UPR-R(river) P(rock) X

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UPR-R(river) P(rock) X

CDR, November 23, 2010Presentation Version 1.3

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Mission Overview

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• 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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• 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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Mission Overview

Team

But we insist,We ARE a team!!!

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Theory and Concepts

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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Step 2 Filter the ions•A quadruple mass filter consisting of an arrangement of 4 metal rods with a time-varying electrical voltage of the proper amplitude and frequency applied•This mechanism helps us to select which ions will pass by his charge which isrelative 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. •Or can scan all the mass to 1 – 200 amu and see what we have in the time. 11


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 particular ion species passed by the mass filter. 12


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 amps at 3.3 x 10-7 Torr. 13

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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

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N2, O2, Ar, CO2

He, Ne, Kr, Xe, H2, N2OCH4, O3, H2O, CO, NO2, NH3, SO2, H2S

Aurora (80km to 160km)Co

ncen

trati

on o

f N2,

O2,

O3,

He

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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)

From the Literature

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Mass spectrum for

methane (CH3), bethane

(C2H4) and an isotope of

hydrocarbons (C6H7).

(MCLafferty, 1993)

Mass spectrum for bithylene

(C2H3) and isotope of

hydrocarbons (C4H7).

(MCLafferty, 1993)

Mass spectrum for neon

(Ne) and its isotopes.

Other examples of single species’ mass spectrum- Ideal cases:

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 .

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ParentGas

RelativeMass

IonsFormed

amu

Hydrogen 2 H2 2

H 1

Helium 4 He 4

Methane 16 CH4 16

CH3 15

CH2 14

Ammonia 17 NH3 17

NH2 16

Water 18 H2O 18

OH 17

O 16

Fluorine 19 F 19

Hydrogenfluoride

20 HF 20

F 19

Neon 20, 22 Ne 20, 22

Nitrogen 28 N2 28

N 14

Ethylene 28 C2H4 28

C2H3 27

CH3 15

CH2 14

Carbon 28 CO2 28

Carbonmonoxide

28 CO2 28

O 16

C 12

Ethane 30 C2H5 29

C2H4 28

C2H3 27

CH3 15

CH2 14

Oxygen 32 O2 32

O 16

Argon 40 Ar 40

36 Ar 36

Hydrocarbons various HC various

C5H11 71

C5H9 69

C4H9 57

C4H7 55

C3H7 43

C3H5 41

Examples of possible species to be found in the atmosphere, relative masses for molecular and atomic components:

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.

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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

Model outputs:•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•temperature at altitudehttp://en.wikipedia.org/wiki/NRLMSISE-00

Example of NRLMSISE-00 output

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Example ConOps

t ≈ 1.3 min

Altitude: 95 km

Star Ionizing, Mass Spectra

t ≈ 15 min

Splash Down

t ≈ 1.7 min

Altitude: 120 km

ReScan, Deployment of

secong MS

-G switch triggered

-All systems on

t = 0 min

t ≈ 4.0 min

Altitude: 120 km

Start recovery sequences

Apogee

t ≈ 2.8 min

Altitude: ≈160 km

End of Orion Burn and

Filaments ON

t ≈ 0.6 min

Altitude: 60 km

t ≈ 4.5 min

Altitude: 95 km

Retract Complete

Altitude

t ≈ 5.5 min

Chute Deploys

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System Overview

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Subsystem Overview

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Critical InterfaceInterface 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

For additional space probably will remove the case that protects the board. Because we believe it will not be necessary and occupies necessary space.

RGA 2 CCU 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

For additional space probably will remove the case that protects the board. Because we believe it will not be necessary and occupies necessary space.

x86 Computer 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.

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

DC-DC power supply This part is on the third floor also. Regulating voltage of the all the parts.

Still we don’t have a perfect size of it, but it will be built.

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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

Legend

Primary Components of the functional diagram.

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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 4-Channel 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 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

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• 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

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Prototyping/Analysis

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Analysis Results

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• 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

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• 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

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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

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Mass BudgetSubsystem Total Mass (lbf)

RGA 1 5RGA 2 5x86 computer board * 3DC to DC Converter(12V) * 0.5DC to DC Converter(24V) * 0.5Boom assembly 1 * 2 Boom assembly 2 * 2 Payload Structure * 10

Total 28Over/Under -2.00

* Estimate mass

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Detailed Power Budget

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Power BudgetSubsystem Voltage (V) Current (A) Time On (min) Amp-Hours

Computer 7-36V 1 15 0.25 RGA 1 24V 2.5 7 0.29167

RGA 2 24V 2.5 7 0.29167

Boom arm 1 TBD TBD 1 TBD

Boom arm 2 TBD TBD 1 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

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Power Connector--Customer SidePin Function1 Computer Power2 DC to DC power in (24V)

3DC to DC power in (24V)

4DC to DC power in (12V)

5 Ground6 Ground7 Ground8 Ground9 Computer Power

10 Boom arm 111 Boom arm 212 Ground13 Ground14 Ground

15 Ground

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Wallops Interfacing: Telemetry

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Telemetry Connector--Customer SidePin 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



17 not used 36 ground18 ground 37 ground19 ground

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

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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

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• Every member of the team cooperates and collaborates in every part of the payload’s design and future construction.

RGA’s Booms Plate Budget Theory

• Start working on booms in January and February• They will be constructed to lower errors in the data recollected.

• Start working on plate in January.• Proper installation of spectrometers in Rocksat plate.

• 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.

•Purchase of RGA’s in Nov. and January• Installation of first RGA in January•Environmental testing

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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


2/20/2011 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


3/23/2011 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


4/18/2010 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


5/18/2011 Second DITL Test Report Due

5/20/2011 Weekly Teleconference 3 (2nd DITL Presentations)


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

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•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

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•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

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•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

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•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

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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

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

Students:

Vladimir Makarov Gerardo Morell Ricardo Morales Gladys Muñoz Guillermo Nery Oscar Resto

Faculty Support:

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• 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.

Conclusion

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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

•9. Young, D. T., B. L. Barraclough, J. -J. Berthelier. Plasma Experiment for Planetary Exploration,(1998 ). Retrieved from: http://nmp-techval-reports.jpl.nasa.gov/DS1/PEPE_Integrated_Report.pdf

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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/science11. Earth’s Atmosphere, Retrieved from: http://www.nasa.gov/audience/forstudents/9-12/features/912_liftoff_atm.html12. W. Reusch, The Mass Spectrometer (1999). Retrieved from: http://www2.chemistry.msu.edu/faculty/reusch/VirtTxtJml/Spectrpy/MassSpec/masspec1.htm13. The Thermosphere, Retrieved from: http://www.windows2universe.org/earth_science/Atm_Science/Temp_structure/structure_thermo.html14. P. Mitchell. 2004, The Venus-Halley Missions, Retrieved from: http://www.mentallandscape.com/V_Vega.htm15.Mission Overview: Stardust. Retrieved from: http://stardust.jpl.nasa.gov/mission/index.html16.Anonymous. Internet tutorial for GCMS. Retrived from: http://www.scientific.org/tutorials/articles/gcms.html

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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.htm20.Russel, Randy (2006). Retrieved from:

http://www.windows2universe.org/earth/Atmosphere/chemistry_troposphere.html

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/wg1/221.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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• 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 formolecules up to 300 amu. The RTOF is a highly sensitive for neutral molecules and for ions.

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• 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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• 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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• 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. extra-solar 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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• IMS design is ideally suited for magnetospheric studies of the Neptune-Triton or Jovian environments (Focus 2) where it could build on the high-mass-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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• 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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