UPR-R(river) P(rock) X
CDR, November 23, 2010
Presentation Version 1.3
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Mission Overview
• Mission Statement
In representation of the University of Puerto Rico,
as a team we intend to get involved in the pilot project
RockSat X 2011 to expand our knowledge and that of
others in aerospace related areas. Carefully selected, the
experiment that will be carried out includes mass
spectroscopy to analyze molecular species and their
respective partial pressures in near space. In this way we
will contribute with valuable information for interstellar
travel and advances benefiting the space bound crew to
collect and replenish essential resources such as water
and fuel.
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Mission Overview
Carrying out this experiment involves a set of
minimum requirements. Our main tool will be a mass
spectrometer that will identify molecular species from 1
to 200 amu. Computers need to be modified and
communication established with them by telemetry. This
is one of the most important requisites needed to carry
out the project properly. It is also necessary to have a
basic knowledge of science in the areas of chemistry and
physics to understand several events/concepts that will
be taking place.
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Mission Overview
• In this experiment, we expect to determine the
abundance of different types of gas molecules,
that exist in the outer atmosphere, and near
to outer space, using mass spectroscopy.
• We want to encourage future space voyagers
to use gas molecules present in outer space to
capture or synthesize necessary resources,
such as water and fuel.
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Mission Overview
• Our data would be used as preliminary
information about what type of molecular gases
are found, at what altitude, and with what
density.
• Having the basic data about gases in outer space,
scientists can develop or apply mechanisms to
start converting gas molecules, or atoms to make
the necessary resources needed in long distance
space flights.
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Team
RockSat
Team
Organization
Oscar Resto
(Mentor/PI)
Omar Rocafort
(Leader)
Yashira Torres
(Secretary)
Marimer Soto
(Team Member)
Joshua Nieves
(Team Member)
Gladys Muniz
(Mentor)
Pedro Melendez
(Software
Technical Leader)
Marisara Morales
(Timekeeper)
Angelica
Betancourt
(Team Member)
Oscar A. Resto
(Team Member)
Guillermo Nery
(Faculty Support)
Ricardo Morales
(Faculty Support)
But we insist,
We ARE a team!!!
Esteban Romero
(Hardware
Technical Leader)
Joseph Casillas
(Team Member)
Luis Maldonado
(Team Member)
Carlos Rodriguez
(Team Member)
Theory and Concepts
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Mass Spectrometry [MS]
• The Mass Spectrometry (MS) is an instrumental analytical
method used to determine atomic masses using the
combined properties of mass and electric charge to
detect and measure the relative abundances of atomic
and molecular species. The instrument will also measure
the total amount of gas and the partial pressures of the
species studied could be also be determined.
• Identify substances by electric charge/mass ratio:
– Positively charge the molecules (ionize them).
– Accelerate the ions through an alternating
electromagnetic field that acts as a filter.
– Detect the number of charged species vs. atomic mass.
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How the instrument works:
Magnetic Filter
Some limitations:
• Big and Heavy magnet
•Limited Flexibility
Electro-Magnetic Filter
Some Advantage
•Small and lighter ionizer and quadruple
•More flexible to modifies to this
experimentation
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How the instrument works (1):
Step 1 Create the ions
•Measure the amount of the gas
•Measure the amount of the electrons that pass through by the source grid
•Measure the partial pressure
•Produce a beam of electrons [70eV] creating ions of the species
•Create a magnetic potential to accelerate the ions through the
quadruple
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How the instrument works (2):
Step 2 Filter the ions
•A quadruple mass filter consisting of an arrangement of 4 metal rods with a timevarying electrical voltage of the proper amplitude and frequency applied
•This mechanism helps us to select which ions will pass by his charge which is
relative to their masses.
•The instrument can be program to scan only selected mass, applying a specific
current, move and measure only the mass that we want to measure.
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•Or can scan all the mass to 1 – 200 amu and see what we have in the time.
How the instrument works (3):
Step 3 Detect the filtered ions
•The ions that pass through the mass filter are focused toward a Faraday
cup and the current is measured with a sensitive ammeter.
• The resultant signal being proportional to the partial pressure of the
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particular ion species passed by the mass filter.
How the instrument works (4):
Step 4 Amplify the signal
•Amplifies the current that the faraday cup receive
approximately 10-14 amps.
•The ions striking the B/A detector wire produce a
comparatively larger current, on the order of 10-9
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amps at 3.3 x 10-7 Torr.
