Transcript Document 7718313

MECN 3974 Aerospace Experience II
Orientation & Precision Measurements with Accelerometer &
Gyroscope Sensors (OP-MAGS) Experiment by the
Inter American Capturing Accelerometer
Measurements Joining Gyroscopes (ICAMJ) Team
A.M. Espinal Mena, C. Nuñez Vélez, M. Fuentes Aviles, J. Muñoz Borrero
Faculty Advisor: Dr. Hien Vo
Scientific Presentation
July 30, 2009
Scientific Objectives
Determine the payload’s precision,
orientation using rotation & tilt data.
 Understand how the surrounding
environment affects the payload.

Scientific Objectives
Maximum capital cost: $200 (on all instruments)
 Payload weight < 500g (Including batteries
 Collect data with the following sensors:
 Dual axis gyroscope
 Three axis accelerometer
 Temperature sensor

Science Background
Earth’s Rotation & Orientation
Earth’s Orientation
to the Sun
Earth’s Rotational Axis
Acceleration data (Summer 2008)
Average Accelerometer Values by TIGRE TEAM
Accelerometer & Gyroscope Sensor


Three Axis Accelerometer
(ADXL330)
 +/- 3 g (Acceleration)
 Output Voltage Range:
0.6 V up to 2.4 V
Dual Axis Gyroscope
(IDG300)
 +/- 500 Degrees/Sec.
 Output Voltage Range:
0.5 V up to 2.5 V
Gyroscope Sensor

•
Gyroscope Work
ICAMJ Electrical Design
Accelerometer Signal Conditions
Gyroscope Signal Conditions
•
ICAMJ Electrical Design
Building a PCB- Print Circuit Board
Accelerometer & Gyroscope Boa
•
ICAMJ Electrical Design
Simulation of Signal Conditions-SC


SC Input Voltage = 0.6 V (ADXL330 minimum  SC Input Voltage = 0.5 V (IDG300
output voltage)
minimum output voltage)
SC Input Voltage = 2.4 V (ADXL330
maximum output voltage)
SC Input Voltage = 2.5 V (IDG300
maximum output voltage)

Sensors & Ballonsat Interface
•
ICAMJ Electrical Design
Temperature Sensor
•
ICAMJ Electrical Design
Power Budget
Component
BalloonSat
12 OpAmps
ADXL330 Three Axis Accelerometer
IDG-300 Dual Axes Gyroscope
Temperature Sensor
Total Current
Current (mA)
56.00
10.00
0.32
9.50
4.50
80.32

80.32 mA* 4 Hours = 320.00 mA*Hour for the entire flight.

We include an extra hour for any unexpected delay, having
a total of 5 hours:

80.32 mA* 5 Hours = 400.00 mA*Hour for the entire flight.
Ultralife 9 V Lithium Battery


U9VLBP Lithium Battery Voltage vs
Service Life
U9VLBP Lithium
Battery Voltage vs
Battery Capacity
External Structure

Description: Polystyrene Foam (better known as blue foam)

Payload form: Octagon from the outside.

Rope hole in both sides to attach it with the balloon cords.
Density
1050 kg/m³
Density of EPS
25-200 kg/m³
Dielectric constant
2.4–2.7
Specific gravity
1.05
Electrical conductivity (s)
10-16 S/m
Thermal conductivity (k)
0.08 W/(m·K)
Young's modulus (E)
3000-3600 MPa
Tensile strength (st)
46–60 MPa
Elongation at break
3–4%
Notch test
2–5 kJ/m²
Glass temperature
95 °C
Melting point[3]
240 °C
Vicat B
90 °C[4]
Heat transfer coefficient (Q)
0.17 W/(m2K)
Linear expansion coefficient (a)
8 10-5 /K
Specific heat (c)
1.3 kJ/(kg·K)
Water absorption (ASTM)
0.03–0.1
ICAMJ Payload Views & Measures
Weight Budget
Component
BalloonSat & connectors
PCB, ADXL330, IDG300 &
connectors
Battery
External Structure & two lids
Internal Structure
Four screws and bolts
Total Weight
Weight (grams)
95 g
95 g
45 g
200 g
20 g
10 g
465 g
Data Storage

