defense and environmental objectives for the russian

9-12 August 2004 AIAA/USU Small Satellite Conference 1RS-D-0289-04 6/1/04

RAMOS


RAMOS

Defense and Environmental Objectives for the Russian American Observational

Satellites (RAMOS) Program

T. Humpherysa, V. Sinelshchikovb, A.T. Stairc, V. Abramovb, I. Schillerc, V. Misnikb, and V. Privalskya

aUtah State University/Space Dynamics Laboratory; bTsNPO Kometa;cVisidyne Inc.

Sponsored by US Department of Defense, Missile Defense Agency (MDA)


Mission Architecture• Circular, coplanar ~ 500 km orbit• Inclination = > 63˚

• Separation = 50-2,600 km• Station-keeping capability

TECHNICAL OBJECTIVES• Defense

• Cyclone strength • Smoke, volcanic plumes• Wind measurement• Water vapor profiles

and structureJoint Mission Operations Center(Moscow)

• Stereo viewing: US, RF missile targets

• Atmospheric IR backgrounds (detection, tracking)

• Solar glint (EW false alarm mitigation)

• Environmental


Defense Objectives

• Demonstrate utility of a unique, stereo-optical imaging capability

• Acquire SWIR, MWIR and LWIR background and target data; make inter-band comparisons

• Measure polarization components of scattered sunlight (e.g., glints)

• Acquire 6.3 µm water band data


Environmental Objectives

• Demonstrate utility of stereo-optical imaging for estimating hurricane strength, volcanic plume volumes and other dynamic events

• Acquire time-dependent stereo imagery to determine and model global 3-D wind velocity

• Acquire 3-D water vapor distribution data to aid in understanding the effect of water vapor on IR background scene structure


Payload Configuration

IR module

Vis/UV module

Visible push-broom(body mounted)

Thermal cover (open)

Satellite 1: SMWIR RadiometerMLWIR RadiometerSMWIR Polarimeter

Satellite 2: SMWIR RadiometerMLWIR RadiometerSMWIR SpectrometerMLWIR Spectrometer

PointingMirrors

(slaved toeach other)

30°x 30° FOR(range of pointing

mirrors)

High-Speed Visible CameraWide FOV Visible CameraSWUV RadiometerLWUV Radiometer

PolarimeterCloud Top Altitude

Sun Shades


Mirror System (1)

• Main mirror directs IR module sensors’ line of sight

• Slaved mirror directs Vis/UV sensors’ line of sight

• IR and Vis/UV instruments thus coaligned• Push Broom scanner body mounted, not

independently pointable


Mirror System (2)

Angular position sensors

Mirror launch lock

Mirror drives

Shutters/ calibrator

Mirror

Sensor interface


Sensor Pointing Modes

• Scanning Mode– Sensors’ LOS fixed w/respect to satellite and scan a

continuously changing scene as satellite moves

• Tracking Mode– Sensors’ LOS watch a specific point (ground, clouds,

etc.) as satellite move; instruments slew to keep point in view

• Step-Stare Mode– Sensors’ LOS watch a specific point for a given time,

then move forward to next point; combination of Scanning and Tracking modes


IR Module

Mirror

Input window shutters (open) Cryostat

Interface flange


IR Module Passbands

SMWIR Filters MLWIR FiltersSatellite #1 Satellite #2 Satellites #1, #2

No. Bandpass (µm) No. Bandpass (µm) No. Bandpass (µm)

1 2.00 – 2.40 (P) 1 1.45 – 1.60 1 4.66 – 4.90

2 2.70 – 2.95 (P) 2 1.95 – 2.19 2 5.40 – 7.20

3 2.95 – 3.20 (P) 3 2.21 – 2.40 3 5.20 – 6.20

4 3.20 – 3.50 (P) 4 2.70 – 2.95 4 5.20 – 7.50

5 3.75 – 4.20 5 3.75 – 4.20 5 4.66 – 7.50

6 4.23 – 4.45 6 4.23 – 4.45

7 4.35 – 4.55 7 4.35 – 4.55


Visible/UV Module

Input window shutters (closed)

Visible/UV radiometer unit

Angular position sensor

Connectors


Visible Push-Broom Scanner

Baffle

Lens

Focal Planes, Electronics


Moving Object Experiment

Rocket Trajectory

IR Radiometer& Visible Cameras Step-

Stare Observations

• Simultaneous MLWIR, MWIR observation of post-boost rocket body against hard earth– Enable optimizing bands for midcourse (BTH) and long-range

