1. Nicole Bryan 3.20.08 Avionics Final Presentation Slides
AAE 450 Spring 2008 1

2. Total System Power: 200 Watts
Power Budget
Total System Power: 200 Watts
Vehicle Flight Time
Balloon Rise Time
Vehicle System
% of Operating Power
Power (W)
Energy Consumption (Wh)
Mass (kg)
Payload 5 10
1.04
0.01
30.00
0.27
Propulsion 35 70
7.25
0.07
0.00
Attitude Control 15 30
3.11
0.03
Communications 20
2.07
0.02
60.00
0.55
Command and Data Handling
Thermal
Power Management 25 50
5.18
0.05
Total
100
200
20.72
0.19
150.00
1.36
Safety Factor of 1.5
300
31.08
0.28 75
225
2.05
Assumptions: 200g Payload Case, Silver Zinc Battery, Balloon Launch (3hr rise time, 373 second flight time) Source: Justin Rhodes and Nicole Bryan
AAE 450 Spring 2008 2
Avionics

3. Non-Space-Rated Sensors
Sensor Type
Part Number
Manufacturer
Unit Price
Thermal
TS3-85
Cantherm
$10.29
Pressure
Measurement Specialties Inc.
$104.06
Flow
26616
Gems Sensors, Inc.
$154.95
Force
FSS1500NSR
Honeywell Sensing and Control
$46.56
AAE 450 Spring 2008 3
Avionics

4. Space-Rated Sensors Sensor Type Part Number Manufacturer Unit Price
Thermal
S /04
Honeywell Sensing and Control
~$800
Pressure
PPTR
$970.00
AAE 450 Spring 2008 4
Avionics

5. Electronic Parts: Component Rating
Commercial
Class B
Class S
Commercial Requirements
Class S Requirements
Infinite production lot size
Built one at a time
No burn-in testing
Extended burn-in time (up to 240 hours)
No detailed failure analysis
Extended failure analysis
No life testing
1,000 hour life test on every lot
No traceability
Traceable to the raw materials
> 1% failure per 1000 hours allowed
0.0001% failures per 1000 hours allowed
1 NASA Electronics Parts Assurance Group
Reference: Justin Rhodes
AAE 450 Spring 2008 5
Avionics

6. References
Wertz, James R., and Wiley J. Larson, eds. Space Mission Analysis and Design, 3rd ed., Torrance, Kluwer Academic and Microcosm Press, 1999.
“Space Applications.” Honeywell Aerospace [online], 2007.
URL:
AAE 450 Spring 2008 6