Transcript SMALL SATELLITE ENGINEERING IN A BOX:

SMALL SATELLITE
ENGINEERING IN A BOX
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THE EYASSAT CONCEPT OF EDUCATING
ASSEMBLY, INTEGRATION AND TEST
PROCEDURES FOR UNDERGRADUATE
SPACECRAFT DESIGN CLASSES
OBADIAH NG RITCHEY
DEPARTMENT OF ASTRONAUTICS
20 APRIL 2004
OVERVIEW
WHAT WE DO
 EYASSAT CONCEPT
 DIFFERENTIATING EYASSAT:
PROMOTING ‘RESPONSIVE SPACE’
 WHAT I HAVE ACCOMPLISHED
 IDEAS FOR THE FUTURE
 ACKNOWLEDGEMENTS AND
REFERENCES

WHAT WE DO (USAFA & SSRC)
CAPSTONE DESIGN COURSES:
 FalconSAT
 FalconLAUNCH
 REAL DOD SCIENCE AND PAYLOADS
 ONLY UNDERGRADUATE
ASTRONAUTICS PROGRAM

EYASSAT CONCEPT INTRO
EYASSAT CREATED IN PART OF A
REVAMPED A331 CURRICULUM
 STUDENT EMPHASIS ON
QUALIFICATION AND TESTING
 SHADOWS THE ‘REAL AIR FORCE’
 ALLOWS FOR DEMONSTRATION AND
EXPERIMENTATION OF A ‘REAL’ SPACE
SYSTEM AT A FRACTIONAL COST

EYASSAT CONCEPT INTRO
CONCEPT NOT USED BEFORE FOR
AEROSPACE UNDERGRADUATE OR
POSTGRADUATE STUDIES
 CONCEPT ALLOWS FOR EXTREMELY
FLEXIBLE LABORATORY
EXPERIENCES

THE EYASSAT STACK
EYASSAT CLASSROOM
PROCESS
NEW
QUESTIONS
CLASSROOM
INSTRUCTION
EYASSAT
INSTRUCTIONAL
PROCESS
LABORATORY
EXPERIENCE
REAL WORLD
DISCOVERY
DIFFERENTIATING EYASSAT
EYASSAT IS MEANT FOR EDUCATION—
NOT SPACE
 EYASSAT HAS GREATER CAPABILITY
(ADACS, SIZE, DECENTRALIZED
COMPONENT OPERATION,
INTEROPERABILITY, ‘PLUG-AND-PLAY’ HOTSWAPPABLE MODULES)
 DATA BUS MUCH MORE FLEXIBLE AND
REDUNDANT
(STAR VS SHARED ‘CAN-BUS’)

DIFFERENTIATING EYASSAT
INTEGRATION ASPECTS NOT YET
REALIZED (NATURE OF PROJECT)
 SUBASSEMBLIES EASILY REPLACED
 ELECTRICAL AND STRUCTURAL
DESIGN ARE MORE INDEPENDENT
 POWER AND UMBILICAL
 MECHANICAL SIZE/COMPLEXITY
 PAYLOADS (TYPE AND VOLUME
AVAILABLE)

DIFFERENTIATING EYASSAT

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SHOCK, VIBE, THERMAL TESTING NOT
YET IN THE PICTURE 
COMPONENT, SYSTEM-LEVEL AND
FUNCTIONAL TESTS ARE!
CONFORMAL COAT/STAKING NOT UTILIZED
(REUSABILITY ASPECT)
COMMERCIAL INTERESTS
CUBESAT ATTEMPTS TO DO ‘FALCONSAT’
WITH ‘EYASSAT’ PARTS AND BUDGET
DIFFERENTIATING EYASSAT
EYASSAT DEMONSTRATES HOW THE
SYSEMS INTERACT WHILE BEING
ABLE TO CARRY OUT A ‘MISSION’
 THE OPERATION IS HANDS-ON, THE
BUILDING IS NOT
 EYASSAT HAS THE POSITIVE
QUALITIES OF BOTH NANO- AND
PICOSATS WHILE BEING RELIABLE
AND EASILY RECONFIGURABLE

WHAT I HAVE ACCOMPLISHED
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0th AND 1st ORDER NOMINAL I-V AND I-P CURVE
SOLAR ARRAY CHARACTERIZATION
COMMUNICATION AND BATTERY MODULE
PRODUCTION—LATER USED BY THE STUDENTS
A331 LABORATORY EXPERIENCE—AT MY OWN
PACE AND DEPARTING FROM STUDENT
LESSONS
RESEARCH THE OTHER ‘DOES SPACE’
UNIVERSITY PROGRAMS FOR COMPARISON
WHAT I HAVE ACCOMPLISHED
COMPLETE ADDITIONAL BASELINE
DATA TO AID IN ACCEPTANCE TESTS
 PRODUCE NOMINAL
CHARACTERIZATION DATA FOR ADCS
USE—FOCUSING ON ENVIRONMENTAL
VARIABLES

SOLAR ARRAY PERFORMANCE
SOLAR ARRAY PERFORMANCE
EyasSAT Solar Array
Array IV
IV Curve
Curve
0.35
0.35
1.6
1.4
0.3
1.2
0.25
0.25
Current
(mA)
Current (mA)
1
0.2
0.8
0.15
0.15
0.6
0.1
0.4
0.05
0.05
0.2
0
0
0
2
4
6
8
Voltage
Voltage (V)
(V)
10
12
14
I vs V
P vs V
ADCS POSITION SENSOR
TESTING ARRANGEMENT
ADCS POSITION SENSOR
READINGS
18-Inch Sensor Readings
120
Sensor 1
Sensor 2
100
Count (Telemetry Data)
80
60
40
20
-100
-80
-60
-40
-20
0
20
Angle (-90 to 90 Degrees)
40
60
80
0
100
ADCS POSITION SENSOR
READINGS
24-Inch Sensor Readings
80
Sensor 1
Sensor 2
70
Count (Telemetry Data)
60
50
40
30
20
10
-100
-80
-60
-40
-20
0
20
Angle (-90 to 90 Degrees)
40
60
80
0
100
IDEAS FOR THE FUTURE
GPS
 DIGITAL IR AND VISIBLE SPECTRUM
IMAGING
 TARGET TRACKING
 PROX-OPS ON AIRTABLE 
(THINK: SPACE ‘BATTLEBOTS’)
 COMPOSITE STRUCTURES
 COLD-GAS PROPULSION MODULE

ACKNOWLEDGEMENTS AND
REFERENCES
DFAS, ESPECIALLY CAPT BARNHART
 MR JIM WHITE, CSS
 SCHAFFNER, CALPOLY PAPER
AUTHOR
 WERTZ AND LARSON, SMAD, ETC.
 TWIGGS, STANFORD’S SSDL
 GUPTA, ANUSAT LEAD, ISRO
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FOR MORE INFORMATION…
WWW.EYASSAT.COM
QUESTIONS?
DEMONSTRATION