Expected results
• MS outputs results in an integrated mass
spectrum with all identifiable species
represented by characteristic fragments of
specific mass/charge ratio in specific proportions.
• Analyze the results to know what species are in
the lower to outer space.
– Verify atmospheric composition.
– Identify possible sources of energy and/or useful
materials.
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Expected gases in our atmosphere
N2, O2, Ar, CO2
He, Ne, Kr, Xe, H2, N2O
CH4, O3, H2O, CO, NO2, NH3, SO2, H2S
Aurora (80km to 160km)
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From the Literature
There are a lots of species that we expect to find, all of them in different concentration in
function of altitude. In a mass spectrum ionic species are represented by their mass/charge
ratio in the x-axis and their relative abundance and the y-axis. From the literature we found
an example of a combined mass spectrum of several species.
Mass Spectrum (log intensity scale) of gases in the atmosphere of
Mars. (MCLafferty, 1993)
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Other examples of single species’ mass spectrum- Ideal cases:
Mass
spectrum
for Mass spectrum for bithylene
methane (CH3), bethane (C2H3)
and
isotope
(C2H4) and an isotope of hydrocarbons
hydrocarbons
of
Mass spectrum for neon (Ne)
and its isotopes.
(C4H7).
(C6H7). (MCLafferty, 1993)
(MCLafferty, 1993)
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Now, why two Mass Spectrums?
• Analyzing the expected results, we conclude that we
need two different MS.
In the first one, it’s quadruple
will measures all masses
between 1 and 200 amu, to
see all the species and their
fragments that are in the outer
space.
In the second one, it’s quadruple
will measures just the masses
that we select to look,
programming the instrument. This
will help to verify the composition
of the atmosphere .
Nitrogen
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N2
28
Examples of possible species to be found in Nthe atmosphere,
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Ethylene
28
CH
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relative masses for molecular and
atomic
components:
2
Parent
Gas
Relative Ions
amu
Mass
Formed
Hydrogen
2
H2
2
H
1
Helium
4
He
4
Methane
16
CH4
16
CH3
15
CH2
14
NH3
17
NH2
16
H2O
18
OH
17
O
16
Ammonia
Water
17
18
Fluorine
19
F
19
Hydrogen
fluoride
20
HF
20
F
19
Carbon
monoxide
Ethane
Oxygen
Argon
4
C2H3
27
CH3
15
CH2
14
CO2
28
O
16
C
12
C2H5
29
C2H4
28
C2H3
27
CH3
15
CH2
14
O2
32
O
16
40
Ar
40
36
Ar
36
HC
various
C5H11
71
C5H9
69
C4H9
57
C4H7
55
28
30
32
Hydrocarbons various
Neon
20, 22
Ne
20, 22
Nitrogen
28
N2
28
N
14
C2H4
28
C2H3
27
CH3
15
C3H7
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CH2
14
C3H5
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CO2
28
Ethylene
Carbon
28
28
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NRLMSISE-00 – Model of the Atmosphere
• NRLMSISE-00 is an empirical, global model of the Earth's
atmosphere from ground to space. It models the
temperatures and densities of the atmosphere's
components. According to the U.S. Naval Research
Laboratory website, NRLMSISE-00 is the standard for
international space research. Model outputs:
Model inputs:
•Year and day
•time of day
•altitude
•geodetic latitude
•geodetic longitude
•local apparent solar time
•81 day average of F10.7 solar flux
•daily F10.7 solar flux for previous day
•Daily magnetic index
http://en.wikipedia.org/wiki/NRLMSISE-00
•Helium Number density
•Oxygen(O) Number density
•Oxygen (O2) Number density
•Nitrogen (N) Number density
•Nitrogen (N2) Number density
•Argon (Ar) Number density
•Hydrogen (H) Number density
•total mass density
•Anomalous oxygen Number density
•Exospheric temperature
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•temperature at altitude
Example of NRLMSISE-00 output
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http://en.wikipedia.org/wiki/NRLMSISE-00
Example ConOps
t ≈ 1.7 min
Altitude
Altitude: 120 km
t ≈ 4.0 min
ReScan,
Deployment of
secong MS
Altitude: 120 km
Apogee
t ≈ 1.3 min
Start recovery
sequences
t ≈ 2.8 min
Altitude: 95 km
Star Ionizing,
Mass Spectra
Altitude: ≈160
km
End of Orion
Burn and
Filaments ON
t ≈ 0.6 min
t ≈ 4.5 min
Altitude: 95 km
Retract Complete
t ≈ 5.5 min
Chute
Deploys
Altitude: 60 km
t = 0 min
-G switch
triggered
-All systems on
t ≈ 15 min
Splash
Down
System Overview
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Subsystem Overview
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Critical Interface
Interface Name
Brief Description
Potential Solution
RGA 1 probe
The RGA 1 will be mounted vertically
with the boom arm attached to it. Support
and protection will be fundamental to get
to apogee with no failure. The RGA main
support will be mounted on the floor of
the RockSat X deck.
