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

28

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)