Transcript Team Name

WVU Rocketeers
Critical Design Review
WVU
Justin Yorick, Ben Province
Advisors: Dr. Vassiliadis, Marc
Gramlich
RockSat-C 2012
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CDR Presentation Content
• Section 1: Mission Overview
–
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Mission Overview
Organizational Chart
Theory and Concepts
Concept of Operations
Expected Results
• Section 2: Design Description
–
–
–
–
–
Requirement/Design Changes Since CDR
De-Scopes/Off-Ramps
Mechanical Design Elements
Electrical Design Elements
Software Design Elements
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CDR Presentation Contents
• Section 3: Prototyping/Analysis
– Analysis Results
• Interpretation to requirements
– Prototyping Results
• Interpretation to requirements
– Detailed Mass Budget
– Detailed Power Budget
– Detailed Interfacing to Wallops
jessicaswanson.com
• Section 4: Manufacturing Plan
– Mechanical Elements
– Electrical Elements
– Software Elements
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CDR Presentation Contents
• Section 5: Testing Plan
– System Level Testing
• Requirements to be verified
– Mechanical Elements
• Requirements to be verified
– Electrical Elements
• Requirements to be verified
– Software Elements
• Requirements to be verified
• Section 6: Risks
– Risks from PDR to CDR
• Walk-down
– Critical Risks Remaining
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CDR Presentation Contents
• Section 7: User Guide Compliance
– Compliance Table
– Sharing Logistics
• Section 8: Project Management Plan
– Schedule
– Budget
• Mass
• Monetary
– Work Breakdown Structure
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Mission Overview
Justin Yorick
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Mission Overview
• The goal of this mission is to measure
and record information about the
atmosphere.
– These experiments will compare
atmospheric readings to current models of
atmospheric behavior.
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Mission Overview
• Experiment overviews
– Flight Dynamics
• This experiment will measure the kinematics of the
rocket flight, and will be used as a reference for the
other experiments.
– Cosmic Ray Experiment
• The atmosphere is constantly barraged by foreign
charge particles and waves from a variety of sources.
The atmosphere shields the surface of the earth from
these particles. As one travels further from the
surface of the earth, the shielding effect decreases.
By using an array of Geiger tubes, the team hopes to
measure the concentration of cosmic rays in the
atmosphere.
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Mission Overview
• Radio Plasma Experiment
– In the earth’s atmosphere, energetic sources
cause the ionization of gas particles. This
region is collectively known as the ionosphere.
The particles are known to oscillate at a given
frequency, as a function of charge density. By
using a variable frequency radio sweep, one can
in theory find the resonance frequency of the
ambient plasma. With this information, one
can find the plasma density as a function of
altitude.
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Mission Overview
• Greenhouse Gas Experiment
– Various gases are thought to play a major role
in the warming trends of earth’s environment.
Certain gases such as water vapor and carbon
dioxide are thought to play the most major
roles in this process. Most atmospheric data for
gas concentration is measured from a fixed
point on the ground. It is the goal of this
experiment to measure the concentration of the
gases as a function of altitude, and provide
some insight into their concentration profiles.
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Mission Overview
• Dusty Plasma Experiment
– Although a plasma is regularly composed of
charged gas particles in a dynamic
equilibrium. In a dusty plasma, neutral
particles of much larger particle diameter
are suspended in a lattice equilibrium
position. In a normal dusty plasma
suspension, gravity plays a key role in
lattice formulation. It is the goal of this
experiment to study these lattices in the
microgravity portions of this flight.
