Cli t Ab
Climate
Absolute
l t R
Radiance
di
and
dR
Refractivity
f
ti it Ob
Observatory
t
(CLARREO)
CLARREO Mission Overview
January 2010
NASA Langley Research Center
p
, Virginia
g
Hampton,
Pre-decisional / For Planning Purposes Only
1
CLARREO Mission Overview
•
Mission Purpose, Objectives, and Requirements
•
Measurements and Instruments
•
Spacecraft Bus and Observatory
•
Launch Vehicle Strategy
Pre-decisional / For Planning Purposes Only
2
Mission Objectives and Purpose
Pre-decisional / For Planning Purposes Only
3
CLARREO Goal and Objectives
Mission Goal:
To provide accurate, broadly acknowledged climate records that are used to
enable validated long-term climate projections that become the foundation for
informed decisions on mitigation and adaptation policies that address the effects
of climate change on society.
Key Societal Objectives:
1. To establish a multi-decade benchmark climate record that is global in extent,
accurate
accu
ate with
t rigorous
go ous ttraceability
aceab ty to international
te at o a sta
standards,
da ds, a
and
d tested
against independent methods.
2. To enable an operational climate forecast that is tested and broadly trusted
through a disciplined strategy using state
state-of-the-art
of the art observations and
mathematically-rigorous analytical techniques to establish credibility.
3. To enable the creation of decision structures that assimilate accurate data and
forecasts into intelligible and specific products, promoting international
commerce, societal stability and security.
Pre-decisional / For Planning Purposes Only
4
- Aerosols
- Albedo
Cli t System
Climate
S t
Model
M d l
- Temperature
- Water Vapor
R and
Roe
dB
Baker,
k 2007
Reducing uncertainty in predictions of ΔT is critical for public
policy affecting adaptation to changes in sea level and
precipitation
Pre-decisional / For Planning Purposes Only
5
CLARREO Science Goal and Requirements
Overall Science Goal:
Make highly accurate, global, SI-traceable decadal change
observations sensitive to the most critical
critical, but least understood
understood, climate
forcings, responses, and feedbacks.
Specific Key Science Requirements:
1. To measure the absolute spectrally resolved radiance in the infrared with high accuracy
(0.1 K 3σ brightness temperature) by downward-directed spectrometers in Earth orbit.
2. To measure the absolute spectrally resolved nadir reflectance of solar radiation from Earth
to space with high accuracy (0.3% 2σ). Solar radiation reflectance constitutes a powerful
and highly variable forcing of the climate system through changes in snow cover, sea ice,
land-use, aerosol, and clouds.
3. To utilize Global Navigation Satellite Systems (GNSS) radio occultation as a source for
another benchmark of the climate system. This technique is traceable to the international
standard second and is an independent method complementing the spectrometers.
4 T
4.
To use CLARREO as a hi
high
h accuracy calibration
lib i standard
d d ffor use by
b operational,
i
l climate
li
relevant infrared and reflected solar instruments like CERES, CrIS, IASI, VIIRS and
Landsat.
Pre-decisional / For Planning Purposes Only
6
CLARREO Mission Description
Launch Requirements
Nominal Orbit
Altitude (Km)
Inclination
Design Operational Life
Estimated Launch Readiness Date (LRD)
CBE Instrument Size
Launch Site Requirement (East or West
Coast)
Mechanical Interface
LEO
609
90°
3 years
NET 2016-19
Variable
West
Mechanical Interfaces
Individual specified interfaces for each payload element
Field Of View (FOV)
Infrared Instrument FOV = 2.4
2 4°
- (Pointed either nadir, zenith, or 45° from zenith)
Reflected Solar Instrument FOV = 500m, with 100 km swath
- (Pointed either nadir or off-nadir up to 120°)
GNSS-RO Instrument
- Occultation antennas (2) centered 65° w.r.t. nadir, ±10° in
nadir-ram/wake planes, ±45° out of plane
- Precise Orbit Determination (POD) antenna, ±75
±75° cone
w.r.t. zenith
Science and C&D Handling
g
Science Downlink Format
Science Data Downlink Frequency
CCSDS
X Band
Science Data Rate (Gb/day)
314 Gb/day
Instrument Housekeeping Telemetry
Instrument Housekeeping Telemetry Data
Rate (Gb/day)
S-Band & X-Band
Onboard Data Storage (Gb)
≥ 314 Gb
~ 1 Gb/day
Attitude Control
Pointing Knowledge (1 sigma)
Pointing Accuracy (1 sigma)
Jitter
ACS
GPS Receiver
Star Trackers
< 0.1 degree or 360 arc sec
< 0.1 degree or 360 arc sec
< 0.1 degree or 360 arc sec over 0.1 second
g
torque
q rods
3-axis stabilized - reaction wheels and magnetic
Minimum 1
Minimum 1
Instrument Thermal
Requirement
Payload Mass
Payload Mass Allocation (w/contingency)
Mass Margin
295 kg
30 percent
NTE Payload Mass (kg)
384
Payload Power
Payload Orbit Average Power Allocation (W)
Payload Peak Power Allocation (W)
Power Margin
405 W
618 W
30 percent
NTE Orbit Average Payload Power (W)
527
Bus Voltage (V)
28
Thermally Isolated
p
Propulsion
Observatory Environmental
& Facility (driven by
Instrument)
NASA Risk Classification
EMI/EMC
Vibe
Th
Thermal
l Vacuum
V
Radiation
Clean Room Class
Special Facility Needs
Yes
5 yyears Mission Capability
p
y
Class C
GSFC 7000
GSFC 7000
GSFC 7000
GSFC 7000
10K
None
Pre-decisional / For Planning Purposes Only
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Mission Goal: To provide accurate, broadly acknowledged climate records that are used
to enable tested and trusted long-term climate projections that become the foundation for
GOAL:decisions
To provide accurate,
credible
and
tested climate
recordsthat
thataddress
lay the the effects of
informed
on mitigation
and
adaptation
policies
groundwork for informed decisions on mitigation
g
g
and adaptation
p
p
policies that
climate change on society
society.
