i ac 2014 presentation

8/10/2019 i Ac 2014 Presentation

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Second Generation EmDrive Pr opulsion Applied toSSTO Launcher and I nterstellar P robe

Roger Shaw yer SP R Ltd

I AC- 14- C4,8.5 Toronto October 20141

Adrian Chesterman/Image publishing
http://www.go2pdf.com/


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2014 Summary of Published Test DATA

Th ru st er DesignSpecific

forcemN/ 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

Th ru ster s ex hi bi t bo th Th ru st an d Re acti on fo rces , th er ef or e ob ey in gNewtons laws

I ncreasing 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

S p e c i f i c T h r u s t ( m N / k W )

Published Specific Thrust Data

Reaction Thrust

Tapered Cavity with Dielectric

Reaction Thrust

Cavity with Dielectric


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Conservation of Energy

Vr Vf

Ff

Vg2

Fr

Vg 1

Cavity Acceleration

Cavity acceleration produces unequalDoppler Shifts in F f and F r during eachwavefront transit.

Doppler Mathematical model illustratesDoppler shift for both Motor andGenerator modes.

0 5 10 15 20 25 30 35 40 45 50

Tra nsi t Nu mb er x 10 6-4 0

-3 5

-3 0

-2 5

-2 0

-1 5

-1 0

-5

0

5

10

15

20

25

30

35

40

D o p p l e r S h i f t ( H z )

motor

generator

Doppler Shift for Fo =4GHz, Qu = 5x10 7


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Superconducting Cavity With Piezoelectric Compensation for Doppler Shift


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2G EmDrive Engine Control

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

0

20

40

60

80

100

120

140

160

180

200

220

Extn Powr Thrust


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Eight Cavity Lift Engine For SSTO Spaceplane

6

915 MHzLH2 Cooled (total loss)667N/ kW0.39m/ s/ s

2 Axis GimballedVertically stabilised


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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


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0 400 800 1200 1600 Time(secs)

0

100

200

300

400

500

600

700

800

V e r t V e l ( m / s ) & H o r i z v e l ( m / s / 1 0 )

Vert

Horiz

0 1000 2000 3000 4000 5000 6000Range (km)

0

50

100

150

200

250

A l t i t u d e a t 1 0 0 s e c i n t e r v a l s ( k m )

Spaceplane Mission

Ascent Profile Velocity Profile


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I nterstel lar 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


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0 1 2 3 4 5 6 7 8 9 10 Tim e ( Ye ars )

0.0

0.5

1.0

1.5

2.0

2.5

3.0

3.5

4.0

V e l o c i t y ( k m / s x 1 0 E - 5

) & D i s t a n c e ( l i g h t y e a r s )

Vel

Dist

I nterstel lar Probe Mission

Nominal acceleration modified by:EmDrive velocity correctionRelativity energy effect

After 9.86 years propulsion: Te rmi na l velo ci ty = 204 ,429 km/ sDistance = 3.96 Light Years


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Mission Efficiencies

Th e Em Dr ive th rus ter ef fic ienc ies can be calcul at ed for each mis si on fr om :

Kinetic energy of spacecraft at terminal velocity To tal microw ave en er gy in pu t du rin g accele rat ion

Th e calcul at ed th rus te r ef fi cien cies w er e:

SSTO spaceplane orbital engine = 0.363I nterstellar probe main engine = 0.31

Th e over al l missi on ef fic iencies can be calcul at ed from :

Kinetic energy of spacecraft at terminal velocity To tal en er gy in pu t du rin g accele rat io n

Th e calcul at ed mis si on ef ficien cies w er e:

SSTO spaceplane to orbital velocity = 0.243I nterstellar probe to terminal velocity = .0046


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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

I nterstellar Probe enabling a 10 year mission to the nearest star

These ( or si mila r) spacecraf t w il l fly

When ?

Who w ill build them ?

i ac 2014 presentation

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