In Orbit Demonstration activities
F. TestonSystems, Software and In-orbit Demonstration DepartmentDirectorate of Technical and Quality ManagementH2020 IOD Workshop - 17/11/2015
IOD Definition and Objectives
ESA’s past experience in IOD
IOD in GSTP
Examples of technology
Examples of IOD mission studies
AIM
CAPTARE
Cubesats and IOD
Summary and Conclusions
IOD in the Directorate for Telecommunications and Integrated
Applications
IOD Definition and Objectives
Why In Orbit Demonstration ?
• A number of European technologies in particular generic technologies
and techniques supporting industry competitiveness, require in orbit
demonstration to achieve and demonstrate their maturity
• A number of mission concept require validation in space before being
used in applications and main stream missions
• A number of space companies want to acquire/demonstrate space
experience
• Allow using new engineering and development methods in real cases
IOD Definition and Objectives
How In Orbit Demonstration ?
• Experiments on carrier of opportunities (Space Shuttle payload
facilities, Foton, Columbus Laboratory/International Space Station,
spacecraft),
• Experiments on launchers,
• “Complete” space missions “dedicated” to technology and techniques
demonstration (e.g. P3),
• Cooperative space missions with technology demonstration and
mission concept/technique validation (e.g. P2, PV).
• IOD has not been performed as “black-boxes” passengers,
• IOD missions have supported the concept of high performance small
missions.
IOD Definition and Objectives
In Orbit Demonstration is part of generic technology programs at ESA:
• Identification of technologies and techniques requiring in orbit
validation (inputs from industry, agencies and projects),
• Maintenance of a TFO database,
• Coordination of related initiatives and flight opportunities,
• Definition of dedicated technology demonstration missions (PROBA
like) and realisation in partnership with technology contributing
entities,
• Cooperation for combined missions, application and technology,
• Review of in orbit technology results and preparation of lessons learnt
for future users (workshops),
• Identification of funding mechanisms in particular for the non
noble/technological parts.
ESA’s Experience in IOD (1)
Technology Demonstration Programme (TDP)• Started in 1987 as optional programme• Objectives:
– TDP ensures timely availability of the necessary technology for the Agency Programmes
– To maintain a high level of competence in space technology in Europe
• Provided technical support & ESA funding for qualification and flight20 technology experiments flown as piggy-back– Using mini satellites as carrier (SMART, MITA, STRV, BREMSAT…)– As barter agreements with NASA, JAXA…– As standalone experiments launched at low cost (NPO-PM)
Technology Flight Opportunities (TFO)
• Flight opportunities funded by GSP
• Management of Flight Opportunities Initiative
• Implementation of IOD on ISS and Shuttle flights
ESA’s Experience in IOD (2)
General Space Technology Programme (GSTP)• GSTP 4, 5 and currently 6• Objectives:
- IOD using carriers of opportunity and small missions,- Study for IOD National programs,
• Provided technical support & ESA funding for qualification and flight- Using small satellites (PROBA 1,2,3,V)- Using carriers of opportunities (ISS, …)
BUT
IOD is also performed by mission programs:- LPF from the Science Directorate,- IXV from the Launcher Directorate,- Earth Explorer missions from Earth Observation Directorate,- LLMS, ALPHASAT, ATLAS from Telecommunication and Integrated
Application Directorate
IOD TDP/TFO (since 1987)• Transputer and Single Event Upset Experiment (UoSAT-E in 1990)• Solid State Micro Accelerometer (Get Away Special GAS-021 on STS-40 in 1991)• Attitude Sensor Package ASP (Hitchhiker on STS-52 in 1992)• Two Phase Flow Experiment TPX (GAS-557 on STS-60 in 1994)• Two Phase Flow Experiment TPX Re-flight (GAS-467 on STS-95, 1998)• Materials Deposition in Orbit EDMO (GAS-485 on STS-64 in 1994)• Liquid Gauging Technology Experiment (GAS-022 on STS-57 in 1993)• Inflatable Space Rigidising Technology Sample ICE (launched on EURECA STS-46 in
1992 and retrieved on STS-57 in 1993)• Atomic Oxygen Detector OXFLUX (BREMSAT on STS-60 in 1994)• Gallium Arsenide Solar Array Panel (STRV-1A in 1994) • Radiation Environment Monitor REM (STRV-1B in 1994)• Standard Radiation Environment Monitor SREM (STRV-1C and -1D and MIR)• Battery Recharge Experiment BRE (STRV)• Control Flexibility Interaction Experiment CFIE (GAS-515 on STS-69 in 1995)• Discharge Detector Experiment DDE (NPO-PM communication satellite in 1997)• MTS-AOMS (TFO, MicroTechSensor for Attitude and Orbit Measurement System) on
