimate or any other . SUPPLEMENTARY NOTES ABSTRACTThis document summarizes the results of 3 and 1/2 years of work by our team on the basic physics and technology required for the development of Colloid Thrusters (also called more recently Electrospray Thrusters). The research covered the basic physics of operation in the mixed ion-droplet mode, later extended to the newly discovered pure ionic mode, the microfabrication in Silicon of two types of arrays of colloid or electrospray emitters, and the development of a quantitative theory for the colloidal regime (no ions). This Executive Summary describes briefly the various achievements, with reference to our interim Reports and to our publications. Special emphasis is placed on the results that were obtained during the one-year extension (2004), which were not covered in our interim reports. The Theses, published papers and Conference papers for 2004 are enclosed in a companion CD disk; earlier Theses and publications were similarly attached to previous Reports. SUBJECT

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Section: Ir-a %V-hired (From -mentioning

confidence: 80%

Colloid Thrusters, Physics, Fabrication and Performance

Martı́nez-Sánchez¹,

Akinwande²

2005

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“…Following research in micro-ion-propulsion systems for attitude control 2 and the miniaturization of ground-based mobile communications, it is known that the satellite power requirement does not reduce linearly with mass. Many small satellite missions simply use body-mounted photovoltaic cells, severely restricting the total available power (because of the small surface area of the satellite).…”

Section: A Mmentioning

confidence: 99%

“…= constant for tape-spring dynamic solution a = width of undeformed tape spring B m = constant for tape-spring dynamic solution C m = constant for tape-spring dynamic solution D = flexural rigidity E = Young's modulus G = shear modulus I array = inertia of unfolding array I y = inertia of tape spring around y axis J = St. Venant torsional constant L = total tape-spring length l 1 , l 2 = array lengths defined from L and µ l s2 = length of tape-spring segment 2 ( = initial longitudinal and transverse radii of curvature, respectively T = torsional moment of tape sprinḡ T = nondimensional torsional moment t = time from deployment release t ts = thickness of the tape spring α = angle subtended by cross-section of spring β = angle of plane (which contains the tape spring) from the horizontal plane γ = total twist angle γ 2 = twist of tape spring segment 2 ( T HE total satellite mass has always been a key parameter in satellite design, and with advances in microtechnology 1 there is an increasing interest in the space industry to develop very lowmass satellites for a wide variety of applications. Following research in micro-ion-propulsion systems for attitude control 2 and the miniaturization of ground-based mobile communications, it is known that the satellite power requirement does not reduce linearly with mass.…”

Section: A Mmentioning

confidence: 99%

Study of the Dynamics of Three Dimensional Tape Spring Folds

Walker

Aglietti

2004

AIAA Journal

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One of the most significant drivers in satellite design is the minimization of mass to reduce the large costs involved in the launch. With technological advances across many fields, it is now widely known that very low-mass satellites can perform a wide variety of missions. However, the satellite power requirement does not reduce linearly with mass, creating the need for efficient and reliable small satellite deployable structures. One possible structural solution for this application is tape springs. Tape springs have been previously studied in many countries for space applications focusing on two-dimensional systems. This work studies the possible impact of using tape springs folded in three dimensions. By first analytically determining the static moments created, simple deployment models can be constructed for tape springs in free space. Then, determining the impact of these moments about an array fold line allows the creation of a dynamic model of an array that is directly comparable to the two-dimensional system. The impact of the three-dimensional fold can then be determined.

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“…Over recent decades there has been growing research and development in the miniaturization of electronic and mechanical technologies [1]. It is now possible to construct very small satellites [2], thereby dramatically reducing the cost of access to space.…”

Section: Introductionmentioning

confidence: 99%

A study of tape spring fold curvature for space deployable structures

Walker

Aglietti

2007

Proceedings of the Institution of Mechanical Engineers, Part G:

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Tape springs, defined as thin metallic strips with an initially curved cross-section, are an attractive structural solution and hinge mechanism for small satellite deployable structures because of their low mass, low cost, and general simplicity. They have previously been used to deploy booms and array panels in various configurations that incorporate a two-dimensional deployment of the tape. However, applications currently exist that incorporate three-dimensional tape springs folds. To accurately model the deployment of an appendage mounted with tape spring hinges, it is necessary to accurately model the opening moments produced from the material strains in the tape spring fold. These moments are primarily a function of curvature. This publication uses a photographic method to analyse the curvature assumptions of twodimensional tape spring folds and to define the curvature trends for three-dimensional tape spring folds as a basis for calculating the opening moment. It is found that although a variation in the curvature can be seen for three-dimensional tape spring folds, its effect is secondary to the tape thickness tolerance. Therefore, constant curvature models are concluded to be accurate enough for general tape fold applications.

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A micro-fabricated colloidal thruster array

Cited by 22 publications

References 4 publications

Colloid Thrusters, Physics, Fabrication and Performance

Colloid Thrusters, Physics, Fabrication and Performance

Study of the Dynamics of Three Dimensional Tape Spring Folds

A study of tape spring fold curvature for space deployable structures

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