macsat - a mini-satellite approach to high resolution

MACSATMACSAT -- A MiniA Mini--Satellite Approach to Satellite Approach to High Resolution Space Imaging High Resolution Space Imaging

The 17th Annual AIAA/USU Conference on Small SatellitesThe 17th Annual AIAA/USU Conference on Small SatellitesAugust 2003, Utah, USAAugust 2003, Utah, USA

BYUNG JIN KIMBYUNG JIN KIMSaTReCSaTReC Initiative Initiative Co. Ltd. (SaTReCCo. Ltd. (SaTReCii))

http://www.satreci.comhttp://www.satreci.combjkimbjkim@@satrecisatreci.com.com

MACSAT – A Mini-satellite Approach to High Resolution Space Imaging -2

SSC01-VI-8: The 17th Annual AIAA/USU Conference on Small Satellites

Program Overview

Joint Development between SaTReCi and ATSB

Mission ObjectivesMedium-High Resolution Earth Remote Sensing

2.5 m (Pan), 5m (4-MS)

Stereo image product generation (DEM)

1:25,000 scale image map generation

Off-axis imaging capability (up to +/- 30 degrees)

Program Period : 3 years (in Two Phases)Phase-I : Mission Definition to EM Development

Phase-II : QM/FM Development to Launch & Operations

Launch Expected : Mid of 2004

Orbit : 600 - 800 km, Near-Equatorial Orbit

Launcher : Falcon (TBD)



Model Philosophy

Phase-IIPhase-I

• Acceptance level• Reduced level

• Qualification level• Aging test

• Functional checkout• Interface checkoutTest

• All the modules must be integrated as flight configuration

• Except some expensive components, all the modules must be identical as flight configuration including payloads

• Modules must have the same function and interface as FM

• Structural Model with dummy mass

Configuration

• Use MIL grade or flight-heritage components

• Industrial grade components may be used in some exceptional occasions

• Use MIL grade or flight-heritage components

• Industrial grade components may be used in some exceptional occasions

• Use commercial or industrial gradeParts /

Components Grade

• Flight• Qualification test• Full functional verification• Spare modules for FM

• Functional verification• Structure verification• Software test bed

Purpose

Flight Model (FM)Qualification Model (QM)Engineering Model (EM)



Program Schedule

QM Development

EM Manufacturing / AIT

CDR

FM Development

Launch Readiness

PDR

Detail Design

SDR

SRR

Mission Analysis

Kick-off

Q3Q2Q1Q4Q3Q2Q1Q4Q3Q2Q1Q4Q3Q2

2004200320022001TASKS



Key System Feature

@EOL>330 WPower

QPSK30 Mbps ( X-band )Data Down Link

3 yearsMission Lifetime

32 GbitsMass Storage Capacity

20 km Swath Width

Panchromatic : 2.5 mMulti-spectral (4-bands) : 5.0 m

Ground Sampling Distance

Medium-sized Aperture Camera, MACPayload

0.2 °Attitude Control Accuracy

Hexagonal typeφ1200mm × H1200mmEnvelope

Including payload

≤ 200 kgMass

7.5 ~ 9 °Inclination

685 kmNominal Altitude

Near Equatorial Low Earth Orbit (NEqO)Orbit

RemarkSpecificationsItem



Operation Requirements

Capable of generating 1:25,000 scale, Class III, image maps.

The localization of image shall be better than 5 m of accuracy (90%) in nadir viewing condition with GCP.

The localization of image shall be within 1 km of accuracy in nadir viewing condition without GCP.

Level I image product generation within 5 hours from reception.

6 visits per day over Malaysian region with good Sun angle



Near Equatorial Orbit

Orbital Passes for 1 day

(13~15 times) Imaging Passes for 2.5m resolution camera

Near Equatorial Constellation



Imaging Flexibility

Mission Control Mission Control StationStation

Flight Flight PathPath

Swathwidth Swathwidth 20km20km

2.8 m @ 2.8 m @ ±±2020oo

500 km500 km

3.5 m @ 3.5 m @ ±±3030oo

800 km800 km6 m @ 6 m @ ±±4545oo

1500 km1500 km

Image Receiving Image Receiving & Processing & Processing

StationStation



Off-Nadir Tilting Capability

0

1

2

3

4

5

6

7

0 5 10 15 20 25 30 35 40 45Tilt Angle (degree)

GSD

(m)

0

100

200

300

400

500

600

700

800

Fiel

d of

Reg

ard

(km

)

GSD

Field of Regard

(Cont..)

