Adaptation and Optimization of the RIT-µX miniaturized … thrust extended / on request Isp max....
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Hans J. Leiter, Christian Altmann, Ralf Kukies and Jan-Patrick Porst 22 April 2015, Berlin (D)
Adaptation and Optimization of the RIT-X miniaturized Ion Propulsion System for Small Satellites
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Outline
The RIT Propulsion System Family Background and Heritage Selection of Propulsion Systems Cost Driving Elements for Geo Satellites and Scientific Missions System Comparison: (ESA) Science System vs. Small Satellites System RIT-X Performance Finally
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Page 3
Missions and their Propulsion Systems Science, GEO, Interplanetary (Non Small Satellites Applications)
Orbit Transfer GEO Satellites Thrust 300-1000mN Power: 5-20kW
Sun-Moon-EarthPlane
Nodal Line
RIT
EIT
RIT EIT
RIT
EIT
RITEIT
RIT
EIT
RITEIT
Ascending Node
Descending Node
Earth-AeqatorialPlane
Interplanetary Probes Thrust
100-300mN Power
5-10kW
In-Situ Fine positioning and orbital control Thrust:
N-mN Power
50-500W
In Orbit Service GEO Satellites Thrust:
10-100mN Power:
0.5-5kW
LINK to Small Satellites
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RIT-X is embedded in the RIT thruster family
nominal thrustextended / on requestIsp
max. demonstratednom. power
mass
NSSK
Ultra fine thrust control
Primary propulsion4)
Electrical orbit raising5)
RIT-22150 mN
50 200 mN
> 3300 s4260 s1)
4669 s2)
> 6000 s
4580 W2)
4740 W3)
7.7 kg
RIT-1550 mN
10 70 mN> 3300 s
> 4000 s1500 W
2.8 kg
RIT-10/EVO15 mN
5 25 mN 1)
> 3300 s
> 3500 s470 W
1.8 kg
Thruster
Application
RIT-X50 500 N3 3000 N300 3000 s
> 3500 s< 50 W
440 g
1) RIT 10 EVO2) Optimised for Geo3) Optimised for Science4) For Science missions5) For Geo missions6) nominal Operation7) Full Range
RIT-2X>165 mN
>4000 s 6)
3000-4500s 7)
< 4.8KW 6)2-6kW 7)
< 8.8kg
Heavy GeoMedium GeoSmall Geo
Small / Mini Satellites
50 200 mN
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5 March 11, 2014
Requirements (Subset of key requirements) High Thrust Resolution Fast Thrust Response Low Thrust Noise Micro to Millinewton Thrust
Regime Non toxic, inert propellant Direct electric feedback of
produced thrust Free of (magnetic) torque
RIT-X Motivation and Application
Compensation of atmospheric drag
Compensation of space weather
Formation Flying & Distributed Instruments
Actuator for Telecomunication Satellites
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Industrial Approach One Thruster body for different thrust ranges and applications
29 April 2015 6
Airbuss industrial approach bases on one thruster body for all relevant thrust ranges
Needs of science missions are very specific
150-2500N Thrust range has the broadest field of applications
Successful & early in orbit operation and attractive recurring price are key to capture commercial market
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Principle and Heritage
In a first step Xenon is ionized in the electro-magnetic field of an rf-coil Xenon ions are accelerated in the electrostatic field of a grid system (ion optics system) Free of permanent magnets Inherent thrust stability Highly scalable Space proven technology:
Ionisation Acceleration EURECA ARTEMIS
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Standard selection criterion for propulsion technology
8
Specific impulse
Heavy S/C
Low mass S/C
System specific Impulse
First Order: Refined Assessemnt:
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ghts
are
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nted
by
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ery
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Could a new sight to propulsion create a paradigme change?
Propulsion considered expensive and risky
Mission designed to spacecraft prime or operator need
No propulsion Simple and low ISP Systems
Propulsion considered as enabler
Mission designed to USER needs
Higher Orbits Minimized delta-v
Lower Orbits Increased delta v
Relaxed environment for EP electronics
Improved observation performance
Inherent Answer to debris avoidance
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ghts
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ery
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is d
ocum
ent o
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Cost Drivers in RIT for GEO and RIT X Science Systems
29 April 2015
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11
Radiation 15+ years in Geo 6+ years at Lagrangian Point
Liability
RITX: Quality of thrust: N Resolution, Stability, Response, Low Noise
RIT-X: System Complexity Coordinated Simultaneous Operation of 8 and more Thrusters
Drivers are introduced by mission and NOT technology
Mission Specific Qualification
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Comparing two System Approaches
29 April 2015
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12
Power BusPower Bus
Data Bus Data Bus
PPU
RFG
FCU R
FG
FCU R
FG
FCU R
FG
FCU
TSU
FCU
RFG
TSU
FCU
RFG
TSU
FCU
RFG
TSU
FCU
RFG
NSU
FCU
RFG
XeXe
Neutralizer
Distributed TopologyPPU Centered Topology
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Present work is focused on science
29 April 2015
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13
However: With the development of an RIT-X bases neutralizer the work on a Distributed System is started
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RIT-X System Thrust Modulation Capabilities
29 April 2015 14
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Results from AIRBUS DS LET Micro Newton Test Facility (Friedrichshafen, Lake Constance)
29 April 2015
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LET Laboratory for Enablng Technologies Micro Newton Thrust Balance
RIT-X500 performing 1N Thrust Steps (Direct thrust measurement):
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ery
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Results from AIRBUS DS LET Micro Newton Test Facility (Friedrichshafen, Lake Constance)
29 April 2015
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16
RIT-X500 performing 0.1 N Thrust Steps (Direct thrust measurement):
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RIT Work Team Work
29 April 2015 17
University of Gieen Davar Feili, Stefan Weis and Benjamin Lotz Kristof Holste and Peter Khler
All the collegues and friends inside Airbus DS Franz Georg Hey (Friedrichshafen Micro Balance)
All the helpful and highly motivated people and firms not listed her
The German Space Agency DLR
The European Space Agency ESA with special thanks to Alexandra Bulit, Davina Maria Di Cara and Clive Edwards, Niccola Kutufa
Your Feedback is much appreciated ([email protected] )
Thank you for your attention!
Foliennummer 1OutlineMissions and their Propulsion Systems Science, GEO, Interplanetary(Non Small Satellites Applications)Foliennummer 4RIT-X Motivation and ApplicationIndustrial Approach One Thruster body for different thrust ranges and applicationsPrinciple and HeritageStandard selection criterion for propulsion technologyFoliennummer 9Could a new sight to propulsion create a paradigme change?Cost Drivers in RIT for GEO and RIT X Science SystemsComparing two System ApproachesPresent work is focused on scienceRIT-X System Thrust Modulation CapabilitiesResults from AIRBUS DS LET Micro Newton Test Facility(Friedrichshafen, Lake Constance)Results from AIRBUS DS LET Micro Newton Test Facility(Friedrichshafen, Lake Constance)RIT Work Team Work