MITA 2002• Com2Plex Two-Phase-Flow Experiment on STS-107 Columbia January 2003• Sloshsat-FLEVO, a small satellite for liquid sloshing test in 0-g, (Ariane 5 ECA V164,
Feb 2005)• MABE Magnetic Bearing Experiment flown on Airbus 0-g June 2005• EuTEF Technology Exposure Facility mounted outside Columbus module on ISS
ESA’s Experience in IOD (TDP/TFO)
ESA’s Experience in IOD (TDP/TFO)
ASP on STS-52 (1992)
DDE (1997) Sloshsat FLEVO on A5ECA (February
2005)
EuTEF for ISS (Oct. 2007)
Com2Plex on STS-107 Columbia (January
2003)
ESA’s Experience in IOD – EuTEF
• Infrastructure to provide accommodation for up to 9 experiments, located on an Express Pallet Adapter (ExPA) on the COLUMBUS module of the ISS
• A DHPU (Data Handling and Power Unit), supplies power and manages TM/TC of the individual experiments.
• EuTEF is designed for a high degree of flexibility and modularity to allow and support quick turn-around times of experiments
First Satellite studying fluid behaviour (sloshing) in weightlessness
ESA’s Experience in IOD – SLOSHAT - FLEVO
Description:
• Total mass 129 kg
• Launched Feb-2005
• Ariane-5 ECA
• Operated for 2 weeks
• GTO (250 x 35941 km)
• Results in exploitation
• PROBA 1 launched in October 2001,
• PROBA 2 launched in November 2009,
• PROBA V (Vegetation) launched in May 2013,
• PROBA 3 Formation Flying Demonstration in implementation phase,
• “Small missions” (1,2,V) of ~100 kg class
• Designed to demonstrate in orbit platform and payload technologies,
• Designed to accommodate a user program exploiting the data
provided by the spacecraft payload (Earth Observation for PROBA 1
and V, Sun monitoring for PROBA 2 and 3).
• PROBA missions are mainly funded through the optional GSTP
program.
ESA’s Experience in IOD – PROBA missions
PROBA 1
Development: 1998-2001
Mission: 2001 – still fully operational
PROBA 2
Development: 2004-2008
Mission: Nov 2009 - …
PROBA 3 – in preparation (CD)
Mission: foreseen 2018 - …
PROBA V (C/D)
Development: 2009-2012
Mission: 2013 - …
Sloshat- Flevo
Mission: Feb 2005
PROBA missions
Technology demonstrator for autonomous operations and Earth observation
Technology Demonstration / innovations:
• Autonomous on board flight dynamics (position, attitude and maneuver determination)
• Avionics technology (ERC32, DSP, 3D modules)
• Low cost autonomous star tracker for attitude and rate
• Gyro-less maneuvering satellite
• Software methodology (auto coding and SVF)
• Battery technology (Li-ion)
• New instruments and sensor test (HRC, MRM, PASS, SIPs)
• Common ground infrastructure (EGSE and mission control centre)
• Ground segment automation
• Compact High Resolution Imaging Spectrometer (CHRIS)
• Radiation (SREM) monitor
• Debris (DEBIE) monitor
PROBA 1
• PROBA – 1 carries a guest payload,
the Compact High Resolution
Spectrometer (CHRIS)
• CHRIS benefits from PROBA-1
technology features, autonomy,
agility, precise AOCS
• Exploited by EOP, PROBA-1
provides data to 160 Cat I projects
based on CHRIS
PROBA 1 – user point of view
Technology demonstrator for autonomous operations and Sun monitoring
Platform:
• lithium-ion battery,• advanced data and power management
system based on LEON• combined carbon-fibre and aluminium
structural panels, • new miniature reaction wheels • Miniaturised star tracker • COTS based GPS receivers• digital Sun-sensor• dual-frequency GPS receiver• fibre-sensor system for temperatures and
pressures • APS based star-tracker (BepiColombo)• New 3 axis magnetometers• very high precision flux-gate magnetometer• Solar panel with a solar flux concentrator• solid-state nitrogen gas generator• exploration micro-camera (X-CAM)• new GNC algorithms
PROBA 2
Science Grade Vector Magnetometer
Bepi Colombo Star Tracker
SWARM
ESA’s Magnetic Field Mission
BEPI COLOMBO
ESA’s Mission to Mercury
Topstar GPS
New generation GPS, with increased accuracy (L2C band). To be used on future missions
ADM-AEOLUS
ESA’s Wind Mission
Credit Card Magnetometer
Following PROBA 2 launch all Technology Demonstrators have been checked-out successfully and are demonstrating their capability for future missions:
Payload:
• SWAP - Sun Watcher using APS detector and image processing, based on new detector and providing high acquisition rate.