(ATH) tracking– Post-processing will reconstruct 3D midcourse trajectory

• SWIR/MWIR/MLWIR/UV observations of ignition through burnout


Backgrounds and Solar Glint

• Measurements in many spectral bands under widely varying background conditions to create stereo backgrounds data base

• Polarization measurements to characterize sunlight reflected from high clouds (“glint”), a source of surveillance system false positives

IR Radiometer& Visible Cameras Stereo Step-Stare

Measurements


Short-Duration Events

• Applicable to explosive signatures: ordnance, missile staging, etc.– Stereo-optical viewing can provide precise geolocation– High-speed measurements can provide data on dynamic nature of

signature– Multi-spectral measurements can provide chemical characterization

IR Radiometer& Visible Cameras Stereo Step-Stare

Measurements


Fast-Changing Events: Cyclones

• Most destructive natural calamities– Worldwide loss of life– Property loss in $ millions

annually

• Current predictive ability local, limited– “Hurricane Hunter” aircraft,

CONUS only– Measurements fairly crude

Hurricane Floyd: 14 Sep 1999


Fast-Changing Events: Volcanic Plumes

• Hazardous to aircraft– Can be far removed from

source– Can have thinned to

translucent cloud

• Affect weather patterns• RAMOS can bound cloud

– Altitude– 3D spatial extent

• Tomography can define spatial distribution of ash Mt. Etna eruption, 24 Jul 2001


Wind Velocity Distribution Measurement

Push-BroomCloud Top Mode

Push-BroomCloud Top Mode

• Measure wind velocity vs. altitude by tracking movement of cloud-top fragments


Water Vapor Profiles• Determine MLWIR

radiometric contribution to spatial scenes– All local zenith angles

including near-horizon viewing geometry

• Determine vertical distribution of atmospheric H2O vapor with spectral measurements

• Demonstrate capability to measure at scale of < 100m


Conclusion

RAMOS: A Unique and Important Program• A “Pathfinder”: the only cooperative space research program

between DoD and MOD• Has enjoyed high-level government support in both countries• More than a decade of fruitful cooperative research• The only program investigating multi-spectral/stereo-optical

techniques to mitigate EW false alarms• The only program using these techniques to assess hazardous

environmental effects world-wide and their potential impact on human health and safety

• In Feb 2004, MDA announced plans to bring RAMOS to an orderly close before the Critical Design Review


Backup Material


System Description (1)

• Satellite System– 2 Satellites– Co-planar circular orbits, ~500 km, ~66°

inclination– Separation (“stereobase”) ~500km, variable– Stationkeeping capability on both satellites– 2-5 year on-orbit lifetime– RF “Universal Space Platform” with US & RF

sensors launched on RF Rokot booster


System Description (2)

• Ground System– Joint Mission Operations Center (JMOC) near

Moscow– Facilities for experiment planning, payload

integration and test, experiment operations, up/ downlink, data processing, data dissemination

– Data shared between US, RF; each nation independently analyses these shared data


RAMOS Overview• Joint US-RF “Pathfinder” program• Two co-orbiting satellites (~ 500 km altitude, 50 – 2,600 km

separation)• IR, visible, UV sensors• Unique stereoscopic measurements

– Defense applications (missile targets, atmospheric backgrounds, solar glint)

– Environmental applications (cyclones, volcanic/smoke plumes, water vapor)

• RAMOS presented as of successful US-RF JPDR in June, 2003

Note: MDA announced plans in February 2004 to bring the RAMOS program to an orderly closure prior to the Critical Design Review


Instrumentation

• Satellites carry complementary (not identical) Suites of Observational Instruments (SOIs).

• Each SOI consists of:– IR module (US-provided), Sat #1 ≠ Sat #2– Vis/UV module (RF-provided), Sat #1 = Sat #2– Visible-domain “Push Broom” scanner (US-

provided), Sat #1 = Sat #2• Pointing mirror system provided by RF


RAMOS Sensors

Pointing Mechanism Satellite #1 Satellite #2

Pointing System 1 IR Radiometer/ Polarimeter IR Radiometer/ Spectrometer

Pointing System 2

WFOV visible cameraHigh-speed visible cameraUV radiometer

WFOV visible cameraHigh-speed visible cameraUV radiometer

Body Mounted Visible Pushbroom Scanner Visible Pushbroom Scanner


IR Module Passbands (2)

