Micropropulsion for NanoSatellites
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Transcript of Micropropulsion for NanoSatellites
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Micropropulsion for NanoSatellites
SNSBs hearing, November 11th 2011
Tor-Arne Grnland
President
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Tor-Arne Grnland
President Tel: +46 8 627 62 00
NanoSpace AB Direct: +46 70 424 41 04
Uppsala Science Park fax: +46 18 55 13 01SE-751 83 Uppsala http: www.sscspace.com/nanospace
SWEDEN e-mail: [email protected]
Point of contact
http://www.sscspace.com/nanospacemailto:[email protected]:[email protected]:[email protected]:[email protected]://www.sscspace.com/nanospace -
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First generation MEMS micropropulsion:
Miniaturised and proportional thrust
Second generation MEMS micropropulsion:
Closed loop thrust control
Other scientific missions
Components
Outline
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NanoSpace
starts
operation
2005
Final delivery
to Prisma
phase B
contract 1st complete
thruster
moduleFirst test of
MEMS
thruster
1 st delivery
of flight H/W
Launch!
2006 2007 2008 20102009
End-to-end
testing on S/C
Core technology developed for Prisma
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Thruster Pod AssemblyPlenty of MEMS inside
Six-wafer-stack MEMS Thruster Chip
= 44 mm (1.73)
Four thrusters per pod
10 N 1 mN
Mass: 115 g
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MEMS Thruster ChipValve package
4 valves/chip
2-way, normally-closed
0 2 mg/s GN2
MEOP 6 bar (87 psi)22x22 mm (0.9)
1.2 mm thick
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Next generationClosed-Loop Thrust Control
ON/OFF
Valve
MEMS Proportional
Flow Control Valve
Mass flow
sensor
Filter
Feed back loopto control FCV
Including front
end electronics
Integrated mass flow sensor provides
closed loop control signal to theproportional flow control valve
Figure: Schematic view of a complete closed loop control thruster.
ON/OFF valve in conventional technology, the rest in MEMS.
Key component:
Integrated MEMS flow control valve
and mass flow sensor
=> Unique performance, enabling new
mission scenarios
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Key capabilitiesLike any other
ON/OFF cycles, full thrust range
0
100
200
300
400
500
600
700
0 10 20 30 40 50 60 70 80 90 100 110 120
Time [s]
Thru
st[N]
Figure: Test result of MEMS thruster operating in ON/OFF mode (open loop, using
solenoid valve only) to show thrust range.
Full thrust can be set in the range 50 micro-Newton to 5 milli-Newton
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Key capabilitiesUnlike any other
Figure: Test result of a MEMS valve operating in closed loop control mode showing the
the thrust response to commanded steps of 5 N.
Low thrust regime step response: 5N steps
0
5
10
15
20
25
45 55 65 75 85 95 105 115 125 135
Time [s]
Thru
st[N]
Commanded ThrustDelivered Thrust
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Unique performance
Figure: Test result of a MEMS valve operating in closed loop control mode responding to
the commanded steps of 0,1 N.
Low thrust regime response: 0.1N steps
4,3
4,4
4,5
4,6
4,7
4,8
4,9
5
5,1
5,2
5,3
40 50 60 70 80 90 100 110 120 130 140 150 160 170 180 190 200
Time [s]
Thrust[N]
Commanded Thrust
Delivered Thrus
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Mission enabling needs
16 closed loop thrust control -thrusters:
0 300 N thrust
0,2 N resolution
250 ms response time
120 million cycles
MICROSCOPE
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QB50: The major Europen nanosat project
Mission ObjectivesQB50 has the scientific objective to study in situ the temporal and
spatial variations in the lower thermosphere (90-320 km) with a network
of 50 double CubeSats carrying identical sensors.
QB50 will also study the re-entry process by measuring a number of key
parameters during re-entry and by comparing predicted and actual
CubeSat trajectories and orbital lifetimes.
TeamingUniversity of Tartu (Estonia), SI-SPACE (Slovenia) and NanoSpace is
teaming up for a joint CubeSat for the QB50 project.
NanoSpace will provide a propulsion module, SI-SPACE will develop
the control electronics and algorithms and University of Tartu will
integrate the satellite.
Objective of technology demonstrationThe objective of the joint CubeSat effort is to demonstrate orbit control
capability with a CubeSat.
Being launched together with 49 other CubeSats does also provide the
possibility of doing proximity operations around another satellite.
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The CubeSat propulsion module
General specification:
Four 1mN thrusters with closed loop thrust control
Thrust resolution:
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Precise control of Xenon flow rate in the range 5 50 g/s (one N-RIT)
Low Flow Control Module - Mini-Ion engines
Specification
Operating media Xenon
Flow Range 5-50 g/sFlow rate resolution 0.5 g/sMass 65 g
Power
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Needed technology:
Low thrust, low noise, highaccuracy, high resolution, short
responde time, high Isp
2 year delay due to:
-Change of microthruster
-Faulty mechanism
Consequence:
-New thruster
-requires new feed system with
precise flow rate < 10 g/s
-Budget implications:
-185 Meuro 2006
-350 Meuro 2011
LISA Pathfinder
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Components
-Isolation valve
-Pressure relief valve-Filters-Pressure sensors
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MEMS isolation valve
An isolation valve near thepropellant tank to ensure
No leak before the system is
operated (similar to a pyro-valve)
A 2 micron filter included
Redundant (2 inlets, 9 outlets)
Chip mass: < 1 g
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Pressure Relief Valve
MEMS devices prov ides mu lt ip le func t ional i ty
To act as passive burst membrane (redundant)
To act as active single shot valve if pressure builds upin system (redundant)
To act as check valve system if opened (actively or
passively) and thus prevent loosing all propellant
To filter the gas passing the check valve
Chip mass: < 1 g
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MEMS FiltersEtched disk technology:
- Filtration rate: 2, 10, 20 micron- Scalable design
- High flow rate/low pressure drop
10m Filter Assembly #1
@ 1.9 Bar and 293 K
-0,008
-0,004
0
0,004
0,008
0,012
0,016
0,02
0,024
0,028
0,032
0,036
0 0,05 0,1 0,15 0,2 0,25 0,3 0,35 0,4
Mass Flow GN2 [g/s]
PressureDrpo[Bar]
Filter Assembly #1 (8 Filter Networks)
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MEMS technology in sensing elementDeveloped by Presens (N)
Unique sensing element Tubular silicon structure Compressive stress
Piezoresistive Wheatstonebridge
P and T measured by same
resistors
Key properties Full-scale up to 10000 bar
(100 000 psi)
Accuracy down to 0,01% of FS
Inherent over-pressureprotection
Insensitive to mounting stress