SEOSAT/INGENIO - A SPANISH HIGH-SPATIAL- RESOLUTION OPTICAL MISSION

Transcription

1 SEOSAT/INGENIO - A SPANISH HIGH-SPATIAL- RESOLUTION OPTICAL MISSION A.E.Marini, F.J. Reina Barragan, G.Crippa, B.Harnisch, I. Fuente ESA/ESTEC, Netherlands, M.Lopez - CDTI, Spain I.Cabeza - Airbus Space & Defence, TRSPEC, Spain D.Zorita - SENER, Spain

2 Acknowledgements This paper summaries a few aspects of the large amount of work carried out at CDTI, at ESA and at the industrial teams. The Industrial teams at Airbus Defense &Space (CASA), SENER, Thales Spain, INDRA, GMV and INTA have provided and are providing a huge and unique contribution to this project The co-authors gratefully acknowledge the work and the effort of all the colleagues not mentioned in this paper. A special thanks to Tomas Belenguer and co-workers at INTA for providing also all the nice images of the integration and testing campaign of the instrument EQM.and don t miss the INTA poster tonight: THE OPTICAL ALIGNMENT PLAN FOR SEOSAT TELESCOPE.

3 Summary 1. The SEOSAT/Ingenio mission 2. System performance and satellite characteristics 3. The SEOSAT/Ingenio high-resolution optical Payload All images courtesy of Airbus Space & Defense, SENER, INTA and Thales Alenia Space España

4 The SEOSAT/Ingenio mission

5 SEOSAT/Ingenio Mission SEOSAT/Ingenio (Spanish Earth Observation SATellite) High-spatial-resolution optical imaging mission. Developed under the Spanish Earth Observation National Program for Satellites (PNOTS) (with Paz, radar satellite). SEOSAT/Ingenio program is funded by CDTI (Spanish Centre for Development of Industry & Technology) CDTI responsible for the programmatic aspects of the mission. ESA entrusted with the technical and contractual management of the industrial activities Industrial consortium involving a large number of Spanish companies together with several European firms. Airbus Defense and Space is the Prime Contractor of the Space Segment, SENER as responsible of the Primary Optical Instrument with Thales España (Opto-el chain) and INTA (AIV). INDRA is the Prime contractor of the Ground Segment

6 Mission Objectives Mission devoted to provide land optical images (panchromatic and multispectral) to Spanish civilian, institutional and governmental users International and European users in the framework of Copernicus Mission objective is to provide images for applications in cartography, land use and mapping, urban and costal management, agriculture monitoring, precision agriculture, water management, environmental monitoring, risk management and land security. Users of some of these applications active as Mission Users Advisory Group (IMAG) Images to be taken with world-wide land coverage Special emphasis on the acquisition of images on the Spanish territory (including carpet-mapping for cartography applications) and other areas of interest like Europe, north of Africa and Ibero-America

7 Mission profile Mission based on one satellite Orbit features polar-heliosynchronous orbit (98.1 ) at 670 km altitude and a revolution period of 14+32/49 rev/day -49 days repeat cycle LTDN 10:30 for optimum illumination conditions, cloud coverage and concurrent passes of other EO satellites (e.g. S-2) World-wide accessibility in less than 3 days. Imaging performance Imaging coverage up to 2.5 Mkm 2 /day Image acquisition Nominal mode:± 6.5 OZA (Observation Zenith Angle) Emergency mode:±40 OZA (3-days accessibility) Full geometrical coverage of Spanish Territory in less than 3 months

8 Mission Operations and products System operated from Ground stations : o o o Torrejon de Ardoz (Spain) primary Control Centre Maspalomas (Canary Islands) backup station. Svalbard passes foreseen to increase accessibility and ensure data throughput. The Ground Segment will generate and distribute to users o o panchromatic and multispectral products processed at Level 1B (radiometrically calibrated), Level 1B-2 (perfect sensor geometry), Level 1C (radiometrically calibrated and orthorectified) GML+JPEG2000 format Catalogue consultation, archive search and retrieval service will be set up and made accessible through a User Service. Higher level products will be left to the user community and to the possibility of creation of a shared toolbox

9 System performance and satellite characteristics

10 Imaging performance Panchromatic and Multispectral images in the Visible and near-infrared 1 PAN band (envelope GR) 4 MS bands (B,G,R,NIR) High spatial resolution PAN GSD = 2.5 m MS GSD = 10 m Swath > 55 km min (60 km x 60 km image cut) High Image quality: SW/SSD < 1.1 Image geo-location accuracy <50m (2-σ) without GCP s (at level 1b) [~30 m actual perf.] <2.5m rms with GCP s (at level 1c) Co-registration accuracy between PAN and MS image: ~0.1 MS pixel (2-σ) for BGR MS bands (0.3 pixel for NIR)

