Development and Simulation of an Embedded Hydrogen Peroxide Catalyst Chamber in Low‐Temperature Co‐Fired Ceramics

Plumlee, Donald; Steciak, Judi; Moll, Amy

doi:10.1111/j.1744-7402.2007.02161.x

Cited by 21 publications

(16 citation statements)

References 10 publications

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“…Further, the impulse bit from thruster can be controlled by regulating the propellant mass flow rate and/ or duration. One of the common chemicals used in monopropellant-based chemical thruster [7] is hydrogen peroxide (H 2 O 2 ) which is nontoxic, decomposed using various catalyst, and possesses similar physical properties to water. However, it is an unstable compound and readily decomposes into water and oxygen.…”

Section: Introductionmentioning

confidence: 99%

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$\hbox{MnO}_{2}$ Nanowire Embedded Hydrogen Peroxide Monopropellant MEMS Thruster

Kundu

Sinha

Bhattacharyya

et al. 2013

J. Microelectromech. Syst.

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Feasibility of chemically synthesized MnO 2 nanowire catalyst embedded silicon microelectromechanical systems (MEMS) H 2 O 2 monopropellant microthruster has been demonstrated. Due to exothermic reaction process, sustenance of thrust generation does not require any heating of propellant thus minimizing electrical power requirement. The thruster device integrates inlet nozzle, microchannel, MnO 2 nanowire embedded reaction chamber, in-plane exit nozzle and a microheater in the silicon layer. Nozzle configuration and catalyst bed was designed using simple analytical equations to achieve complete decomposition of H 2 O 2 and maximum thrust force by controlling the propellant flow. Simulation of hydrogen peroxide decomposition process was carried out to evaluate the thermo-chemical characteristics. The MnO 2 nanowire has been obtained using a low-cost synthesis process and characterized using field emission scanning electron microscopy, Energy-dispersive X-ray spectroscopy, transmission electron microscopy, and X-ray diffraction studies. Thruster fabrication using micromachining process and its testing have been briefly described. The device is capable to produce 1 mN thrust and specific impulse of 180 s using 50 wt.% concentrated H 2 O 2 of flow rate 1.25 mg/s with total ignition energy of 44 J required for preheating the catalyst bed. Detailed thrust measurement was carried out with propellant mass flow rate for different throat area of exit nozzle, and the results were interpreted with theoretical model.[ 2012-0135]Index Terms-Microelectromechanical systems (MEMS), micropropulsion, microthruster, monopropellant, nanowire, thrust. include biomedical and inertial MEMS transducers, BioMEMS, and microfluidic biochips for clinical diagnostics, medical electronics, and very large scale integration unit processing. He played a key role in the development and growth of teaching and research activities in microelectronics technology, MEMS and biosensors, medical electronics, and thin film processing. He has been actively involved in setting up a state-ofthe-art advanced MEMS design and processing laboratory at IIT Kharagpur. He has authored more than 40 research papers in international journals and conference proceedings. He is the Principal Investigator of several research and consultancy projects in the area of MEMS and microsystems funded by various government and private agencies.

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Section: Introductionmentioning

confidence: 99%

“…Silver, in the form of compressed gauzes, is the preferred catalyst for the decomposition of hydrogen peroxide in a conventional thruster [7], [9]. The gauzes themselves are easy to handle thereby facilitating installation and compression within the chamber.…”

Section: Introductionmentioning

confidence: 99%

$\hbox{MnO}_{2}$ Nanowire Embedded Hydrogen Peroxide Monopropellant MEMS Thruster

Kundu

Sinha

Bhattacharyya

et al. 2013

J. Microelectromech. Syst.

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“…Shin et al 14 developed a micro-scale LTCC reformer that can generate hydrogen-rich gas from a methanol solution for application of proton exchange membrane fuel cell. Plumlee et al 15 have validated that LTCC is suitable for fabricating thrusters using hydrogen peroxide monopropellant. Wu and Yetter 16 successfully developed a planar LTCC electrolytic microthruster with a combustion chamber of 1 mm 3 that used electrolysis to initially decompose hydroxylammonium nitrate-based liquid monopropellants.…”

