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Presented to

International Workshop on Earth Observation Small Satellites

for Remote Sensing Applications

Robert Meurer -ATK Space

November 21, 2007

2121ststCentury Remote Sensing Microsatellites

Century Remote Sensing Microsatellites

““ItIt’’ s Not Your Father

s Not Your Father ’’s Oldsmobile

s Oldsmobile””

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It’s Not Your Father’s Oldsmobile

In 1988, General Motors launched a rare anti-branding campaign that sought to

dispel the impression that Oldsmobiles were ‘stodgy box-m

obiles’

•Oldsmobile’s intent was to reinve

nt itself for yo

unger drive

rs and distanceitself from eve

rything for

which it had previously stood

–Hence

the "Not yo

ur father's O

ldsm

obile" slogan was born as a clear attempt to put the shine back in

the brand

•The ad campaign faile

d –

The problems with it, of course, were:

–It said what Olds wasn't, but not what it was, and

–It m

ore or less told a generation of Olds loya

lists that their previous car choice was an

embarrassment

•Net effect was not reinventing the O

lds brand identity but of carving the identity in stone

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In their Heyday

During the period of their greatest vigor, strength, and successOldsmobile

epitomized achievement in distinctly middle-class term

s—a high-quality

car, but nothing so snooty as a Cadillac

Over time, the expression, “Not Your Father’s Oldsmobile”has come to

characterize product offerings that are new, different and better than

whatever came before them

For many reasons, 21stcentury remote sensing microsatellites are not your

father’s remote sensing satellites

Rather, they provide new, different and sometimes better solutions to a

user’s needs

Lest we replicate the failed Oldsmobile campaign, we need to define

•What a small or micro remote sensing satellite is;

•What it can and m

ore importantly cannot do;

•What are the features and benefits of these spacecraft;

•What are the differences in how small remote sensing satellites are developed, and

•Why the loya

lists of 1970 and 1980 vintage remote sensing systems should consider

using them for 21stcentury imaging m

issions

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New Era of Remote Sensing Satellites

The Turn of the Century Marked a New Era of Remote Sensing Satellites

•Both NASA and the U.S. DoD embarked on new visions for smalle

r space systems

NASA

•Created the New M

illennium Program (NMP) with a stated goal to m

ake future

operational spacecraft "faster, cheaper and better" through incorporation of the

technologies validated in that program

•The Earth O

bserver-1 m

ission (the first NMP Flig

ht) was created to flig

ht-validate

advanced technologies for the next generation Earth Science Enterprise science needs

DoD

•U.S. National policy requires an ability to “augment space-based capabilities in a tim

ely

mannerin the event of increased operational needs or [to] minim

ize disruptions due to

on-orbit satellite failures, launch failures, or delib

erate actionsagainst U.S. space

assets

[1] .”

•The O

perationally Responsive Space (ORS) approach to building satellites represents a

new paradigm for the aerospace community and will impact future development

programs to provide operational responsiveness within the tim

eframe of a m

ajor national

emergency and provide direct connectivity to the warfighter in the theater of operations

[1]U.S. Space Transportation Policy, January 6, 2005

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ATK has Been at the Forefront of NMP and ORS

This Paper reviews Major design implementation differences between

legacy systems and these new, smaller remote sensing systems

This paper highlights and contrasts…

•The traditional risk averse approach to space, where it is required and where

adjustm

ents are acceptable to achieve contemporary system goals & objectives

•Key perform

ance m

etrics of current remote sensing small satellites such as power, data

throughput, agility, mass and volume with emphasis on the technologies that enable

higher perform

ance in today’s small buses

•Insight is provided on innovative adaptations of terrestrial andother non-traditional flight

technologies and reuse of existing technology to achieve rapid design, and assembly,

integration and test while

maintaining aggressive perform

ance requirements

ATK’s Responsive Space Modular Bus Program Reflects a rapid design and

production process for highly capable satellite buses to meet the stressing

development requirements of today’s world

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Legacy Systems Have Served Us W

ell

Landsat, SPOT and Other Legacy Systems

Provided a Wealth of Medium Resolution Data

•Landsa

t and SPOT are School Buse

s

•Remote Sensing M

icrosatellites are Smart Cars

Each Provides Capability, but at a Much

Different Level of Perform

ance

3000

May 2002

SPOT 5

2755

March 1998

SPOT 4

1907

September 1993

SPOT 3

1870

January 1990

SPOT 2

1830

February 1986

SPOT 1

1969

April 15, 1999

Landsat7

1740

October 5, 1993

Landsat6

1938

March 1, 1984

Landsat5

1942

July 16, 1982

Landsat4

960

March 5, 1978

Landsat3

953

January 22, 1975

Landsat2

816

July 23, 1972

Landsat 1

Mass (Kg)

