Proyectos del Plan Espacial Nacional

Proyectos del
Plan Espacial Nacional
Fernando Hisas
[email protected]
XXV Seminario Nacional de Presupuesto Público
13 de Mayo del 2011
CONAE: Comisión Nacional
de Actividades Espaciales
• CONAE es una agencia especializada, creada en Mayo
de 1991 para estar a cargo de la actividad espacial en el
país.
• Su Plan Estratégico: el Plan Espacial Nacional, que se
inicia en 1995 y se revisa periódicamente. La versión
actual es 2004-2015.
El Plan Espacial Nacional
El Plan Espacial se centra en el concepto de:
“Ciclos de Información Espacial”
El concepto comprende el conjunto de la
información proveniente de la tecnología espacial
que, junto con información de otras fuentes, tienen
un impacto relevante en ciertas actividades
socioeconómicas claves de nuestro país.
Plan Espacial Nacional
Los seis ciclos del Plan Espacial:
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Agricultura, Pesca y Actividades Forestales
Clima, Hidrología y Oceanografía
Manejo de Emergencias
Manejo de Recursos Naturales
Cartografía, Geología y Producción Minera
Aplicaciones relacionadas con la Salud
Cursos de Acción
Acceso al
Misiones
Satelitales
Espacio
CONAE
Infraestructura
Terrestre
Sistemas de
Información
Desarrollo
Institucional
Infraestructura Terrestre:
Centro Espacial Teófilo Tabanera
Infraestructura Terrestre
Cámaras de Termo-Vacío (sistemas y pequeños satélites)
Infraestructura Terrestre
Cámara para medición de antenas
SAC-C
FIRST
ARGENTINE
EARTH OBSERVATION
SATELLITE
9 instruments:
MMRS, HSTC, HRTC,
DCS
GOLPE, MMP
IST, INES
ICARE
Satellite weight: 475 kg
Size: 1,85 m x 1,68 m x 2,2 m
Orbit altitude: 705 km
Orbit type: quasi polar – Sun synchronous
Inclination: 98.21 degrees
Pass over the Equator: 10.15 AM ( +/- 6
minutes)
launched on November 21, 2000
Revisit: 16 days, with 7-9 days subcycles
Aquarius/SAC-D
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
Satellite weight: 1600 kg
Orbit altitude: 657 km
Orbit type: quasi polar – Sun synchronous
Inclination: 98.21 degrees
Pass over the Equator: 6 PM ascending node
Revisit: 7 days
Partnership
International Partnership Mission
• Aquarius Salinity Microwave
Instrument
• Service Platform and SAC-D
Science Instruments
• Launch Vehicle
• Mission Operations & Ground
System
SAC-D/Aquarius
Aquarius/SAC-D
Observatory
Microwave Radiometer
MWR
Sun-synchronous
orbit
Satélite de Aplicaciones Científicas-D
Service
Platform
6pm ascending
node
SAC-D S/P
New InfraRed Sensor Technology
NIRST
Revisit: 7 days
Altitude 657 km
Launch: 2010
Mass: 1400 Kg
Power:1443 W
Oper. Life: 5 yrs
High Sensitivity Camera
HSC
CARMEN-1
(ICARE-NG & SODAD)
Aquarius
(primary instrument)
Radio Occultation Sounder for the Atmosphere
ROSA
Data Collection System
DCS
Technology Demonstration Package
TDP
Observatory Configuration
Deployed Configuration
Stowed Configuration
Y Anti-Sun
Aquarius
Instrument
Delta 7320-10 C Fairing
Station location in mm
Z
Aquarius
Reflector
Nadir
X FLT DIR
SAC-D Station 4922.0
AQ Station 2382.0
Aquarius
Sunshade
ROSA
SAC-D Station 2540.0
AQ Station 0.0
SAC-D
Service
Platform
NIRST
Star Trackers
Solar Panel
HSC
S-Band
Antennas
MWR
SAC-D Station
0.0
CARMEN-1
(SODAD 1 of 3)
Nav-GPS, ROSA,
TDP and s-Band
Antennas
Aquarius/SAC-D at Integration Facilities
Aquarius/SAC-D Observatory at INVAP integration facility in Bariloche (Argentina).
June 14th, 2010.
Aquarius/SAC-D Observatory at Test Facilities
Aquarius/SAC-D
Observatory inside the
INPE-LIT Thermal
Vacuum Chamber
November 15th 2010
ROSA Instrument
• Primary Objective:
– ROSA (Radio Occultation Sounder for the Atmosphere ) takes measurement of
the phase delay (Excess Phase) resulting from transmission of the GPS signal
through the atmosphere
– One of the ASI Contribution to the understanding of Climate Change is the
GPS Radio Occultation Experiment
• Instrument Description & Measurement Technique:
– ROSA instrument consists of an integrated GPS receiver for scientific space
applications in the field of the atmospheric sounding by radio occultation of
GPS signals.
– The instrument main features consist of accurate measurements of
pseudorange and integrated doppler (raw data) at dual-frequency from GPS
satellites. In addition, the instrument is able to determine position, velocity and
time using GPS signals.
– The instrument provides real-time raw and navigation data (position and time),
as a typical GPS space receiver.
– An occultation of a GPS signal occurs when a GPS Satellite, setting or rising
behind the Earth limb, is viewed by the LEO Satellite accommodating an
instrument like ROSA
– The instrument provides raw data obtained from the GPS Satellites when they
are in conditions of near-occultation, and consequently the radio signals
coming from the GPS Satellites cross the Earth Troposphere before reaching
the ROSA instrument antennas; these data have to be processed later on
ground for scientific purposes.
– The GPS signals are acquired through multiple antennas: a zenith antenna is
used for navigation purpose and for Precise Orbit Determination (POD) on
ground, while two sounding antennas, pointed toward velocity and anti-velocity
satellite vectors respectively, are used for Earth limb rising-setting occultation
observations for scientific purpose.
– Mass: 34 kg; Power: 87 W
– Operational Life: 4 years
Atmospheric studies with GPS occultation
SAOCOM
MISSION OVERVIEW
SAR Mission primary objectives:
 To provide all weather, day/night polarimetric L-Band SAR information
obtained over Argentina and other regions of interest, in real time/store
mode, with high spatial resolution (10 – 100 meters), and with different
incidence angles.
 To comply with the requirements of the Spatial Information Cycles of
the Argentine National Space Plan, with main emphasis in emergencies
and health.
 To obtain specific L-Band SAR derived products, in particular soil
moisture maps, which represent a great help for agriculture,
emergencies and health applications because of their proved
economic impact.
 To obtain L-Band interferometric SAR derived products to be used as a
support for most of applications.
CONFIGURATION:
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Two Satellites with L-Band SAR Instrument
as main instrument
Orbit : 619.6 km
Near Polar Sun-synchronous frozen orbit,
06:00 am ascending node
DIMENSIONS:

