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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
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 ?§
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