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The Vital Role of ICESat Data Products. Dr. Douglas D. McLennan ICESat-2 Project Manager Dr. Thorsten Markus ICESat-2 Project Scientist Dr. Thomas Neumann ICESat-2 Deputy Project Scientist. Land Ice. Sea Ice. Vegetation. Why D o W e N eed ICESat-2?.

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the vital role of icesat data products

The Vital Role of ICESat Data Products

Dr. Douglas D. McLennan

ICESat-2 Project Manager

Dr. Thorsten Markus

ICESat-2 Project Scientist

Dr. Thomas Neumann

ICESat-2 Deputy Project Scientist

Land Ice

Sea Ice

Vegetation

why d o w e n eed icesat 2
Why Do We Need ICESat-2?

“Earth Science and Applications from

Space: National Imperatives for the

next Decade and Beyond “ (National

Research Council, 2007)

http://www.nap.edu

ICESat-2 is one of four first-tier missions recommended by the 2007 NRC Earth Science Decadal Survey

On February 14, 2008 NASA announced the selection of ICESat-2 Project

the first icesat mission
The First ICESat Mission
  • Launched in 2003 as a three-year mission with a goal of returning data for five-years
  • Deployed a space-based laser altimeter – Geoscience Laser Altimeter System (GLAS)
  • Laser lifetime issues mandated change in operational approach
  • Significant Contribution to Earth Science
    • Multi-year elevation data used to determine ice sheet mass balance and cloud properties
    • Topography and vegetation around the globe
    • Polar-specific coverage over Greenland and Antarctic ice sheets
  • Mission ended in 2009 after seven years in orbit and 15 laser-operation campaigns
icesat data swath of antarctica
ICESat Data Swath of Antarctica

Image shows Ice Sheet Elevation and Clouds

next icesat mission
Next ICESat Mission
  • Decadal Survey identified the next ICESat satellite as one of NASA’s top priorities
  • In 2003, ICESat-2 Mission award to Goddard Space Flight Center (GSFC)
  • Observatory will use a micro-pulse multi-beam approach
    • Provide dense cross-track sampling
    • High pulse repetition rate producing dense along-track sampling
  • Improved elevation estimates over high slope areas and rough areas
  • Improved lead detection of sea ice freeboard estimates
slide6

ICESat dH/dt

Thinningthickening

5 years

40 years

50 years

Greenland and Antarctica are losing mass...

especially in the outlet glaciers

10 km

60 years

Jacobshavns Isbrae

slide8

Summer sea ice extent is decreasing faster than predicted by IPCC models

  • From ICESat
  • Sea ice thickness has decreased by about 2.2 ft
  • Area of thick, multiyear ice has decreased by 42%
icesat 2 science objectives
ICESat-2 Science Objectives
  • Quantifying polar ice-sheet contributions to current and recent sea-level change and the linkages to climate conditions
  • Quantifying regional signatures of ice-sheet changes to assess mechanisms driving those changes and improve predictive ice sheet models
  • Estimating sea-ice thickness to examine ice/ocean/atmosphere exchanges of energy, mass and moisture
  • Measuring vegetation canopy height as a basis for estimating large-scale biomass and biomass change
  • Enhancing the utility of other Earth observation systems through supporting measurements
icesat 2 measurement concept
ICESat-2 Measurement Concept

In contrast to the first ICESatmission, ICESat-2 will use micro-pulse multi-beam photon counting approach

  • Provides:
    • Dense cross-track sampling to resolve surface slope on an orbit basis
    • High repetition rate (10 kHz) generates dense along-track sampling (~70 cm)
    • Different beam energies to provide necessary dynamic range (bright / dark surfaces)
  • Advantages:
    • Improved elevation estimates over high slope areas and very rough (e.g. crevassed) areas
    • Improved lead detection for sea ice freeboard
icesat 2 measurement concept1
ICESat-2 Measurement Concept

Single laser pulse, split into 6 beams. Redundant lasers, Redundant detectors.

