IRS and Alta are currently involved in ESA and EU (HIPER) programs aiming for the development of high power electric propulsion systems. In the framework of these programs, two 100 kW applied-field magnetoplasmadynamic thrusters (AF-MDPT) are to be developed and tested within 2011: The steady state gas-fed AF-MPD ZT2 and Alta gas-fed pulsed AFMPD thruster. Such devices present some of the best propulsion systems if it comes to high thrust density and high specific impulse requirements, for example in orbit raising or Mars transfer mission scenarios. However, up to this day, there exists no adequate simple scaling model for AF-MPDT available to mission analysis and engine design which is addressed in this work: The classic Tikhonov model is extended and improved for steady state gas fed AFMPDT. A simplified law of energy conservation is introduced, which can be extended with an improved anode loss model. Both models were fitted using data of existing thrusters. Further, a common envelope of both thrusters has been achieved by overlapping of operational conditions to allow a comparison of both designs. Also, power scaling and performance estimation of the 100 kW IRS AF-MPD ZT1 and the 100 kW Alta AF-MPD thruster are presented in this paper. The knowledge obtained is going to enable IRS andAlta to define the specifications of a future ESA/European AF-MPDT.
Advanced scaling model for simplified thrust and power scaling of an applied-field magnetoplasmadynamic thruster
ANDRENUCCI, MARIANO;PAGANUCCI, FABRIZIO;
2010-01-01
Abstract
IRS and Alta are currently involved in ESA and EU (HIPER) programs aiming for the development of high power electric propulsion systems. In the framework of these programs, two 100 kW applied-field magnetoplasmadynamic thrusters (AF-MDPT) are to be developed and tested within 2011: The steady state gas-fed AF-MPD ZT2 and Alta gas-fed pulsed AFMPD thruster. Such devices present some of the best propulsion systems if it comes to high thrust density and high specific impulse requirements, for example in orbit raising or Mars transfer mission scenarios. However, up to this day, there exists no adequate simple scaling model for AF-MPDT available to mission analysis and engine design which is addressed in this work: The classic Tikhonov model is extended and improved for steady state gas fed AFMPDT. A simplified law of energy conservation is introduced, which can be extended with an improved anode loss model. Both models were fitted using data of existing thrusters. Further, a common envelope of both thrusters has been achieved by overlapping of operational conditions to allow a comparison of both designs. Also, power scaling and performance estimation of the 100 kW IRS AF-MPD ZT1 and the 100 kW Alta AF-MPD thruster are presented in this paper. The knowledge obtained is going to enable IRS andAlta to define the specifications of a future ESA/European AF-MPDT.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
