1. 2011 CoDR 1 UPR-R(river) P(rock) X CDR, February, 2010 Presentation Version 2.1

2. 2011 CoDR 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. 2

3. 2011 CoDR Mission Overview Carrying out this experiment involves a set of minimum requirements. Our main tool will be two mass spectrometers (Residual Gas Analyzer, RGA) 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. 3

4. 2011 CoDR 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 and synthesize necessary resources, such as water and fuel. 4

5. 2011 CoDR 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 and apply mass spectrometry mechanisms for the capture and separation of specific species of gas molecules, or atoms to make the necessary resources needed in long distance space flights. 5

6. Team RockSat Team Organization Oscar Resto (Mentor/PI) Gladys Muniz (Mentor) Guillermo Nery (Faculty Support) Ricardo Morales (Faculty Support) Omar Rocafort (Leader) Pedro Melendez (Software Technical Leader) Esteban Romero (Hardware Technical Leader) Yashira Torres (Secretary) Marisara Morales (Timekeeper) Marimer Soto (Team Member) Angelica Betancourt (Team Member) Joseph Casillas (Team Member) Joshua Nieves (Team Member) Oscar A. Resto (Team Member) Luis Maldonado (Team Member) Carlos Rodriguez (Team Member) Ricardo Morales (Faculty Support) Vladimir Makarov (Faculty Support) But we insist, We ARE a team!!!

7. 2011 CoDR Theory and Concepts 7

8. 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. 8

9. 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 9

10. 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 10

11. How the instrument works (2): 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 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. Or can scan all the mass to 1 – 200 amu and see what we have in the time. 11

12. 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 particular ion species passed by the mass filter. 12

13. 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 amps at 3.3 x 10 -7 Torr. 13

14. 2011 CoDR 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. 14

15. 15 2011 CoDR Expected gases in our atmosphere 17 N 2, O 2, Ar, CO 2 He, Ne, Kr, Xe, H 2, N 2 O CH 4, O 3, H 2 O, CO, NO 2, NH 3, SO 2, H 2 S Aurora (80km to 160km) Concentration of N 2, O 2, O 3, He

16. 16 2011 CoDR 18 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

17. 17 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:

18. 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.

19. 19 Examples of possible species to be found in the atmosphere, relative masses for molecular and atomic components:

20. 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. 20 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 (O 2 ) Number density Nitrogen (N) Number density Nitrogen (N 2 ) Number density Argon (Ar) Number density Hydrogen (H) Number density total mass density Anomalous oxygen Number density Exospheric temperature temperature at altitude http://en.wikipedia.org/wiki/NRLMSISE-00

21. Example of NRLMSISE-00 output 21 http://en.wikipedia.org/wiki/NRLMSISE-00

22. 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

23. 2011 CoDR System Overview 23

24. 2011 CoDR Subsystem Overview

25. 2011 CoDR Critical Interface Interface NameBrief DescriptionPotential Solution RGA 1 probeThe 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 probeThe 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 CCUIt 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 CCUIt 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 ComputerIt 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 supplyThis 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.

26. 2011 CoDR System Level Block Diagram

27. 2011 CoDR Requirement Verification Requirement Verification Method Description Boom extension will deploy maximum 18”. It will too withstand the vibration test. Demonstration of it functionalityBoom 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 WFFFirst designing a strong structure and use materials strong enough to support the vibration test SoftwareRunning a simulate launchOnes the software has been edited and uploaded. We will run a simulation to see if it works.

28. 2011 CoDR Subsystem Design 28

29. 2011 CoDR Block Diagram Legend Primary Components of the functional diagram.

30. 2011 CoDR 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

31. 2011 CoDR 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.

32. 2011 CoDR Risk Matrix Consequence Risk 4Risk 1 Risk 2Risk 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.

33. 2011 CoDR Design Description 33

34. 2011 CoDR 34 River Rock X Sketch Diagram

35. 2011 CoDR 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 Mass Spetrometer survive the vibration test mounted on the booms.  Additional power for the whole system

36. 2011 CoDR Mechanical Design Elements Mechanical Front view design

37. 2011 CoDR 3D image of or payload

38. 2011 CoDR 3d Payload Movie

39. 2011 CoDR Mass Spectrometer 39

40. 2011 CoDR Exploded Mass Spectrometer with Electronics 40

41. 2011 CoDR Ionizer Assembly and Quadrupole Filter 41

42. 2011 CoDR Mass Spectrometer RF Electronics Stack and Computer Control 42

43. 2011 CoDR 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 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 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 43

44. 2011 CoDR Electrical Design Elements

45. 2011 CoDR System ElectricalDiagram

46. 2011 CoDR 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.