flight direction

flight direction

3 km

3 km

3 km

3 km

90 m

Footprint size: 10 m

PRF: 10 kHz (0.7 m)

3 km spacing between pairs provides spatial coverage

90 m pair spacing for slope determination (2 degrees of yaw)

high-energy beams (4x) for better performance over low-reflectivity targets

analog vs photon counting
Analog vs. Photon-Counting

laser pulse

(incident photons)

Threshold

Photon-counting

sampling

(integrated pulses)

Photon-counting

sampling

(single pulse)

Analog approach

(digitized waveform)

IMPORTANT: the integrated photon-counting sample (“histogram”) looks like the analog wave for

but it is not – the information content is different, and the method of analyzing the data is different

analog vs photon counting1
Analog vs. Photon-Counting

can also do it for vegetation

laser pulse

(incident photons)

Threshold

Photon-counting

sampling

(single pulse)

Photon-counting

sampling

(integrated pulses)

Analog approach

(digitized waveform)

IMPORTANT: the integrated photon-counting sample (“histogram”) looks like the analog waveform,

but it is not – the information content is different, and the method of analyzing the data is different.

find the surface return
Find the Surface Return?
  • Simulation assumes horizontal surface (zero slope)
  • 10 noise photons and 1 surface signal photon per pulse
  • Averages 100 Micropulse pulses (equivalent to 1 GLAS footprint)

GLAS spot = 70 meters

Micropulse spots are

10 m with 0.7 m spacing

………………………….

300 m Range Window

data example from p c altimeter
Data Example from P-C Altimeter

Example of a 3-D “image” of an ice chunk in Greenland from a photon-counting laser altimeter using 100 beams and scanning

slide16

Atmospheric example of photon-countingCloud Physics Lidar

Originally developed for the ER-2 aircraft, CPL is an autonomous, 3-wavelength, high-altitude backscatter lidar.

Use of a high rep-rate laser enables photon-counting detection, which in turn enables fast turn-around for data processing.

icesat 2 mission overview
ICESat-2 Mission Overview
  • Single instrument mission
    • Advanced Topographic Laser Altimeter System (ATLAS)
    • Multi-beam micro-pulse laser based instrument – utilizing photon counting
    • Design assembly and test at Goddard
  • Spacecraft
    • Six vendors have shown interest
    • RSDO Spacecraft Procurement
  • Launch Vehicle
    • Selection prior to S/C Preliminary Design Review (PDR)
  • Mission Operations
    • Performed at Mission Operations Center (MOC) location
    • Instrument Support Terminal at GSFC
  • Space Communications
    • NASA Ground Network
  • Project Implementation and Management performed by GSFC

Mission Development Schedule

- Phase A start December 2009

- SRR/MDR May 2011

- PDR: March 2012

- CDR: March 2013

- MOR: April 2014

- PSR: December 2015

- LRD: April 2016

atlas instrument overview
ATLAS Instrument Overview

A key function of the structure is to provide component & subsystem layout

Laser Radiator Struts

2 Star Trackers

Power Distribution Unit (PDU)

TAMS Light Source

LRS & LRS Electronics

Radiators

SIRU

Optical Filter Assembly (OFA)

Beam Steering Mechanism (BSM)

Aft Optics

Diffractive Optic Element (DOE)

LHP Evaporator

DAA Optics & Electronics

Beam Expander (BE)

Optical Bench

Laser Sampling Assembly (LSA)

Telescope & Sunshade

Composite Box Structure

Beam Dump

Fold Mirror

Lasers

Polarizing Beam Combiner (PBC)

SC Interface Flexures

X

X

Y

Optical Bench

Isometric View

Y

Z

structure assembly exploded model
Structure Assembly - Exploded Model
  • Top (+X) Panels
  • PDU, OFA, Laser Radiator Struts
  • Optical Bench (-Z)
  • Lasers, BSM, Beam Expander, DOE, SIRU, LRS, Optics, Star Trackers, TAMS & Laser LTRs