Section: Introductionmentioning

confidence: 99%

Development of Meso‐Scale Co‐Fired Ceramic Tape Axisymmetric Combustors

Sun

Cai

Donadio

et al. 2011

Int J Applied Ceramic Tech

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Meso-scale combustors for use in small chemical thrusters were fabricated from low temperature co-fired ceramic (LTCC) and high temperature co-fired ceramic (HTCC) tape technology, and operated with gaseous fuels and oxidizers. In contrast to previous research with tape technology where two-dimensional planar geometries have been fabricated, the present combustors were cylindrical axisymmetric. Igniters that consist of metal wires or silver pastes were co-fired with the ceramic bodies. Ignition and combustion phenomena were studied in combustors with different volumes and various fuels (H 2 , CH 4 , C 2 H 2 , and C 2 H 4 ) with either oxygen or air. Various injection methods of the reactants were investigated to determine ignition criteria and flame stability. Reliable and restartable ignition was obtained in combustion chambers ranging from 16 to 104 mm 3 . Sustained and stable combustion longer than 600 s was achieved with hydrogen and oxygen under a wide range of equivalence ratios ranging from 0.1 to 1.0. Chemical composition analyses from the combustor exhaust plume were performed with a 64-mm 3 combustion chamber. Combustion efficiencies were determined to be higher than 95% for fuel-lean conditions. However, the thermal efficiency of the 64 mm 3 combustor was estimated to be considerably lower at about 40%. *buaasw@163.com

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“…The research that is currently being conducted at Boise State University involves the development of a miniaturized electric propulsion device for controlling microsatellites in space. Previously, BSU has developed a miniaturized hydrogen peroxide‐powered chemical monopropellant thruster in ceramic materials . In addition to this research at BSU, a miniature electric thruster is being developed.…”

Section: Introductionmentioning

confidence: 99%

“…Previously, BSU has developed a miniaturized hydrogen peroxide-powered chemical monopropellant thruster in ceramic materials. 7 In addition to this research at BSU, a miniature electric thruster is being developed. This device uses an inductively coupled plasma (ICP) source that is fabricated using DuPont Low Temperature Co-fired Ceramic (LTCC) materials.…”

Section: Introductionmentioning

confidence: 99%

Fabrication of an Inductively Coupled Plasma Antenna in Low Temperature Co‐Fired Ceramic

Taff

Yates

Lee³

et al. 2012

Int J Applied Ceramic Tech

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A miniature electrostatic thruster is being developed in Low Temperature Co-fired Ceramic (LTCC) at Boise State University. The thruster is composed of an antenna to create the plasma, a cylinder to contain the plasma, and grids to extract the plasma beam at high velocity. In this work, the development of the inductively coupled plasma (ICP) antenna in LTCC will be presented. This antenna is fabricated using DuPont 951 LTCC tape. A Direct Write dispenser is used to apply silver paste for the spiral ICP antenna. Using LTCC allows for the antenna to be embedded in the device under a thin sheet of LTCC dielectric, which protects the antenna from ion back bombardment during operation. This thin sheet is the seventh layer of the total device, with the ICP antenna one layer below the top. The design of the antenna is based on the research done by J. Hopwood. This article discusses the fabrication and performance of the ICP antennas in LTCC. These ICP antennas are operated at pressures from 10 mTorr to 1 Torr with radio frequencies (RF) of 500 MHz to 1 GHz to inductively couple with low-pressure argon to produce plasma. The performance of the antennas will be verified with data showing the start and stop power of the plasma at various pressures and an electric field map of the RF field above the antenna

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Development and Simulation of an Embedded Hydrogen Peroxide Catalyst Chamber in Low‐Temperature Co‐Fired Ceramics

Cited by 21 publications

References 10 publications

$\hbox{MnO}_{2}$ Nanowire Embedded Hydrogen Peroxide Monopropellant MEMS Thruster

$\hbox{MnO}_{2}$ Nanowire Embedded Hydrogen Peroxide Monopropellant MEMS Thruster

Development of Meso‐Scale Co‐Fired Ceramic Tape Axisymmetric Combustors

Fabrication of an Inductively Coupled Plasma Antenna in Low Temperature Co‐Fired Ceramic

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