NATIONAL SPACE PROGRAM. February 10 th, 2016 Capua, ITALY

Transcription

1 NATIONAL SPACE PROGRAM February 10 th, 2016 Capua, ITALY

2 The National Space Program Space Information Cycle (To go to space to see the Earth ) An opportunity for national technology development 2

3 The National Space Program Information cycles for: agriculture, fishing and forest activities climate, hydrology and oceanography monitoring of the environment and natural resources cartography, geology and mining production disaster management health applications national security 3

4 CETT: Teófilo Tabanera Space Center 4

5 CONAE CETT (Labs) Thermal-Vacuum Chambers (subsystems and small satellites) Anecoid Chamber for Near Field Antenna Measurements Shaker (subsystems and small satellites) 5

6 CONAE in Space 6

7 Ocean circulation, global water cycle, climate interaction, environmental changes, natural hazards, atmospheric parameters, radiation effects 8 instruments: Aquarius, MWR, NIRST, HSC, ROSA, CARMEN 1, DCS, TDP 7

8 International Partnership Mission Aquarius Salinity Microwave Instrument Launch (June 10th, 2011) (NASA) Service Platform and SAC-D Science Instruments Mission Operations & Ground System (CONAE) 8

9 Argentine Payloads MWR DCS TDP Institutions: CONAE UNLP IAR CIOP GEMA Companies: INVAP VENG STI DTA CRUX HSC NIRST 9

10 Solar Panels (CNEA) 10

11 Integration Room (INVAP) INVAP, Bariloche, June 14,

12 12

13 SAOCOM Mission Objectives soil moisture maps (hydrologyincluding floods, agriculture, climate and health) information extraction using SAR interferometry capability (terrain modeling, terrain displacement mapping, volcanology, etc.) emergencies and other applications from the Information Cycles of the National Space Program 13

14 SAOCOM CONFIGURATION: Two Satellites with L-Band SAR Instrument as main instrument Orbit : km Near Polar Sun-synchronous frozen orbit, 06:00 am ascending node DIMENSIONS: h = 4.468m 2.965m stowed envelope 10m x 3.5m (35m 2 ) SAR Active Phase Array antenna 15m2 foldable solar array wing MASS BUDGET: 2800 kg wet mass at launch (+200kg system margin) 14

15 Project Status STM Test Campaign Finalized SAOCOM Structure Qualified 15

16 Project Status Solar Simulator Test Campaign Finalized IABG (Germany) 16

17 Project Status 1 17

18 Project Status 2 18

19 Project Status 3 19

20 SAOCOM Implementation Approach (FS) Implementation Mode Project Management Mission System Engineering Mission assurance SAR Instrument Service Platform Satellite Integration & Testing Satellite Environmental Tests Launch Campaign Mission Operation CONAE CSA (Canadian Space Agency) as IADB Tech. Audit CONAE (SAR System Engineering), agreements with CNEA & IAR for Antenna SAR subsystems, T/R modules designed and manufactured by Thales Alenia Space Italy and PSU by Selex-ES (ASI contract by SIASGE agreement). Contract with INVAP for SAR Central Electronics. INVAP Contract CNEA agreement for Solar Array Manufacturing, Electrical Integration and Testing INVAP Contract at INVAP facilities CONAE logistic; INVAP Contractor; CEATSA Facilities CONAE; INVAP Contract for technical support CONAE (ASI support-siasge agreement) 20

21 Participation of Italian Industry in SAOCOM THALES Alenia Space Italy: 1. LTRM contracted by ASI (SIASGE) 2. GPS assembly, EGSE and GPS SAR Instrument Frequency Rejection L-Band Filter Selex-ES Italia: 1. CTR and LTRM PSU (TAS-I subcontractor, under ASI contract for SIASGE) Elital Srl: 1. PCBs of CTR subassembly and SAR antenna radiating modules 2. Refurbishment of a 10mts antenna of ETC to be compatible with monopulse operation (for SAOCOM, COSMO y SAOCOM CS) Angelantoni Group: 1. Thermal Vacuum chambers (CONAE test facilities) 2. RF Thermal Transparent Chamber for SAR operational test Co.Ri.Sta. 1. SAR Instrument RAW data simulator 2. Technical support for analysis of SAR Instrument Space ENG. S.p.A. 1. Power divider / combiner for SAR Antenna. Power Divider For CTR. Power Junction Box for antenna SAR power distribution 2. Antenna Model used for SAR instrument AIV and SAR Instrument Calibration during mission 3. PARC Antenna Active calibrator ( used during the SAR Instrument in-orbit Calibration Phases on CONAE SAR CAL-Val Facilities) Aresys 1. SAR beams design and analysis. 2. SAOCOM SAR Processor 3. EGSE for SAR testing facilities 21

22 SIASGE Constelation of 6 satellites with SAR instruments on board, 4 italian in X band (COSMO-SkyMed) and 2 argentinean in L band (SAOCOM): Multiband synergy (X & L) High revisit (12 hs) Benefits: Excellent synergy between and L band data, which represents a key for satisfying the different user needs Significant improvement in the accuracy of the discrimination among the different surface components Significant improvement in the geophysical parameters quantitative knowledge Very high revisit for monitoring events of fast evolution Improvement in cartographic and change detection studies 22

23 SIASGE SIASGE INTEGRATION Key technological components (L-Band MTR and PSU) manufactured by italian industry (TAS-I) under ASI contract. TAS-I technical support to SAOCOM under ASI contract. Ground Segment integration (TT&C and SAR data), to provide L, X and X+L band information. Common development in Applications, particularly new developments in X+L 23

24 Next Steps (1): SABIA-Mar SABIA-Mar 1 and 2 Objective: To study the Oceanic Biosphere, its changes along time, and how it is affected and reacts to human activities. Main Payloads: Super-spectral Camera, with 19 bands in the Visible, SWIR, and Thermal ranges, with 200m pixel resolution, and daily repetition rate, for coastal studies and south American continental territory. Similar, but with 1 km pixel resolution, daily repetition rate and global coverage. 24

25 Next Steps (2): Segmented Architecture 1. Small satellites in a network 2. Cluster concept 3. Sharing of Resources 4. Distributed Processing 5. Distributed Payloads 6. Advanced Communications Flexible to requirement changes Flexible to changes in technology Shortens the Mission cycle times Lower Mission costs 25

26 Next Steps (3): SARE AR-1 High Resolution Mission (1 meter panchromatic, 5 meters multispectral) 4 Satellites in polar sun synchronous orbit Revisit time better than 8 days 26

27 Next Steps (4): Launch Vehicle TII Main Characteristics: TII Requirements Length and weight: Empty : Diameter : Thrust 1st stage : Thrust last stage : 28 m and 67 ton 5,1 ton 2,5m 90ton 4ton Polar Orbit Altitude 600 km Weights up to 250 kg Under Development in Argentina Launch site in Argentina 27

28 Next Steps (5): Launch Vehicle TII/TIII Comparison Tronador II - III TII TIII TII TIII Peso lleno ~ 67 ton ~ 89 ton Peso vacío: ~ 5.1 ton ~6.675 ton Orbita Baja LEO Polar Con reencendido de 2da etapa: 250kg@600km NO 750kg@600km 1000kg@600km Altura y diámetro: 28m & 2.5m 34m & 2.5m 28

29 Next Steps (6): Launch Base 29

30 Thanks 30