address the effects of climate change on society.
CLARREO Orbital Path
CLARREO 2
CLARREO 1
Deep Space IR FOV
GNSS
GNSS Radio Occultation (RO):
SI-traceable measurements of
GNSS Doppler shifts (to
determine atmospheric
refractivity)
Nadir IR FOV:
MOC
SI traceable measurements
of the Mid and Far-IR
spectrum of the Earth and
atmosphere
SOC
NEN
EOS Data
Operations System
Users
Science Data Systems
Solar Instrument FOV:
SI traceable direct and
reflected solar
irradiance/reflectance
TDRS
Two spacecraft in 609 km polar orbit.
Spacecraft separated by 90 degrees (TBR).
Nadir IR coverage area with 5 degree cone angle
CLARREO Architecture Top-Level Diagrams
DRAFT
Title: CLARREO Mission High-Level Operational Concept Graphic
Figure/Table/Type: OV-1
Date: 9/24/2009
1 OnlyFigure: 3
Pre-decisional
/ For PlanningVersion:
Purposes
SCaN
CLARREO
GNSS
Users
Science Data Processing Center 9
Measurements and Instruments
Pre-decisional / For Planning Purposes Only
10
CLARREO Measurement Concept & Instrument Suite
Key Measurement Concept :
Make climate measurements that are SI traceable
Payload Suite
Infrared Measurements
• One infrared interferometer
• On-orbit
O
bit calibration
lib ti and
d verification
ifi ti systems
t
• Primary measurement is nadir benchmarking
• Inter-calibration at nadir only
Reflected Solar Measurements
• One suite of grating spectrometers
• Nadir benchmarking approx. 95% of duty cycle
• Sun and lunar views for calibration
• Inter-calibration requires off-axis pointing
GNSS Radio Occultation (RO)
• One GNSS-RO system
• Fore and aft occultation antennas
• Zenith antenna for precise orbit determination
Instrument
Observatory I
FTS
Infrared
Spectrometer
Reflected Solar
Spectrometer 1
Reflected Solar
Spectrometer 2
Reflected Solar
Spectrometer 3
GNSS Radio
Occultation
System
Pre-decisional / For Planning Purposes Only
5 tto 50 micron
i
Observatory II
FTS
5 tto 50 micron
i
Nadir
Nadir
Grating
Grating
320-640 nm
320-640 nm
Gimbal-mounted
Gimbal-mounted
Grating
Grating
600-1200 nm
600-1200 nm
Gimbal -mounted
Gimbal -mounted
Grating
Grating
1150-2300 nm
1150-2300 nm
Gimbal -mounted
Gimbal -mounted
POD
POD
1 Receiver
1 Receiver
3 Antennas
3 Antennas
11
Infrared Instrument Suite
Baseline Instrument Package:
¾ FTS, calibration-verification system, thermal
management hardware, support structure, and
electronics
¾ Mass: 85 kg CBE
¾ Average Power: 158 W CBE
¾ Instrument Dimension: ~42x65x70 cm3
¾ Data Rate: 224 kb/sec
¾ Data
D t Volume:
V l
19.3
19 3 Gb/day
Gb/d
Instrument Description:
¾ A Fourier Transform Spectrometer (FTS) for SI
traceable measurements of the Mid and Far-IR
spectrum of the Earth and atmosphere using two
detectors within a single instrument
¾ Utilizes one ambient black body and deep space as onorbit calibration sources.