• LYRA - Lyman Alpha radiometer using a new type of detector.
• DSLP - Dual Segmented Langmuir Probe for plasma charging measurements
• TPMU - Thermal Plasma Measurement Unit
• SGVM - Science Grade Vectorizedmagnetometer (high accuracy)
• PROBA-2 is first satellite of the Space Situational Awareness Programme. PROBA2 Science Centre is hosted at the Space Weather Center in Brussels
PROBA 2 – user point of view
Gap Filler for Vegetation Mission -> COPERNICUS
OPERATIONAL MISSION
PROBA V
138 kg
800X800X1000mm
Advanced avionics
Autonomy
3-Axis Stabilised
S-Band (TM/TC)
X-Band (PL Data)
Vegetation Instrument
SWIR detector
Wide angle TMA
Technology Payloads
Technological Payloads
1.Gallium Nitride X-Band Transmitter (F)
Is a X-Band transmitter based on GaN RF amplifiers.
2.Energetic Particle Telescope (EPT) (BE)
An ESA newly developed radiation monitoring .
3.Automatic Dependant Surveillance-Broadcast (ADS-B) (DE)
Demonstrate the feasibility of a space based air traffic surveillance
technique.
4.SATRAM (CZ)
Radiation monitoring based on new type of radiation sensor
5.HERMOD (NO)
Demonstrate the utilisation of multi-fibers connectors in Space environment
PROBA V Technological challenges
• From a payload of 160 kg / 150W to an instrument of 30kg / 30 W
• From a payload of 0.7x1x1 m to a full spacecraft of 0.7x0.7x0.8 m
• Very large field of view (102° so 2250 km on earth) with a compact
instrument using advanced new technologies
• Very short development time compared to normal space mission: start of
development Jan 2009 and launch May 2013.
Critical technologies for the Proba-V Instrument have required early pre-developments:
TMA telescope: Mirror manufacturing and
alignment for a TMA with a field of view of 34°
SWIR Detector: Develop a 3000 pixels SWIR detector
Vegetation technology developments
Proba-3 a breakthrough in space
• Proba-3 is a mission for in-orbit demonstration of techniques of satellite precise
Formation Flying (FF) and the concept of distributed instruments. FF is the
operational technique by which separate spacecraft maintain a pre-defined
geometry with high accuracy as a single virtual satellite.
• Proba-3 demonstrates:
Technology and products, for the formation flying itself, including space
products and ground products such as FF system test bed,
Techniques, i.e. mission concepts including distributed instruments
– For research, interferometry, coronagraphy (in this case): very
large focal length telescopes, very long gradiometers and very
large structures in space; e.g. for astronomy, planetology, remote
sensing, etc.
– For operations in orbit: FF, RV, proximity operations, convoy flying,
very high precision relative navigation and control, as required for
Exploration, CleanSpace, etc.
DDV and operation approaches, e.g. use of models, integrated
system/SW
PROBA 3
• Proba-3, in development
• the power of 2 satellites to
synthetise missions unaffordable to
even the largest systems,
• New architecture / system
concepts, distributed instruments,
• New technique: satellite precise
formation flying, to overcome the
limitations of monolithic or
deployable structures,
• Two small satellites flying in formation 150 m
apart with mm and arcsec precision to
synthetise a distributed instrument, a giant
sun coronagraph to produce the perfect
eclipse, observing the sun limb to the lowest
tangent point improving significantly the
performance of previous missions (e.g.
