Title: EGPM
1EGPM
- The European Contribution to Global Precipitation
Measurement
System Concept
C.C. Lin, M. Aguirre, U. Klein, B. Rommen, P.
Vogel ESTEC, Noordwijk, The Netherlands
2Artists View
Active/passive microwave sensing well established
Innovation imaging sounding radar
3Overall System Concept
4th Intl GPM Planning Meeting Greenbelt, 15-17
June 2004 EGPM
3
4EGPM Observation Requirements
(POD probability of detection, FAR false
alarm rate) Notes () this also includes e.g.
hail () this is liquid water equivalent ()
this requires a GPM constellation
5Orbit Selection
- Sun-synchronous orbit LTDN1430 is complementary
to other GPM satellites - NPOESS-1 (0930 des.)
- NPOESS-2 (1330 asc.)
- NPOESS-3 (0530 des.)
- Specified orbit range was 500-675 km, but 530-590
km zone is unsuitable due to Earth resonance - Phase A studies lead to orbit in 510-520 km range
- Coverage is function of the altitude
6Instrument Registration
- Conically scanning radiometer
- Nadir looking precipitation radar with three
beams - The 3 beams of the radar fill the central pixels
of the reference 36 GHz radiometer channel
7Radiometer - I
- Five channels 18.7, 23.8, 36.5, 89 and 150 GHz
- Dual Polarization except for 23.8 GHz
- Two sounding bands 52.5 and 118.75 GHz, each one
with 4 channels - Antenna aperture ? 1 m for 510 km orbit altitude
- Rotation speed 31 rpm
- Radiometric sensitivity
- 0.5 K for lowest frequencies
- 1 K for 89 GHz and higher
- Footprint diameter at 36.5 GHz ? 13.5 km
- Instrument mass ? 130 kg Power ? 110 W Data
rate ? 62 kb/s
8Radiometer - II
9Precipitation Radar
- 35.505 GHz
- Three switched beams
- Short pulse, EIK driven
- Sensitivity
- Integration Thres. Goal
- 4 km -0.7 dBZ 1.7 dBZ
- 20?13 km2 -7.7 dBZ -4.4 dBZ
- Vertical resolution 200 m
- Antenna diameter 1.3 m
- 4.3 km diameter footprint
- Instrument mass ? 55 kg Power ? 85 W Data rate
? 45 kb/s
10Satellite and Platform
- Earth pointed satellite with radiometer on zenith
face and radar on anti-sun face - Configuration drivers
- Need for radiometer fore and aft views
- Radar/Radiometer radio-frequency compatibility
- Drag reduction
- All sub-systems based on qualified technologies
- GaAs solar array fixed for drag minimization
- S and X (10Mb/s) band
- downlinks
- Centralized OBDH
- AOCS compensates the angular momentum of the
radiometer. Unbalances and misalignments limited
by manufacturing tolerances.
11Satellite Budgets and Launcher
- Satellite mass ? 800 kg
- Satellite power ? 600 W
- Satellite life of 3 years for the satellite (2
additional years for consumables) - Pointing accuracy (3?) is 2 mrad (3.5 required),
co-registration is 1.55 mrad (2 required) - 0.9 Gb per orbit, 3 Gb of memory
- Compact satellite
- Comfortable mass and adequate volume margins for
launchers of the Rockot-Vega family
12Ground Segment
13Engineering Performance Radar - I
Radiometric performance at the top of the
precipitation layer for an along-track
integration distance of 4 km (single beam)
14Engineering Performance Radar - II
Radiometric performance at the top of the
precipitation layer for 20 km ? 13 km integration
(mission reference resolution)
15Engineering Performance Radiometer
- Performance figures obtained by standard
modelling techniques - Figures used as inputs to the end-to-end
performance analysis - All figures within requirements, but for NE?T
(sensitivity) at 150 GHz - Performance fulfills mission requirements
16System Concept Summary
- Compact satellite design with a maximum
science-to-cost ratio (two very similar satellite
designs) - High sensitivity radiometer and radar, optimised
for observation of high latitude precipitation
(low rate and solid precipitation). - Satellite design adaptable to different LTDN
- The ground segment concept supports the needs of
the various types of users science and
operational in NRT and RT, and interfaces with
the GPM PPS (expected to further evolve under
Earth Watch/GMES context) - The phase A study teams under the leaderships of
Astrium Ltd. and Carlo Gavazzi Space are
acknowledged for their excellent design work