Launch Date

Mission

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Remote Sensing Microsatellites

What They Are and W

hat They Are Not

Legacy Systems –Global Coverage at Moderate Spatial and Spectral Resolution:

••Landsat

Landsat: Multispectral 30 x 30 m

; Pan 15 x 15 m

; 185 km swath

••SPOT

SPOT: M

ultispectral 20 x 20 m

(60 km swath); Pan 10 x 10 m

(117 km swath)

Contemporary Remote Sensing Microsatellites –Sophisticated imaging platform

s

with equal or better spatial and spectral perform

ance as compared to larger systems,

providing regional vice global coverage and better temporal resolution when

launched in small constellations

•Typ

ical Resolution 1 to 3m PAN & 4 to 8m M

ultispectral with a 10-25 km Swath W

idth

••The Image Capacity of Small EO Satellites is Typically a Fractio

The Image Capacity of Small EO Satellites is Typically a Fraction of the Legacy Systems

n of the Legacy Systems

Legacy National Im

aging Systems

0

50

100

150

200

250

05

10

15

20

25

30

35

40

Spatial Resolution

Swath Width

Landsat

Landsat

SPOT

SPOT

= Panchromatic

= M

ultispectral

21st Century Earth Observation Satellite

0

10

20

30

0.0

2.0

4.0

6.0

8.0

10.0

Spatial Resolution

Swath Width

FormoSat-2

FormoSat-2

TopSat

TopSat

RazakSAT

RazakSAT

Ikonos

KOMPSAT-2

WorldView-2

WorldView-2

Ikonos

KOMPSAT-2

21st Century Earth Observation Satellite

0

10

20

30

40

0.0

5.0

10.0

15.0

20.0

25.0

30.0

Spatial Resolution

Swath Width

EO-1 Hyp

erspectral

EO-1 ALI

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Comparing ATK’s EO-1 and RSMB Development

EO-1 and RSMB Are Similar Low-Earth

Orbit Imaging Systems

•Guidance, Navigation and Control (G

N&C),

Avionics and Software Challenges are Sim

ilar

Between the M

issions

•Each Spacecraft Carries a Hyp

erspectral-

Imaging (HSI) Payload In Low-Earth O

rbit

–EO-1 Also Hosted the Adva

nce

d Land Imager

EO-1 was a Conventionally Designed

Contemporary Earth Observing Mission

•Deve

loped Using a Traditional NASA Class-B

Design and Risk Approach

RSMB W

as An ORS Class-D Approach

•More Ambitious Perform

ance, Cost and

Schedule Drive

rs Associated W

ith

Operationally Responsive Space (ORS)

Objective

s Required an Aggressive

Engineering and Deve

lopment Approach

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EO-1 Mission Overview and Objectives

EO-1 –first of the New Millennium Program (NMP) Earth-orbiting missions

•The primary payload, the Advanced Land Imager (A

LI) is a reflective triplet telescope

with m

ultispectral detectors producing the Landsat bands plus four other spectral bands

•Secondary Payload (added Late in the Development Cycle) was the H

yperion

hyp

erspectral im

ager (H

SI)

•The EO-1 spacecraft was launched from Vandenberg Air Force Base using a

Delta

7320 vehicle on November 2000

–Circular, nadir pointing, sun-syn

chronous polar orbit at an altitude of 705 km

-The descending nodal crossing tim

e is 10:01 a.m

.

–EO-1 flies in a form

ation flying arrangement with Landsat-7 and EOS-AM (Terra)

Key Mission Objectives:

•Perform

an on orbit evaluation of several instrument and spacecraft technologies that, if

proven, would greatly reduce m

ass, power, cost & development time of future Landsat

missions, while

sim

ultaneously increasing perform

ance by severalorders of magnitude

•Mission O

bjective was O

ne Year; Design Life of 1.5 Years; Perform

ance of 7+ Years

Any notion that small spacecraft are unreliable has been disproven by EO-1

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EO-1 –Taking a Closer Look

High Power, Precision Pointing Low-Earth Orbit Bus

•1.5 Year Design Life In Low-Earth Orbit; 1-year Mission

–16 Day Repeat Orbit -Circular Sun-S

ynchronous at 705 Km,

98.7º, 99 M

inutes, Descending Nodal C

rossing Tim

e of 10:15

AM

•Compatible W

ith Delta II and Other ELVs

–Shared Launch

with

Argentina’s SAC-C

Satellite on Boeing

Delta

II (7920-10C) Launch Vehicle From Vandenberg, AFB

•Launch Mass 588 Kg (Wet)

