1. Thruster and Power Processing Unit Development for an Advanced Electric Propulsion (EP) System NNC15ZCH014R Industry Day June 10, 2015 National Aeronautics and Space Administration www.nasa.gov

2. Sign-in sheets at the counter when you entered Refreshments Internet (nasaguest) Restrooms Emergency Procedures Badge Turn In Lunch One-on-one meetings Facility and in-house hardware tours Small Business Officer Meetings Microphones Welcome and Logistics 2

3. Lunch (11:30-12:30) 3

4. Agenda (1 of 3) 4 8:00 – Welcome/Logistics/Review of AgendaMike Meyer 8:15 – Comments from Space Technology Mission DirectorateAndy Petro 8:30 – Comments from the Solar Electric PropulsionMike Barrett Technology Demonstration Project Leadership 8:45 – Comments from GRC Center Director James Free 9:00 – Industry Day Objectives/Guidance for Meeting Leahmarie Koury 9:15 – Draft RFP Overview Overview of hardware deliverablesMike Meyer Contract schedule – Base and Option Periods 9:20Overview of Hardware Technical Requirements Steve Snyder Dan Herman Walter Santiago

5. Agenda (2 of 3) 5 9:50Contracting Officer’s OverviewLeahmarie Koury PricingHeather Linden EVM/IPMRBob Sefcik 10:20-10:30 Break 10:30 Overview of related NASA in-House technology maturation activities and documentation provided with Draft RFP 10:30 Power Processing UnitWalter Santiago 10:55 ThrusterRich Hofer 11:20NASA Facilities and Analytical ToolsMike Meyer Rich Hofer Ioannis Mikeledes 11:30 Lunch – GRC Cafeteria

6. Agenda (2 of 3) 6 12:30 – 4:30 One-on-one meetings (Side Room off Lobby) Tour of Facilities (Bus pick-up in front of main entrance) Small Business Officer Table (Back of the display area) 4:30-5:00 Closing Session Leahmarie Koury and Mike Meyer Review of the specific draft feedback requested Answers to question cards Review Procurement Schedule CO Guidance Communications plan from Industry day to final RFP Points of Contact

7. Thruster and Power Processing Unit Development for an Advanced Electric Propulsion (EP) System NNC15ZCH014R Programmatic Perspectives June 10, 2015 National Aeronautics and Space Administration www.nasa.gov

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9. Thruster and Power Processing Unit Development for an Advanced Electric Propulsion (EP) System NNC15ZCH014R Industry Day- Opening Ground Rules June 10, 2015 National Aeronautics and Space Administration www.nasa.gov

10. National Aeronautics and Space Administration Purpose To give Project/Center context to the procurement To give insight in to requirements and DRFP/RFP specific items To introduce primary points of contact To relay information about in-house work and available facilities To make our Office of Small Business Programs available for consultation To gather feedback/questions This is your day – make the best of it! 10

11. National Aeronautics and Space Administration Notecards and Q&A Notecards are available in the welcome area If you would like to ask a question and cannot find a good opportunity to do so, please fill out a card and drop it in the designated box. Questions will be anonymous, from the notecards, one-on-ones, and general sessions. 11

12. National Aeronautics and Space Administration ****Disclosure**** Whatever you hear today – no matter who said it – the final RFP is the controlling document, period. 12

13. Thruster and Power Processing Unit Development for an Advanced Electric Propulsion (EP) System NNC15ZCH014R Draft RFP Overview June 10, 2015 National Aeronautics and Space Administration www.nasa.gov

14. Contract Schedule 14 Three year total contract duration broken into a base and option period NASA Notional Schedule for Base and Option Period 26 month base Critical Design Review (CDR) at 20 months is decision gate to exercise Option Base continues 6 months after CDR to closeout CDR actions and to conduct/continue thruster wear test 16 month Option with 6 months overlap Offerors will propose optimal durations for their Base and Option. CY16CY17CY18CY19 Contract Effective Date CDRFinal EP String Delivery

15. Scope by Performance Period Base Period: Engineering Development Unit (EDU): one complete EP string Note: EP String: The combination of the thruster, PPU, low-pressure Xenon Flow Controller, and electrical harnesses (or power cables and command & data handling cables in the case of the EDU) integrated. A second EDU thruster for wear testing; 2 additional cathodes for wear testing, 1 additional discharge channel for embedded probe measurements Spares Long-lead materials required to meet schedule in the Option phase Option Period: 5 flight EP strings (1 qualification string, 4 flight strings) Note: EP String: The combination of the thruster, PPU, low-pressure Xenon Flow Controller, and electrical harnesses integrated. Thruster spares PPU spares Hardware Deliverables by Performance Period 15

16. Thruster and Power Processing Unit Development for an Advanced Electric Propulsion (EP) System NNC15ZCH014R Requirements Overview June 10, 2015 National Aeronautics and Space Administration www.nasa.gov

