Steady state applied-field magnetoplasmadynamic thruster promises good compromise between thrust density and specific impulse, making them relevant for interplanetary missions requiring high thrusts. The IRS 100 kW gas-fed steady-state AF-MPD SX3 thruster has shown promising results in previous held test campaigns. Experimental results in those campaigns showed non-linear behavior of tare forces, resulting in respective error in the thrust measurement and this error then propagates in further calculation of Isp, thrust efficiency, etc. This motivated improvement in the thrust balance and measurement technique. Various error sources in the thrust measurement technique were identified and solutions to mitigate them were presented. A number of...
An optical interferometric proximeter system (IPS) for measuring thrusts and im-pulse bits of pulsed...
A thrust stand for use with high power electric propulsion devices was designed and tested. The thru...
An investigation of operative instabilities affecting the SX3 thruster has been performed by mean of...
Steady state applied-field magnetoplasmadynamic thruster promises good compromise between thrust den...
The arcjet development at the Institute of Space Systems (IRS) at Stuttgart is intended to deorbit s...
Currently available or realizable applied eld magnetoplasmadynamic (AF–MPD) thrusters operating in ...
Electric space propulsion thrusters only produce low thrust forces. For the fulfillment of a space m...
With evermore stringent requirements towards pointing accuracy and platform stability, in both comme...
A momentum flux measuring instrument (MFMI), which ranges from 1 mN∼300 N, is designed to measure th...
Direct thrust measurements by means of a thrust balance (TB) are the golden standard for measuring t...
A description and an analysis of the three methods used to measure the thrust of the SERT n (Space E...
IRS and Alta are currently involved in ESA and EU (HIPER) programs aiming for the development of hig...
An increasing number of future space missions and experiments are going to require propulsion system...
Accurate, direct measurement of thrust or impulse is one of the most critical elements of electric t...
In the context of investigations for a su�cient attitude control thruster for LISA, we have develop...
An optical interferometric proximeter system (IPS) for measuring thrusts and im-pulse bits of pulsed...
A thrust stand for use with high power electric propulsion devices was designed and tested. The thru...
An investigation of operative instabilities affecting the SX3 thruster has been performed by mean of...
Steady state applied-field magnetoplasmadynamic thruster promises good compromise between thrust den...
The arcjet development at the Institute of Space Systems (IRS) at Stuttgart is intended to deorbit s...
Currently available or realizable applied eld magnetoplasmadynamic (AF–MPD) thrusters operating in ...
Electric space propulsion thrusters only produce low thrust forces. For the fulfillment of a space m...
With evermore stringent requirements towards pointing accuracy and platform stability, in both comme...
A momentum flux measuring instrument (MFMI), which ranges from 1 mN∼300 N, is designed to measure th...
Direct thrust measurements by means of a thrust balance (TB) are the golden standard for measuring t...
A description and an analysis of the three methods used to measure the thrust of the SERT n (Space E...
IRS and Alta are currently involved in ESA and EU (HIPER) programs aiming for the development of hig...
An increasing number of future space missions and experiments are going to require propulsion system...
Accurate, direct measurement of thrust or impulse is one of the most critical elements of electric t...
In the context of investigations for a su�cient attitude control thruster for LISA, we have develop...
An optical interferometric proximeter system (IPS) for measuring thrusts and im-pulse bits of pulsed...
A thrust stand for use with high power electric propulsion devices was designed and tested. The thru...
An investigation of operative instabilities affecting the SX3 thruster has been performed by mean of...