–Bus M

ass ~370 Kg; Payload M

ass Fractio

n of 23%

–Hexagonal A

l Structure, 1.25m ∅

(Across Flats); 0.73m High

•Zero Momentum 3-axis Stabilized for Inertial and Nadir

Pointing

–Knowledge Capability = < 35 arcseco

nds (3σ)

–Control C

apability = < 50 arcseconds (3σ)

–Pointin

g Stability (Jitter) = <0.5 arcseconds/seco

nd

•Robust Power Capability

–800W Total A

rray Power; 1 W

ing, 3 Panels, Articulatin

g

–350W O

rbit Ave

rage Power @

28V

–Super Ni-Cd, 50 Ah Battery

•Mongoose V, RISC CPU W

ith 48 Gbits of Bulk Memory

–MIL-STD-1773 Fiber Optic Data Bus

–VxW

orksOperatin

g System

–AutoCon

on-board software pack

age for autonomously

planning, executin

g, and calibrating routin

e spacecraft

maneuve

rs to m

aintain Landsat-7/EO-1 form

atio

n

•Propulsion

–Four 1 N Thrusters, Hyd

razine Propulsion System (Primary)

–PPT Secondary Propulsion System –

Technology

Demonstratio

n

EO-1 Flies in Trail of Landsat-7 by 60 Seconds

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EO-1 –Functional Block Diagram

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RSMB Mission Overview and Objectives

Responsive Space –a U.S. National initiative in Support of the Warfighter

Responsive Space Provides:

•Satellite to Shooter –Space Capabilities Delivered Directly to the O

perational and

Tactical Warfighter Within M

inutes of a Collection O

pportunity;

•Capacity to Respond to Unexpected Loss or Degradation of Selected Capabilities;

•Tim

ely Availa

bility of Tailo

red or New Capabilities to Support National Security

Requirements;

•Fielding Space Capability in a Responsive M

anner within Cost andSchedule

ATK’s Responsive Space Modular Bus (RSMB) Addresses DoD Needs to

Rapidly Field New Capability in Support of Tactical Users Providing

Demonstrable Military Utility RSMB –First bus built from scratch to

address ORS mission needs

•Primary Payload -Tactically Effective M

ilitary Imaging Spectrometer (ARTEMIS)

•Key Program O

bjectives:

–Design, Fabricate and Deliver the Bus in 12 M

onths (Achieve

d 15 M

onths)

–Ove

rall Mission Cost <$50M –

Bus, Payload and Launch

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RSMB –Taking a Closer Look

High Power, Precision Pointing, Agile LEO Bus

•1 Year Design Life in

Low-Earth O

rbit‡

–Baseline O

rbit -LEO Circular at Any Inclinatio

n

–Compatib

le W

ith Any Beta Angle

‡Extendable W

ith Hardware Upgrades

•Compatib

le W

ith M

inotaur and O

ther Small ELVs

–Baseline Design is M

inotaur I From W

allops Island, VA

•Launch

Mass Contin

gent Upon on Payload Accommodation

and Power Requirements

–Bus M

ass ~200 Kg†; Payload M

ass Fractio

n of 50%

†Designed for Rapid Productio

n; Mass M

ay Be Further Optim

ized

•Zero M

omentum 3-Axis Stabilize

d Precision Pointer

–Knowledge Capability = 5 arc-seconds (3σ)*

–Control C

apability = 20-80arc-seconds (3σ)*

*Referenced to Payload M

ountin

g Deck

•Robust Power Capability

–Up to 700 W

atts Total P

eak Payload Power

–Optim

ized for Sunlit Payload O

peratio

ns

–~100 W

-hr of Payload Power Ove

r 15 M

inute W

indow

–~3m²ATJ Solar Array in 3-W

ing Configuratio

n

–24 A-hr Battery (Optio

nal 4

8 A-hr Battery)

•High Speed CPU W

ith 1 G

byte of Bulk M

emory

–Mature, Heritage C&DH Software

–Autocoded G

N&C Software

–Adva

nced O

n-board Autonomy and Automated Test

–RS422 Interfaces to Critical Payload and Bus Elements

–Hardware-In-The-Loop Sim

ulator to Support Flight Software and

Hardware/Software Integratio

n

The Inherent Modularity of RSMB Enables

Upsizing or Downsizing of the Bus to Fit on

Multiple Launch Vehicles or Support Missions

Requiring Lesser or Greater Performance

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RSMB –Functional Block Diagram