17. National Aeronautics and Space Administration ****Disclosure**** Whatever you hear today – no matter who said it – the final RFP is the controlling document, period. 17

18. EP String Definition

19. Procurement Requirements EP String will be developed to support ARRM, but it is also intended to be used for additional future missions Complete requirements are found in attachment J.1(c)  Performance  Environmental  Design  Operational  Interface Draft requirements contain  6 TBDs (5 document references, 1 crew-safe interface definition)  29 TBRs

20. EP String Requirements Total Input Power Range6.67 to 13.33 kW System Operational Lifetime8 years Thruster Lifetime10 8 N-s total impulse PPU Input Voltage95 V to 140 V Xenon Flow ControllerIndependent control and metering of anode and cathode flows

21. EP String Performance Requirements Beginning-of-life string performance System shall be continuously throttleable in discharge current at each discharge voltage, between the input powers shown EP String Total Input Power (kW) Discharge Voltage (V)Thrust (mN) 1 Mass Flow Rate (mg/s) 2 System Efficiency 3 13.3340068630.640.58 13.3360058922.810.57 13.3370055320.360.56 13.3380052618.520.56 10.0030056229.690.53 10.0040052124.300.56 10.0050048220.890.56 10.0060044618.310.54 10.0070041316.170.53 10.0080034212.880.45 6.6730038621.650.52 6.6740034217.550.50 6.6750031114.830.49 6.6760025411.450.42 6.677002429.990.44 1 Thrust shown here is Current Best Estimate minus experimental uncertainty. 2 Mass flow rate shown here is Current Best Estimate plus experimental uncertainty. 3 System Efficiency is shown here for information only (it is calculated directly from the other parameters).

22. EP String Performance Chart

23. National Aeronautics and Space Administration www.nasa.gov Thruster and Power Processing Unit Development for an Advanced Electric Propulsion (EP) System NNC15ZCH014R June 10, 2015 Power Processing Unit (PPU) Requirements Description

24. NNC15ZCH014R: PPU Requirements Description Power Processor Unit (PPU) requirements are located in Draft RFP Attachment: J.1 (C) Electric Propulsion String Requirement Document. Captures the PPU subsystem requirements to afford successful operations within the Electric Propulsion (EP) string and compatibility with the spacecraft bus. PPU performance capabilities will rely on Table 3-1: Thruster System Performance of attachment J.1(C) The PPU requirements covers  Performance  Environment  Operating Modes  Mechanical Design Requirements  Electrical Design Requirements  Mass, Volume  Mechanical and Electrical Interfaces with potential vehicle  EEE Parts  Thermal Interface Offeror’s PPU Design Solution shall meet all PPU requirements

25. NNC15ZCH014R: PPU Requirements List 3.4 PPU Requirements 3.4.1PPU Performance  Maximum Input Power 3.4.2PPU Environments  PPU Baseplate Mounting Temperature  PPU Thermal - Non-Operating Temperature Limits  PPU Thermal performance  PPU Single-Event Effects  PPU Single-Event Effects Actions 3.4.3PPU Operational  PPU Automatic Operation  PPU Operating Modes 3.4.4PPU Mechanical Design  PPU Resonant Frequency  PPU Interchangeability

26. NNC15ZCH014R: PPU Requirements List 3.4.5PPU Electrical Design  PPU Input Voltage, High-Voltage Bus Nominal  PPU Input Voltage, High-Voltage Bus Off-Nominal for 1.8 AU  PPU Input Voltage, High-Voltage Bus Non-Operational from Eclipse  PPU Input Voltage, Low-Voltage Bus  PPU Low Voltage Max Power  PPU Magnet Supply Output Polarity Reversal  PPU Undervoltage Protection – High Voltage  PPU Undervoltage Protection – Low Voltage  PPU Overvoltage Protection – High Voltage  PPU Overvoltage Protection – Low Voltage  PPU Analog Telemetry Sensors  PPU Status Flags  PPU Digital Enables  PPU Analog Set-points  PPU Telemetry  PPU Electrical Filter  PPU - XFC Interface – Power, Control and Telemetry  PPU Fault Protection  PPU Distribution Wiring  PPU Input Bus Isolation  PPU Output Isolation

27. NNC15ZCH014R: PPU Requirements List 3.4.6PPU Parts, Materials, and Processes  Electronic, Electrical, Electromechanical (EEE) Parts  Parts Derating 3.6.1Loads, Structural, and Mechanical Requirements  PPU Volume  PPU Mass  PPU Mounting Surface  PPU Baseplate Finish  PPU Connection Plate 3.6.5 Thermal Interface  PPU Thermal Power Dissipation  PPU Maximum Power Dissipation  PPU Maximum Heat Flux

28. National Aeronautics and Space Administration www.nasa.gov Thruster and Power Processing Unit Development for an Advanced Electric Propulsion (EP) System NNC15ZCH014R June 10, 2015 Thruster Requirements Description

