Second Generation EmDrive Propulsion Applied to SSTO Launcher

Second Generation EmDrive Propulsion Applied to SSTO Launcher

Second Generation EmDrive Propulsion Applied to
SSTO Launcher and Interstellar Probe
Roger Shawyer
SPR Ltd
Adrian Chesterman/Image publishing
IAC-14-C4,8.5
Toronto October 2014
1
2014 Summary of Published Test DATA
1.73
Thrust
NASA tapered
cavity with
dielectric section
6.86
Thrust
SPR tapered cavity
with dielectric
section
18.8
Thrust
SPR Demonstrator
Engine
NWPU Thruster
Reaction
Thrust
Tapered Cavity
SPR Flight Thruster
CANNAE
superconducting
214
243
Thrust
Reaction
288
Reaction
330
Reaction
952
Thrust
100
10
1.E+08
Tapered Cavity with Dielectric
CANNAE room
temperature
Published Specific Thrust Data
1000
1.E+07
Thrust
Force
Direction
1.E+06
Reaction
Specific
force
mN/kW
1.E+05
Cavity with Dielectric
Thruster Design
1.E+04
Thrust
Specific Thrust (mN/kW)
Reaction
Q
Thrusters exhibit both Thrust and Reaction forces, therefore obeying
Newton’s laws
Increasing cavity Q increases specific force
2
Conservation of Energy
Doppler Shift for Fo =4GHz, Qu = 5x107
Ff
40
35
Fr
30
Vg2
Vg1
25
20
Vr
Vf
Cavity Acceleration
Doppler Shift (Hz)
15
10
5
motor
0
-5
0
5
10
15
20
25
30
35
40
45
50
generator
-10
Cavity acceleration produces unequal
Doppler Shifts in Ff and Fr during each
wavefront transit.
-15
-20
-25
-30
Doppler Mathematical model illustrates
Doppler shift for both Motor and
Generator modes.
-35
-40
Transit Number x 106
3
Superconducting Cavity With Piezoelectric Compensation for Doppler Shift
4
2G EmDrive Engine Control
Extn
Powr
Thrust
220
200
180
160
140
120
100
80
60
40
20
0
0
20
40
60
80
100
120
140
Time (msec)
160
180
200
220
5
Eight Cavity Lift Engine For SSTO Spaceplane
915 MHz
LH2 Cooled (total loss)
667N/kW
0.39m/s/s
2 Axis Gimballed
Vertically stabilised
6
All-Electric SSTO Spaceplane
Orbital Engine
1.5GHz
LH2 cooled (total loss)
185mN/kW
6m/s/s
Launch mass 9,858 kg
Payload mass 2,000 kg
Length 8.8m
Width 4.5m
Height 2.9m
500kW Fuel cell
7
Spaceplane Mission
800
250
Vert Vel (m/s) & Horiz vel (m/s/10)
700
600
Altitude at 100sec intervals (km)
200
500
150
400
Vert
300
100
Horiz
200
100
50
0
0
0
1000
2000
3000
Range (km)
4000
Ascent Profile
5000
0
400
800
Time (secs)
1200
1600
6000
Velocity Profile
8
Interstellar Probe
Main Engine
500Mhz
LN2 cooled (closed cycle)
304N/kW
1m/s/s
200kW nuclear generator
Spacecraft mass 8,936 kg
Payload mass 1000 kg
Length 28.2 m
Width 12.8 m
9
Nominal acceleration modified by:
EmDrive velocity correction
Relativity energy effect
After 9.86 years propulsion:
Terminal velocity = 204,429 km/s
Distance = 3.96 Light Years
Velocity (km/sx10E-5) & Distance (light years)
Interstellar Probe Mission
4.0
3.5
3.0
2.5
Vel
2.0
Dist
1.5
1.0
0.5
0.0
0
1
2
3
4
5
6
Time (Years)
7
8
9
10
10
Mission Efficiencies
The EmDrive thruster efficiencies can be calculated for each mission from:
Kinetic energy of spacecraft at terminal velocity
Total microwave energy input during acceleration
The calculated thruster efficiencies were:
SSTO spaceplane orbital engine = 0.363
Interstellar probe main engine = 0.31
The overall mission efficiencies can be calculated from:
Kinetic energy of spacecraft at terminal velocity
Total energy input during acceleration
The calculated mission efficiencies were:
SSTO spaceplane to orbital velocity
= 0.243
Interstellar probe to terminal velocity = .0046
11
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 ?
12