Digital micropropulsion

Lewis, David H.; Janson, Siegfried; Cohen, Randolph B.; Antonsson, Erik K.

doi:10.1016/s0924-4247(99)00260-5

Cited by 205 publications

(88 citation statements)

References 3 publications

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“…We think that this size is marginal, although further miniaturization is expected. Previous studies 2,3) only confirmed the preliminary concept of the thruster. In this paper, we propose a novel structure with electrical feedthroughs to ignition heaters for practical application.…”

Section: Design and Structurementioning

confidence: 93%

“…3). First, the sil- icon substrate is thermally oxidized, and the oxidized layer is patterned using buffered hydrofluoric acid (HF) solution to form mask openings (2). Through the mask openings, the silicon substrate is etched to a depth of 2.5 µm using tetramethyl ammonium hydroxide (TMAH) solution (3).…”

Section: Fabricationmentioning

confidence: 99%

“…4). First, a sputter-deposited chromium (Cr) mask is patterned (2), and the glass substrate is etched to a depth of 30 µm using buffered HF solution (3). After removing a photoresist film on the Cr mask, propellant cylinders with a diameter of 0.8 mm are formed by grinding using a high-speed milling machine (modified F-MACH 442, Toshiba Machine) (4).…”

Section: Fabricationmentioning

confidence: 99%

“…Recently, several kinds of MEMS-based thrusters, such as cold gas jet thrusters, 1) solid propellant rocket thrusters, 2,3) vaporizing liquid thrusters 4,5) and a bi-propellant rocket thruster, 6) are under development. TRW has proposed a solid propellant array thruster, "Digital Micropropulsion Thruster."…”

Section: Introductionmentioning

confidence: 99%

“…TRW has proposed a solid propellant array thruster, "Digital Micropropulsion Thruster." 2) Is is composed of one-shot solid propellant micro-rockets arrayed on a substrate, allowing thrust to be controlled digitally. LAAS-CNRS, CNES and LacroixRuggieri have also developed a similar thruster.…”

Section: Introductionmentioning

confidence: 99%

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MEMS-Based Solid Propellant Rocket Array Thruster with Electrical Feedthroughs.

Tanaka

Hosokawa

Tokudome

et al. 2003

Trans. Japan Soc. Aero. S Sci.

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The prototype of a solid propellant rocket array thruster for simple attitude control of a 10 kg class micro-spacecraft was completed and tested. The prototype has 10 × 10 φ0.8 mm solid propellant micro-rockets arrayed at a pitch of 1.2 mm on a 20×22 mm substrate. To realize such a dense array of micro-rockets, each ignition heater is powered from the backside of the thruster through an electrical feedthrough which passes along a propellant cylinder wall. Boron/potassium nitrate propellant (NAB) is used with/without lead rhodanide/potassium chlorate/nitrocellulose ignition aid (RK). Impulse thrust was measured by a pendulum method in air. Ignition required electric power of at least 3-4 W with RK and 4-6 W without RK. Measured impulse thrusts were from 2 × 10 −5 Ns to 3 × 10 −4 Ns after the calculation of compensation for air dumping.

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Section: Design and Structurementioning

confidence: 93%

Section: Fabricationmentioning

confidence: 99%

Section: Fabricationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

MEMS-Based Solid Propellant Rocket Array Thruster with Electrical Feedthroughs.

Tanaka

Hosokawa

Tokudome

et al. 2003

Trans. Japan Soc. Aero. S Sci.

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Micropropulsion for Space — A Survey of MEMS-based Micro Thrusters and their Solid Propellant Technology

Rossi

2002

Sensors Update

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In the last two decades, advances in microsystems technology have made micro mechanics mature enough to envisage miniaturization in the space industry. The motivation behind this development is the reductions in mass, satellite costs and launch costs in parallel with an increase in the reliability and flexibility of satellites. A cluster of many small satellites, commanded from a mothership, or totally independent, will, without any doubt, reduce the risk of mission failure and increase mission flexibility. This revolution in the space industry will rely on propulsion system development to ensure the maneuvering and fine positioning of micro and nano satellites (defined as satellites with mass between 20-100 kg and under 20 kg, respectively). This paper is provides a stateof-the-art review of micro thruster technologies for space applications. the intention is to overview the different technical solutions under investigation in the micropropulsion field, to assess their merits and disadvantages and to try to identify the promising ones in relation to future missions needs. First, the principles of propulsion and basic concepts and equations useful in describing and comparing propulsion systems are described. Then, a review micropropulsion needs for space is made and the options and technologies available for propulsion are presented. An outline is given of the technological efforts made in miniaturizing propulsion systems through examples from current research programs and the different micropropulsion technologies are compared. After illustrating the assets of microsystem technology in the micropropulsion field by the detailed presentation of one particular micropropulsion option investigated at LAAS-CNRS, namely solid propellant micro thruster arrays, a short discussion is given of the capability of microsystem technology to serve micropropulsion needs.

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