Second Generation EmDrive Propulsion Applied toSSTO Launcher and Interstellar Probe

Roger Shawyer SPR Ltd

IAC-14-C4,8.5 Toronto October 20141

Adrian Chesterman/Image publishing

2

2014 Summary of Published Test DATA

Thruster DesignSpecificforcemN/kW

ForceDirection

CANNAE roomtemperature

1.73 Thrust

NASA taperedcavity withdielectric section

6.86 Thrust

SPR tapered cavitywith dielectricsection

18.8 Thrust

SPR DemonstratorEngine

214243

ThrustReaction

NWPU Thruster 288 ReactionSPR Flight Thruster

330 Reaction

CANNAEsuperconducting

952 Thrust

Thrusters exhibit both Thrust and Reaction forces, therefore obeyingNewton’s laws

Increasing cavity Q increases specific force

Reaction Thrust

Tapered Cavity

1.E

+0

4

1.E

+0

5

1.E

+0

6

1.E

+0

7

1.E

+0

8

Q

10

100

1000

Sp

ecif

icT

hru

st(m

N/

kW)

Published Specific Thrust Data

Reaction Thrust

Tapered Cavity with Dielectric

Reaction Thrust

Cavity with Dielectric

3

Conservation of Energy

Vr Vf

Ff

Vg2

Fr

Vg1

Cavity Acceleration

Cavity acceleration produces unequalDoppler Shifts in Ff and Fr during eachwavefront transit.

Doppler Mathematical model illustratesDoppler shift for both Motor andGenerator modes.

0 5 10 15 20 25 30 35 40 45 50

Transit Number x 106

-40

-35

-30

-25

-20

-15

-10

-5

0

5

10

15

20

25

30

35

40

Dop

ple

rS

hif

t(H

z)

motor

generator

Doppler Shift for Fo =4GHz, Qu = 5x107

4

Superconducting Cavity With Piezoelectric Compensation for Doppler Shift

5

2G EmDrive Engine Control

0 20 40 60 80 100 120 140 160 180 200 220Time (msec)

0

20

40

60

80

100

120

140

160

180

200

220

Extn Powr Thrust

Eight Cavity Lift Engine For SSTO Spaceplane

6

915 MHzLH2 Cooled (total loss)667N/kW0.39m/s/s2 Axis GimballedVertically stabilised

7

All-Electric SSTO Spaceplane

Orbital Engine1.5GHzLH2 cooled (total loss)185mN/kW6m/s/s

Launch mass 9,858 kgPayload mass 2,000 kgLength 8.8mWidth 4.5mHeight 2.9m500kW Fuel cell

8

0 400 800 1200 1600Time (secs)

0

100

200

300

400

500

600

700

800

Vert

Vel(

m/s

)&H

oriz

vel(

m/s

/10)

Vert

Horiz

0 1000 2000 3000 4000 5000 6000Range (km)

0

50

100

150

200

250Al

titud

eat

100s

ecin

terv

als

(km

)

Spaceplane Mission

Ascent Profile Velocity Profile

9

Interstellar Probe

Main Engine500MhzLN2 cooled (closed cycle)304N/kW1m/s/s200kW nuclear generator

Spacecraft mass 8,936 kgPayload mass 1000 kgLength 28.2 mWidth 12.8 m

10

0 1 2 3 4 5 6 7 8 9 10Time (Years)

0.0

0.5

1.0

1.5

2.0

2.5

3.0

3.5

4.0

Velo

city

(km

/sx

10

E-5

)&

Dis

tan

ce(l

igh

tye

ars

)

Vel

Dist

Interstellar Probe Mission

Nominal acceleration modified by:EmDrive velocity correctionRelativity energy effect

After 9.86 years propulsion:Terminal velocity = 204,429 km/sDistance = 3.96 Light Years

11

Mission Efficiencies

The EmDrive thruster efficiencies can be calculated for each mission from:

Kinetic energy of spacecraft at terminal velocityTotal microwave energy input during acceleration

The calculated thruster efficiencies were:

SSTO spaceplane orbital engine = 0.363Interstellar probe main engine = 0.31

The overall mission efficiencies can be calculated from:

Kinetic energy of spacecraft at terminal velocityTotal energy input during acceleration

The calculated mission efficiencies were:

SSTO spaceplane to orbital velocity = 0.243Interstellar probe to terminal velocity = .0046

12

Conclusions

Published Test Data from four independent sources, in three countries confirms§EmDrive theory

Mathematical model quantifies acceleration energy conservation effect at high Q§

Engine design studies illustrate method for compensating for acceleration§

Spacecraft design studies demonstrate:§

SSTO Spaceplane giving low cost access to space

Interstellar Probe enabling a 10 year mission to the nearest star

These (or similar)spacecraft will fly§

When ?§

Who will build them ?§