Development and Ground Tests of a 100-Millinewton Hydrogen Peroxide Monopropellant Microthruster

Kuan, Chih-Kuang; Chen, Guan-Bang; Chao, Yei-Chin

doi:10.2514/1.30440

Cited by 42 publications

(24 citation statements)

References 10 publications

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“…We measured the thrust force of this pressure wave using a micro-force sensor configuration (see Supplementary Fig. S13) to be substantially higher per total propulsion system mass than many other comparable microthrust generators in the literature [35][36][37][38][39][40] . The MWNT array was placed either normal or parallel to the force sensor surface, and immobilized in both directions during testing.…”

Section: Experimental Geometries and A Histogram Of Reaction Front Vementioning

confidence: 99%

Chemically driven carbon-nanotube-guided thermopower waves

et al. 2010

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Theoretical calculations predict that by coupling an exothermic chemical reaction with a nanotube or nanowire possessing a high axial thermal conductivity, a self-propagating reactive wave can be driven along its length. Herein, such waves are realized using a 7-nm cyclotrimethylene trinitramine annular shell around a multiwalled carbon nanotube and are amplified by more than 10(4) times the bulk value, propagating faster than 2 m s(-1), with an effective thermal conductivity of 1.28+/-0.2 kW m(-1) K(-1) at 2,860 K. This wave produces a concomitant electrical pulse of disproportionately high specific power, as large as 7 kW kg(-1), which we identify as a thermopower wave. Thermally excited carriers flow in the direction of the propagating reaction with a specific power that scales inversely with system size. The reaction also evolves an anisotropic pressure wave of high total impulse per mass (300 N s kg(-1)). Such waves of high power density may find uses as unique energy sources.

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Section: Experimental Geometries and A Histogram Of Reaction Front Vementioning

confidence: 99%

Chemically driven carbon-nanotube-guided thermopower waves

et al. 2010

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“…In terms of performance, monopropellant thrusters offer a greater range of total impulse, thrust level, and impulse bit; fabrication and propellant handling is also simpler than in bipropellant systems [4]. Monopropellant thrusters [5]- [8] typically rely upon a catalyzed chemical decomposition of the liquid propellant as the source of energy. The chemical decomposition is a highly exothermic process which produces energetic gaseous reactants that expand and then exit through a micronozzle, providing a very small and precise impulse bit.…”

Section: Introductionmentioning

confidence: 99%

“…However, it is an unstable compound and readily decomposes into water and oxygen. The decomposition reaction is exothermic, and the temperature of the decomposition products is dependent upon the initial concentration of the hydrogen peroxide and the efficiency of the decomposition [8]. Although it is a less energetic propellant fuel than hydrazine, hydrogen peroxide is considered to be a "green" propellant due to its low toxicity and the innocuous nature of its decomposition products.…”

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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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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“…The integrated heater should prevent the cold start and assist the propellant decomposition in the reaction chamber (Spadaccini 2004;Chiarini et al 2006;Scharlemann et al 2006;Kuan et al 2007) leading to a longer catalyst lifetime and higher fuel efficiency. The integration of seven temperature sensors should enable detailed investigation and control of the thermal performance of the microthruster and thus facilitate further optimization of the system.…”

Section: Introductionmentioning

confidence: 99%

MEMS-based microthruster with integrated platinum thin film resistance temperature detector (RTD), heater meander and thermal insulation for operation up to 1,000°C

Miyakawa¹,

Legner²,

Ziemann³

et al. 2012

Microsyst Technol

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We have fabricated microthruster chip pairs-one chip with microthruster structures such as injection capillaries, combustion chamber and converging/diverging nozzle machined using the deep reactive ion etching process, the other chip with sputtered platinum (Pt) thin film devices such as resistance temperature detectors (RTDs) and a heater. To our knowledge, this is the first microelectromechanical systems-based microthruster with fully integrated temperature sensors. The effects of anneal up to 1,050°C on the surface morphology of Pt thin films with varied geometry as well as with/without PECVD-SiO 2 coating were investigated in air and N 2 and results will also be presented. It was observed that by reducing the lateral scale of thin films the morphology change can be suppressed and their adhesion on the substrate can be enhanced. Chemical analysis with X-ray photoelectron spectroscopy showed that no diffusion took place between neighboring layers during annealing up to 1 h at 1,050°C in air. Electrical characterization of sensors was carried out between room temperature and 1,000°C with a ramp of ±5 Kmin -1 in air and N 2 . In N 2 , the temperature-resistance characteristics of sensors had stabilized to a large extent after the first heating. After stabilization the sensors underwent up to eight further temperature cycles. The maximum drift of the sensor signal was observed for temperatures above 950°C and was less than 8.5 K in N 2 . To reduce the loss of combustion heat, chip material around microthruster structures was partially removed with laser ablation. The effects of thermal insulation were investigated with microthruster chip pairs which were clamped together mechanically. The heater was operated with up to 20 W and the temperature distribution in the chip pairs with/without thermal insulation was monitored with seven integrated RTDs. The experiments showed that a thermal insulation allows the maximum temperature as well as the temperature gradient within the microthruster chip pairs to be increased.

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Development and Ground Tests of a 100-Millinewton Hydrogen Peroxide Monopropellant Microthruster

Cited by 42 publications

References 10 publications

Chemically driven carbon-nanotube-guided thermopower waves

Chemically driven carbon-nanotube-guided thermopower waves

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

MEMS-based microthruster with integrated platinum thin film resistance temperature detector (RTD), heater meander and thermal insulation for operation up to 1,000°C

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