29. NNC15ZCH014R: Thruster Requirements Description Captures the thruster requirements to afford successful operations within the Electric Propulsion (EP) string and compatibility with the spacecraft bus. Requirements as defined in the document are derived from the top-down mission requirements and conceptual vehicle compatibility. Performance capabilities will rely on Table 3-1: Thruster System Performance of attachment J.1 (C) Electric Propulsion String Requirement Document The thruster requirements covers  Performance  Environments  Design Requirements  Mechanical Design Requirements  Electrical Design Requirements  Mass, Volume  Mechanical Interface Requirements Offeror’s thruster Design Solution shall meet all thruster requirements

30. NNC15ZCH014R: Thruster Requirements List 3.3 Thruster Requirements 3.3.1Thruster Performance  Thruster Life Time  Thrust Vector  Thrust Accuracy 3.3.2Thruster Environments  Thruster Thermal 3.3.3Thruster Design  Backsputter Resistance, Voltage Standoff  Backsputter Resistance, Thermal Properties

31. NNC15ZCH014R: Thruster Requirements List 3.3.4Thruster Mechanical Design  Resonant Frequency  Covers  Interchangeability  Alignment  Neutral Flow Uniformity  Magnetic Field Measurement Provisions 3.3.5Thruster Electrical Design  Isolation  Grounding  Harness  Magnetic Field Uniformity  Magnetic Circuit Response

32. NNC15ZCH014R: Thruster Requirements List 3.6.1Loads, Structural, and Mechanical Requirements  Thruster Volume  Thruster Mass  Thruster Radiator Mass  Thruster High Voltage Harness Mass  Thruster Mounting Surface  Thruster Connections, Electrical and Fluid  Thruster Propellant Lines  Thruster Interfaces 3.6.3 Environmental Control Requirements  Thruster Shock  Thruster Random Vibration  Environmental Testing

33. NNC15ZCH014R: Thruster Requirements List 3.6.4Gases and Fluids Requirements  Propellant Fluid  Alternate Fluids and Gases

34. National Aeronautics and Space Administration www.nasa.gov Thruster and Power Processing Unit Development for an Advanced Electric Propulsion (EP) System NNC15ZCH014R June 10, 2015 Xenon Flow Controller (XFC) Requirements Description

35. NNC15ZCH014R: XFC Requirements Description Captures the Xenon Flow Controller (SFC) main requirements to afford successful operations within the Electric Propulsion (EP) string and compatibility with the spacecraft bus. Requirements as defined in the document are derived from the top-down mission requirements and conceptual vehicle compatibility. Performance capabilities will rely on Table 3-1: Thruster System Performance of attachment J.1 (C) Electric Propulsion String Requirement Document The XFC requirements covers  Performance  Environments  Design Requirements  Mechanical Design Requirements  Gases and Fluids Requirements  Mass, Volume  Mechanical Interface Requirements Offeror’s Xenon Flow Controller Design Solution shall meet all XFC requirements

36. NNC15ZCH014R: XFC Requirements List 3.5 Xenon Flow Controller (XFC) Requirements 3.5.1XFC Performance  Flow Control Independence  Flow Metering  Inlet Pressure  Flow Control Accuracy  Flow Uncertainty  Flow Throttle Response 3.5.2XFC Environments  XFC Thermal, Operating and Non-operating  XFC Thermal Design 3.5.3XFC Design  XFC Marking, Flow Direction

37. NNC15ZCH014R: XFC Requirements List 3.5.4XFC Mechanical Design  Resonant Frequency  Internal Leakage  External Leakage  Interchangeability  Flow Isolation 3.6.1Loads, Structural, and Mechanical Requirements  XFC Volume  XFC Mass  XFC Mounting Surface  XFC Connections, Electrical and Fluid  XFC Propellant Lines

38. NNC15ZCH014R: XFC Requirements List 3.6.3 Environmental Control Requirements  XFC Shock  XFC Random Vibration  Environmental Testing 3.6.4Gases and Fluids Requirements  Propellant Fluid  Alternate Fluids and Gases

39. Thruster and Power Processing Unit Development for an Advanced Electric Propulsion (EP) System NNC15ZCH014R DFP/RFP Specific Procurement Slides Industry Day Presentation June 10, 2015 National Aeronautics and Space Administration www.nasa.gov

40. National Aeronautics and Space Administration 40 Government Insight/Oversight The Government expects to have a close partnership with the contractor team through the development, modeling, test and production of the thruster string. The Contractor shall propose an operational plan that will allow for government participation throughout the contract. The Contractor shall provide adequate reporting to allow government participation in the implementation of contracted activities and technical decision-making. The Contractor shall identify cost control measures as part of the design process. The Contractor shall document the proposed processes and methods of Government participation in the Project Management Plan, DRD 01.001, as part of the Communication Plan. This baseline plan will be delivered with the proposal and the pages do NOT count towards the 85 page Mission Suitability limit.