h = 4.468m  2.965m stowed envelope
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10m x 3.5m (35m2) SAR Active Phase Array antenna
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15m2 foldable solar array wing
MASS BUDGET:

2800 kg wet mass at launch (+200kg system margin)
SAOCOM Implementation Approach (FS)
Implementation Mode
Project Management
CONAE
Mission System Engineering
CSA (Canadian Space Agency) as IADB Tech. Audit
Mission assurance
SAR Instrument
CONAE (SAR System Engineering), agreements with CNEA &
IAR for Antenna SAR subsystems, T/R modules design and
manufacturing by Thales Alenia Space – Italy (SIASGE
agreement). Contract with INVAP for SAR Central Electronics.
Service Platform
INVAP Contract
CNEA agreement for Solar Array Manufacturing, Electrical
Integration and Testing
Satellite Integration & Testing
INVAP Contract at INVAP facilities
Satellite Environmental Tests
CONAE logistic; INVAP Contractor; INPE /ESTEC Facilities
Launch Campaign
CONAE; INVAP Contract for technical support
Mission Operation
CONAE (ASI support-SIASGE agreement)
SARAT as Pre-SAOCOM:
Campaign 2006
Península de Valdés surroundings
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)
El Futuro:
1.
2.
3.
4.
5.
6.
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Arquitectura Segmentada
Módulos operando en red
Comunicaciones
inalámbricas
Computación distribuida
Navegación en cluster
Transferencia de energía
inalámbrica
Cargas útiles distribuidas
Flexibilidad ante los cambios
Diversificación de las funciones
Distribución en el tiempo y el espacio de los subsistemas y cargas
útiles
El Futuro:
Vehículo Lanzador TII
Requerimientos de Misión TII
•
Orbita Baja (LEO)
• Orbita Polar
• Altitud 600 km
• Satélites hasta 250 kg
• Desarrollado en la Argentina
• Lugar de lanzamiento Argentina
Principales Características
Largo total y Peso :
Peso vacio :
Diámetros :
Empuje 1er Et. :
Empuje 2da Et. :
Empuje Ult Et :
32 m y 70 ton
8ton
2,5m - 1,5m
90ton
30ton
4ton
Gracias