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Direct Thrust Measurements and Full Performance Mapping of the IFM Nano Thruster at ESA ESTEC Facilities
David Krejci et al.
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MODULARIZATION-> STANDARDIZATION
-> MULITPLE CONSTELLATIONS
Propellant Reservoir for 5000 Ns
Ion Emitter
Power Electronics
IFM Nano Thruster
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INDIUM FEEP ion emitter
Building on30 Yearsof Development at FOTEC
Debris safe
Non-Toxic
No Pressure
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• 100% INCOMING INSPECTION OF ALL MECHANICAL PARTS• 100% TRACEABILITY OF ALL PARTS, MANUFACTURING AND TESTING• LEAN PRODUCTION (KANBAN) FOR HIGH THROUGHPUT• BATCH TESTING ON PART, COMPONENT AND SYSTEM-LEVEL
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• 100% Testing: Every emitter fired 2x• Batch testing to increase throughput
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2 thrusters with low impedance emitters were selected
à Allow to maximize thrust at low powerà Do not allow to reach Isp > 4000s
ESA performance mapping
ESA thrust balance
2 identical thrusters
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ESA performance mapping
ESA thrust balance
2 identical thrusters
thrusters with low impedance emitters were selected
Verification of thrust telemetry with direct thrust balance measurements
From: Krejci et al: Full Performance Mapping of the IFM Nano Thruster including Direct Thrust Measurements, submitted to JoSS
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ESA performance mapping
ESA thrust balance
2 identical thrusters
2 thrusters with low impedance emitters were selected for testing
From: Krejci et al: Full Performance Mapping of the IFM Nano Thruster including Direct Thrust Measurements, submitted to JoSS
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High Dv optimized thrusters
Thrusters currently in delivery: high impedance to increase total impulseHigh emitter impedance selection optimized for high delta V missions
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After full commissioning verifying all subsystems
30 mins firing
Latest inorbit data
3U CubesatSSO orbit
0
20
40
60
80
100
120
140
160
180
200
0 0.5 1 1.5 2 2.5 3 3.5 4
Tem
pera
ture
[deg
C]
Relative time [h]
reservoir_temp
housing_temp
board_temp
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After full commissioning verifying all subsystems
Thrust steps: uncontrolled steps
Latest inorbit data
3U CubesatSSO orbit
0
1000
2000
3000
4000
5000
6000
7000
0
50
100
150
200
250
300
2.5 2.6 2.7 2.8 2.9 3 3.1
spec
ific i
mpu
lse [s
]
thru
st [u
N]
Relative time [h]
thrust thrust commanded specific_impulse
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After full commissioning verifying all subsystems
Thrust steps with controlled transients
Latest inorbit data
3U CubesatSSO orbit
0
1000
2000
3000
4000
5000
6000
7000
8000
0
50
100
150
200
250
300
2.5 2.55 2.6 2.65 2.7 2.75 2.8 2.85 2.9 2.95
spec
ific i
mpu
lse [s
]
thru
st [u
N]
Relative time [h]
thrust
thrust commanded
specific_impulse
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After full commissioning verifying all subsystems
Thrust steps with controlled transients
Latest inorbit data
0
1000
2000
3000
4000
5000
6000
7000
8000
0
50
100
150
200
250
300
2.5 2.55 2.6 2.65 2.7 2.75 2.8 2.85 2.9 2.95
spec
ific i
mpu
lse [s
]
thru
st [u
N]
Relative time [h]
thrust
thrust commanded
specific_impulse
3U CubesatSSO orbit
>5000s Isp operation on a 3U Cubesat!
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Multiple thrusters per week shipped to customers, enabled by standardization and batch testing
Performance mapping at ESA thrust facility provided additional verification of thrust models to measured thrust and showed capability to operate at any operational point within the performance envelope
Double digit number of thrusters in space now, firing tests presented show good controllability of thrust
Operation at >5000s impulse on a 3U Cubesat
Conclusion
High rate
Independently verified performance envelope
In-orbit verification
Record-setting
16 www.enpulsion.comMARKET LEADER FOR SMALL SAT PROPULSIONcompany presentation