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Organizational Chart
Project Manager
Justin Yorick
System Engineer
Marc Gramlich
Faculty Advisor
Dimitris Vassiliadis
Mark Koepke
Yu Gu
CFO
Dimitris Vassiliadis
Safety Engineer
Phil Tucker
Testing Partners
ATK Aerospace
WVU CEMR
Sponsors
WVSGC,
Dept. of Physics,
ATK Aerospace
Structural Design
Ben Province
Legacy
Components
B. Province
GHGE
B. Province
RPE
Mike Spencer
RockSat-C 2012
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DPE
J. Yorick
Simulation and
Testing
J. Yorick
12
RockSat 2011: Concept of Operations
h=117 km (T=02:53)
Apogee
h=75 km (T=01:18)
RPE Tx ON
DPE ON
h=75 km (T=04:27)
RPE Tx OFF
DPE OFF
h=52 km (T=00:36)
End of Orion burn
DPE begins
h=10.5 km (T=05:30)
Chute deploys
Redundant atmo. valve closed
h=0 km (T=13:00)
Splashdown
h=0 km (T=00:00)
Launch; G-switch activation
All systems power up except
RPE Tx and DPE
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RockSat 2012 GHGE: Detailed Con-Ops
H=TBD km t=TBD
CV decompresses to T= -5C
#2 H=27.1 km t=035s (T=40C)
#3 H=17.2 km t=322s (T=-5C)
#4 H=10.0 km t=352s (T=-5C)
…
#17 H=1.8 km t=742s (T=-5C)
#1 H=1.7 km t=005s (T=40C)
H=1.52 km t=771 s
Wallops Valves Close
H=1.52 km t=004.x s
Wallops Valves Open
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Expected Results
• FD
– The expected results of the FD are the same
as previous years, as the flight conditions
are expected to vary little.
• CRE
– The CRE is expected to vary little from the
2010 rocksat flight. In general, the counts
are expected to increase as the vehicle
gains altitude.
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Expected Results: CRE
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Expected Results
• GHGE
– Current models predict that Carbon Dioxide
is uniformly distributed in the lower
atmospheric regions. The team assumes
that this hypothesis is true due to the
relatively homogenous nature of the lower
atmosphere.
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RockSat 2012 GHGE Temperature Ranges
300
250
200
Temperature (C)
150
100
Static Temperature (C )
Dynamic Temperature (C )
50
Sensor Temp Range
(-25 to 60 C)
0
0
100
200
300
400
500
600
-50
-100
-150
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Time (s) CDR
700
800
900
RockSat 2012 GHGE Detailed Con-Ops
400000
Sample# Time (s) Altitude(km) T_target (C ) P_target (kPa) F_max (N)
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
350000
Pressure (Pa)
300000
250000
200000
150000
5
35
322
352
382
412
442
472
502
532
562
592
622
652
682
712
742
1748
27060
17294
10065
6591
5497
5119
4739
4406
4061
3728
3392
3090
2784
2420
2132
1838
40
40
-5
-5
-5
-5
-5
-5
-5
-5
-5
-5
-5
-5
-5
-5
-5
126.69
13.34
27.30
58.55
63.07
64.98
65.70
66.45
67.13
67.86
68.59
69.35
70.06
70.79
71.70
72.43
73.21
F_max (lbf)
513.80
98.46
177.46
190.47
114.63
83.87
72.25
60.01
48.79
36.66
24.44
11.57
142.07
147.34
153.87
159.23
164.90
115.50
22.13
39.89
42.82
25.77
18.85
16.24
13.49
10.97
8.24
5.49
2.60
31.94
33.12
34.59
35.80
37.07
Static Pressure
Stagnation Pressure
P at 40 C
P at -5 C
1
7
5
100000
6
4
9
8
11
10
13
12
15
14
17
16
50000
3
2
0
0
100
200
300
400
500
600
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Time (s)
CDR
700
800
900
Expected Results
• DPE
– In a regular dusty plasma, gravitational
forces play a key role in the equilibrium
position of the plasma lattice. The team
expects to see an equilibrium lattice that is
different in size and shape from standard
models.
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Design Description
Ben Province
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De-Scopes
– GHGE
–Originally, the team had hoped to
measure the concentration of more GHG’s
in real time. This setup could not be
realized under the current power, size
and weight restrictions on the payload.
Instead, the team has settled on
measuring water vapor and Carbon
Dioxide concentration, as a series of
discrete steps throughout the payload’s
flight.
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Descopes
• RPE
– Originally, the team hoped to use a
relatively large Langmuir probe to verify
the data found by the swept antennae. The
size of the Langmuir probe has been
reduced in size to be in compliance with
WFF regulations.
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Descopes
• DPE
– The original goal for the DPE was to
control and stimulate a dusty plasma under
microgravity conditions. At this point, the
team is focusing on solely creating a dusty
plasma in a microgravity setting.
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Off-Ramps
• GHGE
– The team is currently finalizing a temperature
control system for the GHG control volume. As
it stands, current calculations show the air
temperatures to be below chosen sensor ranges
for portions of the flight. To control this
problem, the team is attempting to use a
master piston and cylinder to compress the air
until it reaches the desired temperature. If this
control scheme cannot be fully realized, the
team will not take samples during portions of
the flight with unacceptable temperatures.