¾ Utilizes one phase-change cell equipped blackbody
and an emissivity monitoring system
¾ Uncooled
U
l d pyroelectric
l ti d
detector
t t ffor th
the F
Far-IR
IR and
d an
actively cryocooled MCT detector for the Mid-IR
Characteristics:
¾ Spectral Range: ~ 5-50 μm (200-2000 cm-1)
¾ ~5 to 15 μm (actively cooled MCT)
¾ ~15 to 50 μm (Pyroelectric)
¾ Unapodized Resolution: 0.5 cm-1
¾ Radiance Scale Accuracy: 0.1 K 3σ
¾ FOV: ~2.4 deg
¾ GIFOV: ~24
24 km
¾ Integration Period: ~ 8 seconds
Pre-decisional / For Planning Purposes Only
12
Reflected Solar Instrument Suite
Baseline Instrument Package:
¾ Three spectrometers, thermal management, and
electronics
¾ Mass: 75 kg CBE
¾ Average Power: 99 W CBE
¾ Instrument Suite Dimension: ~185x58x91cm3
¾ Data Rate: Up to 160 Mb/sec (compressed)
¾ Data
D t Volume:
V l
U
Up tto 130 Gb/day
Gb/d ((compressed)
d)
Instrument Description:
¾ A trio of pushbroom hyperspectral imagers with high
spatial and spectral resolution for SI traceable direct
and reflected solar irradiance measurements
¾ Calibration of detectors obtained through precision
apertures -neutral density filters rotated via filter
wheels
¾ Field of regard (FOR) needed for Solar-Lunar
Calibrations, Intercalibrations, and Benchmarking
achieved with two-axis gimbal
Characteristics:
¾ Spectral Range: 320 – 2300 nm
¾
¾
¾
¾
¾
¾
¾
~320 to ~640 nm (“Blue”)
~600
600 to ~1200
1200 nm ((“Red”)
Red )
~1150 to ~2300 nm (“NIR”)
Spectral Sampling: ~2 – 4 nm
Range of pointing: 120 degrees
Swath Width: ~100 km cross-track
S i lS
Spatial
Sampling
li :~0.5
0 kkm at Nadir
N di
Pre-decisional / For Planning Purposes Only
13
GNSS Radio Occultation Instrument
Figure from “COSMIC Update and Highlights” C. Rocken, UCAR
Baseline Instrument:
¾ Receiver, antennas, and cabling
¾ Mass: 16 kg CBE
¾ Average Power: 32 W CBE
¾ Dimensions:
¾ Receiver: ~19x12x23 cm3
¾ POD Antenna: ~31 cm dia. x 4 cm (cone)
¾ RO (Ram-Wake)
(R
W k ) Antennas:
A t
~48x87x2
48 87 2 cm3
¾ Data Rate: 112 kb/sec
¾ Data Volume: 10 Gb/day
Instrument Description:
¾ GNSS (Global Navigation Satellite Systems) receiver
using radio occultation (RO) to measure atmospheric
refractivity through Doppler shifts
¾ Traceable to international standards (time)
¾ Used to derive atmospheric pressure, temperature,
and water vapor concentration
Instrument Subsystems:
¾ One GNSS receiver
¾ One zenith facing, choke ring, precise orbit
determination ((POD)) antenna
¾ Electronically steerable phased array ram and wake
RO antennas
Instrument Operations:
¾ Number of occultations : ~2000/day/observatory
¾
¾
Rising and Setting Occultations
¾
¾
1000 each from GPS and Galileo
Ram/Wake antennas provide both options with
observatory yaw flip
Clock corrections on ground if necessary
Pre-decisional / For Planning Purposes Only
14
Spacecraft Bus and Observatory
Pre-decisional / For Planning Purposes Only
15
S
Spacecraft
ft Requirements
R
i
t and
d Drivers
Di
•
Mission Orbit:
-
•
Mission Lifetime:
-
•
Instrument Field of Regard’s (FOR’s) –drives instrument location and solar array design
Launch Vehicle:
-
•
The mission lifetime shall be a minimum of 3 years
Operational consumables for 5 years of life
Post-mission orbit lifetime: <25 years – Controlled de-orbit drives propulsion system
P l d
Payload:
-
•
The spacecraft will be in nearly circular polar orbits at 609 km (+/-200m)
( / 200m) altitude, 90 degree
inclination angle (+/-0.1) degree and 90°separation in longitude of ascending node between
observatories – beta angle in 90 degree orbit drives solar array design
Minotaur
Mi
t
IV+ Launch
L
h Vehicle
V hi l launch
l
h capability,
bilit ffairing
i i di
diameter
t and
d CG offset
ff t lilimits
it – drives
di
instrument location, mass of spacecraft, and solar array design
Mission Success:
-
Spacecraft Reliability allocation –drives
drives redundancy
redundancy, mass and costs