Body Tilting : ± 30o (45o @max)Short Revisit PeriodExtended Field-of-Regard : ± 750km



GSD from Different Altitudes

0 5 10 15 20 25 30 35 40 450

1

2

3

4

5

6

7

8

Tilt Angle (deg)

Gro

und

Sam

plin

g D

ista

nce

(m)

300km400km500km600km700km800km



Image Data Applications

Mapping & GIS

Infrastructure

Disaster Monitoring

Land Management

Natural Resources

Environment

Business

Security



Image Product Generation

Precision Correction DEM

Fully Automated Ground Station

PC Based System

Radiometric and Geometric Correction

Precision and Ortho Correction

Catalogue Browse System

Value Added Product Generation

Fly Through Simulation

3D Visualization



System Architecture

MSM1

MCM1MSM1

MCM1

MMU

TPUFPA Telescope

PMS

EOS

Operational Heater

Survival Heater Pyro

PPS

MAC

SPUSPU

PCMPCM PDM1, 2

Pyro1Pyro1Pyro1

+28V

+5V+12V-12V

+28V

+5V+12V-12VSo

lar A

rray 1

BM1

Batt.1

BCR1BCR1 BDR1BDR1

OBC1,OBC2

TCM1

EPS

Survival Heaters

OBC1

C&DH GPS

TCM1(P)TCM1(P)TCM1(P)

TCM2(P)

OBC2

DMUX

Demod1

RX1

9.6KbpsFSK

1.2KbpsAFSK

RX2

9.6Kbps FSK

1.2KbpsAFSK

Umbilical

Demod2

DMUX

DMUX

DMUX

1.2KbpsAFSK

38.4KbpsFSK

9.6KbpsFSK

1.2KbpsAFSK

38.4KbpsFSK

Umbilical

TX1

TX2

Mod1

Mod2

DMUX1DMUX2

AMUX1AMUX2

ITUITU

TS

9.6KbpsFSK

2/

MT1FSS1

RW1RW1CSS1

MT1MAG1

MUX

MT1MT1

STS1STS1

RW1RW1RW1RW1

RW1RW1RW1GRX

/4

2/ /

4

ACS

BCU1 SeparationSwitch

TCM1,TCM2

Umbilical

SerialPowerBi-level Command/ TelemetryPulse Per Second

Pyro Electronics

Note: Umbilical lines are in a single connector

OBC1 OBC2



Configuration

ReactionWheel

X-bandAntenna

Battery

StarSensor

PayloadManagementSubsystem

Payload: MAC

In-orbitConfiguration

Entrance Baffle



Payload (MAC) Configuration

Storage Unit

Control Unit

Power Unit

Processing Unit

FPA

CorrectionLenses

M1A

M2A

Entrance Baffle

HousingBus I/F

Metering Structure

Electro-Optical Subsystem

P/L ManagementSubsystem



MAC Key Specifications

8 bitsQuantization

ProgrammableSignal Gain

≥ 70SNR

≤ 50 kgMass

≤ 50 WPeak Power

Image/Quick-look Data30 Mbps (QPSK)Data Tx. Speed

@ BOL≥ 32 GbitsStorage Capacity

@ 685 km≥ 20 kmSwath Width

@ Nyquist freq.PAN ≥ 8 %MS ≥ 15 %

MTF

@ nadirPAN : 2.5 mMS : 5.0 m

GSD

450 ∼ 520, 520 ∼ 600, 630 ∼ 690, 760 ∼ 890 nm

4 MS

510 ∼ 730 nm1 PANImaging Bands

RemarkSpecificationsItem



MAC Payload

FPAMAC Alignment

Primary Mirror

Integrated Configuration



Current Status

MACSAT development has been conducted since June 2000 for flight readiness by mid-2004.

17 Malaysian engineers are participating in this program.– 6 for imaging payload

– 11 for spacecraft bus

Development of engineering model for spacecraft bus and imaging payload was completed.

Qualification Model (QM) AIT is being performed and QM environment test is scheduled in August and September, 2003



Joint Development

Assembly in Malaysia

Assembly in Korea

Joint Harness Manufacturing

Joint Testing of MAC



Hardware Development

On-Board Computer

Telemetry & Command Module

Battery

Battery Charge Regulator

Battery Control Unit

Power Distribution Module

(cont.)



Image Transmission Unit

X-band Antenna Modem

S-band Transmitter S-band Receiver

S-band Antenna

Hardware Development(cont.)



Power Conditioning Module

GPS Receiver

Pyro and Heater Controller

Fine Sun Sensor

Coarse Sun Sensor

Pyro Device

Heater Patch




Magnetorquer Controller

Torquer Bar

Magnetometer

Reaction Wheel

Fiber Optic Gyro

Star Sensor




ACS Software Development

• 3-axis attitude determination & control

• Kalman Filter for gyro drift compensation

• Orbit environment simulation

• Sensor output simulation

• Real-time simulation using OBC

Ground Track

Attitude Display - GraphAttitude Display – 3D



EGSE / Test Bed



PCM/PDM1-TCM1P-TCM1S

Pyro Control-OBC1-OBC2

Integration with Structure

QM Integration



Integration & Test

Telescope in T/V Chamber

Telescope Bake-out MAC EOS +

MACSAT Frame

MACSAT EM on Shaker



Summary

Cost-effective solution for medium-high resolution Earth observation satellite platform and payload

Successful development and testing of EM and QM

International CooperationIntegrated team approach

Joint design and manufacturing in two countries

Model approach for developing world



Thanks for your AttentionThanks for your Attention

macsat - a mini-satellite approach to high resolution

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