Therm

al

Control

Avionics / C&DH / T&C

Mission

Payload

Transponder

Attitude Determ

ination and Control Subsystem

Reactio

n W

heels

Torquer Bars

Dual Head

Star Tracke

r

CSS x 6

3-Axis

Magnetometer

S-Band

Uplink /

Downlin

k

Power Subsystem

Power

Conversion &

Regulation

Auxiliary Electronics

Box

Power Control

Electronics

24Ah

24Ah

Solar Arrays

•PowerPC 750

Processor

•Data Storage

•Payload Control

& Power

•ADCS

Subsystem

Electronics

•I/O for Bus

Systems

Mission Unique

Support

Electronics

GPS Rx

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RSMB–Packaging and Mechanical Layout

Bus Top Deck Can Support 160 Kg Payload and Additional Boxes Internally

•Payload Interface Is Adaptable to O

ther Form

Factors

Six Side “Equipment Panels”Can Hold Various Components

•Three Are Used by the Bus W

ith the Remaining Three Ava

ilable forPayload

Bottom Deck Is Designed for 96.5cm (38”) Lightband and Other 38”Interfaces

66 cm

116.8 cm

Payload

Mountin

gDeck

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Notional Instrument

Mounting Points

RSMB –Payload Accommodation Capability

Mass –160+ Kg

Volume –1.0 m

3

Payload Power –

•700 W

atts –

Total Peak

•~100 W

-hr of Payload Power Ove

r 15 M

inute W

indow

Data Rate (SGLS)

•Uplink

Data Rate: 2 Kbps Encryp

ted

•DownlinkData Rate: 2 M

bps Encrypted

•Encryption/Decryption Compatib

le

Notio

nal

Instrument

Accommodatio

n

RSMB

RSMB

Payload

Deck

Notional Instrument

Mounting Points

RMSB is Designed to Support

Imaging Payloads Requiring

Precision Pointing

•Power and Volume to Support High-

Capacity Data Downlinks

•Highly Agile to Enable Rapid

Reorientation of the Spacecraft

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RSMB–Electrical Power Subsystem

Solar Array

•3 Segments, ~500W Each M

aximum

–GaAs Triple Junctio

n, 28.3% Efficient

–72 Strings –

19 Cells Each

String

–1.4% Loss Per Failed String

•Vmp : BOL 44.03V, EOL 43.63V

Lithium Ion Battery

•Twin 24 Ah Batteries (48 AH Capacity)

•Industry Standard 28V ±4V

•Prove

n Flight Heritage Design

Peak Power Tracker

•Buck Regulator, Verified 94.3% Efficient

•20 Amps M

ax Output / 500 W

atts Each

Power Control Electronics

•Heritage ATK THEMIS Design

•Approve

d 2 Fault Tolerant Safety Inhibits

•High Accuracy 14 Bit 50KSPS A/D Conve

rter

Power Control Electronics from THEMIS

24 or 48 Ah

Lithium Ion

Battery

ATK S

pac e

Division

PCE

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RSMB–GN&C Subsystem

Perform

ance Capabilities*

•Attitude Knowledge

–5 arc-seconds (3σ) *

•Attitude Control

–20-80 arc-seconds (3σ) *

•Jitter:

–High Freq: <0.2 arc-seco

nds O

ver 40 m

sec Integration Tim

e–

Low Freq Drift: 20-80 arc-seconds O

ver 40-Seco

nds

-Assumed Attitude Control Requirement During Image Sca

n

•Slew Rate Capability

–2°-5°/se

c x,y,z axis or any desired Eigen slew axisŦ

–Slew Acceleratio

n Capability 0.02°to 0.04°/se

c²Ŧ

*Reference

d to Payload M

ountin

g Deck

Ŧ(Contingent Upon final Spacecraft MOI)

Pointing Budget Analysis Assumptions

•Budget Allocation Is Based on ATK EO-1 Analysis & Exp

erience

•Star Tracker With Dual Camera Head Units (CHU) Mounted on Payload O

ptical Bench to M

inim

ize

the M

isalignment Errors.