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Off-Ramps
• DPE
– As it currently stands, the team hopes to
create, stabilize, and study a dusty plasma
in microgravity conditions. If it becomes
impossible to achieve all of these goals for
one reason or another, the team may simply
focus on creating the dusty plasma, and
forgo the controlled stimulations of the
sample.
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Payload Mechanical Overview (1)
RockSat-C 2012
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Payload Mechanical Overview (2)
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Payload Mechanical Profile
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GHGE Mechanical Overview (1)
17-Tooth
Cog
ANSI #35
Roller-Chain
3/8” Ball Shaft
3/8” Ball Nut
26-Link
ANSI #35
Roller-Chain
(not shown)
Thrust Bearings
9-Tooth Cog
ANSI #35
Roller-Chain
2” Bore X 1.5”
Stroke Pneumatic
Cylinder
Control
Volum
e
Solenoid
s
1/8” NPT Piping
(not finalized)
RockSat-C 2012
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Color Code:
Plates Which Must
Be Machined
Threaded Rod
Unthreaded Rod
GHGE Mechanical Overview (2)
Color Code:
Plates Which Must
Be Machined
Threaded Rod
Unthreaded Rod
RockSat-C 2012
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GHGE Mechanical Overview (3)
12VDC
Electric
Motor
¼” to
3/8”
Coupler
10-Tooth Pulley
MXL Timing Chain
75-Tooth Loop
MXL Timing Chain
Optical Encoder
Wheel
(not finalized)
60-Tooth Pulley
MXL Timing Chain
Color Code:
Plates Which Must
Be Machined
Threaded Rod
Unthreaded Rod
¼” Threaded Rod
supports plates
Adapter Plate
mates to canister floor
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GHGE Mechanical Overview (4)
Color Code:
Plates Which Must
Be Machined
Threaded Rod
Unthreaded Rod
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GHGE Mechanical Overview (5)
Color Code:
Plates Which Must
Be Machined
Threaded Rod
Unthreaded Rod
GHGE
Control
Board
Makrolon Plate
(not finalized)
RPE
Rx
Board
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Optical Plate Mechanical Overview
Power
Board
FD
Board
Optical
Camera
Geiger
Tubes
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Optical Plate Mechanical Top View
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Optical Plate Mechanical Bottom View
CRE
Geiger
Board
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DPE Mechanical Overview
Plasma
Control
Volume
Laser
DPE
Control
Board
Optical
Camera
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DPE Mechanical Top View
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Electrical Design Elements
• PSS pcb:
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Electrical Design Elements
• FD pcb
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Electrical Design Elements
• CRE pcb
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Electrical Design Elements: FD Board
Flash
Memory
PSS
Camera
μg
Geiger
Counters
Temperature
Ax/Ay/Az
Inertial
Sensor
P/Q/R
Camera
Optical Port
Mag X/Y/Z
D
I
G
I
T
A
L
uMag X/Y/Z
uController
Flight Dynamics
A
D
C
Thermistor
Z Accel
Gyro X/Y
Legend
Power/Reg
Power flow
Comp/Store
Comm/Con
Sensors
Data flow
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Battery
43
Electrical Design Elements: PSS board
Batt V
+9V
Power Supply
RBF
G
+3.3V
+5V
555
Timer
-5V
GND
Legend
Power/Reg
Power flow
Comp/Store
Comm/Con
Sensors
Data flow
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Electrical Design Elements: FD Board
Flash
Memory
PSS
Camera
μg
Geiger
Counters
Temperature
Ax/Ay/Az
Inertial
Sensor
P/Q/R
Camera
Optical Port
Mag X/Y/Z
D
I
G
I
T
A
L
uMag X/Y/Z
uController
Flight Dynamics
A
D
C
Thermistor
Z Accel
Gyro X/Y
Legend
Power/Reg
Power flow
Comp/Store
Comm/Con
Sensors
Data flow
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Battery
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Software Design Elements
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Prototyping/Analysis
Justin Yorick
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Analysis Results
• CRE
• The CRE has been prototyped thus far by building a
Geiger circuit and developing code to interface this
circuit with the Netburner microprocessor .
• Initial prototyping results suggest that the circuit will
interface without major problems or failures.
• FD
• To ensure the FD subsystem functions as required a
drop tower is being developed to test the accelerometers
in axial directions, while spin testing with WVU CEMR
will provide a suitable testing platform to monitor spin.
