Minimagnetosphericplasmapropulsion

Mini-Magnetospheric Plasma Propulsion (M2P2) • R. M. Winglee, G. K. Parks, M. McCarthy Geophysics Program, Univ. of Washington

• J. Slough, T. Ziemba Aeronautics and Astronautics, Uni. Of Washington

• J. Burch Southwest Research Institute

• A. Goodson Boeing Corporation NIAC March 25, 1999

Mini-Magnetospheric Plasma Propulsion (M2P2) • Facilitate High Speed Spacecraft For the Exploration of the Solar System and Beyond

• Enabling Technology Exists Today to attain 50-80 km/s in 3 month accel. period

• Immediate Return to NASA Missions - Interstellar Probe Precusor race Voyager 1 out of the Solar System - Geostorm - Solar Wind Monitoring

- Sun Synchronous Orbiter - Mercury Orbiter

Standoff Distance : 10 m Inner Radius

(Solar Wind - 500 km/s @ 6 particles/cc) Standoff Distance (m) Standoff Distance (m)

1.E+055 10

1.E+044 10

1.E+03 103 0 tilt 45 tilt extrapolation

1.E+02 102

101 1.E+01 1.E+03 103

Simple Dipole

1.E+04 104

1.E+05 105 Bcoil (nT) Bcoil (nT)

1.E+06 106

1.E+07 107

Thrust (N)

10

1 MPD

M2P2

Electrothermal Arcjet

.1 Resistojet

Ion

.01

100

1,000

10,000

Specific Impulse (sec)

100,000

M2P2 Lab. Prototype

Gas Feed Thru

Copper Housing Coil Connections Stainless Enclosure for Helicon Source Helicon Source Coil

Magnetic Coil (25 cm OD)

Quartz Tube (5 cm OD) Potting Material

Quartz End Plug

Force Exerted by Solar Wind (mN)

0.6 N per 100 kg

50 km/s in 3 months

Force exerted by Solar Wind (mN)

1.E+03 103 1.E+02 102

1.E+01 101 1.E+00 100

0 tilt - Radial 45 tilt - Radial

1.E-01 10-1

45 tilt - Azimuth Extrapolate - Radial Extrapolate - Azimuth

1.E-02 10-2 -4 10 1.E-04

-3 -2 -1 0 10 10 10 10 1.E-03 Force from 1.E-02 Plasma1.E-01 Source (mN) 1.E+00

1 10 1.E+01

Force from Plasma Source (mN) M2P2 : 1 mN Expended : 400 mN For Acceleration

Near Future Solar Sails (e.g Geostorm)

M2P2 15- 30 km

40 - 70 m

Momentum Flux :

1 nN/m2

4.7 uN/m2

Total Force :

0.6 -3 N

0.025 - 0.075 N

Weigh :

20 - 40 kg

100 kg

Power :

3 kW

0W

Method :

Electromagnetic

Mechanical

Interstellar Wind

Heliopause : End of the Plasma Solar System

Voyager 1: Launched 1978

Termination Shock: Subsonic Solar Wind Solar Wind

Formation of a Magnetic Wall Supersonic Solar Wind (400 - 1000 km/s)

Magnetic Wall •15 - 30 km radius

Streamlines & Contours of density

•ElectromagneticPlasma Interaction •Not Mechanical •Constant Force Surface

Creating A Mini-Magnetosphere Magnetic Field + Plasma Injection = Strong Solar Wind Coupling IMF

Bow Shock

Plasma Injection Solar Wind

Spacecraft Magnetic Field

Dipole : B ~ R

-3

Current Sheet : B ~ R -1

Mini-Magnetospheric Plasma Propulsion • STRONG COUPLING through Plasma Injection + Magnetic Field to the Solar Wind (400 - 1000 km/s) Azimuthal : Inner Solar System Radial : Outer Solar System • Constant Force is attained irrespective of position in the Solar System • Enabling Technology Exists

Helicon Plasma Sources Propellant Storage Magnetic Coil

Status of Present Work -Completed computer simulations showing feasibility -Lab. Prototype fully designed and being constructed Near-Future -Demonstrate magnetic wall inflation Small Tank (factor of 2) Large Tank (factor of 10) -Specify spacecraft mission for proof of principle goal of 50-80 km/s in 3 months -Facilitate exploration of outer solar system Long Term - Constant power supply for 1 yr allow 200-320 km/s -Utilization of Dusty Plasma would allow propulsion

by Solar Photons without the need for mechanical struts with unprecedented area to attain 10,000 km/s