The RGA will be held together by a
circular tube of aluminum or stainless
steelthat will withstand the 50 G’s
presumed to be sustained by the rocket.
RGA 2 probe
The RGA 2 will be mounted vertically
with the boom arm attached to it. Support
and protection will be fundamental to get
to apogee with no failure. The RGA main
support will be mounted on the floor of
the RockSat X deck.
The RGA will be held together by a
circular tube of aluminum or stainless
steelthat will withstand the 50 G’s
presumed to be sustained by the rocket.
RGA 1 CCU
It will be mounted at the center of the first
floor of RockSat X deck and will be
connected through wires to the RGA
sensor 1
It will be mounted at the center of the
second floor of RockSat X deck and will
be connected through wires to the RGA
sensor 2
It will be mounted on the third floor of
RockSat X deck. It will be connected to
both board stacks. It will receive all the
data and will record and send it back thru
the telemetry to us down on earth.
This part is on the third floor also.
Regulating voltage of the all the parts.
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For additional space probably will remove
the case that protects the board. Because
we believe it will not be necessary and
occupies necessary space.
For additional space probably will remove
the case that protects the board. Because
we believe it will not be necessary and
occupies necessary space.
The connections of the wired will be all
over the floors. So we will organize the
running of the wires and glue then good
so the vibrations won’t break any
connections to the boards
Still we don’t have a perfect size of it, but
it will be built.
RGA 2 CCU
x86 Computer
DC-DC power supply
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System Level Block Diagram
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Requirement Verification
Requirement
Verification Method
Description
Boom extension will deploy
maximum 18”. It will too
withstand the vibration test.
Demonstration of it functionality
Boom will drop from vertical
position to horizontal position
and extend 12” for a total of
24”. Later on to retract to its
original state.
Total voltage of equipment and
complete functionality of the
DC-DC converter.
Experimentation of the whole
system ready for launch
Ones all the parts are
assembled , build and
connected they will be turned
on as it were for flight. Then the
current will be measured for
total voltage.
Support for the RGA 1 & 2
sensors must hold the
complete vibration test.
Vibration test date on WFF
First designing a strong
structure and use materials
strong enough to support the
vibration test
Software
Running a simulate launch
Ones the software has been
edited and uploaded. We will
run a simulation to see if it
works.
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Subsystem Design
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Block Diagram
Primary Components of the functional
diagram.
Legend
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Trade Studies
• Embedded x86 computer mainboard
 VIA EPIA P820-12L Pico ITX Mainboard
 VIA EITX-3001 Em-ITX
• DC-DC Converter
 Intelligent DC-DC converter with USB
interface
• I/O Board
 RS-232 Relay Controller 4-Channel 5 Amp
SPDT + 8-Channel 8/10-Bit A/D
 RS-232 4-Channel Solid State Relay
Controller + 8-Channel 8/10-Bit A/D
• Data storage
 OCZ Onyx Series OCZSSD1-1ONX32G 1.8"
32GB SATA II MLC Internal Solid State Drive
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Trade Studies
• For mainboard considering cost, number serial
ports, power requirements and form factor,
option A for the prototype will be VIA EITX-3001
Em-ITX.
• For I/O Board considering cost, configuration
options and form factor, option A for the
prototype will be RS-232 Relay Controller 4Channel 5 Amp SPDT + 8-Channel 8/10-Bit A/D
which has more option for configuring the relay
and has a smaller footprint.
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Risk Matrix
Risk 4 Risk 1
Consequence
Risk 2 Risk 3
Possibility
Risk 1 – Computer system crash during flight and data couldn’t be collected
mission objectives couldn’t be completed.
Risk 2 – A boom arm failure during deployment occurs and probe performs
measurements inside the payload.
Risk 3 – Telemetry error between x86computer and wallops leaving experiment
data only on the payload storage which will have survive landing on the sea.