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Analysis Results
• GHGE
– The designs for the GHGE are reaching a
finalized state. With final dimensions, ANSYS
finite element modeling will be utilized to
calculate system stresses as well as heat
transfer information in the piston, testing
volume, and piping.
– Temperatures in the system are derived from
an isentropic expansion of air. As the rocket is
traveling above Mach 1, these assumptions
yield the team with guideline values only.
– If needed, simple CFD may be performed using
ANSYS or a suitable program.
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Analysis Results
• RPE
– The RPE requires the successful timing of
two swept frequency radio transmitters and
receivers. The circuits are to be built, and
tested using proper computational
programs(name?) and oscilloscopes.
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Analysis Results
• DPE
– The dusty plasma requires a RF
transmitter with sufficient power to excite
and ionize gas particles in a control volume.
Once the circuit is finalized, the emitter
must be tested both with an oscilloscope to
ensure proper circuit output.
– The system must be used to actually excite
a gas as well to ensure proper emitter
design. (not sure how we test this..)
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Detailed Mass Budget
Part
Previous Payload
- Batteries
-antennas and CLE*
Mass+ (g) Mass- (g) Quantity Cumulative Mass (g)
2346
1
2346
45.6
10
1890
100
1
1790
1790
GHGE Solenoids
50
5
2040
GHGE Cylinder
540
1
2580
GHGE Motor*
750
1
3330
GHGE brackets
190
1
3520
GHGE Rods
283
1
3803
GHGE Bearings, couplers, etc.*
300
1
4103
GHGE Plumbing*
300
1
4403
DPE*
900
1
5303
5303
Batteries
45.6
15
5987
Target Mass (g) +2%
kg
5942 6060.84 6.06084
lbf
13.333848
* indicates an estimate
GHGE brackets assumed 1/4" aluminum
GHGE rods assumed to be steel
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Detailed Power Budget
Power Budget
Subsystem
Component
Netburner
Netburner
uMag XYZ
IMU
GYRO XZ
Z Accelerometer
Thermistor
Flash
Flash
Op Amp
Op Amp
DPE
GHGE
CRE
Voltage (V)
+3.3
+3.3
+5
+5
+3.3
+5
+3.3
+3.3
+3.3
-5
+5
+3.7
+12
+3.3
Current (A)
.120
.120
.020
.070
.0065
.001
.00033
.006
.006
.068
.068
.438
1
.120
Time On (min)
20
20
20
20
20
20
20
20
20
20
20
10
2
20
Total (A*hr):
Over/Under
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Amp-Hours
.04
.04
.0066
.0233
.00216
.00033
.00011
.002
.002
.02266
.02266
.073
.4
.04
.67482
.32518
53
Manufacturing Plan
Ben Province
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Mechanical Elements
• FD
– The FD subsystem needs little modification
or manufacturing. The only foreseeable
modifications could come in ballast
placement to ensure proper GC and mass
alignment of the canister.
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Mechanical Elements
• CRE
– The CRE pcb must be finalized and readied
for flight. The board will be ordered from
PCBexpress.
– The Geiger array with varying shielding
must be either rebuilt or reused from a
previous flight. This is not anticipated to be
an area of concern for the team.
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Mechanical Elements
• GHGE
– The control volume must be assembled, most likely
a custom glass vessel built by the chemistry
department or the team.
– The appropriate tubing must be bought for the
inputs, as well as control solenoids for the valve
operations.
– A piston is to be ordered, and must be soundly
interfaced to the system such that it forms an air
tight seal with the CV, even at relatively high
pressures.
– These components must all be assembled so that
the experiment can control input temperatures
during the flight.
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Mechanical Elements
• RPE
– The antennae must be procured, and
properly attached to the payload.
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Mechanical Elements
• DPE
– The DPE will most likely required the use
of a custom made, low pressure sealed
experimental control volume. The team
must also build a mechanism to disperse
the dust within the vessel during flight. The
team must also properly design, build, and
attach the RF generator to the control
volume.
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Mechanical Elements
Mechanical element construction Gant Chart
December
January
February
Construction and Mounting of Geiger array
Purchase of piston cylinder
Purchase of tubing and solenoid valves
Purchase of minor mechanical system components
Fabrication of piston assembly
Purchase of GHGE sensors
Construction of patch antenna
Construction of CV for DPE
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Electrical Elements
• FD
– The FD board requires little if any revision.