LASCO on SOHO)
Proba-3
± 0.7 mm
30 arcsec
Target vector oriented towards sun
Inter Satellite Distance: 150 m
Required Position control
Lateral: 0.7 mm (1 @ 150 m ISD)
Longitudinal: 1.5 mm (1 @ 150 m ISD)
PRECISE FORMATION FLYING The relative lateral and longitudinal positions are controlled The absolute attitude is controlled The « line of sight » of the formation is controlled A virtual large and solid structure is built and oriented
± 0.7 mm
PROBA 3 Mission overview
Small missions the right approach to IOD
Why are small missions important for ESA ?
Small missions allow to test new space technologies and techniques
They serve targeted scientific applications
They foster efforts of national industries in delivering a complete space
system
Small missions are small in size but real space missions in all extent
requiring high tech industry to achieve them
They provide high visibility to a country
They provide opportunities for creating links between industries of ESA
member states
Recently cubesats projects have also been initiated.
Recent IOD on carrier of opportunities
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Demonstration of AIS signal detectionfrom space:
Verify signal environment
Receiver technology
As a first step, reception of AIS signals from space is being demonstrated on Columbus, together with SDR and algorithms,
AIS on ISS : Maritime surveillance
AIS on ISS : Maritime Surveillance
2 versions of an AIS receiver were uploaded to the ISS, allowing also investigation and improvement of performances.
ADS-B on PROBA V : Air traffic
Proba-V ADS-B unit (Automatic Dependant Surveillance-Broadcast – from DLR)
is meant to demonstrate the feasibility of a space based air traffic surveillance
technique.
Proba-V ADS-B is continuously active and acquiring data, and data processed by
the SES ADS-B User Segment (L).
• SMART-1, launched 2003, is the first ESA mission to the moon
• The < 370 kg spacecraft demonstrated
technology, ion propulsion, miniaturised payloads
techniques and environment, low thrust travel to the moon, autoguidance, communications, electrical environment
significant scientific results with its 5 scientific instruments
IOD in programs
GIOVE-A is achieving its objectives of
Securing frequency filings,
Validating key technologies such as the rubidium clocks,
Experimenting with the reception of signals from Medium Earth Orbit (MEO) orbit,
Characterizing the MEO environment using two different radiation monitoring instruments,
Experimenting with the signal using two transmission channels in parallel.
GIOVE-A has demonstrated new approaches to development, verification and operations
Programmatic Framework (1)
IOD Programmatic Needs
1. suitable Programmatic Framework to be responsive and offer opportunities at reasonable cost,
2. supports other Programmes of the Agency
3. provides a natural follow-on to technology development activities
4. allows technology precursor missions as well as technology demonstrations mission on a regular basis
5. provides balanced opportunities to participating Member States, in terms of leadership, quality of the
contribution, return and procurement from the Industrial Team
6. allows Member States to provide In-Kind-Contributions resulting from national activities
Experience from previous programmes
1. Individual In-Orbit Demonstration Programme (e.g. TDP) is not necessarily offering a self-sustaining
framework providing Member States with the needed flexibility and responsiveness
2. Technologies at lower maturity level often need dedicated development effort before embarking on an
IOD Mission
3. Lack of regular IOD opportunities leads to lack of perspective and phasing issues between technology
developments and in orbit opportunity
4. Lack of regular IOD opportunities does not also allow to reduce high costs for common elements like
launcher, ground segment and operations
Programmatic Framework (2)
IOD - History and Outlook
1. TDP (1992 - 1997)was supposed to offer an adequate framework for IOD, however only
very limited interest and funding was raised (about 2 M€ p.a.)
2. GSTP2 (1996 - 2000) was considered to accommodate the objectives of TDP, thus leading
to some selected IOD support, worth to mention PROBA1 (about 5 M€ p.a.)
3. GSTP3 (2001 - 2004) continued with one main IOD project, PROBA2 and EXPERT
(demonstration of re-entry technologies), average funding per year about 8 M€
4. GSTP4/5 (2004 - 2013) dedicated elements for IOD, supported PROBA-V and technologies
related to in-orbit demonstration and initiated cubesat activities.
5. GSTP6 (2014 – on going) dedicated elements for IOD, supporting in particular PROBA3.
Within GSTP (optional program) most of the ESA participating and associated States
have been involved and contributed to IOD activities.
Programmatic Framework (3)
Procedure
1. ESA regularly prepare and issue calls for In-Orbit Demonstration proposals and
conduct the selection process
2. ESA maintain a repository for IOD demands and IOD offers
3. ESA propose for approval by Participating States the IOD candidates for
further analysis in a “Definition Phase”
4. After completion of the Definition Phase, ESA propose for approval by Member
States the IOD candidates selected for implementation
GSTP – STRUCTURE FOR PERIOD 6
WP activities + Announcement of Opportunity (AO)
WP activities – Including cross cutting initiatives.
