PPE_Studies_NextSTEP-2_BAA_App_C_Final_RFP.pdf

National Aeronautics and Space Administration NASA Headquarters Human Exploration and Operations Mission Directorate

300 E ST SW

Washington, D.C. 20546-0001

Next Space Technologies for Exploration Partnerships -2

(NextSTEP-2)

Omnibus Broad Agency Announcement(BAA)

Appendix C: Power and Propulsion Element (PPE) Studies

NNH16ZCQ001K-PPE

Draft Originally Issued: August 11, 2017 Issue Date: August 30, 2017 (tentative)

Proposals Due: September 26, 2017 by 12:00 PM Eastern Time

NextSTEP-2 Appendix C: Power & Propulsion Element Studies

NextSTEP-2 Appendix C: PPE Studies Change Log

Version Description of Changes Date

DRAFT Appendix C released AUG 11, 2017 Appendix C draft updated and released AUG 30, 2017

Table of Contents 1 Introduction and Background

2 The Mission of the Deep Space Gateway (DSG) Power and Propulsion Element (PPE)

2.1 Objectives

3 Description of Study Topics

4 General Information

5 Eligibility Information

5.1 Eligibility of Applicants

5.2 Corporate Resources

5.3 Organizational Conflicts of Interest (OCI)

6 Proposal Submission Information

6.1 Instructions for Proposals

6.1.1 Proposal Format and Contents

6.1.2 Additional Proposal Guidance

7 Proposal Review Information

8 Award Information

9 References

Attachment A: Acronym List

Attachment B: PPE Capabilities Summary

Attachment C: Model Contract

1 Introduction and Background NASA supports public-private partnerships for achieving its strategic goals and objectives for expanding the frontiers of knowledge, capability, and opportunities in space. In fact, an important part of NASA’s strategy is to stimulate the commercial space industry while leveraging those commercial capabilities through public-private partnerships and potentially through future contracts to deliver mission capabilities at lower costs. The second Next Space Technologies for Exploration Partnerships (NextSTEP)-2 omnibus Broad Agency Announcement (BAA), NNH16ZCQ001K, solicits proposals through appendices in areas including, but not limited to:

• Studies to support mission architecture definition;

• New approaches to rapidly develop prototype systems;

• Demonstration of key capabilities;

• Validating operational concepts for future human missions beyond low-Earth orbit; and

• End-to-end design, development, test, and in-space evaluation of future flight systems.

As part of NASA’s approach for expanding human presence beyond low Earth orbit and consistent with the NASA Transition Authorization Act of 2017, a Deep Space Gateway and Transport (DSG&T) concept is being examined. A Power and Propulsion Element (PPE) would be the initial element in the Deep Space Gateway (DSG) concept and would conceptually launch as a co-manifested payload with the Orion crewed vehicle on the Space Launch System (SLS) on Exploration Mission-2 (EM-2).

This NextSTEP-2 Appendix C builds upon prior efforts in flight demonstration and mission use of advanced solar electric propulsion technologies for NASA and other potential partner applications and NextSTEP-2 partnership concept and development efforts. The mission concept activities for first use of advanced solar electric propulsion in the Asteroid Redirect Robotic Mission provides a useful common point of departure for examining requirements and concepts of operations and risk. Please refer to the following website for additional information on the Asteroid Redirect Robotic Mission: www.nasa.gov/arm

The first appendix under NextSTEP-2, Appendix A, focuses on developing deep space habitation concepts, engineering design and development, and risk reduction efforts leading to a habitation capability in cislunar space. This NextSTEP-2 Appendix C is complimentary to the efforts sought under NextSTEP-2 Appendix A on habitation, and specifically seeks proposals for areas necessitating further study in this timeframe to assist in the development of the PPE concept and approach. Note, activities performed under NextSTEP-2 Appendix A and Appendix C are distinct and separate activities. Additional information on NextSTEP-2 is available at the NextSTEP Website: www.nasa.gov/nextstep

2 The Mission of the Deep Space Gateway (DSG) Power and Propulsion Element (PPE) http://www.nasa.gov/arm http://www.nasa.gov/nextstep

The DSG concept being examined is a crew-tended spaceport in lunar orbit that would serve as a gateway to longer duration missions and enhanced capability to extend human presence. In addition to the power and propulsion functions, a PPE would host communications functions and potentially an partner provided payload or system. A complete set of PPE capability descriptions are provided for reference in Attachment B to this Appendix.