Risk 4 – Power failure on some of the component making funtionability limited.
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Design Description
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River Rock X Sketch Diagram
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De-Scopes and Off-Ramps
•The scope of our project haven’t changed.
•So far all our mission statements will be done in our
experiment.
•Concerns(In order of importance)
Creation of the booms.
Will the RGA survive the vibration test mounted
on the booms.
Additional power for the whole system
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Mechanical Design Elements
Mechanical Front view design
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3d imaged
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3D image of or payload
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Materials Part List and Prices
•
x86 computer $88.99 ocz ssd
http://www.newegg.com/Product/Product.aspx?Item=N82E16820227553&cm_re=
ocz_ssd-_-20-227-553-_-Product
•
$369.00 via emitx motherboard http://www.e-itx.com/eitx-3001.html
•
control boards es solo uno tenemos dos opciones $124 RS-232 4-Channel Solid
State Mixed SSR Relay Controller + 8-Channel 8/10-Bit A/D
http://www.controlanything.com/Relay/Device/ADSSR4xPROXR_MIX
•
$124 RS-232 Relay Controller 4-Channel 5 Amp SPDT + 8-Channel 8/10-Bit A/D
http://www.controlanything.com/Relay/Device/ADR45PROXR
•
DC-DC converter $59.95 Intelligent DC-DC converter with USB interface
http://www.mini-box.com/DCDC-USB?sc=8&category=981
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Electrical Design Elements
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Electrical Design Elements
• Power lines 10 and 11 are not shown connected to
anything because this lines will power the boom arms
motors which have not selected yet and because of
this power requirement is to be determined
• Relays R1-4 on the control board will be used to
activate the boom arms to relays per boom.
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Software Design Elements
• Software development still at its beginning
• Studying of the API’s of the payload hardware
• Research how to use the telemetry interfaces to
achieve better results
• Analyzing which procedures are needed to
control the payload and collect all data correctly
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Software Design Elements
System starts
Wait for G-switch signal
Set both RGAs to start ionizers
when pressure is adequate
t=1.3
Start data collection when
ready
System shutdown
Stop data collection
t = 5.5
Close boom on re-entry
t=4.5
Deploy boom arms
when rocket skin is
release
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Prototyping/Analysis
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Analysis Results
• What was analyzed?
• Boom extension was a matter of
importance because of the outgassing
bubble created by the rocket and the
equipment on it.
• The RGA’s ionizer filament survival to the
launch conditions
• Strong payload structure to survive
launch conditions
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Analysis Results
• Resultant design
• Boom arm is needed to extend 24” to
minimize outgassing noise on reading
• The RGA’s ionizer filament most be
unused before launch because its
crystallize after the first use
• RGA’s will be mounted vertically while
using a stacked confugiration for the
electronics
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Prototyping Results
In order to make the first prototype our
team is waiting for the first RGA to arrive
and start making mock ups of the system.
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Detailed Mass Budget
Mass Budget
Subsystem
Total Mass (lbf)
RGA 1
RGA 2
x86 computer board *
DC to DC Converter(12V) *
DC to DC Converter(24V) *
Boom assembly 1 *
Boom assembly 2 *
Payload Structure *
5
5
3
0.5
0.5
2
2
10
Total
Over/Under
28
-2.00
* Estimate mass
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Detailed Power Budget
Power Budget
Subsystem
Computer
RGA 1
RGA 2
Boom arm 1
Boom arm 2
Voltage (V)
7-36V
24V
24V
TBD
TBD
Current (A)
Time On (min)
1
2.5
2.5
TBD
TBD
15
7
7
1
1
Amp-Hours
0.25
0.29167
0.29167
TBD
TBD
Total (A*hr):
0.83334
Over/Under
-0.16666
Boom arm current consumption will be determine once
boom arm motor are chosen.