41. National Aeronautics and Space Administration 41 Government Insight/Oversight (cont.)

42. National Aeronautics and Space Administration 42 Performance Fee Incentive Contract Specific Clause Language Clause H.11

43. National Aeronautics and Space Administration Performance Fee Incentive (cont.) 43 Table 1. Incentive Requirements Performance Incentive Description Method of MeasureTimelineIncentive AvailableNotes System EfficiencySystem efficiency is calculated, consistent with references 1 -4, based on measured data and instrumentation uncertainty. Selected test conditions are specified below. All measurements will be conducted during hot- fire testing in NASA facility VF-5. Incentive A: EM unit measured performance based on test data reports and CDR presentation. Incentive B: Following acceptance by NASA of test data report for successful Qualification Unit Testing. Tier I and Tier II incentives are cumulative. Maximum value of incentive A is $500K. Maximum Value of incentive B is $500K. The efficiency criteria at both the 2000 second specific impulse and 3000 second specific impulse operating points must be met to qualify for either Tier I or Tier II, as defined in the table 2 below. Maximum available incentive for overall efficiency is $1M. CDR efficiency incentive (A) is only avaialble at CDR, and not available at Qualification testing incentive (B). Early Delivery of Flight Electric Propulsion String Sucessful System Acceptace Review following final flight EP string delivery. 60 to 70 calendar days prior to contract required 36 month delivery $1M

44. National Aeronautics and Space Administration Performance Fee Incentive (cont.) 44

45. National Aeronautics and Space Administration Performance Fee Incentive (cont.) 45 Operating conditionSystem Efficiency Requirement Tier I incentive ($250k) Tier II Incentive ($250k Additional) Total system power = 13.33 kW, Thruster discharge voltage = 800.0 V ≥ 56.0% after subtracting uncertainty ≥ 57.0% after subtracting uncertainty ≥ 58.0% after subtracting uncertainty Total system power = 10.00 kW, Thruster discharge voltage = 300.0 V ≥ 53.0% after subtracting uncertainty ≥ 54.0% after subtracting uncertainty ≥ 55.0% after subtracting uncertainty

46. National Aeronautics and Space Administration 46 JPL For the purposes of this procurement, JPL is considered on the NASA Government team. Therefore they are unavailable as potential subcontractors. When the RFP refers to “NASA” JPL is included.

47. National Aeronautics and Space Administration NAICS Code/Size Standard NAICS code selected was 541712 Research and Development in the Physical, Engineering, and Life Sciences (except Biotechnology) Due to Space Flight Hardware being procured, the 1000 person exception will be used. NAICS Code/Size Standard 47

48. National Aeronautics and Space Administration Subcontract Plan Goals 48 Small Businesses (SB) 10.40% Small Disadvantaged Business Concerns (SDB) 2% Women Owned Small Business Concerns (WOSB) 2% Historically Black Colleges and Universities (HBCU)/Minority Institutions (MI) 0.5% HUBZone Small Business Concerns (HUBZone) 1% Veteran Owned Small Business Concerns (VOSB) 1.5% Service-Disabled Veteran-Owned Small Business Concerns (SDVOSB) 1% Small Business subcontracting goals are as follows:

49. National Aeronautics and Space Administration Page Counts (L.16 1852.215-81 Proposal Page Limitations (FEB 1998)) Source Selection Information - See FAR 2.101 and 3.104 49 Volume Number and Title Page Limit I - Mission Suitability*85 II - Past Performance30 III – CostN/A * 1852.245–80 Government Property Management Information. (JANUARY 2011). The content of these plans and information will not be counted in the 85 page Mission Suitability page limit. However, the submitted pages for these documents should be concise and not overly burdensome. * Per L.22 (PM1.2) Communication Plan – pages will NOT be counted as part of the overall Mission Suitability 85 page limit. However, the submitted pages for these documents should be concise and not overly burdensome.

50. National Aeronautics and Space Administration 50 Past Performance Three tier approach to Past Performance: Tier I – Volume II submittal (30 pages) Tier II – PPQ responses (and rebuttals if needed) Tier III – PPIRS, CPARS, and outside information database research Relevancy when using time as a consideration - The Government will evaluate contracts, subcontracts and projects within the last fifteen years. However, the Government gives higher weighting to contracts, subcontracts or projects within the last five years. Major subcontractors, for the purpose of Past Performance are any contractors performing $1M or more of the total contract effort. Jason Siewert is the Past Performance POC – for delivery of PPQs Past Performance Volume II due date, as well as PPQ due date will be earlier than Mission Suitability and Price Volumes – stay tuned for final RFP for dates.

