ELECTRIC PROPULSION Introduction Classification of Electric Thrusters Professor, Department of Aerospace Engineering, University of Pisa, Italy Chairman.

ELECTRIC PROPULSION

Introduction

Classification of Electric Thrusters

Professor, Department of Aerospace Engineering, University of Pisa, Italy

Chairman and CEO, Alta S.p.A, Via A. Gherardesca 5, 56121 Ospedaletto, Pisa, Italy

e-mail: [email protected]

Mariano Andrenucci

ESA/ESTEC, Noordwijk,September 15-19, 2008

Advanced Course: Electric Propulsion Concepts and SystemsM. Andrenucci

Slide 2.2

Introduction

• Expansion of human presence in space will certainly pose the need to develop very high power propulsion systems

• High power electric propulsion can enable sending probes to the edge of the Solar System, exploring Kuiper belt, Oort Cloud, Heliopause, and performing deep Space observation…

• High Isp propulsion needed for the higher energy missions, with Isp levels of 10,000 s to 15,000 s to minimize launch mass

• High power levels also needed for crewed planetary exploration vehicles, but larger thrust leves required for acceptable trip times

• High power applications to be generally based on nuclear power systems; high performance photovoltaic power generation also applicable for inner solar systems operations

• Higher power propulsion systems obtainable in principle by clustering; but 0.1 to >1 MW single thruster capability needed so that the number of thrusters per spacecraft is reasonable.

Introduction



Slide 2.3

Introduction

Propulsion Options

• Among the various electric propulsion concepts, several types of devices provide, in principle, the ability to process hundreds of kilowatts to megawatts of power at reasonably high efficiencies• Ion thrusters• Plasma thrusters

• Hall Effect Thrusters• MPD Thrusters

• Arcjets• Other Concepts

• VASIMR• Pulsed Inductive Thrusters• . . .

• Among the above categories only the first two seem to meet the relevant selection criteria for the intended missions in terms of performance capability, lifetime potential, mid-term TRL, . . .

• Ion thrusters, in particular, appear especially suited for very high Isp, while plasma thrusters allow achieving higher thrust densities



Slide 2.4

Introduction

Propulsion System Classification



Slide 2.5

Introduction




Slide 2.6

Introduction




Slide 2.7

Introduction




Slide 2.8

Introduction

Performance Levels



Slide 2.9

Introduction

The Thrust-Density Issue

SF-MPDT: 103

AF-MPDT: 102

GIT: 100

HET: 101

Order ofmagnitude

Source: IRS, Stuttgart



Slide 2.10

Introduction

Power vs. Thrust, Isp



Slide 2.11

Introduction

Power vs. Thrust, Isp



Slide 2.12

Introduction

Thrust vs Isp, T , for given Power Level



Slide 2.13

Introduction

Thrust vs Isp, T , for given Power Level

ELECTRIC PROPULSION Introduction Classification of Electric Thrusters Professor, Department of Aerospace Engineering, University of Pisa, Italy Chairman.

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