SWIR

MWIR

MLWIR

Solar Scatter

Thermal Emission

Earth Radiance from Space Nadir View

1.E-08

1.E-07

1.E-06

1.E-05

1.E-04

1.E-03

1.E-02

1.E-01

1 2 3 4 5 6 7 8

W avelength (micron)

Rad

ianc

e (W

/cm

2/sr

/mic

ron)

Spectrometer 2.33 - 4.66 Spectrometer 4.66 - 7.50

Rad

ianc

e (W

/cm

2/sr

/µm

)

Wavelength (µm)

Blackbody 300 K

Earth/Atmosphere Day

Earth/Atmosphere Night


IR Module, Satellite #1

• 2-channel (SMWIR/MLWIR) imaging radiometer

• Polarimetry capability in SMWIR channel• Each channel has several filtered passbands• Can function as

– Imaging radiometer capable of simultaneous SMWIR/MLWIR measurements, or

– Simultaneous MLWIR imaging radiometer and SMWIR imaging polarimeter


IR Module, Satellite #2

• 2-channel (SMWIR/MLWIR) imaging radiometer

• 2-channel (SMWIR/MLWIR) imaging spectrometer– Diffraction gratings on both channels

• Each channel has several filtered passbands• Radiometer and Spectrometer can operate

simultaneously (4 channels at once)


Vis/UV Modules

• Visible high-speed camera/radiometer– Filter wheel with 3 passbands, 1 open position

• Visible wide FOV matrix camera– Array of 5 cameras with adjacent FOVs filling

FOR• UV radiometer

– 2-channel (SW, LW) instrument with 4-position filter wheels on each channel


Vis/UV and VPB Passbands

1.0E-08

1.0E-07

1.0E-06

1.0E-05

1.0E-04

1.0E-03

1.0E-02

1.0E-01

1.0E+00

0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1Wavelength (µm)

Rad

ianc

e(w

/cm2 sr

µm

)

UV

VPB

Nadir Viewing Day Radiance

VHSC

WFOV

Solar Scatter Angle = 180


1.0E-08

1.0E-07

1.0E-06

1.0E-05

1.0E-04

1.0E-03

1.0E-02

1.0E-01

1.0E+00

0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1Wavelength (µm)

Rad

ianc

e(w

/cm2 sr

µm

)

1.0E-08

1.0E-07

1.0E-06

1.0E-05

1.0E-04

1.0E-03

1.0E-02

1.0E-01

1.0E+00

0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1Wavelength (µm)

Rad

ianc

e(w

/cm2 sr

µm

)

UV

VPB

Nadir Viewing Day Radiance

VHSC

WFOV




Defense-Related Experiments

• Moving Object Experiment (MOE)– MWIR/MLWIR comparison

• Multi-Spectral/Stereo Backgrounds (MSB)– MWIR/MLWIR comparison

• Background Effects of Solar Scatter (BES)– SWIR, window bands

• Short-Duration Events (SDE)– All window bands: UV, visible, IR


Environment-Related Experiments

• Fast-Changing Events (FCE)– All window bands (UV, visible, IR)

• Wind Velocity Distribution (WND)– Visible, including VPB cloud-top filters

• Water Vapor Profiles (WVP)– SMWIR and MLWIR spectrometer


Sensor Fields of View

- -


Vis/UV Module Passbands (1)

Visible high-speed camera/radiometerNo. Bandpass (�m) No. Bandpass (�m)1 0.600 – 0.960 3 0.910 – 0.9602 0.500 – 0.650 4 0.400 – 0.960

Visible wide field of view matrix cameraChannel 1 Channel 2

No. Bandpass (�m) No. Bandpass (�m)

I. 2 0.540 – 0.565 II. 2 0.840 – 0.870I. 3 0.459 – 0.497 II. 3 0.910 – 0.960I. 4 Blank II. 4 0.400 – 0.960

I. 1 0.620 – 0.670 II. 1 0.740 – 0.760


Vis/UV Module Passbands (2)

UV RadiometerChannel 1 (SW) Channel 2 (LW)

No. Bandpass (�m) No. Bandpass (�m)

I. 2 0.230 – 0.280 II. 2 0.320 – 0.350I. 3 0.280 – 0.300 II. 3 0.350 – 0.400I. 4 0.200 – 0.300 II. 4 0.300 – 0.400

I. 1 0.200 – 0.230 II. 1 0.300 – 0.320


Visible Push Broom Scanner

• Linear-array sensor, 5 linear focal planes– 3 polarization filters w/electric field vectors at