51. National Aeronautics and Space Administration Pricing Follow RFP instructions Cost realism analysis will be conducted Price evaluations will include –Status of Offerors’ business systems –Total proposed price consisting of the base effort and one option –Evaluation of the proposed fee rates Source Selection Information - See FAR 2.101 and 3.104 51

52. National Aeronautics and Space Administration Pricing Flexible base/option periods –Base period ends at Critical Design Review –Option 1 begins at flight hardware production –Total Base and Option periods combined must no more than 36 months –Base and Option periods may overlap based on the offeror’ s methodology Pricing templates broken out by six work areas –Project Management (PM), Systems Engineering & Integration (SE&I), Safety Mission Assurance (SMA), Power Processing Unit (PPU), Thruster, and Flow Controller. Source Selection Information - See FAR 2.101 and 3.104 52

53. National Aeronautics and Space Administration Pricing Schedule incentive- 3 incentives totaling $2M –Include incentive payment dates in your proposal Base at CDR Option 1 at Quality Engine Test Option 1 at Delivery Pricing disposal/freight/shipping –These costs will be removed as part of a probable cost adjustment for the successful Offeror. –Do not add fee to shipping/freight –Government will not pay for Work in process (hardware) Shipping cost for WIP Source Selection Information - See FAR 2.101 and 3.104 53

54. National Aeronautics and Space Administration www.nasa.gov Thruster and Power Processing Unit Development for an Advanced Electric Propulsion (EP) System NNC15ZCH014R June 10, 2015 Financial Reporting/Earned Value Management

55. National Aeronautics and Space Administration www.nasa.gov Contractor Financial Management Report (533M) The standard contract clause for implementing NASA contractor financial management reporting as set forth in NFS 1852.242-73, NASA Contractor Financial Management Reporting, is not included in the RFP. A Monthly Contractor Financial Management Report (533M) is not required. In lieu of the 533M report, the Integrated Program Management Report (IPMR) for earned value and integrated master schedule reporting has been tailored to meet financial reporting needs.

56. National Aeronautics and Space Administration www.nasa.gov Earned Value Management The standard contract clause for implementing NASA earned value management reporting as set forth in NFS 1852.234-2 Earned Value Management System, is included in the RFP (I.138.) (As well as provision L.11 1852.234-1 Notice of Earned Value Management System. (NOV 2006) CPR and IMS data requirements identified in NFS 1852.234-2(a)(2) are replaced by the Integrated Program Management Report (IPMR) per Procurement Information Circular (PIC) 15-06 (April 2015), Guidance on the Integrated Program Management Report for Earned Value Management: “Contracting Officers shall include a DRD/CDRL in the solicitation and resultant contract to describe the specific reporting requirements of the IPMR when Earned Value Management Systems is required in accordance with NFS 1834.201. ”

57. National Aeronautics and Space Administration www.nasa.gov Integrated Program Management Report (IPMR) NASA has adopted the use of the IPMR (per DID-MGMT-81861) to replace the Contract Performance Report (CPR) and the Integrated Master Schedule (IMS) and will use the IPMR to satisfy financial reporting requirements for this procurement. Data Requirements Description (DRD) Guidance –The Base and the Option, if exercised, shall have separate IPMRs –Delivery of Formats 1, 3, 5, 6, and 7 –Preliminary IMS (Format 6) with proposal. First submission of all required Formats within 12 working days after the end of the second full accounting period following ATP –Subsequent submission of all Formats monthly by the 12 th working day after the close of the contractor’s accounting month –IPMR formats shall be completed according to the instructions outlined in DI-MGMT-81861 except as modified in the DRD

58. National Aeronautics and Space Administration www.nasa.gov IPMR Tailoring for Financial Reporting Format 1 – Work Breakdown Structure –Provide reporting at WBS level 3 or at the cost account, whichever is lower –Capital equipment and long lead items, if any, shall be their own separate control accounts. –Tailoring: For each reporting element, provide elements of cost (direct labor, material, overhead, etc.) and direct labor hours. Include G&A and COM as add. –Format 1 – Section 8.a example data:

59. National Aeronautics and Space Administration www.nasa.gov IPMR Tailoring for Financial Reporting Format 7 – History and Forecast File –Format 7 is required at the same level as Format 1 reporting –Tailoring: Provided monthly instead of yearly with emphasis on getting accurate forecasts for the next two months estimate to complete (ETC) to replace 533 estimate –Format 7 – Contractor format of the following example data:

60. Thruster and Power Processing Unit Development for an Advanced Electric Propulsion (EP) System NNC15ZCH014R NASA In-House Technology Maturation Activities SWITCH PRESNTATIONS June 10, 2015 National Aeronautics and Space Administration www.nasa.gov

61. Thruster and Power Processing Unit Development for an Advanced Electric Propulsion (EP) System NNC15ZCH014R NASA Facilities and Analytical tools June 10, 2015 National Aeronautics and Space Administration www.nasa.gov