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Wallops Interfacing: Power
Power Connector--Customer Side
Pin
Function
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
Computer Power
DC to DC power in (24V)
DC to DC power in
(24V)
DC to DC power in
(12V)
Ground
Ground
Ground
Ground
Computer Power
Boom arm 1
Boom arm 2
Ground
Ground
Ground
Ground
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Wallops Interfacing: Telemetry
Telemetry Connector--Customer Side
Pin
Function
Pin
Function
1 TBD
20 to mainboard parallel port
2 TBD
21 to mainboard parallel port
3 TBD
22 to mainboard parallel port
4 TBD
23 to mainboard parallel port
5 TBD
24 to mainboard parallel port
6 TBD
25 to mainboard parallel port
7 TBD
26 to mainboard parallel port
8 TBD
27 to mainboard parallel port
9 TBD
28 to mainboard parallel port
10 TBD
29 to mainboard parallel port
11 to mainboard parallel port
30 to mainboard parallel port
12 to mainboard parallel port 31 not used
13 to mainboard parallel port 32 to mainboard COM1
14 to mainboard parallel port 33 to mainboard COM1
15 to mainboard parallel port 34 not used
16 to mainboard parallel port 35 not used
17 not used
36 ground
18 ground
37 ground
19 ground
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Analog to digital
converters line are
not being use in the
payload design for
now because all
sensor communicate
via serial port to the
computer directly
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User Guide Compliance
Requirement
Status/Reason (if needed)
Center of gravity in 1" plane of
plate?
TBD
Max Height < 12"
yes
Within Keep-Out
yes
Using < 10 A/D Lines
yes
Using/Understand Parallel Line
Will be use to monitor states of the experiment
Using/Understand Asynchronous
Line
9600 Baud
Using X GSE Line(s)
1
Using X Redundant Power Lines
1
Using X Non-Redundant Power
Lines
3
Using < 1 Ah
Total Ah TBD
Using <= 28 V
24V & 12V
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Project Management Plan
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Work Breakdown Structure
•
Every member of the team cooperates and collaborates in every part of the payload’s design and future
construction.
RGA’s
•Purchase of
RGA’s in Nov.
and January
• Installation of
first RGA in
January
•Environmental
testing
Booms
• Start working on
booms in January and
February
• They will be
constructed to lower
errors in the data
recollected.
Plate
• Start working on
plate in January.
• Proper
installation of
spectrometers in
Rocksat plate.
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Budget
Theory
• Raise a $13,000
budget for March.
• Make arrangements
for acquiring the
necessary materials
for construction of
the payload.
• Have more information
about our expected
results.
• Results would be
modified, depending on
the development of the
model that will work with
the samples.
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Date
10/26/2010
Group Meeting for PDR
10/27/2010
Preliminary Design Review (PDR) Due
10/29/2010
Preliminary Design Review (PDR) Teleconference
11/02/2010
Group Meeting for CDR
11/04/2010
Group Meeting for CDR
11/09/2010
Group Meeting for CDR and Online Progress Report 2
11/12/2010
Online Progress Report 2 Due
11/17/2010
Critical Design Review (CDR) Due
11/19/2010
Critical Design Review (CDR) Teleconference
11/23/2010
Group Meeting
11/30/2010
Group Meeting
12/3/2010
Post CDR Action Item Generation
12/14/2010
Start working on the software
1/1/2011-3/31/2011
Raise a budget of 16,000
1/14/2011
Final Down Select—Flights Awarded
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1/20/2011
Purchase first and second spectrometers
1/22/2011
Construction of Rock Sat X plate
1/26/2011
Environmental test(First spectrometer attach to the plate)
1/28/2011
Post CDR Action Item Review
2/1/2011-3/31/2011
Dual mass spectrometer after environmental and vacuum test
2/4/2011
First Installment Due
2/18/2011
Online Progress Report 3 Due
2/20/2011
Start working on the booms
2/23/2011
Individual Subsystem Testing Reports Due
2/25/2011
Individual Subsystem Testing Reports Teleconference
3/10/2011
Basic Integration
3/18/2011
Online Progress Report 4 Due
3/23/2011
Payload Subsystem Integration and Testing Report Due
3/25/2011
Payload Subsystem Integration and Testing Report Teleconference
April 2011
RockSat Payload Decks Sent To Customers (Pending Completion)
4/1/2011
Final Installment Due
4/15/2011
Online Progress Report 5 Due
4/18/2010
Partial Integration
4/20/2011
First DITL Test Report Due
4/22/2011
DITL 1 Teleconferences
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5/6/2011
Weekly Teleconference 1
5/9/2011
Full Integration
5/13/2011
Weekly Teleconference 2
5/18/2011
Second DITL Test Report Due
5/20/2011
Weekly Teleconference 3 (2nd DITL Presentations)
5/27/2011
Weekly Teleconference 4
5/29/2011
Software test
5/30/2011
Redesign final review
6/3/2011
Weekly Teleconference 5 (Travel Logistics)
6/10/2011
Launch Readiness Review 1 (LRR) Due
6/13/2011
Launch Readiness Review 1 (LRR) at Wallops
6/14-16/2011
Environmental Testing/Integration at Wallops
6/17/2011
Action Item Meeting with Wallops
7/8/2011
Post Environmental Tag-Up 1
7/29/2011
Post Environmental Tag-Up 2
7/30/2011
Final LRR Due
7/30/2011
Final Payload Inspections
7/30-31/2011
Final LRR and Inspections
08/1-2/2011
Final Payload Integration
8/4/2011
Launch!