Status end of June 2015: • 200 activities approved
GSTP-6
Element 6.1Support
Technology for Projects & Industry
Element 6.3Technology Flight
Opportunities
Element 6.2Competitiveness
Announcement of Opportunity (AOs). Unsolicited proposals from Industry. Co-funding (50%, 75%, 100%)Status end of June 2015: • 53 activities
Precise Formation Flying DemonstrationElement 6.4: Ph. CDE Proba-3Potential other missions in study
GSTP-6 E1 – Support technology activities for projects and industry
• Development of technologies and products for projects and
industry, from low TRL to qualification. Target TRL 4-6.
• Platform, Payload, Ground Segment, and Engineering tools
• Technology spin-in.
• Compendium sent to Delegations and published on EMITS News
to enable Delegation/Industry dialog, and expressions of
support.
• Regular update of Work Plan according to support expressed by
Delegations.
GSTP-6 E3 – Technology Flight Opportunities (TFO)
• In-orbit Demonstration of technology and products
• Target TRL is 7-8
• Essential for products requiring flight heritage for commercial customers
• Development and consolidation of capabilities in Member States
• Does not include technology development (shall be E1).
• Needs are identified systematically as part of technology roadmaps.
• Flight opportunities are identified with ESA projects and launches, with
National agencies and with primes, and with commercial missions.
• Special relation is established with National programmes with demonstration
objectives.
• Call for flight needs and opportunities published in ESA web site (TFO
database).
TFO database
• An “Open Call for Technology Flight Demonstrators and Carrier Flight
Opportunities” is implemented for the entire GSTP Period 6
• It is supported by an on line data base accessible to flight opportunity
providers as well as “requesters” since Nov 2013
• TFO publicized internally, via ESA website, TAWG and workshops
• Technology developments are on going and a survey of last GSTP
developments show that > 40 activities could have been candidate TFO’s
(it is probably the same in other ESA R&D programs and National
programs).
• Flight opportunities are difficult but do exist, there are margins on
spacecraft, on launchers, ISS can accommodate experiments, …
• ESA believes that there are lost opportunities and with a wider knowledge
of candidate technologies and flight opportunities there could be a
significant improvement -> GSTP-6 Elt-3
IOD in GSTP (SMOS example)
Component Building Blocks Equipment Sub-SystemEE
Mission
Component Building Blocks Equipment Sub-System
IOD in GSTP (PROBA V example)
IODPrecursorGap Filler
IOD next …
System studies on IOD initiated following a CFI in GSP:
• Mars Sample Return IOD
• Ion Beam Shepard IOD
• Integrated THz Mission for Atmospheric Sounding (LOCUS)
• Precursor for Real-time Operations in Maritime Protection and Tracking (PROMPT)
• Precursor for Maritime surveillance mission based on the NAVRAD payload (NAVRAD
mission)
• M2M IOD
Previous IOD system studies:
– Satellite Based Space Surveillance,
– GNSS reflectometry,
– ADSB demonstration mission
– AIS (Maritime Surveillance),
– FMP (Frequency Monitoring),
– Altius (Athmospheric Chemistry),
– Inter Planetary small mission,
Demonstration Technology Techniques Relevance
AIS - sensitive VHF receivers, antennas, software radio, - data processing, FPGA
- signal intelligence - Civil Security - IAP
ALTIUS (same name as
National mission)!