2.1 Objectives

The objectives of this solicitation are to seek proposals from industry for the conduct of studies specifically focused on the envisioned DSG PPE capabilities as stated in Attachment B of this Appendix, including areas of differences between previous architectures/configurations for 50kW-class SEP demonstration.

Specific objectives NASA would like to accomplish include:

• Identification and understanding of areas of significant potential synergies between the PPE specific capabilities and current and/or future commercially available capabilities.

This includes identification of PPE specific capabilities that may be beyond current and/or future planned commercial capabilities. This could also include a variety of topics such as but not limited to the use of advanced solar electric propulsion, innovative ideas for partnership business models including intellectual property, asset ownership, and timing of delivery of the asset and/or services to the Government.

• Evaluate and understand driving technical differences and implications between prior concepts and approaches developed under the Asteroid Redirect Robotic Mission (ARRM) and the proposed concept for the PPE, such as implications to meeting reference technical requirements and/or drivers for validating a concept of operations.

• To obtain data that supports NASA’s ability to define, derive, and validate the PPE requirements and a baseline mission concept to include identification of options and approaches to meeting PPE specific capabilities as described in Attachment B of this Appendix and for contributing reliability and verification/validation data for a PPE approach that supports a human rated DSG system.

3 Description of Study Topics

All Offerors shall provide a single proposal in response to any combination of one or more of the following study topics under one CLIN. The proposal shall identify by number the specific study topic(s) that the Offeror is responding to in their proposal. For additional reference information on the PPE capabilities, please refer to Attachment B, PPE Capabilities Summary (PPE High Level and Second Level).

The study topics are:

1. An approach for the PPE design and verification to provide the required functionality with sufficient reliability, fault protection and availability to operate as part of a human-rated system for all crewed mission phases. This could include the use of relevant data from on-orbit operation of subsystems if the PPE use case is applicable, sufficient number of units and cumulative operating have been achieved, and failure modes are sufficiently well understood to establish the confidence and margin needed for use as part of a human-rated system.

2. An approach to the use of standards, specifications, and engineering processes to assure a PPE design that cost-effectively minimizes the probability of the occurrence of failure modes through the application of selective redundancy, factors of safety, or other design margins as necessary for operation as part of a human-rated system.

3. An approach to performing propulsive orbital maintenance maneuvers for entire DSG integrated with a range of possible stack configurations.

4. An approach for PPE operation during the rendezvous and docking of crewed and uncrewed visiting vehicles including Orion with a DSG.

5. An approach for the PPE to provide a DSG with uncrewed autonomous orbit-transfer capability.

6. An approach for the design, development, and operation of a high-reliability PPE power generation and power transfer capability as part of a DSG.

7. An approach to hosting two IDSS passive interfaces and assessment for how this drives system technical risk, cost, and schedule.

8. An approach to addressing the minimal 15 year PPE operational lifetime requirement.

9. An approach to long-term autonomous operation in the cis-lunar environment including fault monitoring, detection, and handling.

10. An approach for the PPE to provide high-reliability communications for a DSG.

11. An assessment of accommodating an optical communication demonstration onboard the

PPE.

12. An assessment, including reviewing and providing comments, of NASA defined engineering design & construction standards, interoperability standards, and/or safety and mission assurance standards that may be proposed for the PPE in a human rated DSG.

13. Identification of areas of significant potential synergies between the PPE specific capabilities and both the current and future capabilities for the commercial market. This includes identification of PPE specific capabilities that may be beyond current or planned commercial capabilities. This could also include a variety of topics such as but not limited to the use of advanced solar electric propulsion and innovative ideas for partnership business models including options for potential cost share or cost contributions that addresses intellectual property, asset ownership, and timing of delivery of the asset and/or services to the Government.