• CRE
– The team will utilize a custom built pcb for
the Geiger array. This board must have the
various components soldered to their correct
locations.
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Electrical Elements
• GHCE
– A pcb must be designed to enable to the
sensors to interface with the Netburner,
and also allow the Netburner to control the
piston and valve system.
– Although this circuit should be relatively
simple, some revisions may be needed
because this will be the first round of the
design process for the system component.
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Electrical Elements
• RPE
– Multiple heritage elements will be used in
this pcb. Slight revisions may be needed due
to a change in antenna type from previous
flights.
– The patch antenna itself must still be
finalized and built. Although less likely, it
is possible the antenna itself may need to be
revised if not satisfactory.
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Electrical Elements
• DPE
– The DPE makes use of an RF generator, a
laser , as well as a camera. The complexity
of this task will result in an equally
complex circuit.
– Due to the relatively complexity of this
circuit, it seems probable that multiple
revisions may be needed to have an
acceptable and usable experiment.
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Electrical Elements
Electrical Element construction Chart
December
January
February
Revision of FD PCB
Construction of CRE
Design of GHGE PCB
Construction of GHGE PCB
RPE PCB revisions
DPE PCB design
DPE PCB Construction
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Software Elements
• FD
– Some code modification will be needed to
successfully activate and record data from
new experiments.
– This code block affects all others because it
controls the activation of further
subsystems.
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Software Elements
• CRE
– The CRE code will remain largely
unchanged from previous years, and has
little affect on other code blocks.
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Software Elements
• RPE
– The general layout for this experiment’s
coding will remain largely unchanged from
previous flights. Changes will be focused on
improving system performance and
adapting the system to a new antenna.
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Software Elements
• GHGE
– The code blocks for this must execute two
primary functions. The first must record data
from the gas sensors.
– The second major block must control valve
settings and piston position, based on
temperature predictions in addendum to
current temperature readings.
– The team is considering the addition of a
second Netburner to aid in control and data
processing for this experiment.
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Software Elements
• DPE
– The DPE code is yet to be fully developed,
but is expected to accomplish the following:
• The code must be able to activate and deactivate
the experiment at the desired points in flight.
• The code must be able control the stimulation of
the dusty plasma upon release of the dust into
the CV.
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Testing Plan
Justin Yorick
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System Level Testing
• FD
– As a whole, the FD must activate with g-switch
triggering, as well as provide accurate
recording of flight kinematics.
• CRE
– The CRE must activate and deactivate at its
assigned times in flight (see Con-Ops).
– The CRE must also be able to detect high
energy particles. To test this, the CRE will be
placed next to known radioactive samples.
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System Level Testing
• RPE
– The RPE must activate and deactivate at its
assigned times.
– The transmitter and receiver will be tested
on ground. The results aren’t expected to
match ionosphere conditions, but this test
will provide insight into the proper timing
of the system.
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System Level Testing
• DPE
– The DPE must activate and deactivate at
proper times. The system must also be able
to produce a plasma in the CV, and insert
the dust particles at the proper time, as
determined in the ConOps section.
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System Level Testing
• Schedule
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Mechanical Testing
• FD
– The FD subsystem will be assessed by
placing it on a drop tower and then a spin
platform. These test will not only verify the
mechanical soundness of the system, but
will aid in instrument calibration for the
kinematic sensors.
– Test will also be used to find system mass
and CG location.
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Mechanical Testing
• CRE
– The CRE will be subjected to vibration and
spin testing in addition to test that will
measure the subsystem mass and CG.
• RPE
– The RPE will be vibration and spin tested.
The subsystem will also be tested to find its
mass and CG.
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Mechanical Testing
• GHGE
– The redundant valves must be tested such that they
are able to properly seal the canister in a water landing.
This can tested by placing the valves in water.
– The solenoid control valves must be tested with
pressurized air to ensure they are able to reach the
required compression values.
– The piston should be strain tested to ensure failure is
improbable.
– Spin and vibration testing will be used as well to ensure
the system will survive.
– The mass and CG of this experiment are also very
important due to the relative size of the piston.
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Mechanical Testing
• DPE
– The DPE testing must verify that the low
pressure CV will not break during the
harsh conditions of the rocket launch. The
subsystem will be spin and vibration tested
to ensure its stability.
– The mass and CG of the system will also be
found.
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Electrical Testing
• FD
– The FD circuits remain largely unchanged.
Testing with a DMM will ensure proper power
distribution to other subsystems and the
microprocessor.