60° increments– 2 unpolarized filters for spectral measure-ments

of light reflected from cloud tops

Filter No. Bandpass (�m)

1 (Polarization) 0.730 – 0.7802 (Cloud top I) 0.760 – 0.7673 (Cloud top II) 0.740 – 0.747


RAMOS Experiments

• 7 Generic Experiment Types with Numerous Variations

• Address Both Defense and Environmental Objectives– 4 generic defense-related experiment types– 3 generic environment-related types– Some crossover application between groups


MOE Goals

• Acquire and Observe Theater-Class Rockets in Mid-Course (i.e., Post-Boost) Under Difficult Viewing Conditions

• Obtain Multi-Spectral Boost-Phase Measurements for Later Study

• Three Primary Measurement Objectives:– Compare post-boost MWIR, MLWIR measurements– Demonstrate stereo viewing utility– Compare SWIR/MWIR/MLWIR/UV boost phase

measurements


MOE Approach, Product

• Data Collection– MWIR-MLWIR scene pairs – Collected from both satellites/stereo image data– Step-stare mode following predicted target

trajectory (no autonomous onboard tracking capability)

• Analytical Product– Scene processing to extract target from

background, reconstruct 3-D trajectory


MSB Goals

• Acquire Spatial/Temporal Radiance Stereo Image Databases of Earth Backgrounds, Simultaneously in MWIR, MLWIR Bands

• Compare H2O Vapor Absorption Band (5.4µm to 7.2µm) Against CO2 Absorption Band (4.23µm to 4.43µm)


MSB Approach, Products

• Data Collection– Image quadruplets (MWIR v. SLWIR stereo

pairs) for a range of observation conditions– Supporting data to character radiance source

regions and environments• Analytical Product

– MWIR/MLWIR scene comparison– Stereo background images suitable for

midcourse tracking and model building


BES Goals

• Examine Three Approaches to Minimizing Potential for False Alarms in EW systems:– Stereo-optical measurements– Simultaneous multispectral measurements– Polarization measurements


BES Approach, Products

• Data Collection– Emphasis on specular and non-specular solar glint – Polarized SWIR image data for range of observation

conditions– Supporting visible polarization data– Two-color (SWIR/MLWIR) glint data

• Analytical Product– Characterization of solar glint phenomenology– Assessment of polarization, multi-angle, multi-spectral

false alarm mitigation techniques


SDE Goals

• Observe Short-Duration Events (e.g., Explosions, Rocket Launch Ignition Spikes) Under Adverse Conditions (e.g., Clouds)

• Demonstrate Ability to Accurately Geo-locate These Events in Three Dimensions


SDE Approach, Products

• Data Collection– High frame-rate stereo and multispectral image

data of short-duration events (e.g., few to few hundred milliseconds)

– Simultaneous measurements in visible, SWIR, MWIR and MLWIR and UV bands

• Analytical Products– Assessment of ability to detect, identify and

geolocate short-duration events under a variety of observing conditions


FCE Goals

• Demonstrate Utility of High Spatial Resolution, Multi-Spectral, Stereo-Optical Remote Sensing in Characterizing Such Events as Cyclones, Volcanic Plumes, and Effluents from Industrial Accidents


FCE Approach, Products

• Data Collection– Multi-spectral stereo-optical measurement data

from suitable events (e.g., hurricanes, volcanic plumes, etc.)

• Analytical Products– Demonstration of ability to accurately estimate

hurricane strength globally– Demonstration of ability to accurately estimate

volume and extent of effluent plumes (volcanic, industrial, forest fires, etc.)


WND Goals

• Demonstrate Ability of Stereo-Optical Remote Sensing to Determine World-Wide Three-Dimensional Distribution of Wind Velocities


WND Approach, Products

• Data Collection– Time-dependent visible-regime stereo-optical

image pairs– Time-spaced VPB measurement sweeps using

cloud-top filters• Analytical Products

– 3-dimensional distributions of wind velocity


WVP Goals

• Characterize the 3-dimensional Distribution of Water Vapor Concentration in the Lower 10 km of the Atmosphere at a Horizontal Scale of 100 m


WVP Approach, Products

• Data Collection– 3-dimensional “cubes” of SMWIR, MLWIR

data from spectral data obtained on a 2-dimensional grid

• Analytical Products– 3-dimensional water vapor distribution model– Improved understanding of water vapor impact

on IR scene structure

defense and environmental objectives for the russian

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