14. An assessment of acquiring high power, high throughput Electric Propulsion strings as part of the commercial bus, rather than through a Government Furnished Equipment route.

15. An approach to providing accommodations of potential (international or domestic partner provided) hardware such as robotic fixtures, science and technology demonstration and utilization and other possible elements.

16. An approach to addressing ability to manage batteries charge and discharge during different eclipse durations

17. A PPE conceptual layout including identification of any potential clearance or blockage issues which may exist for the PPE.

18. An approach to PPE that is tolerant to crew exercise and implications of extended crew stay durations.

19. An approach to PPE Assembly, Integration and Test, including a description of industry practices and available data and identification of unique Government capabilities if needed.

20. An approach to extensibility and possible future PPE configurations or use of systems/subsystems for future exploration vehicles/activities.

21. An approach to providing and validating propulsive and non propulsive attitude control for a DSG with a range of possible stack configurations. Include an assessment of:

a. The integrated stack envelope mass versus the contractor’s standard payload and accommodation of the same by contractor’s bus primary structure.

b. Whether new structure is added below the existing bus structure, or if new primary structure would have to reside inside the bus.

c. Performing attitude control, orbit maintenance and orbit transfer on the integrated DSG with masses and center of mass distances different than those in the stated PPE capabilities to identify breakpoints of control authority where significant cost, risk or schedule impacts arise.

22. An assessment of transferring additional power to DSG elements during non-eclipse periods, higher than those in the stated capabilities, including the identification of transferred power levels where significant cost, risk or schedule impacts arise.

23. An approach to PPE avionics, time-triggered Gigabit Ethernet, internal modular avionics & software including an assessment of utilizing Core Flight Systems (CFS) software on the PPE and/or to use CFS as a software interface to the rest of DSG. Please refer to the following for more information: http://coreflightsystem.org/

4 General Information

• Agency: National Aeronautics and Space Administration

• Announcement Title: NextSTEP-2 BAA, Appendix C: Deep Space Gateway and

Transport (DSG&T) Power and Propulsion Element (PPE) Studies, RFP

80GRC017R0025

• Responsible Headquarters Office:

• Human Exploration and Operations Mission Directorate NASA Headquarters Washington, DC 20546

• Selection Official:

• Michele Gates, Director for the Power and Propulsion Element for the Human Exploration and Operations Mission Directorate

• Responsible Implementing Center:

http://coreflightsystem.org/

• NASA Glenn Research Center 21000 Brookpark Road Cleveland, OH 44235

• Points of Contact:

o Contracting Officer:

Richard Amiot, Contracting Officer Glenn Research Center 21000 Brookpark Road Cleveland, Ohio 44135 Email: Richard.W.Amiot@nasa.gov o Technical Point of Contact:

Michael Barrett

Manager, Power and Propulsion Element NASA Glenn Research Center

21000 Brookpark Road Cleveland, Ohio 44135

Email: Michael.J.Barrett@nasa.gov

• Inquiries: There will be an opportunity to submit written questions on the final release of

Appendix C. The questions shall not contain proprietary information nor require proprietary information in the response. NASA will not provide evaluations, opinions, or recommendations regarding any suggested approaches or concepts.

o All questions shall be directed to the Contracting Officer, Richard.W.Amiot@nasa.gov, by September 11, 2017, no later than 5:00pm Eastern Time.

o Inquiries shall identify the Company Name and BAA number in the subject field of e-mails.

• Proposals Due: The Offeror’s proposals must be submitted electronically to the following email: GRC-PPE-Procurement@mail.nasa.gov in accordance with instructions no later than September 26, 2017, no later than 12:00pm Eastern Time.