8/5-7/2011
Contingency Launch
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Testing Plan
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System Level Test
•Verify with the environmental test that all
components of the payload are secure.
Perform simulation test to ensure that all
subsystem (electronic, mechanical and software)
levels are working to perfection.
Do mass spectroscopy tests on RGAs . This test the
out gassing of each RGA.
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Mechanical Test
•Our boom is still to be designed. The boom is the
extension part of the payload that consist mostly of
mechanics. The boom contains the RGA, which need
to be slightly modified in order to operate properly.
•We have planned to make an environmental test.
Which will help us to secure the payload.
(vibration test)
•We are still making arrangements to perform an
additional environmental test on RGAs in January
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Electrical Test
•We will simulate the experiment by using the
standard voltage of the guideline. This test will be
use to verify all electronic components.
•Plate 3- CPU and DC to DC converter
•Plate 4-(if necessary for additional battery power)
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Software Test
•It will be tested by simulating the programming
of the mission to ensure the synchronization and
performance of all the components of the system
(Electronics, RGA and boom)
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Budget
Equipment, Materials, and Trips
Cost
Materials for Pilot:
$5,000
Computer protector
Production canister
Materials:
$2,500
Computers
x-86 ocz ssd
$88.99
Via emitx motherboard
$369.00
Power supplies
Teflon cables, connectors
Capton tape, insulators
Control Board
RS-232 4-Channel Solid State
$124
RS-232 $-Channel 5 Amp
$124
DC-DC Converter
$60
GC MassSpec
$22,500
Residual Gas Analizer(3)
$10,350
Consumable Materials
$7,650
Electron Multiplier(3)
$4,500
Payload flight
$24,000
Trip to Wallops August 2011
$20,600
Flight
$5,000
Hotel
$8,400
Car
$2,400
Food
$4,800
Trip to Wallps June 2011
$4,790
Flight
$1,500
Hotel
$1,960
Car
$500
Food
$840
Team Polo's
$600
Estimate Total
$82,820
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Team Members
Students:
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Faculty Support:
Angelica Betancourt
Joseph Casillas
Luis Maldonado
Pedro Melendez
Marisara Morales
Joshua Nieves
Oscar A. Resto
Omar Rocafort
Carlos Rodriguez
Esteban Romero
Marimer Soto
Yashira Torres
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Vladimir Makarov
Gerardo Morell
Ricardo Morales
Gladys Muñoz
Guillermo Nery
Oscar Resto
64
Conclusion
• The aim in this experiment is to analyze the atomic/molecule species that
could be found during the flight of the payload, ionizing and analyzing them
by their atomic mass components and partial pressures. With this kind of
analysis we intend to study the possibility of in-flight energy/materials
resource collector for long term and deep space vehicles.
• Issues, concerns, any questions
– 6 amps at 28 volts to confirm with actual equipment
– Battery plate
– Boom Design
– Budget !!!
• Plan for where you will take your design from here?
– Purchase the fierst MassSpectrometerd
– Atmospheric, and vibration test on the Mass Spectrometer will be send to
be tested by mail.
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References
1. Anonymous. Internet tutorial for GCMS. Retrived from:
http://www.scientific.org/tutorials/articles/gcms.html
2. Anonymous. Bioinstrumentation class (internet based) (1998). Retrieved from:
http://www.gmu.edu/depts/SRIF/tutorial/gcd/gc-ms2.htm
3. Extorr Instrument manual (2006). PDF download retrieved from:
http://extorr.com/manual.htm
4. Meng, Alan and Hui. Retrived from: http://www.vtaide.com/png/atmosphere.htm
5. Russel, Randy (2006). Retrieved from:
http://www.windows2universe.org/earth/Atmosphere/chemistry_troposphere.html
6. Tans, Pierter. Retrived from: http://www.esrl.noaa.gov/gmd/ccgg/trends/#mlo
7. Uherek, Elmar (2004) “What is up in air in the troposphere?” . Retrieved from:
http://www.atmosphere.mpg.de/enid/1__Extensi_n_y_composici_n/_componentes_2vv.html
8.UNEP/GRIP (2003). Retrieved from:
http://www.grida.no/publications/other/ipcc%5Ftar/?src=/climate/ipcc_tar/wg1/221.
htm
2011
•
9.