62. 62 Use of NASA Facilities Contractor is responsible for all testing to include interface, environmental and requirements verification NASA facilities shall be proposed for use by the Offeror for any testing involving hot-firing of a thruster at the component or system level –Facility options include VF-5, VF-6, VF-12 and VF-16 at GRC and the Owens Chamber at JPL Proposals will not include cost of operating these large scale vacuum test facilities (will be GFE) –NASA labor, utilities and propellant Contractor will include their costs to support testing and all hardware and special test equipment not listed in attachment J.1(d) Proposals shall include a detailed “Test Strategy” –Section L&M, TA1.7, TA2.8, TA3.5 –Appropriateness and efficiency of test plans (including rationale) and will be evaluated

63. Thruster and Power Processing Unit Development for an Advanced Electric Propulsion (EP) System NNC15ZCH014R Facilities, Diagnostics, and Modeling Capabilities for High-Power Electric Thrusters at the Jet Propulsion Laboratory June 10, 2015 National Aeronautics and Space Administration www.nasa.gov

64. Jet Propulsion Laboratory California Institute of Technology Owens Chamber 64 Owens Chamber at JPL –3 m diameter X 10 m long –71 m 3 volume –Graphite lined interior, stainless steel walls –230,000 L/s pumping speed –Control systems for unattended operation –Digitally-controlled mass flow controllers with Bios Dry-cal for feed system calibration –Auxiliary xenon feed system for backpressure control Multiple probe- and optically-based diagnostics for assessing performance, stability, thermal, and wear characteristics –Thrust stand –Thrust vector probe –Laser Induced Fluorescence (LIF) ion velocimetry –Current probes for measuring discharge voltage/current oscillations –Thermocouples & infrared thermal camera –Far-field ExB, RPA, ESA, combined ESA-ExB, Faraday, & emissive probes –Near-field, high-speed ion current density probe, emissive probes, and Langmuir probes (j i, φ, T e ) –Flush-mounted wall probes (j i, φ, T e ) –High-speed video (FASTCAM) –Quartz Crystal Microbalance (QCM) for measuring carbon backsputter rate –Residual Gas Analyzer (RGA) –Xenon-calibrated ionization gauges mounted at thruster exit plane Far-field view Near-field view

65. Jet Propulsion Laboratory California Institute of Technology JPL OrCa2D and Hall2De Scientific Codes Orificed Cathode (OrCa2D) Code - Used to simulate the plasma and erosion processes in hollow cathodes Plasma power deposition are used as inputs for thermal modeling. May be licensed at no cost for research funded by the US government to commercial and academic institutions through the California Institute of Technology. Hall2De Code - Used to simulate the plasma and erosion processes in Hall thrusters, including the plume region for spacecraft integration studies. Plasma power deposition are used as inputs for thermal modeling. May be licensed at no cost for research funded by the US government to commercial and academic institutions through the California Institute of Technology. 65 Plume simulations Discharge Chamber

66. Jet Propulsion Laboratory California Institute of Technology Axial beam Radial beam Collection optics Feedthru flange Translation stages Laser and laser diagnostics Vacuum setup Airside setup Laser Induced Fluorescence (LIF) and Thruster Inspection Systems Axial & Radial Ion Velocities Optical Bench Surface profilometry (CMM & Nanovea) –Coordinate measuring machine (30 um resolution) –Nanovea ST-400 non-contact surface profiler (1 um resolution, 20 mm depth-of-field, 3-axis motion control) Surface profilometry (CMM & Nanovea) –Coordinate measuring machine (30 um resolution) –Nanovea ST-400 non-contact surface profiler (1 um resolution, 20 mm depth-of-field, 3-axis motion control)

67. Jet Propulsion Laboratory California Institute of Technology Environmental Testing Thruster thermal vacuum testing can be accomplished in multiple large vacuum chambers at JPL and GRC with the NASA GRC large thermal shroud for testing over temperatures of -140 to >250 degrees C. 67

68. Lunch Break – Resume at 12:30 National Aeronautics and Space Administration www.nasa.gov

69. Thruster and Power Processing Unit Development for an Advanced Electric Propulsion (EP) System NNC15ZCH014R Industry Day Closing Points June 10, 2015 National Aeronautics and Space Administration www.nasa.gov

70. National Aeronautics and Space Administration 7 Question Areas to Industry (1 of 4) NASA Insight/Oversight - Communication Plan. Is the required interaction clear? Is there enough data provided to propose a comprehensive Communication Plan? What in addition should be provided? Testing Strategy - Is the division between Offeror/Government facilities to be used clear? Are there any alternative suggestions? Is there enough data provided to propose a comprehensive Testing Strategy?

71. National Aeronautics and Space Administration 7 Question Areas to Industry (2 of 4) Performance Incentive Fee - Are the incentives clear? Are there any alternative suggestions for incentivizing technical performance? Is two months a reasonable expectation for an early delivery incentive? Assured Supply - Is the Government's intent clear for evaluating assured supply favorably (attributes that minimize future government investment/cost to assure availability)? Are there suggestions on how to measure assured supply abilities?

