0 衛星結構設計 (ii) 祝飛鴻 6/17/2004. 1 what you should learn from this course? ...
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![Page 1: 0 衛星結構設計 (II) 祝飛鴻 6/17/2004. 1 What you should learn from this course? 低軌道小衛星發展趨勢 Why spacecraft structure fails?](https://reader036.vdocuments.net/reader036/viewer/2022081418/56649e255503460f94b138d2/html5/thumbnails/1.jpg)
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衛星結構設計衛星結構設計 (II)(II)
祝飛鴻
6/17/2004
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What you should learn from this course?
低軌道小衛星發展趨勢 Why spacecraft structure fails?
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What you should learn from this course? Concept of System Engineering
Concept of Development Process
You may not have the opportunity to learn
from other courses.
These 2 concepts can be applied to any field
and will be extremely useful when you are
in a management role or decision making
position.
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Concept of System Engineering: Each system can be logically or functionally break into subsystems.
Each subsystem is not a stand alone item but interface with each
other by some means.
Best subsystem design will not lead to a best system. In some
cases, best subsystem could lead to an unworkable system.
Iterative compromise between subsystems is unavoidable in
achieving a workable system design.
A good system engineer must know the inter-relationship between
subsystems and relative importance of each key parameter.
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StructureSubsystem
EPS
• Type of solar array.• Size• Weight• Area
TT&C
C&DH
TCS
ADCS
RCS
• Radiation area• Thermal conductivity
• Tank size• Thruster alignment
• Size• Weight• Type of antenna• Field of view
• Size• Weight• Field of view• Alignment
• Weight• Size
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Concept of Design Process: Materialize the flow and steps necessary to complete the task.
Mission Orbit
Candidate LV
Target Weight
Fairing Size
System & SubsystemDesign Concept
Hardware Selection
Hardware Size
Orientation & FOVRequirement
StructureConfiguration
MechanicalLayout
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Target Weight
Candidate LV
Weight Allocation
HeritageData
Design Concept
SystemDesign
Weight Estimation
Weight Re-allocation
PreliminaryDesign
WeightCalculation
DetailDesign
WeightReduction
FinalWeight
ActualWeight
Actual HW
Over Weight
?
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低軌道小衛星發展趨勢
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Ref. 1: JPL Technology for Small Space Missions, Les Deutsch, March 29 2001
JPL Development Trend (Ref. 1)
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Formation Fly
Paradigm Shift- same mission with lighter and smaller satellite -
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Single Large Spacecraft Single Small Spacecraft
Limited by
physical law
and state-of-
the-art technology
Virtual Satellite Technology Breakthrough
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Satellite Design: Past, Present, and Future, Cyrus D. Jilla,
International Journal of small satellite Engineering, 1997. The Present:
Conventional subsystem by subsystem design
Modular design for multiple missions
Small satellite: low cost high risk design
The Future:
Multifunctional structures
Nanotechnology & MEMS systems
Distributed satellite system
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Solar Array- Specific Power
Current technology: ~200W/Kg.
Future goal: ~300W/Kg
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Li-ion
130Wh/Kg
Battery- Specific Energy
Thin-film lithium battery
300Wh/Kg
NiH2
25-40Wh/Kg
NiCd
25-30Wh/Kg
Rechargeable lithium batteries sees as future. (Ref. 2)
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ADCS: (Ref. 2)
Compact, light weight sensors and components.
Integration of components (GPS & Attitude Sensors)
Complete spacecraft autonomy
Sun Sensor
Star Tracker
Gyro
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Why spacecraft structure fails?
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Un-execusive Event
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Unforeseen Event
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Unfortunate Event
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Unlucky Event
Design Loads vs Coupled Loads Results
Random Vibration Loads
Shock loads
Load Source
Response Prediction
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Unforgivable Event
Design to failure
Analysis oversight
Over testing