–Both CHUs Are Assu

med to Have

Valid Stars in the FOV W

ithout AnyIntrusion

•Scene Is Assumed to Be Located Along the Nadir Direction

•Post Launch G

round Calibrations Are Used to Calibrate the System

–Static M

isalignments Among ST, IRU and Payload LOS; IRU Sca

le Factor Calibratio

n

•Orbit Propagation and Automated G

uidance Errors Are Assumed W

ith0.002 Seconds Equivalent

Tim

e Delay

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RSMB –Therm

al Subsystem

Passive Therm

al Design

•Internal Spacecraft and Payload Electronics

Use High Emittance (>0.8) Coatings to M

aintain

Uniform

Spacecraft Bus Temperatures

•Passive Radiators Remove

Excess Heat From

the Spacecraft Bus Equipment Panels

–Design Philosophy Prove

n on EO-1 M

ission

–Radiator Sizing Easily Adjusted As the Design

Matures

–All Radiators Sized for Hot Environmental

Conditions and End-of-life (EOL) Properties

•Plug-n-Play 1-W

ire®Temperature Controlled

Heater Concept Validation

•Multi-Laye

r Insulation (MLI) Blankets and

Therm

al Coatings Cove

r Unused Areas on the

Bus Exterior

–Decrease

s the Effect of On-O

rbit Environmental

Changes

–Only Sensor Apertures, Solar Arrays and Therm

al

Radiators Exp

ose

d

•Uniform

Temperature Range for the Spacecraft

Bus Projected to be -15°C

to +50°C

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RSMB –Avionics / Plug and Play

C&DH Design Leverages COTS Products

High Perform

ance PowerPC

®750FX

Processor

•Single-Slot Conductio

n-C

ooled 3U Compact-PCI

(cPCI) Single Board Computer (SBC)

•1856 Dry M

IPS, 24.8 SPECfp95

•128 M

B SDRAM, 64 M

B Flash,

1 GB NV Flash Memory

2X 12 Port RS-422 Interface Board

•12-Full Duplex Syn

c/Asyn

c RS-422 Ports

•2 M

bps Asyn

c, 10 M

bps Syn

c

Digital I/O

•Reactio

n W

heel Tach

ometer

•Torque Rod Drive

rs

•GPS Rece

iver

•Solar Array Drive

Electronics (Unused)

Plug-and-Play Avionics

•1-W

ire®Base

d Telemetry and Therm

al Control

Subsystem

SDTN or SGLS Transponder

•Fully STDN, CCSDS or SGLS Compatib

le Radios

•2000, 1000, 500 bps Uplink (Factory Set)

•BPSK/FM Downlink; 4.0 M

sps m

ax.,

Power PC 750 SBC

12 Port RS-422

Interface Board

Digital I/O CXS-610 STDN/USB/DSN

Space Transponder

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Optional Mono-Prop Subsystem

Optional Propulsion Module Built to be

Integrated Between the Launch Vehicle and

the RSMB Bus

•Lightband Is M

ove

d From The Bottom of the Bus To The

Bottom of the Propulsion M

odule

Key Components

•Two or Four Mono-Propellant Tanks with Sim

ple Propellant

Management Device

–Sim

ilar to THEMIS Tanks

•Four Aerojet Thrusters

•Single Latch Valve, 2 F/D Drains

•One-W

ire®/RS-422 Interface

for T&C

Top View of Module,

Central Deck for Tank Support

Bottom View of Module,

Bottom Panel with Thruster Mount

PP/V

F/D

FLT

LV

P-DCR

T1

T2

T3

T4

15µm

40µm

20µm

20µm

20µm

20µm

0.61 m

m

N2H4

GN2

N2H4

GN2

N2H4

GN2

N2H4

GN2

PP/V

F/D

FLT

LV

P-D

CR

T1

T2

T3

T4

15µm

40µm

20µm

20µm

20µm

20µm

0.61 m

m

N2H4

GN2

N2H4

GN2

4 Tank

2 Tank

•13.5”tanks, @75% Fill Fraction holds 16 kg

•2 tanks @

32 kg

•4 tanks @

64 kg

80.1

151.5

131.3

0.0

Minotaur I Fairing

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Remote Sensing Microsatellites