5 Eligibility Information

5.1 Eligibility of Applicants

This Appendix is open to non-Government U.S. institutions (companies, universities, nonprofit organizations) only. NASA civil servants, Jet Propulsion Laboratory (JPL) employees, national laboratories, and Federally Funded Research and Development Centers (FFRDCs) shall not be proposed as a Prime Contractor on any effort associated with this announcement but may participate as a team member. Other eligibility information is also included in the omnibus portion of this BAA.

mailto:Richard.W.Amiot@nasa.gov mailto:Michael.J.Barrett@nasa.gov mailto:GRC-PPE-Procurement@mail.nasa.gov

5.2 Corporate Resources

Offerors are required to show a minimum corporate contribution of 20% (10% for a Small Business as defined by the SBIR small business eligibility, as posted here:

http://sbir.nasa.gov/content/nasa-sbirsttr-program-definitions ) made within the last year, that is directly relevant to the proposed effort for eligibility to participate in this solicitation effort. The overall effort is defined as the combination of corporate contribution and government resources invested in the proposed effort. 50% of the Corporate Contribution must be invested coincident with the period of performance of this effort. Offerors shall describe how they intend to meet this eligibility requirement in Section II of the proposal. Additional information on corporate resources is contained in the omnibus portion of this BAA.

Corporate contribution may be in the form of direct labor, travel, consumables or other in-kind contributions. Also, other reasonable forms of corporate contribution may include investments in special facilities or equipment, tooling or other prior private investment, and internally funded technology maturation such as Independent Research and Development (IRAD) are deemed acceptable for this effort. For this BAA, state and local government contributions may be included with private corporate resources.

The value of participation by federally funded Government funded participants and/or the use of federal government facilities shall be added to the price to the Government for determining whether the 20% required corporate contribution has been met.

Criteria and procedures for the allowability and allocability of cash and non-cash contributions shall be governed by FAR Parts 30 and 31, and NFS Parts 1830 and 1831. NASA reserves the right to hold due diligence discussions to make reasonable determinations regarding corporate contributions.

5.3 Organizational Conflicts of Interest (OCI)

NASA has determined that the receipt of a contract from this appendix will not constitute an OCI based on biased ground rules. An OCI based on biased ground rules could prevent the recipients from proposing on subsequent solicitations regarding the PPE. NASA based this determination on FAR Section 9.505-2 (b) (1) (iii), which provides an exception for preparing specifications or work statements. This exception applies when more than one contractor has been involved in preparing the statement of work. NASA intends to award two or more contracts for studies.

Additionally, the studies will provide valuable information for the Statement of Work, but are not to write the specifications or work statement.

6 Proposal Submission Information

6.1 Instructions for Proposals

See the omnibus BAA for general instructions. Where instructions are different, the specific instructions in this section are in addition to or supersede the general instructions in the omnibus

BAA.

http://sbir.nasa.gov/content/nasa-sbirsttr-program-definitions

6.1.1 Proposal Format and Contents

The proposal format and content requirements as outlined in this section below are specific to this appendix and supersede the instructions in the omnibus BAA. The required sections of the proposal must be submitted as one searchable, unlocked PDF file with edit permission enabled.

Applicants must comply with the format and page limit requirements as described in this Appendix.

There is a 10mB limit for the electronic media file size for proposals. Only attachments that are specifically requested in this Appendix should be submitted. The requested proposal electronic naming convention is as follows: Company Name - NNH16ZCQ001K-PPE

Requirements in this Appendix supersede any requirements in the NASA Guidebook for Proposers or in the omnibus BAA. If any requirements conflict between the omnibus solicitation, Appendix C takes precedence.

Pages in excess of the page limits for each section will not be evaluated. A page is defined as one side of a sheet, 8 1/2" x 11" with at least one-inch margins on all sides, using not smaller than 12-point font, with the exception of tables and figures, which may use 8-point font. Offerors may submit foldout pages (11” x 17” or smaller) however the fold out will be considered as two (2) 8 ½” x 11” pages. Any font that the Government determines smaller than this amount will not be evaluated.

Applicants shall use the email: GRC-PPE-Procurement@mail.nasa.gov for proposal submissions. The e-mail submission shall identify the email as Company Name - NNH16ZCQ001K-PPE Proposal Submission in the subject field of the e-mail.