- AOCS Agility, autonomous pointing and co-
registration,
- Acousto-optic tunable filters, row-dependent
sensitive detectors, - ASICS, FPGA
- Limb –fore-back- side-
hyperspectral imaging
- Autonomy and agility
- Surveillance of space
- Atmospheric chemistry
SBVS - wide field imager, curved arrays
- low light detectors, - mini lidar
- Image intelligence
- Tracking
- Surveillance of Space
- Atmospheric imaging
FPS - RF technology,
- software radio, data processing, FPGA
- Electronic intelligence - Civil Security
- IAP
MM-wave synthetic approach
- mm-wave technology, Schottky - data processing, ASIC, FPGA, optical harness
- aperture synthesis - interferometry
- Civil Security - (meteo)
Paris - GNSS receiver, antenna technology, ASIC - GNSS reflectometry - Ocean Forecast
- Civil Security
Large antennas - Materials, mechanisms, AOCS - deployable
- inflatable
- Signal intelligence, security
- telecommunications, EO
Neo-demo - Micro-nano technology, several PF and PL - RV, proximity operations, fly
around, autonomy, manufacturing,
AIV technology
- Exploration
- Surveillance of Space
NightSideObserver Ultra-fast, wide angle optics, detectors Detection fast objects, e.g. meteorids
and observation clouds, auroras,
Security, Surveilance, meteorology
EXTRAS / quantum
entanglement
Clocks, quantum entanglement for synch Navigation, security
Mars Relay Satellite (not in Mars orbit) – blocks
only
Ultra-light structures, thermal protection, GNC, AOCS, power, data handling (SOC), antennas, RF
sources,
Aeroassist, new RF bands, Exploration, communications, security, EO
examples
IOD workshop 2008
The Proba Next missions
Remote sensing:
1. Small Proba-Next based satellites can be flown in
tandem / convoy with larger operational satellites
and deliver totally new missions.
a. Proba-A (atmospheric), Proba-Next
would carry the ALTIUS instrument, a
limb imager capable of operating as well
in occultation mode to retrieve a number
of GCOS variables
b. Proba-R (radar), Proba-Next would
carry a radar receiver to exploit in bistatic
configuration the radar signal of the L-
band SAR of the Argentinian SAOCOM
c. Proba-T (thermal), Proba-Next would
carry a sensor operating in the TIR and
possibly MIR and fly in formation with
Sentinel 2 thus enhancing the product
portfolio
CSSAOCOM
SAOCOM CS
Altius with MetOp
Objective: ocean mesoscale altimetry demonstration, ice topography, soil moisture, ionospheric monitoring
Challenge: • Payload: antenna, receiver and processing technologies, • Platform: avionics, OB-SW, micro-propulsion, AOCS
Status• Now GEROS on ISS
ESA Don Qiuixote concept
nadir track
tracks of PARIS
glistening points
nadir track
tracks of PARIS
glistening points
PARIS
PAST FUTURE
Limb scan
Filter or grating spectrometers
No gradients
Full 2-D limb imaging
Acousto-optical filters
Horizontal gradients
ALTIUS uses the simple concept of a spectral camera, i.e., a combination of an AOTF filter with a 2-D imager
ALTIUS
SAOCOM – CONAE’s L-band SAR
• Two satellites, SAOCOM-1A/1B, fly in constellation with COSMO-SkyMed
L-band SAR at 1275 MHz, bandwidth up to 50 MHz
peak RF transmit power 3.1 kW
antenna dimensions 10 m x 3.5 m
fully polarimetric, interferometric capabilities
multiple modes (Stripmap, TOPS)
• CONAE offered free launch of a small satellite
together with SAOCOM-1B, provided it enhances its science return
ESA proposed a passive bistatic SAR enhancing the SAOCOM mission return
Courtesy of CONAE
SAOCOM-CS as in-orbit demonstrator
SAOCOM-CS will be a demonstrator for :
- at science level, biomass observations from SAR interferometric
tomography and many other new observations from various bistatic
geometries
- at observation technique level, passive bistatic SAR with small
satellites flying in tandem with SAR satellites, including much new ground
processing; e.g. similar concepts can be applied to C-band (Sentinel-1), etc
- at technical level, formation flying design and operations up to
small separation (some km) and synchronisation between add-on passive
satellites and SAR satellites, without special requirements on the latter and
with operations in different control centres
Space based observations for SSA
Possible Objectives:
Observation of Earth Orbital Population complementary to ground based systems for Space Surveillance and Space Situational Awareness
Orbit determination of objects
Observation of debris/space weather
High resolution imaging and/or photometry in combination with spectroscopy of Earth Orbital Population objects
RF Frequency patrolling
Mission:
LEO
Technology:
Short term: demonstration of Space Surveillance. Basic technology available.
Medium term: high resolution imaging based on light-weight, multi-aperture instruments
SBSS
PROBA-InterPlanetary
Upcoming Phase A (GSP) Study:
Following previous ESA Study Activities in the
same domain (DQ Ph.A and CDF Studies),
Preliminary design of a low-cost precursor
mission in the frame of IOD series.
