using small satellites for new applications: next

Swedish Space Corporation

Using Small Satellites for New Applications:

Next Generation Swedish Space Corporation

Spacecraft

Erik Clacey, Nils Pokrupa, Staffan Persson, Åke Rosenqvist

Swedish Space Corporation – 2006 Small Satellite Conference

Content

IntroductionPrisma – The technology demonstrator

MissionPayloadPlatform

SVEA – A Swedish reconnaissance satelliteMissionPlatformPayload

Conclusions


Introduction


Introduction• Small scientific satellites are key to SSC satellite success for

the last 20 years– Viking, Freja, Astrid, Astrid 2, Odin, Smart-1– Involvement in SES Sirius satellites

• Also: sounding rockets, microgravity payload, stratospheric balloons, satellite TT&C at Esrange Space Center and maritime surveillance

• SSC - a comprehensive space company


Introduction

• New capabilities for small satellites are developed for the Prisma formation flying mission– Uses small satellite philosophy for:

• formation flying development, proximity ranging and novel propulsion technologies

– Launch date: March 2009

• Prisma developed technology used for Svea satellite proposal– High resolution, “low cost”, reconnaissance satellite– Launch date: ~2010 (depending on gov’t decision)

• Prisma and Svea were started on SSC & SNSB initiative


PrismaThe technology demonstrator


Mission


Prisma Mission

• SSC and SNSB has identified the need to provide a dedicated technology demonstrator for new formation flying and propulsion techniques.

• This serves as a precursor to exploration, interferometry and rendezvous missions such as Darwin, Simbol-X and ConeXpress.

• SSC (in co-operation with SNSB, and other European agencies and companies) has created the following manoeuvering experiments to test all of the new developments:– Autonomous formation flying– Homing and Rendez-Vous– Proximity Operations– Final Approach/Recede Manoeuvres

• Program is in Phase C (PDR completed in late 2005)


Prisma Mission


Payload & Platform


Prisma Payload

• Precise formation position determination using RF metrology techniques by CNES and Alcatel.

• Vision based position and attitude determination by the Danish Technical University, using their existing star camera technologies and applying new image algorithms to determine orientation and pose of the second object.

• Precise formation position determination using differential GPS by DLR.

• HPGP – or “high performance green propulsion” – thruster system being developed by SSC.

• Micro thrusters using MEMS technology and xenon cold-gas being developed by NanoSpace AB (subsidiary of SSC).


Prisma PayloadPayload SpecificationFFRF Range: 100m to possibly 30km

Accuracy: <150mmVision Based Range: 0.1-10m (short) & 10m to ???km (long)

Accuracy: <1.0mm and <0.5degGPS Range: determined by the ISL range

Accuracy: 5cm to 2mHPGP <1.0NMEMs cold-gas 10µN to 1.0mN

44 m

m

HPGP test firingMEMS cold-gas thruster


Prisma Payload

• The status of the various payloads are: – A breadboard FFRF package has been developed and proven

on an ESA contract and presently CNES is developing the flight hardware.

– The Vision Base system is based on using the existing micro Advanced Stellar Compass recently developed by DTU. Presently DTU is developing the algorithms required for object recognition.

– The GPS system is assumed to be the baseline navigation system.

– The 1N HPGP EM has gone through 17000 pulses, 400 thermal cycles, and run for over 3 hours continuously.

– The 1mN MEMs cold-gas EM system has been built and is under development testing.


Prisma Platform

Short range VBS camera

Micro-propthruster pods

RF metrologyantennae

Long range VBS camera (using LEDs)

HPGP thrusters

1.35

m


SVEAA Swedish reconnaissance satellite


Mission


SVEA Mission

• Svea may become a national reconnaissance satellite for Swedish governmental and nongovernmental agencies– Support defense, national and international crisis management

• Response to gov’t inquiry on the need and feasibility– SSC and SAAB Ericsson Space

• Svea will:– Reduce reliance on other systems– Reduce time delay between image request and delivery– Increase reliability, integrity and security on sensitive data– Reduce cost by using existing technology from Prisma

• Show that a reconnaissance satellite can be competitive, cost effective and efficient when developed as a small satellite


SVEA Mission

Customer requestsand prioritization Misson planning TT&C

Data aquisition andstorage

Preprocessning of data(Radiometric och

geometric corrections)

Satellitehousekeeping and

system checks

Tele

met

ry

Image data

CommanduplinkTarget list Mission

commands

Data distribution tocustomer

Customer

Satellite

Processes encompassed bySvea

Svea data flow


SVEA Mission

• Sun synch orbit @ 500-700 km– 14-15 rev/day– Global coverage– 5 year lifetime

• Spatial ground resolution 1-2 m(~39-78 in) in nadir• Esrange ground station• Flexible and agile platform ±45o

stereo image capability• Pointing accuracy 15-20 m


Platform


SVEA Platform

• Clear and focused mission requirement– Reduces complexity– Limit non-mission critical functionality– Requires optimization tradeoff

• May not be the most elegant but it does the job– Thus can cut costs for new developments

• Prisma platform as baseline– AOCS inc. software– Propulsion – HPGP/Hydrazine– Data handling – LEON 3– Passive thermal rejection

• Addition of 60-100 Gbit mass memory


SVEA Platform

1.5m1.2m

1.1m

Sunsensor

High res. camera

HPGP

Startracker

GPS

1 Mbps S-band

60-100 Mbps X-band

Launcher interface


Payload


SVEA Payload

• Stand alone COTS unit– RGB + NIR– 1-2 m PAN / 3-6 m XS– 50-80kg– 10-15 km swath width– ~740 km swaths/orbit is foreseen

• Future payloads may include TIR and SAR– Wide range of satellites/payloads will complement each other


SVEA Payload

• Improve signal-to-noise ratioPitch Control Maneuver Time delay Integration

Satellite motion

15 km

Image acquisition time: ~4 seconds Image acquisition time: ~2 seconds

Satellite motion

15 km

0 100 200 300 400 500 600 700 800 900-50

-40

-30

-20

-10

0

10

20

30

40

50

degr

ees

seconds

angle reference


Conclusions


Conclusions

• Small satellites, such as Prisma and Svea– Enable quick and cost effective development of key future

technologies– Showcase technology– Efficient reuse of technology demonstrators– Cost efficient

• Faster turn-around time– Effective test for formation flying and rendezvous missions – High resolution imagery with COTS technologies

• Smaller space nations can have independent image source• Proliferation international disaster and crisis monitoring


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