Pre-decisional / For Planning Purposes Only
16
CLARREO Ob
Observatory
t
Concept
C
t
CLARREO Observatory
On-orbit Configuration
CLARREO Observatory (stowed
configuration in Minotaur IV+)
Pre-decisional / For Planning Purposes Only
17
S
Spacecraft
ft Bus
B S
Subsystems
b
t
•
•
Central Electronics Processor
Provide C&DH, Communications, Thermal, Propulsion
and payload command and telemetry interfaces (SSR,
C&DH computer)
-
•
Propulsion System
-
Monopropellant – Hydrazine blowdown system
-
4 +4 22 N Thrusters for orbit maintenance and
controlled re-entry
Thermal System
-
•
X-Band for downlink for stored engineering
g
g and
payload data
S-band for command uplink and telemetry downlink
Data Volume: 314 Gbits/day
Th
Thermal
l control
t l using
i radiators
di t
and
d MLI
Mechanical/Structural System
-
Communications System
-
•
158 A-Hr Li-ion batteryy capacity
p
y
28V Direct Energy Transfer Power Bus
Deployable, 10.0 m2 (1060W EOL)
Command and Data Handling
-
•
•
Electrical Power System
Aluminum sheet over aluminum honeycomb
panels
Attitude Determination & Control System
-
3-axis
3
i stabilized
t bili d attitude
ttit d control
t l system
t
Star trackers, IMU’s, CSS, Magnetometers
Reaction Wheels and Magnetic Torque Bars
GPS for Orbit determination
•
Pre-decisional / For Planning Purposes Only
18
Launch Vehicle Strategy
Pre-decisional / For Planning Purposes Only
19
Launch Vehicle Trades
Pre-Phase A trade studies evaluated multiple launch vehicle options to
id tif the
identify
th mostt cost-effective
t ff ti access-to-space
t
solution.
l ti
Options Considered
¾
Individual launches
–
–
–
–
–
–
Falcon 1 and 1e
Pegasus XL
Taurus XL
Minotaur I and IV+
Taurus 2
Falcon 9
¾
Single launch with dual manifest on an EELV (Atlas V or Delta 4) using
the Dual Satellite System (DSS) currently under development
¾
Evaluation for Pre-Phase
Pre Phase A focused mainly on the costs of the different
options
Pre-decisional / For Planning Purposes Only
20
CLARREO
Launch Vehicle Options
9,000
Ma
ass to 609 k
km Polar Orrbit (kg)
8,000
Currently Available for Planning
through NASA Launch Services
Currently Under NLS Contract but not Expected
to be Available for CLARREO Launch
7,000
Expected to be Added to the
NLS Contract in 2010
6 000
6,000
5,000
4 000
4,000
3,000
2 000
2,000
30% System Margin
CLARREO Allocated Wet Mass (950 kg)
1,000
0
Falcon I Pegasus Minotaur Falcon 1e Taurus Minotaur
XL
I
3210
IV+
Delta II
Pre-decisional / For Planning Purposes Only
Taurus II
Atlas V
Delta IV Falcon 9
Series
(Low)
21
Mission Architecture Strategy for MCR
•
The three most cost competitive and viable mission architectures
available when future launch vehicles are included in the trade space are:
-
Launch two observatories as a dual-manifest on a single EELV
•
-
Launch two observatories individually on two Minotaur IV+ vehicles
•
•
Derivative
D
i ti conceptt iis tto replace
l
th
the EELV with
ith a F
Falcon
l
9 if th
the F
Falcon
l
9 proves
to have polar orbit capability and dual-manifest capability
Derivative concept is to replace the Minotaur IV with a Falcon 9 if the Falcon 9
proves to have polar orbit capability
Launch four observatories with one spectrometer (IR or RS) on four Falcon
1e launch vehicles (assumes that the Falcon 1e cost < Minotaur IV cost)
Based on current data, the Minotaur IV+ appears to be the most costeffective solution, but launch vehicle trade studies will continue to be
conducted in Phase A
Pre-decisional / For Planning Purposes Only
22
Mission Architecture Decision Tree
Orbit 1
Orbit 2
IR Suite
IR Suite
RS Suite RS Suite
GNSS RO GNSS RO
IR + IR + S + S
IRS + IRS
Individual
Launches
Dual
Manifest
Individual
Launches
M1
M2
M3
M4
M5
Minotaur IV+
Taurus II
Falcon 9
EELV w/DSS
Falcon 1e
M6
Secondary
Payloads
M7
Taurus XL Minotaur IV+
Taurus II
EELV
Falcon 9
Future
Phase A
Trade
Space
Pre-decisional / For Planning Purposes Only
24