Main Objectives:
Assessment of capabilities of microsatellite
platforms (< 300 kg w/m) in the frame of non-
Earth-bound missions targeting minor celestial
bodies (NEOs),
Platform mass minimisation (wrt current
minimum assessed value of >500 kg) with
maximum use of advanced/ miniaturised
technologies and tight requirements control,
Mission operational costs reduction using S/C
autonomy at maximum possible extent in all
mission phases.
New IOD missions (now AIM)
In orbit demonstration and cubesats
• CubeSats may serve several objectives in the context of
IOD at ESA:
A driver for drastic miniaturisation of systems, and
totally new approaches to packaging and integration,
with benefits for larger systems
An opportunity to demonstrate innovative
technologies in orbit at a low cost and fast pace
An opportunity to carry out distributed in-situ
measurements of the space environment
simultaneously
Potential to deploy small payloads in a constellation
or swarm system, where the potential deficit in
performance may be largely compensated by the
multitude of satellites
CubeSat and IOD
Credit: ISIS
Technology IOD
(cubesat)
Techniques IOD
(cubesat)
CUBESATS IOD MISSIONSIN DEVELOPMENT
GOMX-3 Mission (launched and commissioned)
• Contractor: GomSpace (Denmark)
• 3U CubeSat telecommunications payload demonstrator
Improved Detection/de-coding of ADS-B signals broadcast by aircraft
Characterisation of Spot beams broadcast by GEO telecom satellites
Primary Payload: L-band Reconfigurable Software Defined Radio receiver
Additional payloads: 3-axis ADCS, Syrlinks X-band transmitter
Launch to ISS via GomSpace/NanoRacks on 16 August 2015
Deployment during Short Duration Mission of ESA astronaut Andreas Mogensen
Credit: GomSpace
• Contractor: Von Karman Institute (Belgium)
• Atmospheric re-entry demonstrator
New heat shield materials -> ablation, plasma field measurements
Aerodynamic drag augmentation and passive attitude stabilisation system
Telemetry data relay system during re-entry via the Iridium constellation
Launch on QB50 flight in 2016 to 380 km altitude, 98° inclination
Platform: custom, subsystems from various suppliers
QARMAN Mission
Credit: VKI
Status: CDR passed
• Contractor: Royal Meteorological Institute and KU Leuven (Belgium)
• Sun-Earth radiometric science demonstrator:
Measure the Essential Climate Variables of Total Solar Irradiance, Earth Radiation
Budget and Sun-Earth radiation imbalance
Payload: absolute cavity radiometer (RMI), 3-axis ADCS with star tracker (KUL)
Platform: 3U CubeSat (ISIS)
Heritage: Sova-P instrument on CNES Picard mission; Diarad on SOHO
Launch: TBC in 2016 to SSO <600 km
SIMBA Mission
Credit: RMIB
Status: CDR in 2015
• Contractor: Belgian Institute of Space Aeronomy (BISA), VTT Finland, Clyde Space UK
• Atmospheric chemistry science demonstrator
Limb sounding of solar disk with a compact multi-spectral imager -> Stratospheric Ozone
distribution & Mesospheric Temperature profile
Development/demo of the VISION multi-spectral imager based on MEMS Fabry-Perot
Interferometer technology funded by TRP (VTT)
Electron density in the ionosphere with Sweeping Langmuir Probe (BISA)
Platform: 3U CubeSat (Clyde Space)
Launch: TBC in 2016 to SSO <600 km
PICASSO Mission
Credit: BISA
Status: CDR in 2015
OPS-SAT Mission
• A representative (but low cost, cubesat based) platform for in-orbit
demonstration of innovative operations concepts for future ESA missions
• Accept risks, expect failures, ensure recovery
• ESA will capitalize on past investment, demonstrate what works and what
doesn’t. Industry will get freedom, a platform, a reference story and contacts.