Side (+Y) Panel

DAA Optics & Electronics, MEB, Laser Radiator & Flexures

2 Laser Radiator Flexures

4 Titanium Blade Flexures

Optical Bench Interface

Sunshade

Back (-Z) Panel

  • Front (+Z) Panel

Side (-Y) Panel

Fiber Test Bracket

Bottom (-X) Panel

Instrument to SC Electrical Bracket

6 Panel Bonded Assembly

ACD Heritage Composite Edge Clip Approach

4 Titanium Blade Flexures

Spacecraft Interface

instrument block diagram
Instrument Block Diagram

S/C command/telemetry and clocks/pulses

Gyro (S/C)

Signals Key:

Cmnds/Telem

Clocks/ pulses

Power

ICE Sat-2 Spacecraft

S/C command/telemetry and clocks/pulses

Star

Tracker (S/C)

Stars

(Zenith)

IEM

1553

LRS

Processor

Spacewire

Spacewire

16 channel counting

1PPS

LTR

Diffractive Element

1PPS

Laser 1

Laser 2

Data / Science

To Earth

(Nadir)

Start pulse

BAM

Start Pulse

Mechanisms

Thermal

Thermal / HK

Main

Start Pulse Detector

LRS

PDU

Telescope

Fiber

delay

line

Laser

HVPC

Det

From Earth

(Nadir)

Ultra

stable oscillator

20 MHz

Narrowband Filter

Spot images

Photon counting detector

Fibers (≤16x)

Survival

Thermistors

slide21

ATLAS Functional Block Diagram

ICE Sat-2 Spacecraft

Signals Key:

Commands/Telemetry

Clocks/Pulses

Power

Beam Dump

Fold Mirror 1

Fold Mirror 2

Avionics

Laser

Sampling

Assy

Polarizing Beam Combiner

Start pulse detectors

and electronics (x2)

Laser 1

Laser 2

Detector Electronics Module (x6)

Detector Select Mechanism (x6)

Detector Modules

MEB

Optical Path

1553

Processor

Spacewire (x2)

6 Laser Beams

to Earth

(Nadir)

Beam

Expander

Memory/

Serial

Interfaces

Detector Optical

Module

Gyro (S/C)

Board

A

(primary)

Etalon

Fiber-Optic

DOE

PMT

A

Transmit LTR

1pps

(x2)

Star trackers 2x (S/C)

Photon Counting Tracks 1-3

Stars

(Zenith)

Beam Steering Mechanism

(tip/tilt mirror)

LRS

MCE

LRS electronics

Wavelength Tracking Loop Optics

Wavelength Tracking Module

Board

B

(redundant)

TAMS LTR

HK/Thermal

BCE Test

Port

LVPC

TAMS light Source (4 fibers)

USO (x2)

(x6)

Laser Energy Return from Earth

(Nadir)

HVPC

HVPC (x2)

Fiber-Optics

300 µm (6x)

Main (x2)

Detector Array Assembly

Telescope Aft-Optics

Assy

PDU

( x2)

PDU

( x2)

Command I/F Board

OFA

Det (x2)

Receiver

Alignment

Test Port (x6)

PMT

B

Laser (x2)

R-C Telescope

0.8m , 3.6 m EFL

Beryllium

Thermal Control

access to space

Access to Space

  • ICESat-2 is baselined as a co-manifest dual-payload launch
  • Working several options – DMSP-20 is the primary opportunity
  • This approach is mandated because of the lack of qualified medium-class launch vehicles
  • There are several challenges and risks associated with this approach that must be “managed”
    • Schedule issues complicated this process
    • Engineering design issues overlay a added level of complexity
    • Challenges associated with interactions between NASA and partner – at all levels of management