72. National Aeronautics and Space Administration 7 Question Areas to Industry (3 of 4) 533M-Q/EVM - Is the Government's intent clear that the 533M/Q requirement is intended to be removed, that EVMs templates with slight modifications are to be used in lieu of this requirement? Does that streamline the process, or are there different/additional recommendations in this area? Internal R&D - How far are the Government's EP goals from the commercial sector? How could we modify our requirements to more closely align the capabilities of these EP Strings with your commercial application needs?

73. National Aeronautics and Space Administration 7 Question Areas to Industry (4 of 4) Overall comments/suggestions - Do the due dates and page counts seem adequate? Are there contract clauses that raise concern? Are there DRD suggestions for streamlining? Are any of the requirements overly constraining? Could the requirements be streamlined while still meeting the primary goals?

74. National Aeronautics and Space Administration DRAFT SCHEDULE EventDate Draft RFP ReleaseMay 21, 2015 Industry ConferenceJune 10, 2015 Comments on Draft DueJune 22, 2015 Final RFP ReleaseJuly 14, 2015 Proposal Due DateAugust 28, 2015 Contract AwardMarch 29, 2016 Draft Procurement Schedule

75. National Aeronautics and Space Administration ****Disclosure**** Whatever you hear today – no matter who said it – the final RFP is the controlling document, period. 75

76. National Aeronautics and Space Administration Communication Process Industry Day through Final RFP Q&As from today will be gathered and posted One additional team meeting (per Offeror team) is available between June 10 th release of Final RFP. After the Final RFP is published, the blackout period is in effect. All communication must occur in writing to the Contracting Officer ONLY. 76

77. National Aeronautics and Space Administration Points of Contact: Contracting Officer: Leahmarie Koury Leahmarie.Koury@nasa.gov Technical POC/Lead: Michael Meyer Michael.L.Meyer@nasa.gov 77

78. National Aeronautics and Space Administration Your Title Here 78 SignOffPage

79. Jet Propulsion Laboratory California Institute of Technology BACKUP 79

80. Jet Propulsion Laboratory California Institute of Technology JPL OrCa2D and Hall2De Scientific Codes Orificed Cathode (OrCa2D) Code –Used to simulate the plasma and erosion processes in hollow cathodes. Plasma power deposition are used as inputs for thermal modeling. –Solves the conservation laws for the partially-ionized gas in hollow cathodes, in 2-D axisymmetric geometry Electrons: Ohm’s law and time-dependent energy equation based on continuum approximation. Ions: time-dependent continuity and inviscid momentum equations based on continuum approximation. Neutrals: time-dependent full Navier-Stokes equations in the cathode interior transitioning to collision-less gas in exterior. Time-dependent energy equation solved for the heavy species (ions & neutrals) Accounts for applied magnetic field. Uses magnetic field aligned mesh generator. Electrode boundary conditions including electron emission from insert. Large computational region encompassing cathode interior (emitter region), cathode plate and keeper orifice regions, near-plume and anode regions. –Started development at JPL in 2004 Written in Fortran90 using the Intel Visual Fortran Composer XE 12.0 compilers (Intel Parallel Studio XE 2011 or higher) and the Intel Math Kernel Library (MKL) 10.3 (or higher). Makes use of Intel’s parallel sparse matrix solvers (PARDISO) to take advantage of multi-core multi-thread processors. –May be licensed at no cost for research funded by the US government to commercial and academic institutions through the California Institute of Technology. –References Mikellides, I. G., Katz, I., Goebel, D. M., and Polk, J. E., "Hollow Cathode Theory and Experiment, II. A Two-Dimensional Theoretical Model of the Emitter Region," Journal of Applied Physics, Vol. 98, No. 11, 2005, pp. 113303 (1-14). Mikellides, I. G., Katz, I., Goebel, D. M., Jameson, K. K., and Polk, J. E., "Wear Mechanisms in Electron Sources for Ion Propulsion, II: Discharge Hollow Cathode," Journal of Propulsion and Power, Vol. 24, No. 4, 2008, pp. 866-879. 80

