A digital xenon flow controller based on ChEMS technology

Cardin, Joe; Otsap, Ben

doi:10.2514/6.1999-2563

Cited by 5 publications

(3 citation statements)

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“…The flow dependence on both the channel length and cross-sectional area can be effectively exploited to scale up and down the regulation range. Flow regulators based on an array of selectable fixed flow rate restrictors [28] or even nozzles [3], have been already proposed for satellite thrusters. Using our approach to individually modulate the flow in each channel of the array can drastically reduce the minimum number of elements necessary to achieve the required resolution.…”

Section: Discussionmentioning

confidence: 99%

A Closed-Loop Mass Flow Controller Based on Static Solid-State Devices

Bruschi

Navarrini

Piotto

2006

J. Microelectromech. Syst.

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A mass flow controller, based on an integrated flow sensor and a thermally actuated solid state regulator, is presented. The sensor is a miniaturized differential calorimeter obtained by postprocessing a silicon chip fabricated by a standard microelectronic process. The regulator consists in a microchannel etched into the surface of a silicon substrate and sealed with a glass plate, joined to the silicon die using anodic bonding. Flow regulation is achieved by varying the channel temperature by means of a chromium resistor. The two devices are connected in closed-loop through a low noise—low offset electronic circuit. Experimental data, demonstrating the effectiveness of the flow controller, are presented. Limitations of the proposed approach and possible improvements are discussed

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Section: Discussionmentioning

confidence: 99%

A Closed-Loop Mass Flow Controller Based on Static Solid-State Devices

Bruschi

Navarrini

Piotto

2006

J. Microelectromech. Syst.

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“…The harness and chassis weights are included in the pertinent component weight. In this estimation, it is assumed that a lightweight propellant flow controller based on MEMS technology [11] is adopted in the propellant supply system.…”

Section: Thruster Performancementioning

confidence: 99%

Sub-Milli-Newton Class Miniature Microwave Ion Thruster

Nakayama

Funaki

Kuninaka

2007

Journal of Propulsion and Power

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A miniaturized microwave ion source with a 1.6-cm beam diameter grid system was designed and then evaluated experimentally. Based on the HAYABUSA 10 neutralizer, we fabricated a small 18-mm-diam discharge chamber, into which 4.2 GHz microwaves were launched through an L-shaped antenna that was located in a magnetic field created by permanent magnets and iron yokes. Ion beams were emitted from the small discharge chamber when operated with a grid system whose respective hole diameters of the screen grid and acceleration grid were 0.72 and 0.43 mm, and the total number of grid holes was 211. For a beam voltage of 1500 V and a microwave input power of 10 W, the typical thruster performance was thrust of 0.34 mN, a thrust/power ratio of 16 mN=kW, propellant utilization efficiency of 68%, and a specific impulse of 3200 s. If we were able to further reduce the ion production cost (circa 3000 W=A in the current experiment), this thruster would be a candidate for main propulsion of a small satellite or precise attitude control of various sizes of satellites.

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“…ChEMS TM technology consists of multiple layers of etched and bonded metal sheets to form components and their interconnecting flow paths. 31 Figure 6 illustrates an integrated pressure and flow control unit capable of meeting many propulsion needs. The program has recently been initiated, and over the next three years will demonstrate functionality of an integrated pressure and flow control unit with a Hall thruster and gridded ion thruster.…”

Section: (12) Evaluation and Development Of Lightweight/low Cost Commentioning

confidence: 99%

NASA's Hall thruster program

Jankovsky

Jacobson

Rawlin

et al. 2001

37th Joint Propulsion Conference and Exhibit

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NASA's Hall thruster program has base research and focused development efforts in support of the Advanced Space Transportation Program, Space-Based Program and various other programs. The objective of the base research is to gain an improved understanding of the physical processes and engineering constraints of Hall thrusters to enable development of advanced Hall thruster designs. Specific technical questions that are current priorities of the base effort are: (1) How does thruster life vary with operating point? (2) How can thruster lifetime and wear rate be most efficiently evaluated? (3) What are the practical limitations for discharge voltage as it pertains to high specific impulse operation (high discharge voltage) and high thrust operation (low discharge voltage)? (4) What are the practical limits for extending Hall thrusters to very high input powers? and (5) What can be done during thruster design to reduce cost and integration concerns? The objective of the focused development effort is to develop a 50 kW-class Hall propulsion system, with a milestone of a 50 kW engineering model thruster/system by the end of program year 2006. Specific program year 2001 efforts, along with the corporate and academic participation, are described.

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A digital xenon flow controller based on ChEMS technology

Cited by 5 publications

References 0 publications

A Closed-Loop Mass Flow Controller Based on Static Solid-State Devices

A Closed-Loop Mass Flow Controller Based on Static Solid-State Devices

Sub-Milli-Newton Class Miniature Microwave Ion Thruster

NASA's Hall thruster program

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