Proposals received after September 26, 2017, 12:00 PM Eastern Time by the Government after will not be accepted. Hard copies will not be accepted.

Proposal Section Page Limitations

Title Page 1 Executive Summary (Section I) 2 Proof of Eligibility (Section II) 3 Qualifications of the Offeror (Section III) 5 Approach to Conducting Studies (Section IV) 25 Intellectual Property (Section V) 1 Signed Model Contract (Section VI) No limit Price Proposal (Section VII) No limit Attachments No limit

Title Page:

• Include any Notice of Restriction on Use and Disclosure of Proposal Information.

• An optional graphic image may be included.

• The Proposer’s name of the proposal or proposed project

• Date of the proposal

• The title and solicitation number mailto:GRC-PPE-Procurement@mail.nasa.gov

• Organization name and address

• Proposer Point of Contact name, title, e-mail address, and phone number

I. Executive Summary: Describe the proposal’s prominent and distinguishing features.

The Executive Summary should provide an overview of the proposed effort that is suitable for release through a publicly accessible archive should the proposal be selected.

II. Proof of Eligibility: Provide information showing that the Respondent and all team members are eligible participants as stipulated in Section 3 of the omnibus BAA and Section 5 of this Appendix. Describe compliance with eligibility requirements as needed. Explain how the required corporate contribution resources will be satisfied.

III. Qualifications of the Offeror: Provide information on the organization’s capabilities and the qualifications of key personnel.

IV. Approach to Conducting Studies: The Offeror shall describe their approach to conducting the study topics. The Offeror shall identify by number the specific study topic(s) that the Offeror is responding to and the proposed approach for addressing the identified study topics from Section 3.0 of this Appendix including how they map to meeting the objectives identified in Section 2.1 of this Appendix.

V. Intellectual Property: The Offeror shall describe the approach for data rights, and how they meet the objectives outlined in the omnibus BAA, Section 2.7, Intellectual Property Developed Under an Award.

VI. Signed Model Contract: A Model Contract is provided in Attachment C of this Appendix. Please be advised that all sections designated with the text [OFI] represent “Offeror Fill-Ins”. Offerors should fill in [OFI]’s and submit as part of the signed model contract with the proposal submittal. Additionally, sections designated with the text [TBD] stand for “To Be Determined”. Offerors should not fill in the [TBD]’s.

The Government will update these after contract award. Offerors may take exception to, or have unique interpretations of any model contract clauses. These exceptions and/or unique interpretations should be listed clearly in a Summary of Exceptions.

Note, taking exception to, or having unique interpretations of any required clauses MAY have a negative impact on potential selection. The government does not intend to conduct negotiations. However, the Government reserves the right to negotiate with selected Offerors, cost/price terms and any other terms, if it is deemed in the best interest of the Government.

VII. Price Proposal: The price proposal shall include the overall firm fixed price in a single Contract Line Item (CLIN) in the range of $150K-$500K and not to exceed $500K. The Offeror shall provide total direct labor hours by skill mix, travel, and subcontracts in accordance with the price proposal sample format set forth in the omnibus BAA, Attachment A.

• The Government may select execution of the proposal based on programmatic requirements and availability of resources.

• In the Price Forms contained in the omnibus BAA instructions, the Offeror shall add a table listing the breakout and value of corporate resources.

• In the Price Forms contained in the omnibus BAA instructions, the Offeror shall add a list of Government-contributed resources, if any, and the estimated value.

Note, there is no GFE/GFP envisioned for the performance of the study contracts.

Attachments:

• Attachment A: Statement of Work: The Offeror shall provide a draft Statement of Work that includes a work breakdown structure and a description of the major tasks, milestones, and deliverables.

• Attachment B: Payment Milestones: The proposal shall include two payment milestones at contract start plus 60 days and at contract completion or 120 days. The Offeror shall propose the associated objective success criteria/deliverables for the individual study topics and the payment amount.

