TIHTUS Thrust Measurement with a Baffle Plate

Böhrk, Hannah; Auweter‐Kurtz, Monika

doi:10.2514/6.2007-5297

Cited by 5 publications

(6 citation statements)

References 4 publications

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“…In the present study, the thrust measurement was performed by impinging the gas jet coming out from the thruster on a microbalance stage, a validated method among various precision thrust measurement scheme published the literature [31]- [33]. The detail of measurement scheme is available elsewhere [21].…”

Section: Thrust Measurementmentioning

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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Section: Thrust Measurementmentioning

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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show abstract

“…Figure 12 shows the schematic of the thrust measurement setup to evaluate the VLM performance. While a variety of custom-build thrust measurement schemes have been employed to study the thruster characteristics [43][44][45][46][47], in this study, thrust measurement was conducted by impinging the vapor jet coming out from the VLM on the stage of a microbalance, a validated method published in the literature [35,[48][49] for precision thrust measurement. A high sensitivity laboratory balance (DV215CD, OHAUS Discovery Semi-micro Dual Range Balance) was adopted for the measurement in this study.…”

Section: Thrust Measurementmentioning

confidence: 99%

Design, fabrication and performance evaluation of a vaporizing liquid microthruster

Kundu¹,

Bhattacharyya²,

Das³

2012

J. Micromech. Microeng.

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A recent application domain of MEMS technology is in the development of microthrusters for micro-/nanosatellites. Among the various types of MEMS microthruster developed so far, the vaporizing liquid microthruster (VLM) has been widely explored for its capability to produce continuously variable thrust in the micro-Newton (µN) to mili-Newton (mN) range. This paper reports the design and experimental validation of silicon MEMS VLM consisting of a microcavity, inlet channel and converging–diverging (C-D) in-plane exit nozzle integrated in two micromachined bonded chips and sandwiched between two p-diffused microheaters, located at the top and bottom surface of the device. Structural configuration was designed using simple analytical equations to achieve maximum thrust force by controlling the inlet propellant flow and heater power of VLM in an efficient way. In addition, a 3D model using a computational fluid dynamics technique was constructed to simulate the aft section of VLM for the investigation of its aerodynamic behavior. The device fabrication and testing have been briefly described. The fabricated VLM is capable to produce 1 mN thrust using maximum heater power of 3.6 W at a water flow rate of 2.04 mg s−1 using an in-plane C-D exit nozzle of throat area 130 µm × 100 µm. A detailed thrust force measurement was carried out with the variation of input heater power for different mass flow conditions and exit to throat area ratio of the exit nozzle, and the results were interpreted with the theoretical model. The model gives considerable physical insight in the operation of the VLM. Finally, a performance comparison with other published VLM results indicates that the present design can yield comparatively more thrust force with much less input power. A performance comparison with other published VLM results indicates that the present design can achieve improved performance by integrating two heaters with appropriate chamber volume in respect of propellant flow rate and input power for obtaining a supersaturated dry stream.

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“…For establishing specific impulse and thrust efficiency, it is necessary to measure thrust, discharge current, discharge voltage and propellant flow rate. The thrust was measured by the target method [25,26]. As shown in figure 2, the thrust stand mainly consists of a target, elastic beam, displacement sensor and moveable platform.…”

Section: Performance Measurementsmentioning

confidence: 99%

Increasing the effective voltage in applied-field MPD thrusters

Tang

Wang

et al. 2018

J. Phys. D: Appl. Phys.

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Increasing the effective voltage is proposed to improve applied-field magnetoplasmadynamic thrusters (AF-MPDTs) efficiency. An analytical model for both effective voltage and thrust is presented and discussed on the basis of the generalized Ohm’s law. According to such a model, the effective voltage contributes to plasma acceleration and measures can be taken to affect it, including adjusting the fraction of cathode gas injection, applied magnetic field strength and discharge current. In order to verify the model, experiments were conducted on the conditions of stable operation of a 10 kW AF-MPDT. The results showed that discharge current affected thruster efficiency mainly by enhancing the back electromotive effect in plasma acceleration processes. The thrust efficiency was enhanced by an average of 9.1% by raising discharge current from 90 A to 180 A. The fraction of cathode gas injection mainly affected the resistive and Hall effect, and the thrust efficiency was enhanced by an average of 7.3% by increasing the fraction of cathode gas injection from 0.1 to 0.9. The applied magnetic field influenced the thruster performance by enhancing both the resistive and Hall effect and the back electromotive effect. The thrust efficiency was increased by an average of 3.0% by raising the applied magnetic field strength from 0.05 T to 0.17 T. It was found that the plasma acceleration of AF-MPDT was dominated by effective voltage, and increasing the effective voltage was an effective and comprehensive way to improve thruster performance.

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TIHTUS Thrust Measurement with a Baffle Plate

Cited by 5 publications

References 4 publications

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

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

Design, fabrication and performance evaluation of a vaporizing liquid microthruster

Increasing the effective voltage in applied-field MPD thrusters

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