• CRE
– The CRE must provide a digital out signal at
less than 5v. The team must ensure this is met
to avoid destroying the Netburner. The circuit
must also provide the high potential voltage to
the Geiger tubes. Both of these parameters can
be verified with a DMM.
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Electrical Testing
• RPE
– The RPE board must produce a relatively high
frequency signal output with swept pulses.
Upon completion, this circuit will be attached
to an oscilloscope for output signal verification.
– The receiver can be attached to a similar scope
to verify the receiver picks up the output pulses
from the transmitter.
– This data must also be output in a form that
can be recorded by the Netburner.
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Electrical Testing
• DPE
– The DPE electrical components must produce
an RF signal capable of producing a plasma in
the low pressure CV environment. An
oscilloscope would be a good tool to measure
the outputs of this emitter.
– A DMM can be used to measure the signal
outputs to the scanning laser.
– A more in depth software based approach may
be needed to verify that the camera works to its
specifications.
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Electrical Testing
• GHGE
– The GHGE electronics must be able to provide
sufficient power to the piston actuator, while
also being able to power the solenoid valves.
This can be tested by doing a test run in static
air, as well as with a DMM.
– The signals from the GHGE sensors must also
be within an acceptable voltage range to be
successfully recorded by the Netburner.
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Software Testing
• FD
– By triggering the g-switch, the team will be
able to see if the current code will activate
the payload as well record flight dynamics
information.
– Although this code is paramount for other
codes to activate, it is a successful heritage
element from previous flights and major
modifications are not expected.
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Software Testing
• CRE
– The CRE code must be able to decipher
digital pulses into a numerical count. This
code sequence is also a heritage element,
and little modification work is expected.
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Software Testing
• RPE
– The RPE is expected to be able to send
variable frequency wave pulses into a
plasma environment. The coding must
accurately control the RF circuit such that
the pulse out and received are properly
compared to one another.
– This task will require the completion of the
previously mentioned electrical testing of
this subsystem.
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Software Testing
• DPE
– This code must be able to control the RF
generation circuit and record the sensor
data from the refracted laser.
– This software testing will rely heavily on
the successful mechanical and electrical
completion of the system.
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Software Testing
• GHGE
– The GHGE code must be able to maintain
the CV temperature in the prescribed
range.
– To do this the team will simulate flow
temperatures with compressed air. The
algorithm must be able to position the
piston such that the CV temperature lies
within the acceptable range.
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Risks
Ben Province
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Risk Walk-Down
Netburner
fails in flight
RPE sweep
timing Failure
DPE CV pressure
loss
• Further research and
Design have mitigated
multiple risk in this mission.
• Further time must still be
spent to lower the risk in
the DPE apparatus.
Consequence
GHGE thermal
controller fails
Geiger tube array
breaks on launch
Possibility
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Risk Walk-Down
•
Patch antenna
Not properly
calibrated
GHGE temp
sensors fail
•
Consequence
GHGE piston
controller fails
•
One risk of particular
interest is the failure of the
temperature controller
mechanism in the GHGE
Design refinement and
thorough testing will result
in a much lesser risk of this
component failing.
The risk of antenna failure
will be lessened through
the previously mentioned
prototyping procedures.
Possibility
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User Guide Compliance
Ben Province
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User Guide Compliance
• Mass : current predictions have payload at
13.33lbf
• CG: Although the CG is yet to be found
through testing, it is believed to lie in the
proper space, due in part to properly
distributed battery cells and the relative
magnitude of mass in the GHGE. It can be
noted from the solid models that this
experiment lies in the central axis of the
payload.
• Batteries: current power predictions have the
total battery count as 15 9volt alkaline
batteries.
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Sharing Logistics
• The optical port from the
Puerto Rico team canister will
be used as the Special Port for
the WVU payload.
• This is the only sort of sharing
for this flight, because the
WVU team purchased the
entire canister space.
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Project Management Plan
Justin Yorick
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Budget
• Approximate budgets:
• PSS: $200
• FD incl. magnetometers: $1100
• RPE: $600
• CRE: $200
• GHGE: $375
• Lead times: of the order of <1 week to 10 days.
• Funding sources: West Virginia Space Grant
Consortium, department of physics.
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Conclusion
• At this point, the GHGE and DPE need
to be finalized in design.
• Once all component designs are
finalized, the prototyping plan outlined
in this presentation will be enacted.
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