81. Jet Propulsion Laboratory California Institute of Technology JPL OrCa2D and Hall2De Scientific Codes Hall2De Code –Used to simulate the plasma and erosion processes in Hall thrusters, including the plume region for spacecraft integration studies. Plasma power deposition are used as inputs for thermal modeling. –Solves the conservation laws for the partially-ionized gas in Hall thrusters, in 2-D axisymmetric geometry Magnetized electrons: anisotropic Ohm’s law and time-dependent energy equation. No assumptions made regarding isothermal properties of electrons along lines of force. Un-magnetized ions: time-dependent continuity and inviscid momentum equations based on continuum approximation. Neutrals: Collision-less gas – solution obtained using view-factors. Numerical approach for all species is inherently free of statistical noise since particle methods are not used. Uses magnetic field aligned mesh to allow for highly-anisotropic solution to the equations for the electrons with minimal numerical diffusion. Insulator and conducting boundary conditions. Large computational region allowing for self-consistent incorporation of cathode boundary. –Started development at JPL in 2009. Core code structure the same as that of OrCa2D. Many of the Hall2De algorithms also taken from OrCa2D. Written in Fortran90 using the Intel Visual Fortran Composer XE 12.0 compilers (Intel Parallel Studio XE 2011 or higher) and the Intel Math Kernel Library (MKL) 10.3 (or higher). Makes use of Intel’s parallel sparse matrix solvers (PARDISO) to take advantage of multi-core multi-thread processors. –May be licensed at no cost for research funded by the US government to commercial and academic institutions through the California Institute of Technology –References Mikellides, I. G., and Katz, I., "Simulation of Hall-effect Plasma Accelerators on a Magnetic-field-aligned Mesh," Physical Review E, Vol. 86, No. 4, 2012, pp. 046703 (1-17). Katz, I., and Mikellides, I. G., "Neutral Gas Free Molecular Flow Algorithm Including Ionization and Walls for Use in Plasma Simulations," Journal of Computational Physics, Vol. 230, No. 4, 2011, pp. 1454-1464. 81

82. Jet Propulsion Laboratory California Institute of Technology Other Diagnostics & References Thrust stand –Hofer, R. R. and Anderson, J. R., "Finite Pressure Effects in Magnetically Shielded Hall Thrusters," AIAA Paper 2014-3709, July 2014. High-speed plasma probes –Hofer, R. R., Goebel, D. M., Mikellides, I. G., and Katz, I., "Magnetic Shielding of a Laboratory Hall Thruster Part II: Experiments," Journal of Applied Physics 115, 043303 (2014). –Jorns, B., Hofer, R. R., and Mikellides, I. G., "Power Dependence of the Electron Mobility Profile in a Hall Thruster," AIAA Paper 2014-3620, July 2014. Far-field plume probes (Faraday, Langmuir, ExB, RPA) –Hofer, R. R., Goebel, D. M., Mikellides, I. G., and Katz, I., "Design of a Laboratory Hall Thruster with Magnetically Shielded Channel Walls, Phase II: Experiments," AIAA-2012-3788, July 2012. Surface profilometry (CMM and Nanovea) –Coordinate measuring machine (30 um resolution) Hofer, R. R., Jorns, B. A., Polk, J. E., Mikellides, I. G., and Snyder, J. S., "Wear Test of a Magnetically Shielded Hall Thruster at 3000 Seconds Specific Impulse," Presented at the 33rd International Electric Propulsion Conference, IEPC-2013-033, Washington, DC, Oct 6-10, 2013. –Nanovea ST-400 non-contact surface profiler (1 um resolution, 20 mm depth-of-field, 3-axis motion control) Sekerak, M., Hofer, R. R., Polk, J. E., Jorns, B. A., and Mikellides, I. G., "Wear Testing of a Magnetically Shielded Hall Thruster at 2000 S Specific Impulse," Presented at the 34th International Electric Propulsion Conference, IEPC-2015-155, Kobe, Japan, July 4-10, 2015. FLIR Infrared Camera –Hofer, R. R., Jorns, B. A., Polk, J. E., Mikellides, I. G., and Snyder, J. S., "Wear Test of a Magnetically Shielded Hall Thruster at 3000 Seconds Specific Impulse," Presented at the 33rd International Electric Propulsion Conference, IEPC-2013-033, Washington, DC, Oct 6-10, 2013. FASTCAM –Jorns, B. A. and Hofer, R. R., "Plasma Oscillations in a 6-kW Magnetically Shielded Hall Thruster," Physics of Plasmas 21, 5, 053512 (2014). 3-axis Gaussmeter (Lakeshore 460) with automated data acquisition and motion control 82

83. Industry Day Attendance List 6/10/15 83 Aerojet RocketydyneJackson, Jerome Aerojet RocketydyneMyers, Roger Aerojet RocketydyneHoskins, William A Aerojet RocketydyneLu, Cheng-Yi Aerojet RocketydyneSpores, Ron Zin Technologies IncJohanson, Michael R Zin Technologies IncChmiel, Alan Zin Technologies IncBontempo, Jim Zin Technologies IncGrodsinsky, Carlos BoeingCarreno, Adriel BoeingBienhoff, Dallas BoeingHairapetian, Garnick BoeingDiep, Ba BoeingElsperman, Michael SSLvan Ommering, Gerrit SSLLord, Peter W. SSLTilley, Scott SSLLiang, Ray Busek Co. Inc.Hruby, Vladimir Busek Co. Inc.Williams, Wallace D. Busek Co. Inc.Pote, Bruce Moog Inc.Chaves, Marc Moog Inc.King, Paul Moog Inc.Illig, Mitchell Ball Aerospace, Inc.Deining, William Sierra Lobo, Inc.Yeckley, Alex