Required bytes during
flight:
4 hours x 60 minutes/ 1 hours =
240 minutes
28 bytes x 240 minutes = 6720
bytes for the entire flight.
We include an extra hour for any
unexpected delay:
5 hours x 60 minutes/ 1 hours =
300 minutes
28 bytes x 300 minutes = 8400
bytes for the entire flight.
Byte
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
Description
Time Stamp: hour
Time Stamp: minute
Time Stamp: seconds
Accelerometer: X axis Max
Accelerometer: X axis Min
Accelerometer: X axis Average
Accelerometer: Y axis Max
Accelerometer: Y axis Min
Accelerometer: Y axis Average
Accelerometer: Z axis Max
Accelerometer: Z axis Min
Accelerometer: Z axis Average
Gyroscope: X axis Max
Gyroscope: X axis Min
Gyroscope: X axis Average
Gyroscope: Y axis Max
Gyroscope: Y axis Min
Gyroscope: Y axis Average
Temperature Sensor
Data Storage
External FM24C512
RAMTRON Memory

•
•
•
•
•
Non volatile memory
Employ an advanced ferroelectric
process.
Reliable data retention for 45
years.
Perform writes operations at bus
speed.
The next bus cycle may commence
immediately without the need of
data polling.
Temporary Variable
Ramtron Location
Acc_X_Min
0
Acc_X_Max
1
Acc_Y_Min
2
Acc_Y_Max
3
Acc_Z_Min
4
Acc_Z_Max
5
Acc_Sum_X
6
Acc_Sum_Y
8
Acc_Sum_Z
10
X_Rate_Min
20
X_Rate_Max
21
Y_Rate_Min
22
Y_Rate_Max
23
X_Rate_Sum
24
Y_Rate_Sum
26
Pre-Flight Software
During Flight Software

General Cycle
Sensor
Accelerometer X axis
Accelerometer Y axis
Accelerometer Z axis
Gyroscope X Rate
Gyroscope Y Rate
Temperature
ADC0838 channels
0
1
2
4
3
5
Mux (Multiplexer)
24
28
25
26
29
30
Post Flight Software
ADXL330 & IDG300
prototypes
Shock Test
Temperature
Sensor
prototype
Temperature Test
Temperature Test
ICAMJ Work Breakdown Schedule (WBS)
Material Acquisition Plan
Equipment
Part Number #
Quantity
Price
Accelerometer &
Gyroscope
SEN-00741
1
$109.95
Analog-to-Digital
Converter
ADC0838CIWMX/NOPB
1
$2.86
FM24C512-G
1
$11.51
A724-ND
1
$5.95
579-24LC256-I/P
1
$1.23
1N457 Small Signal Diode
1
$0.05
LM334
1
$0.38
Memory RAM
Memory RAM Board
EEPROM Memory
Temperature Sensor
Constant Current Source
Total
$131.93
Risk Management and Contingency
Risk Category
Electrical failure
Scheduling
Electrical failure
Mechanical
failure
Power failure
Potential Risk
The measurement from one
gyroscope may not be enough for
the analysis
Not getting the PDR ready for the
dead-line
Is that the circuit get to hot inside
and get into fire the payload
The payload structure can break
into pieces during flight
Battery discharge during the flight
due to sensors heat.
Electrical Failure During the travel to the launch
place the cables may break
Contingency Plan
Putting another gyroscope to get
more accuracy.
Getting more hours of work and
more days in the lab.
Isolating the circuit for safety
protection.
Ensure that the structure will be
enough strong to resist shocks.
Putting a battery backup into the
circuit that when the battery is
getting low of energy the backup
charges the batteries.
Bringing extra cables to fix a
possible broken cable.
Conclusion
Determine
acceleration
and
rotational
measurements of the ICAMJ payload.
 Gather the data of the payloads movements during
flight and relate it with the different altitudes.
 Compare the data with previous experiments to
establish the differences and similarities .