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Young, D. T., B. L. Barraclough,
J. -J. Berthelier. Plasma Experiment for
10. D. Offermann, K. Pelka and U. Von Zah, Mass spectrometric measurements of
minor constituents in the lower thermosphere, Retrieved from:
http://www.sciencedirect.com/science
11. Earth’s Atmosphere, Retrieved from:
http://www.nasa.gov/audience/forstudents/9-12/features/912_liftoff_atm.html
12. W. Reusch, The Mass Spectrometer (1999). Retrieved from:
http://www2.chemistry.msu.edu/faculty/reusch/VirtTxtJml/Spectrpy/MassSpec/massp
ec1.htm
13. The Thermosphere, Retrieved from:
http://www.windows2universe.org/earth_science/Atm_Science/Temp_structure/struct
ure_thermo.html
14. P. Mitchell. 2004, The Venus-Halley Missions, Retrieved from:
http://www.mentallandscape.com/V_Vega.htm
15. Mission Overview: Stardust. Retrieved from:
http://stardust.jpl.nasa.gov/mission/index.html
16. Anonymous. Internet tutorial for GCMS. Retrived from:
http://www.scientific.org/tutorials/articles/gcms.html
2011
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17. Anonymous. Bioinstrumentation class (internet based) (1998). Retrieved from:
http://www.gmu.edu/depts/SRIF/tutorial/gcd/gc-ms2.htm
18. 18. Extorr Instrument manual (2006). PDF download retrieved from:
http://extorr.com/manual.htm
19. Meng, Alan and Hui. Retrived from: http://www.vtaide.com/png/atmosphere.htm
20. Russel, Randy (2006). Retrieved from:
http://www.windows2universe.org/earth/Atmosphere/chemistry_troposphere.ht
ml
21. Tans, Pierter. Retrived from: http://www.esrl.noaa.gov/gmd/ccgg/trends/#mlo
22. Uherek, Elmar (2004) “What is up in air in the troposphere?” . Retrieved from:
http://www.atmosphere.mpg.de/enid/1__Extensi_n_y_composici_n/_componentes_2vv.html
23. UNEP/GRIP (2003). Retrieved from:
http://www.grida.no/publications/other/ipcc%5Ftar/?src=/climate/ipcc_tar/wg1/2
21.htm
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Mission Overview: Previous Research
• Mass spectrometers have been used at other planets and moons.
Two were taken to Mars by the Viking program. In early 2005
the Cassini-Huygens mission delivered a specialized GC-MS
instrument aboard the Huygens probe through the atmosphere of
Titan, the largest moon of the planet Saturn. This instrument
analyzed atmospheric samples along its descent trajectory and
was able to vaporize and analyze samples of Titan's frozen,
hydrocarbon covered surface once the probe had landed. These
measurements compared the abundance of isotope(s) of each
particle comparatively to earth's natural abundance.[42] Also
onboard the Cassini-Huygens spacecraft is an ion and neutral
mass spectrometer which has been taking measurements of
Titan's atmospheric composition as well as the composition of
Enceladus' plumes. A Thermal and Evolved Gas Analyzer mass
spectrometer was carried by the Mars Phoenix Lander launched
in 2007.[43]
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Mission Overview: Previous Research
• Rosetta is a European Space Agency-led robotic spacecraft
mission launched in 2004. Once attached to the comet, expected
to take place in November 2014, the lander will begin its science
mission: around characterization of the nucleus, determination of
the chemical compounds present, including enantiomers and
study of comet activities and developments over time. It includes
instruments for gas and particle analysis, like for example
ROSINA(Rosetta Orbiter Spectrometer for Ion and Neutral
Analysis) the instrument consists a double focus magnetic mass
spectrometer DFMS and a reflectron type time of flight mass
spectrometer RTOF. The DFMS has a high resolution for
molecules up to 300 amu. The RTOF is a highly sensitive for
neutral molecules and for ions.