47. 2011 CoDR Software Design Elements 47 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

48. 2011 CoDR Software Design Elements 48 System startsWait for G-switch signal Set both RGAs to start ionizers when pressure is adequate t=1.3 Start data collection when ready Deploy boom arms when rocket skin is release Close boom on re-entry t=4.5 Stop data collection t = 5.5 System shutdown

49. 2011 CoDR Prototyping/Analysis 49

50. 2011 CoDR Analysis Results 50 What was analyzed? Boom extension was a matter of importance because of the outgassing bubble of outgas created by the rocket and the equipment on it. The Mass Spectrometer’s ionizer’s filament’s survival to the launch vibration conditions. Strong payload structure to survive launch conditions

51. 2011 CoDR Analysis Results 51 Resultant design Boom arm is needed to extend up to 24”, to minimize outgassing noise on reading The Mass Spectrometer’s ionizer filament most be unused before launch because its crystallize after the first use. Mass Spectrometer’s will be mounted vertically while using a stacked configuration for the electronics.

52. 2011 CoDR Actual Prototyping Results 52 Linear Y Scale vs AMU, Air Sample, main peak H2O (18 AMU), H ( 1 AMU), N2 (28 AMU), O2 (32 AMU), etc.

53. 2011 CoDR Actual Prototyping Results 53 Logarithmic Y Scale vs AMU, Air Sample, main peak H2O (18 AMU), H ( 1 AMU), N2 (28 AMU), O2 (32 AMU), etc. Residual partial pressure of different gases species identification can be measure for up to 7 orders of magnitude.

54. 2011 CoDR Detailed Mass Budget 54 Mass Budget SubsystemTotal Mass (lbf) RGA 15 RGA 25 x86 computer board *3 DC to DC Converter(12V) *0.5 DC to DC Converter(24V) * 0.5 Boom assembly 1 *2 Boom assembly 2 *2 Payload Structure *10 Total28 Over/Under-2.00 * Estimate mass

55. 2011 CoDR Detailed Power Budget 55 Power Budget SubsystemQty.Voltage (V)Current (A)Time On (min) Computer17-36V115 Mass Spectrometer224V0.627 I/O board112V0.515 Pneumatic Solenoid124V0.151 Total3.89 Over/Under

56. 2011 CoDR Detailed Power Budget – Mass Spectrometer 56 idleHost ComputerFilament ONElectron Mult. ONDegas Mode With R420.150.490.790.821.44 Without R42 mass 20.150.170.430.471.14 Without R42 mass 1000.150.260.500.531.20 Without R42 mass 2000.150.350.570.621.32 ExTorr Mass Spectrometer Power Requirements in amperes, initial powering, surge as a 1000uf capacitor, and currents at different states of the system during flight.

57. 2011 CoDR Wallops Interfacing: Power 57 Power Connector--Customer Side PinFunction 1Computer Power 2DC to DC power in (24V) 3 4 DC to DC power in (12V) 5Ground 6 7 8 9 Computer Power 10Boom arm 1 11Boom arm 2 12 Ground 13 Ground 14 Ground 15 Ground

58. 2011 CoDR Wallops Interfacing: Telemetry 58 Telemetry Connector--Customer Side PinFunctionPinFunction 1TBD20 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 port30 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 used36 ground 18 ground37 ground 19 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

59. 2011 CoDR User Guide Compliance 59 RequirementStatus/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

60. 2011 CoDR Project Management Plan 60

61. 2011 CoDR Work Breakdown Structure 61 Every member of the team cooperates and collaborates in every part of the payload’s design and future construction. RGA’sBoomsPlateBudgetTheory 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