Significant Program Execution Differences

EO-1

•GSFC M

anagement; ATK Spacecraft Bus

•Classical NASA Deve

lopmental A

pproach

•Deve

lopment Schedule Followed Typ

ical NASA

Science Programs –

3+ Years

–Design Conve

rgence

Review at 6 m

onths

–Critical Design Review at 12 m

onths

–Pre-Environmental Review at 26 m

onths

–Flight Readiness Review and la

unch at 39 m

onths

-Note: This schedule includes the addition of a

major instrument, the Hyp

erion Instrument after

the program CDR

–Environmental tests perform

ed at GSFC

–GSFC proce

sse

s (plans, proce

dures, standards,

etc.) were followed

–Most of the spacecraft and in

strument hardware

was custom-designed (including substantia

l new

flight software) alth

ough m

any were derive

d from

previous designs

–All of these

factors resu

lted in

a competitive

spacecraft bus cost for a NASA science

space

craft

of this size and perform

ance

RSMB

•AFRL M

anagement; ATK Spacecraft Bus

•Risk Tolerant Deve

lopment Methodology

•Aggressive, 12-M

onth M

ission Deve

lopment

Schedule

–Use of Plug-&-Play (P&P) Standards and Interface

s

in a Class-D

Point-Design Bus

–Design Based on Readily Ava

ilable Components

(COTS W

here Applicable), Trading Perform

ance

&

Flight Heritage for Cost & Schedule

–Sim

ple M

odular Design; Mass O

ptimizatio

n as a

Seco

ndary O

bjective

–Large Design M

argins in

Critica

l Parts/Subsystems

(e.g., Solar Arrays & Batteries) to Acce

lerate

Procu

rement

–Targeted and Focuse

d Testin

g to Reduce

Sch

edule

–Lim

ited, Esse

ntia

l QA O

nly

–Extensive Reuse

of Existing Plans and Procedures

–Leve

raging of Capital Inve

stm

ent in Swales

Operatio

nally-responsive FlatSat and Integrated

Avionics (SOFIA) Testbed

–Use of Flight Prove

n Software, GN&C Autoco

ding

and P&P Implementatio

n

International W

orkshop on EOSS forRemote

Sensing, 20-23 Nov 2007, Kuala Lumpur, M

alaysia > Dr. R. Sandau > 22

1 M$

10 M$

100 M$

cost

1 yr

2 yrs

5 yrs

response

time

Examples

CubeSat:

1 kg, ca. 2 yrs, 0.2 M$

ENVISAT:

8 t, 15+ yrs, 3 ×109$

mass

1 kg

10 kg

100 kg

10 000 kg

Pico

Nano

Micro

Mini

Small Satellites

Large Satellites

1000 kg

EO

EO-- 11

RSMB

RSMB

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Remote Sensing Microsatellites

Features and Benefits

Perform

ance

•Spatial and spectral equivalency if not superior

•Temporal resolution m

ay be higher

•Ove

rall capability tailored to user needs

Technical –COTS technology is enabling

•Months old technology vs. decades old

•Leve

rages a larger inve

stm

ent

Schedule –Development Time is Short

•Traditional systems take a decade or more

•Modern systems m

ay be built in 12-18 m

onths

Cost –is Relative

•Smaller satellites cost less to build and launch,

but have

significantly lower data capacity

•Can you build a system that is cost competitive

to the purchase of im

agery from a big satellite?

Flexibility -You own it, you control it

•Data tim

eliness can be m

uch improve

d; yo

u set

the priorities

•A constellation of eve

n a few m

icrosatellites,

may significantly increase the revisit rate

Risk –Need not be Greater, But it Must

be Managed

•A launch failure results in a smaller financial

loss

•A constellation provides system resiliency in

the face of a single spacecraft failure

National Prestige –Priceless

Why should the loyalists of 1970 and 1980 vintage remote sensing

systems consider using them for 21stcentury imaging missions?

An adva

nced weapon and space systems company

Decem

ber 19, 2007

Oldsmobile vs. SMART

The last Oldsmobile Alero left the Lansing, Michigan plant on April 29, 2004

SMART (Swatch Mercedes ART) began in 1993 as a joint venture between

Daimler-Benz and Swiss watchmaker Swatch

SMART continues to innovate as market forces demand new capability

As with any industry, continued innovation and out-of-the-box thinking is

required to maintain a market edge

Small Remote Sensing Satellites Provide a SmartAlternative for Earth Observation