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Mission Overview: Previous Research
• For the in situ investigation of planetary atmospheres a small
Mattauch‐Herzog mass spectrometer has been developed. Its
high‐pressure performance has been improved by incorporating
differential pumping between the ion source and the analyzing
fields, shortening the path‐length as well as increasing the extraction
field in the ion source. In addition doubly ionized and dissociated
ions are used for mass analysis. These measures make possible
operation up to 10−2 millibars. Results of laboratory tests related to
linearity, dynamic range, and mass resolution are presented, in
particular for CO2.
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Mission Overview: Previous Research
•
Mass spectrometric measurements of minor constituents in the lower thermosphere
D. Offermanna, K. Pelkaa and U. Von Zahna a Physikalisches Institut, Universität
Bonn W. Germany Received 1 November 1971. Available online 15 November 2001.
• Abstract
The feasibility of measurements of CO2, NO, N and H2O in the lower
thermosphere by means of rocket-borne mass spectrometers with helium-cooled and
with conventional ion sources is discussed. Three recent night-time experiments above
Sardinia are described. They took place on October 13, 1970, at 0208 CET (payload
SN5, helium-cooled ion source) and on February 7, 1971, at 0022 CET and 0445 CET
(payloads ESRO S80-2 and -3, respectively, uncooled ion sources). Preliminary results
indicate CO2 to be mixed up to the turbopause and to be in diffusive equilibrium higher
up. The ratio NO: N2 was found to be in fair agreement with recent model calculations
of Strobel (1971) for the altitute range 140 to 200 km.
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Mission Overview: Previous Research
• Proposed project of a cometary coma is composed of material outgassed and
sputtered from the nucleus. Photoionization, charge exchange, and direct surface
sputtering all generate a substantial ion population. A PEPE-class instrument can
efficiently sample and analyze the ion population. Example targeted
measurements are the cometary 13C/12C ratio (a possible test of solar vs. extrasolar system origins), the 18O/16O ratio (Halley is the only outer solar system
object for which this is known), trace molecular abundances including the CO/N2
ratio which a PEPEclass instrument is uniquely capable of measuring [2], and
heavier organic molecules up to 135 amu. PEPE possesses a unique advantage
over mass spectrometers flown on Giotto and those on known future comet
missions: the carbon foil used to generate timing signals breaks up molecules,
allowing isotopic ratios of volatile species such as H, C, N, O to be analyzed
without interferences from hydride molecular ions (H2, CH, NH, OH, H2O, etc.)
[2].
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Mission Overview: Previous Research
• IMS design is ideally suited for magnetospheric studies of the NeptuneTriton or Jovian environments (Focus 2) where it could build on the highmass-resolution studies of the Saturnian system planned with Cassini IMS
[2]. Because our IMS/PEPE designs measure composition, they are also
invaluable for the study of the ionospheres of outer planet moons, and
indirectly, their atmospheric and surface chemistries (Focus 1). For the
Neptune-Triton system, a PEPE-class instrument could give a first in-situ
glimpse of the magnetosphere and help determine key processes in Triton's
atmosphere, as well as yielding some key isotope ratios. Galileo's IMS
mass resolution of only 2 amu did not allow Na to be distinguished from O,
an important goal for the understanding of Io's ionospheric and exospheric
processes. Key isotopic measurements, e.g. 34S/32S, at Io are also crucial
to understanding that body's evolution. Similarly, a highmass- resolution
instrument in low Europa orbit may give a better understanding not only of
its tenuous atmosphere, but also of key isotopic and elementalsurface
compositions in lieu of a lander.
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Mission Overview: Previous Research
• The Stardust spacecraft brought back samples of interstellar dust,
including recently discovered dust streaming into our Solar System from
the direction of Sagittarius. These materials are believed to consist of
ancient pre-solar interstellar grains and nebular that include remnants
from the formation of the Solar System. Analysis of such fascinating
celestial specks is expected to yield important insights into the evolution
of the Sun its planets and possibly even the origin of life itself. During
the Stardust project, the spacecraft traveled more than 3 billion miles
over seven years, rendezvous-ing with the comet Wild 2 during the
second of three orbits around the sun. The end of the mission marked
the beginning of another adventure: Examining the comet particles with
powerful scientific instruments called mass spectrometers, which are
able to identify what isotopes the stuff is made of. Using mass
spectrometry, the researchers found the amino acid on samples from the
comet Wild 2, adding fuel to the argument that life on Earth may have
had its start in outer space and that life may exist outside of Earth.
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