# Presentation: 247798

## Electric Propulsion for Future Space MissionsPart I

**Bryan Palaszewski**
**Digital Learning Network**
**NASA Glenn Research Center **
**at Lewis Field**

## Introduction

- Why electric propulsion?
- Types
- Applications
- Some history
- Future missions and vehicles
- A very cool future

## Solar Electric Propulsion Module

**Solar Electric Propulsion Module**

## Why High Exhaust VelocityIs Important

## Chemical & Electric Propulsion Have Intrinsic Differences

**Chemical & Electric Propulsion ****Have Intrinsic Differences**

## Solar and Nuclear Electric Propulsion Subsystems

**Solar and Nuclear Electric Propulsion ****Subsystems**

## Electric PropulsionHistorical Overview

**Electric Propulsion****Historical Overview**

**1903 -- K. E. Tsiolkovsky derived the “Tsiolkovsky” or “Rocket” Equation commonly used to show the benefits of electric propulsion**
**1906 -- R. Goddard wrote about the possibility of electric rockets**
**1911 -- K. E. Tsiolkovsky independently wrote about electric rockets**
**1929 -- World’s first electric thruster demonstrated by V. P. Glushko at the Gas Dynamics Laboratory in Lenningrad**
**1960 -- First “broad-beam” ion thruster operated in the U.S. at the NASA Lewis (now Glenn) Research Center**

## Electric PropulsionHistorical Overview

**Electric Propulsion****Historical Overview**

**1964 -- First successful sub-orbital demonstration of an ion engine (SERT I) by the U.S.**
**1964 -- First use of an electric thruster on an interplanetary probe (Zond 2) by the USSR**
**1970 -- Long duration test of mercury ion thrusters in space (SERT II) by the U.S.**
**1972 -- First operation of a xenon stationary plasma thruster (SPT-50) in space (Meteor) by the USSR**
**1993 -- First use of hydrazine arcjets on a commercial communications satellite (Telstar 401) by the U.S.**

## The First Electric Thruster

**The First Electric Thruster**

**Developed by V. P Glushko at the Gas Dynamics Laboratory in Lenningrad, 1929 - 1933**
**Solid and Liquid Conductors Were Vaporized by High Current Discharges in the Plenum Chamber and Expanded Through the Nozzle**
**Power Provided by 40 kV, 4 mF Capacitors**

## Types Of Electric Thrusters

**Electrostatic**
**Ion**
**Hall**
**Electrothermal**
**Arcjet**
**Resistojet**
**Electromagnetic**
**Magneto plasma dynamic (MPD)**
**Many others**

## Types Of Electric Thrusters

## Ion Thruster

**Ion Thruster**

## Ion Thruster

## Ion Thruster Layout

**Ion Thruster Layout**

## Hall Thruster

**SPT-100**
**1350 W**
**1600 lb****f****-s/lb****m**** **
**(Nominal)**

**SPT-70**
**700 W**
**1450 lb****f****-s/lb****m**** **
**(Nominal)**

**SPT-140**
**4000 W**
**1700 lb****f****-s/lb****m**** **
**(Nominal)**

**SPT-50**
**300 W**
**1200 lb****f****-s/lb****m**** **
**(Nominal)**

**Thrusters designed and fabricated by the **
**Design Bureau Fakel, Kaliningrad (Baltic Region), Russia, and offered by International Space Technology, Inc.**

## Hall Thruster

## Hydrazine Arcjet

**Primex Aerospace Hydrazine Arcjet: 1.8 kW, 200 mN, 500 lb****f****-s/lb****m**

## Arcjet Thruster

## Arcjet Thruster

**Ship Set of Four Olin Aerospace 500 lb****f****-s/lb****m**** Hydrazine Arcjets **
**and Power Processing Unit**

## Magneto Plasma Dynamic (MPD) Thruster

## Magneto Plasma Dynamic (MPD) Thruster

## Pulsed Plasma Thruster

## Pulsed Plasma Thruster

## Pulsed Plasma Thruster

## NASA Glenn Electric Propulsion Laboratory (EPL)

## NASA Glenn Electric Propulsion Laboratory (EPL) Contributions

**On September 23, 2001, the Deep Space 1 ion thruster set a record of 16,000 hrs. of operation while propelling the spacecraft on its encounter with Comet Borrelly. **
**In preparation of MErcury Surface, Space ENvironment, GEochemistry and Ranging (MESSENGER) probe mission, VF-6 was used to characterize components under a 10-sun solar insolation environment. **
**On December 3, 2000, hollow cathodes, which were developed at GRC and tested in VF-5 as part of the Plasma Contactor Unit, began protecting the International Space Station from harmful space plasma voltage potentials.**** **

## NASA Glenn Electric Propulsion Laboratory (EPL) Contributions

**A refractive secondary concentrator (RSC) achieved temperatures of 1455 Kelvin with an 87% throughput in VF-6. **
**On January 4, 2002, a pulsed plasma thruster on Earth Observing 1 demonstrated a highly fuel efficient method of controlling spacecraft attitude and "pointability."**
**Conducted first integrated solar dynamic system test from solar input to electrical power in VF-6.**** **

## Jupiter

**Jupiter**

## Saturn

**Saturn**

## Uranus

**Uranus**

## Neptune

**Neptune**

## Neptune and Ion Thruster

**Neptune and Ion Thruster**

## Pluto

**Pluto**

## Deep Space 1

**Deep Space 1**

## Deep Space 1 Thruster / Spacecraft Compatibility Testing

**Deep Space 1 Thruster / Spacecraft ****Compatibility Testing**

## Deep Space 1 Thruster

**Deep Space 1 Thruster**

## Launch of Deep Space 1
Boeing Delta II (7326) Rocket
October 24, 1998

**Launch of Deep Space 1**
**Boeing Delta II (7326) Rocket**
**October 24, 1998**

## DS-1 Trajectory

**DS-1 Trajectory**

## Autonomous Navigation

**Autonomous Navigation**

## Comet Borrelly

**Comet Borrelly**

## Comet Borrelly

**Comet Borrelly**