• Attachment C: List of Proposed Deliverables: The Offeror shall provide a list of proposed deliverables that is consistent with the Additional Proposal Guidance regarding Study Deliverables set forth in Section 6.1.2 below. Each deliverable description shall include a descriptive title, objectives, description of content, proposed format of deliverable, and submittal date(s) based on contract start date plus [OFI] days.

• Attachment D: Corporate Resources Documentation: The Offeror shall provide documentation showing proof of corporate contributions. An example is provided in the omnibus BAA Section 3.2.5

• Attachment E: Quad Chart: A quad chart summarizing the proposed objectives, team, milestones, and funding requirements. The Offeror may propose the format.

• Attachment F: Resumes: Resumes may be included for key personnel, limited to no more than 1 page each.

6.1.2 Additional Proposal Guidance

Contract Structure

• The Study contract will consist of 4 months in duration.

• Payment milestones should occur approximately midway and at the conclusion of the study contract.

• Payment milestones should reference studies completed for that payment.

Study Deliverables

• Conduct a Kickoff Meeting at the start of the contract to discuss the study topics and the proposed plans for conducting the study. The location of the briefing shall occur at the Contractor’s facility (with WebEx) unless otherwise agreed to by the Government.

• Bi-weekly coordination telecons with NASA.

• Conduct a 45 day Study Status briefing focusing on overall study status/progress and specifically addressing a response to study topic #14, for identification of areas of significant potential synergies between the PPE specific capabilities and both the current and future capabilities for the commercial market. This includes identification of PPE specific capabilities that may be beyond current or planned commercial capabilities. This could also include a variety of topics such as but not limited to the use of advanced solar electric propulsion and innovative ideas for partnership business models including options for potential cost share or cost contributions that addresses intellectual property, asset ownership, and timing of delivery of the asset and/or services to the Government.

• Conduct a pre-final Study briefing at 90 days to present the draft study results. The location of the briefing shall occur at the Contractor’s facility (with WebEx) unless otherwise agreed to by the Government.

• Conduct a final Study briefing at 120 days to present the final study results. The location of the briefing shall occur at the Contractor’s facility (with WebEx) unless otherwise agreed to by the Government.

• A written report, in MS Word and PDF format, 1 week prior to the pre-final Study briefing with a final update to the written report including delivery of all supporting data 1 week prior to the final Study briefing.

• The draft and final written report shall address how the Contractor met the objectives stated in Section 2.1 of this Appendix and the results of the specific study topics as proposed by the Offeror. All study topic supporting data shall be provided with the draft and final report, for example: CAD models, mass estimates, results of analysis, etc.

• A written response to questions submitted by the Government following the pre-final and final briefings and receipt of the written draft and final reports

• Deliverables are to be submitted to the NASA Contracting Officer (CO) in electronic format using standard Microsoft Office software (Word, Excel, and PowerPoint).

• Additional deliverables may be proposed by the Offeror.

7 Proposal Review Information

NASA will review and evaluate proposals in accordance with the omnibus BAA, Section 5.

NASA will evaluate proposals using the following evaluation factors, with each factor having equal weight:

Factor 1 – Relevance: The Government will evaluate the relevance of the proposal to meet the overall objectives of the Power and Propulsion Element studies for which the proposal was submitted.

Factor 2 – Technical Merit: The Government will evaluate the quality, depth, and thoroughness of the proposed technical approach and the organization’s capabilities and the qualifications of key personnel.

Factor 3 – Price: The Government will evaluate the overall cost reasonableness of the firm fixed price estimate and corporate contributions including the extent to which the

Offeror complied with the specified dollar limits in this Announcement. The Government will evaluate the total direct labor hours by skill mix, travel, and subcontracts. Also an analysis will be done on the corporate contribution to ensure that it properly aligns with the proposed effort.

8 Award Information Contract Award: NASA reserves the right to select for award multiple, one, or none of the proposals received in response to this solicitation. The overall number of awards will be dependent upon funding availability and evaluation results. The Government intends to evaluate proposals and award contracts based on initial proposals, without discussions. However, the Government reserves the right to conduct discussions if deemed in the best interest of the Government. Accordingly, each Offeror should submit its initial proposal to the Government using the most favorable terms from a cost and technical standpoint.