5.4m Short PLF

DMSP-20

5.4m Short Envelope

DSS4 2.5Plug

IceSat2

C13 Adapter

Centaur Forward Adapter

icesat 2 operational concept
ICESat-2 Operational Concept
  • ICESat-2 is a 3-year mission divided into five phases:
    • Pre-Launch Phase - The Pre-Launch Phase consists of all design, development, test, and integration activities for the spacecraft, instrument, ground system, and launch vehicle through launch readiness
    • Launch and Early Orbit - The Launch and Early Orbit (LEO) Phase begins with the final launch countdown through the observatory attaining the initial orbit
    • Commissioning - The Commissioning Phase begins after the initial orbit is attained and lasts for no more than 60 days. During the Commissioning Phase, spacecraft and instrument checkout and initial calibration will be completed
    • Operations - The Operations Phase begins at the completion of the Commissioning Phase and will last for 3 years during which time science data will be collected on the observatory, dumped to the ground for processing and distributed for science use
    • Decommissioning - The Decommissioning Phase begins at the completion of the Operations Phase and at the direction of NASA. It includes all the planning and activities required to passivate the observatory, concluding with the successful de-orbit of the observatory
slide26

A Day in the Life of ICESat-2

Continuous Ranging

Back-up contact

S-band contact

Back-up contact

X-band dump

Xfer to LZP/L0 proc

Xfer to SIPS/L1 proc

Ocean scan

Round the world scan

Once per 8 days

Point to vegetation tracks

at mid-latitudes

Orbit adjust maneuver

Up to once per week

Day/night

Ground track latitude

l1a reformatted telemetry
L1A – Reformatted Telemetry
  • Parsed, reformatted, time ordered telemetry remaining in downlink units
  • Conversions of selected parameters of data ordering and monitoring
l1b science unit converted telemetry
L1B – Science Unit Converted Telemetry
  • Science unit converted time ordered telemetry. Reference Range/Elevations determined by ATBD Algorithm using Predict Orbit and s/c pointing. All photon events per channel per shot.
  • L1B is a per-event product –Contains all data.
  • Will not contain precise geolocation, only uses predict orbits or coarse location is available in the telemetry.
  • L1B provides all of the telemetry pieces that go into the ground finding and geolocation:
      • For a given shot: times of photon events; retains beam information, channel information, etc…
l2a high rate geophysical
L2A – High Rate Geophysical
  • Reference Range/Elevations determined by ATBD Algorithm using POD and PPD. All photon events per shot per beam. Includes POD and PPD vectors.
  • The conversion from L1B to L2A is where the Science algorithms take over.
  • Geolocation provided on a per-shot, per beam basis.
  • Geolocation requires finding the surface, as such an algorithm will need to aggregate many photon events and many consecutive shots.
  • L2A will report the reference range used in the geolocationcalculationfor the reported lat, lon of a each shot. This range need not be the highest-accuracy range possible, but should be correct to < ~100m.
  • Recall: downlinked data will have limited telemetry range window(0.5 to 6 km), per flight algorithm use of DEM and DRM. Therefore it will not contain photon events from high in the atmosphere. It will be subject to false alarm and contain noise within the telemetry range window.
  • L2A provides all of the pieces needed for alternate/refined/selective algorithm ground finding, surface characterization and geolocation for higher level products or research:
      • For a given shot: times of photon events; retains beam information, components of POD, PPD analyses at natural rates; rotation matrix, etc…
l2a reference range
L2A- Reference Range
  • How to decide which photons to use to find ground? Algorithm TBD, but will require many shots. This could be done many ways, but one approach needs to be selected to produce a reference range.
  • Once a reference range is determined, then a geolocate a center of each illuminated footprint, on a per-shot per-beam basis will be computed.
  • Process requires interpolation of both POD and PPD and a combination of many along-track shots. For some shots, we may not have any surface-reflected photons, but will still report a geolocation center for that shot.
what s next
What’s Next
  • Spacecraft contract in place this summer
  • Instrument PDR in late fall
  • Detailed design underway in late 2011
  • Mission PDR in early 2012
  • Mission CDR in early 2013
  • Launch from Vandenberg Air Force Base April 2016
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