11 SEOSAT/Ingenio images The challenge of SEOSAT/Ingenio imaging is to provide at once: o o o Large image area (~60 km swath) High-resolution (2.5 PAN) with good image quality (SW/SSD=1.1) Excellent radiometry (SNR BOL) at nominal radiance (80 W/m 2 sr) o PAN:110 o MS Blue: 125 o MS G,R, NIR: 200 Achieved with a twin-camera system: Two Korsch telescopes jointly covering ~5 FOV Each camera has a focal-plane with staggered detectors (2 PAN, 2 MS to cover the camera swath) Overlapping individual telescope FOV to account for in flight settling, AOCS instability and thermo-elastic deformation.

12 SEOSAT/Ingenio satellite - 1 SEOSAT/Ingenio satellite: platform (service module) Primary Payload 3 opportunity instruments (CSP) On-board mass memory Data compression Data throughput (per camera) Downlink data rate Lifetime Delta-V and fuel budget Candidate launchers Mass / power 1 TBit Quasi-lossless, 2 to 6 bpp Mpixel/s PAN Mpixel/s MS 280 MBit/s 7 years + consumables for 10 years (+de-orbit) ~200 m/s, 80 kg Dnepr, Rockot, Vega 820 kg / 1000 W Launch readiness End 2016

13 SEOSAT/Ingenio satellite -2 Platform based on the AstroSat 250 product (Airbus Space & Defense), conceived for medium-size Earth Observation missions. Structure: box-shaped design with a hexagonal base and 6 faces Al- sandwich panels 3 solar array, total solar panel area of about 5.40 m 2. The panels of the platform can be opened as petals to ease AIV operations Technical challenges: Gyro-less AOCS ensuring high accuracy attitude stability New/low heritage avionics equipment like: on-board computer (LEON-3 processor), G-link data handling bus, advanced star-tracker, PCDU new design

14 Complementary Scientific Payload Sensosol (University of Seville) Miniaturized solar sensor based on MEMS technology TTT / The Two Towers (INTA) in-orbit dosimeter and radiation spectrometer hosting different sensors (solid-state) UVAS (CSIC Consejo Superior de Investigaciones Cientificas) UV and Visible atmospheric sounder (CCD-based grating spectrometer) CSP EM/EQM models - Courtesy of Univ. Sevilla, INTA, CSIC

15 The SEOSAT/Ingenio highresolution optical imaging Payload

16 SEOSAT/Ingenio PP Overview Push-broom imager 2 cameras Korsch telescope Focal plane (+Proximity el.) Video unit Common :1 VSU, 1 ICU High Stability Support Panel (sandwiched Al honeycomb in CFRP skins) Star trackers mounted on HSSP FOV 4.5 MTF at Nyquist: PAN >0.115 MS> 0.3 ~140 kg, ~250 W

17 Korsch telescope Non-telecentric system Three aspherical mirrors aligned along the optical axis Flat 45 folding mirror F=3.65 m D = 260 mm FOV ~ 2.5 Zerodur mirrors on Ti/Invar isostatic mounts [REOSC] Invar Struts, Ti Optical Bench Refocusing device (0-g/ launch in-orbit adjustment)

18 Focal planes Each Focal Plane has: 2 PAN CCD s (20x6000 pixels, 13 µm pitch, T int =0.3 ms 5-TDI operation) [E2V] 2 MS CCD s (4x1500 pixels, 52 µm pitch, T int =1.46 ms ) [E2V] 2 PAN + 2 MS Proximity electronics, flex-connected to VU PAN and MS Micro-strip filters (directly coated on fused Si substrate) aligned and mounted on the CCD [JOP] SiC Focal plane plate Al Radiation shield Isostatically mounted to the Optical Bench

19 SEOSAT/Ingenio Primary Payload development PP Model philosophy and status Engineering Qualification Model (EQM) Based on one FM telescope and flight-like focal plane and PP electronics FM HSSP One dummy telescope, structure fully FM-representative Went through Vibration and Thermal vacuum tests Telescope under refurbishment for FM build Flight Model All units available, Payload electronics fully integrated with Focal plane and all through unit flight acceptance test. Second FM telescope under integration Electrical Model Based on PPE EQM. Delivered to Airbus Defense & Space for electrical and functional testing at system level.

20 Primary Payload EQM

21 AIV at INTA radiometric verification

22 PP EQM Vibration test (at INTA)

23 PP EQM in Thermal vacuum testing (INTA)

24 Thank you for your attention!