Period of Performance: As indicated in Section 6.1.2, NASA desires a nominal period of performance of 4 months for this effort. NASA may elect to simultaneously continue one or more awardees for additional period(s) of performance if it is deemed in the best interest of the Government.

Award Date: Award is anticipated on or about November 24, 2017. NASA may not make any awards to those selected until NASA receives the fiscal year 2018 appropriations or may choose to only award a portion of those selected and reserve the remaining awards pending the final appropriations for the fiscal year. Any reduced appropriations or continuing resolution may effect NASA’s ability to award selected Offerors.

Funding Allocation: NASA anticipates individual award amounts of $150K-$500K per study contract across 4-6 potential efforts. Contracts shall be firm fixed price with two milestone payments. The Government’s obligation to make awards is contingent upon the availability of appropriated funds from which payments can be made and the receipt of proposals that NASA determines are acceptable.

9 References o NextSTEP Reference Website: www.nasa.gov/nextstep o FedBizOps Reference Website for the Appendix C Synopsis:

https://www.fbo.gov/notices/4a9a70d396472e75e5ad5bca8f6af881 o NPR 8705.2C, Human-Rating Requirements for Space Systems, available at https://nodis3.gsfc.nasa.gov/displayDir.cfm?t=NPR&c=8705&s=2C o NASA Guidebook for Proposers, available at https://www.hq.nasa.gov/office/procurement/nraguidebook/ o NASA Core Flight Systems information, available at http://coreflightsystem.org/ o Asteroid Robotic Redirect Mission information, available at www.nasa.gov/arm http://www.nasa.gov/nextstep https://www.fbo.gov/notices/4a9a70d396472e75e5ad5bca8f6af881 https://nodis3.gsfc.nasa.gov/displayDir.cfm?t=NPR&c=8705&s=2C https://www.hq.nasa.gov/office/procurement/nraguidebook/ http://coreflightsystem.org/ http://www.nasa.gov/arm o Interoperability Standard draft documents will be posted to FedBizOps when available.

Attachment A: Acronym List

ARRM Asteroid Redirect Robotic Mission

BAA Broad Agency Announcement

CLIN Contract Line Item Number

EM Exploration Mission

EVR Extravehicular Robotics

FAR Federal Acquisition Regulation

FFRDC Federally Funded Research and Development Centers

DSG Deep Space Gateway

DSG&T Deep Space Gateway and Transport

EP Electric Propulsion

FAR Federal Acquisition Regulation

HEOMD Human Exploration and Operations Mission Directorate

IDSS International Docking System Standard

IRAD Independent Research and Development

JPL Jet Propulsion Laboratory

NASA National Aeronautics and Space Administration

NextSTEP-2 Next Space Technologies for Exploration Partnerships -2

NFS NASA Federal Acquisition Regulation Supplement

NOI Notice of Intent

NRHO Near Rectilinear Halo Orbit

POC Point of Contact

PPE Power and Propulsion Element

RCS Reaction Control System

SEP Solar Electric Propulsion

SLS Space Launch System

TBD To Be Determined

Attachment B: PPE Capabilities Summary

PPE-RQMT-0067

National Aeronautics and Revision Status: Initial Release Space Administration Effective Date: 08/30/2017

John H. Glenn Research Center at Lewis Field CAGE Code No.: 1QFP5 Cleveland, OH 44135

Power and Propulsion Element (PPE)

Level 3 and 4 Requirement Document

Distribution:

[ ] NASA (U.S. Gov. Only) [ ] Project Only [ X ] Government and Contractors

Availability:

[ X ] Public (No Restriction) [ ] Export Controlled [ ] Confidential/ Commercial [ ] Internal Use Only

1.1 TOP REQUIREMENTS

The following sections contain the mission requirements for the Power and Propulsion Element.

L3-PPE-01 Power and Propulsion Element Lifetime

The Power and Propulsion Element shall have a minimum operational lifetime of 15 years in cis-lunar space.