• CDR in 2015
Spacecraft highlights: • Powerful processing core (Dual core 800 MHz
processors + integrated reconfigurable FPGA)• Camera (<80m ground resolution, video) • Fine ADCS with star tracker (<<1°)• X band down (50 Mbps) • S band up/down (CCSDS compatible)• Optical uplink
MISSION STUDIES
• Contractor: Swiss Space Center, EPFL
• Objective:
IOD and operational validation of critical ADR technologies
at sub-scale for future use on full-scale ADR missions
• CADRE 1 mission concept:
Rendezvous sensors (Flash Lidar, VIS/IR cameras, radar)
Inspection/Motion reconstruction of uncooperative target
• CADRE 2 mission concept:
Net capture system dynamics & target interaction
Coupled two-body tether dynamics and control
• System concept:
8U Chaser satellite + 4U Target satellite
Coupled together and launched in 12U deployment system
Low velocity mutual separation after LEOP
Close proximity ops with 6 DoF chaser around “passive”
target with settable attitude rates
• Next steps: CADRE 1 Phase A/B & Tech Development
CubeSat Active Debris Removal Experiment (CADRE)
Credit: Swiss Space Center
Status: study completed Sept 2014
Nano-satellites for Commercial Telecommunication Services
• ARTES 1 Study
Any revenue generating service from
telecom (e.g. M2M, signal detection,
frequency monitoring etc)
Assessment of technical feasibility and
commercial viability of selected concepts
Single nano-satellites or nano-satellite
constellations
CubeSats or other form factors up to
12U/16 kg
Status: Open competitive Invitation To
Tender, contract awarded to Clyde Space
Remote Sensing with MultipleCooperative Nanosats
• GSP SysNova Challenge
High spatial or temporal resolution data
products enabled by nanosat constellations
or swarms
Areas:
o Land (hyperspectral Vis/IR optical)
o Atmospheric Chemistry (NO2 optical)
o Weather (Radio occultation, passive
microwave)
CubeSats or other form factors up to 20 kg
System ROM cost <60 MEuro
Open competitive Invitation To Tender
4 parallel studies awarded
ESA CDF concurrent review study for the
joint winners:
o ORORO (SSTL/UK Met Office)
o HAPI (TAS-UK/Uni.Leicester)
Interplanetary CubeSats supporting the Asteroid Impact Mission (AIM)
ESA AIM spacecraft observes nearby impact
NASA DART spacecraft impacts binary asteroid [65803] Didymos in 2022
Announcement of Opportunity for CubeSats to enhance mission return
GSP Sysnova challenge:5 parallel studies to be awarded, then CDF study
Why IOD missions should NOT be done ?
• Most ESA missions are demonstration missions anyway,• In-orbit demonstration missions are as expensive as a real mission:
costs of launch, bus, operations, internal costs. Reducing costs may increase risk and “failure is not really an option”,
• In orbit demonstration results are not exploited (no target, not timely, …) or not useful,
• IOD missions compete for space budget with “real missions”.
IOD FAQ from past experience
Why IOD missions should be done ?• An increase shall be expected in spin-in ground technologies to space; in
orbit demonstration could be a cost effective way of showing their suitability for space,
• Some techniques are instrumental for expensive missions but can not be acquired with sufficient confidence on ground, e.g. PROBA-3 FF, RVD, PROBA-1 BRDF,
• Some technologies require real in orbit environment, GPS, star tracker, GNC,
• Sometimes precursors are beneficial before committing a large investment, e.g. Giove
• Some development approaches enabled by new D&D and AIV techniques need to be tried for real in “simple” but representative missions – e.g. PROBA-1 GNC/SW approach
• Some technical expertise needs to be acquired hands-on, e.g. re-entry with IXV, signal intelligence
• Some basic modelling requires in-orbit data like propagation studies, signal at satellite altitude, sloshing (FLEVO), Bi-static data, GNSS reflectometry, fluorescence, low energy detection …
IOD FAQ
CONCLUSION
• ESA has a significant experience in IOD and will continue implementing IOD
activities in response to Member States needs,
• IOD is multi-form (at least at ESA),
• However, IOD is requested but the implementation is often difficult budget
wise (costs outside technology),
• Small missions present good opportunities to combine several types of
needs for IOD and an “operational/user” aspect,
• IOD needs to be part of an overall scheme for technology and mission
identification,
• IOD has involved/required at ESA European Cooperation despite relatively
low budgets,
Thank you for your attention
Thank you for the invitation
Contacts
Directorate of Technical and Quality Management
• Frederic Teston – System, software and in orbit demonstration department (TEC-S)
• Ian Carnelli – Head of GSP program (TEC-SF)
• Robin Biesbroek – Study manager of E-DEORBIT and CAPTARE (TEC-SY)
• Roger Walker – Study manager for cubesat projects and activities (TEC-SY)
• Antonio Danesi – Technology Lead Engineer (TEC-TI)
Directorate for Telecommunications and Integrated Applications
• Paul Greenway – Flight Heritage and Hosted Payloads (TIA-TPH)
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