Performance and endurance tests of a laboratory model multipropellant resistojet

Morren, W. Earl; Whalen, Margaret V.; Sovey, James S.

doi:10.2514/3.23218

Cited by 11 publications

(2 citation statements)

References 4 publications

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“…However, for heavy and bulky systems, a target balance is needed [11]. Techniques for measuring the thrust magnitude of electric propulsion devices have been developed based on a spring restoring force, a pendulum and a gas-bearing turntable [12][13][14][15][16][17][18]. The present paper reports an attempt made to measure the thrust produced by an SPT by developing a measurement system using strain gauge sensors.…”

Section: Introductionmentioning

confidence: 99%

Strain gauge based thrust measurement system for a stationary plasma thruster

Stephen

Rajanna

Dhar

et al. 2001

Meas. Sci. Technol.

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A thrust measurement system has been developed for the purpose of measuring the thrust produced by a stationary plasma thruster. The measurement system designed and fabricated mainly consists of a thrust balance assembly with strain gauge sensors and associated signal conditioning circuitry. Performance of the system developed was studied, in a vacuum chamber under space simulated conditions, by activating the thruster using xenon as the propellant. Details of the in situ calibration procedure followed are given. The thrust output for discharge powers ranging from 170 to 260 watts was measured and found to be in the range of 4-14 millinewtons. The measurement accuracy and resolution were found to be ±1 mN and 0.3 mN respectively. Specific impulse and thrust efficiency were also estimated.

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Section: Introductionmentioning

confidence: 99%

Strain gauge based thrust measurement system for a stationary plasma thruster

Stephen

Rajanna

Dhar

et al. 2001

Meas. Sci. Technol.

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“…The difference between these two voltages correspond to a force of 1.03x9.8 = 10.1 mN. This was repeated a few times to check the consistency of the change in the output voltage corresponding to the force of 10.1 mN and the values were found to be consistent. This change in output voltage was utilized, as follows, in estimating the thrust produced when the thruster was activated.…”

Section: P=rmentioning

confidence: 97%

Thin film strain gauge sensors for ion thrust measurement

Stephen

Rajanna

Dhar

et al.

Proceedings of IEEE Sensors

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In order to measure the thrust produced by a Stationary Plasma Thruster, a measurement system has been developed using a thrust balance with thin Jilm strain gauge sensors. For this purpose, strain gauges were designed and deposited on the columns of the thrust balance fabricated and necessary signal conditioning circuit has been used. Performance of the system developed was studied, in a vacuum chamber under space simulated conditions, by activating the thruster. Insitu calibration was done using Lami's principle. For discharge powers varying @om 210-275 Watts, the measured values of thrust were found to be in the range of 11-16 mN with an accuracy off. ImN and resolution of 0.12 mN. Specijk impulse and eflciency were also estimated.

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