62. 2011 CoDR Date 10/26/2010Group Meeting for PDR 10/27/2010Preliminary Design Review (PDR) Due 10/29/2010Preliminary Design Review (PDR) Teleconference 11/02/2010Group Meeting for CDR 11/04/2010Group Meeting for CDR 11/09/2010Group Meeting for CDR and Online Progress Report 2 11/12/2010Online Progress Report 2 Due 11/17/2010Critical Design Review (CDR) Due 11/19/2010Critical Design Review (CDR) Teleconference 11/23/2010Group Meeting 11/30/2010Group Meeting 12/3/2010Post CDR Action Item Generation 12/14/2010 Start working on the software 1/1/2011-3/31/2011 Raise a budget of 16,000 1/14/2011Final Down Select—Flights Awarded

63. 2011 CoDR 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) 1/28/2011Post CDR Action Item Review 2/1/2011-3/31/2011 Dual mass spectrometer after environmental and vacuum test 2/4/2011First Installment Due 2/18/2011Online Progress Report 3 Due 2/20/2011 Start working on the booms 2/23/2011Individual Subsystem Testing Reports Due 2/25/2011Individual Subsystem Testing Reports Teleconference 3/10/2011Basic Integration 3/18/2011Online Progress Report 4 Due 3/23/2011Payload Subsystem Integration and Testing Report Due 3/25/2011Payload Subsystem Integration and Testing Report Teleconference April 2011RockSat Payload Decks Sent To Customers (Pending Completion) 4/1/2011Final Installment Due 4/15/2011Online Progress Report 5 Due 4/18/2010 Partial Integration 4/20/2011First DITL Test Report Due 4/22/2011DITL 1 Teleconferences

64. 2011 CoDR 5/6/2011Weekly Teleconference 1 5/9/2011Full Integration 5/13/2011Weekly Teleconference 2 5/18/2011Second DITL Test Report Due 5/20/2011Weekly Teleconference 3 (2nd DITL Presentations) 5/27/2011Weekly Teleconference 4 5/29/2011 Software test 5/30/2011 Redesign final review 6/3/2011Weekly Teleconference 5 (Travel Logistics) 6/10/2011Launch Readiness Review 1 (LRR) Due 6/13/2011Launch Readiness Review 1 (LRR) at Wallops 6/14-16/2011Environmental Testing/Integration at Wallops 6/17/2011Action Item Meeting with Wallops 7/8/2011Post Environmental Tag-Up 1 7/29/2011Post Environmental Tag-Up 2 7/30/2011Final LRR Due 7/30/2011Final Payload Inspections 7/30-31/2011Final LRR and Inspections 08/1-2/2011Final Payload Integration 8/4/2011Launch! 8/5-7/2011Contingency Launch

65. 2011 CoDR Testing Plan 65

66. 2011 CoDR System Level Test 66 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.

67. 2011 CoDR Mechanical Test 67 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

68. 2011 CoDR Electrical Test 68 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)

69. 2011 CoDR Software Test 69 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, Mass Spetrometer and boom)

70. 2011 CoDR Budget 70 Equipment, Materials, and TripsCost 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

71. 2011 CoDR 71 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:

72. 2011 CoDR 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. 72

73. 2011 CoDR 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 73

74. 2011 CoDR 74 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 http://stardust.jpl.nasa.gov/mission/index.html 16.Anonymous. Internet tutorial for GCMS. Retrived from: http://www.scientific.org/tutorials/articles/gcms.html

75. 2011 CoDR 75 17.Anonymous. Bioinstrumentation class (internet based) (1998). Retrieved from: http://www.gmu.edu/depts/SRIF/tutorial/gcd/gc-ms2.htm 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/wg1/221.htm http://www.grida.no/publications/other/ipcc%5Ftar/?src=/climate/ipcc_tar/wg1/221.htm 24.Direct’ evidenceforwater(H2O) inthesunlitlunarambiencefromCHACEon MIP of ChandrayaanI, R. Sridharan n, S.M.Ahmed1, Tirtha Pratim Das,P.Sreelatha, P.Pradeepkumar, Neha Naik, Gogulapati Supriya, Planetary and Space Science 58 (2010) 947–950

76. 2011 CoDR 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] 76

77. 2011 CoDR 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. 77

78. 2011 CoDR 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. 78

79. 2011 CoDR 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. 79

80. 2011 CoDR 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. 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]. 80

81. 2011 CoDR Mission Overview: Previous Research 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. 81

82. 2011 CoDR 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.comet Wild 2 82