Rationale: The Power and Propulsion Element lifetime of 15 years initiates when the element is launched. The Power and Propulsion Element lifetime terminates when DSG Disposal orbit insertion is complete.

Children:

L4-PPE-104 Maximum Solar Distance

The PPE shall operate at a maximum solar distance of 1.03 AU (TBR-011).

Rationale: Operational regimes do not include low lunar orbit. Assumes operation between translunar injection and cislunar orbits.

L4-PPE-101 Disposal

The PPE shall perform disposal of exploration elements at end of operational life per NPR-8715.6B NASA Procedural Requirement for Limiting Orbital Debris and Evaluating Meteoroid and Orbital Debris Environments.

L4-PPE-102 Operational Lifetime

The PPE shall have a minimum operational lifetime of 15 years in cis-lunar space.

L4-PPE-103 Minimum Solar Distance

The PPE shall operate at a minimum solar distance of 0.97 AU (TBR-017).

Rationale: Operational regimes do not include low lunar orbit. Assumes operation between translunar injection and cislunar orbits.

L3 New: The PPE shall be capable of surviving an eclipse for up to 1.5 hours

(TBR-019).

L3-PPE-02 Power and Propulsion Element Power

The Power and Propulsion Element shall transfer up to 27kW of electrical power to the Exploration Elements throughout its lifetime.

Rationale: The 27kW electrical power value represents the maximum amount of power transferred to the external hardware other than the Power and Propulsion Element. This limits the available power for SEP thrusting.

L4-PPE-106 Power Transfer During Eclipse

The PPE shall be capable of providing at least 8 kW (TBR-018) of electrical power to Exploration Elements during an eclipse for up to 1.5 hours (TBR-019) duration through end of life.

L4-PPE-105 Power Transfer During Non-Eclipse

The PPE shall be capable of providing at least 27 kW (TBR) of electrical power to Exploration Elements in the absence of eclipse through end of life.

L3-PPE-03 Power and Propulsion Element Propulsion Capability

The Power and Propulsion Element shall provide orbit transfer for all un-crewed configurations of the Exploration Elements with maximum masses and center of masses shown in Table 1 (TBR), with the center of masses relative to the coordinate system in Figure 1.

Rationale: The capability of the Power and Propulsion Element provides in-space transportation for the external hardware.

Table 1: Orbit Transfer (All values TBR)

Figure 1: Base Coordinate System

L4-PPE-107 Orbit Transfer

The PPE shall provide orbit transfer for all un-crewed configurations of the Exploration Elements with maximum masses and center of masses per Table 1 (TBR), with the center of masses relative to the coordinate system in Figure 1.

L3-PPE-04 Power and Propulsion Element Xenon Capacity

The Power and Propulsion Element shall have 2,000 kg-class tank Xenon capacity.

Rationale: The capability of the Power and Propulsion Element to provide in-space transportation to the external hardware is expressed in terms of Xenon load. The 2000 kg class tank capacity is derived from commercial spacecraft.

The PPE tank capacity of 2000kg is imposed to protect the capability for late addition of extra Xenon if SLS Co-manifested payload performance exceeds the 8t limit imposed on the PPE. It is anticipated that a partial load would be nominally launched, but if additional SLS performance is available, additional Xenon could be added in the tank capacity.

L4-PPE-109 Xenon Tank Capacity

The PPE shall have a 2,000 kg-class Xenon capacity.

L3-PPE-05 Power and Propulsion Element Launch Vehicle

The Power and Propulsion Element shall be compatible with the SLS vehicle co-manifested launch on EM2.

Rationale: The Power and Propulsion Element will be subject to the SLS constraints documented in the SLS Mission Planners Guide (document reference) and additional constraints associated with launch on EM-2. As EM-2 is planned to be launched on the first crewed Block 1B SLS launch. Co-manifesting Power and Propulsion Element with Orion on EM-2 will limit its mass more than if it was on later Exploration Missions. Currently this would constrain the Power and Propulsion Element to 7,500 kg total launch mass including the Payload Adapter and any partner provided hardware or systems. As such, the Power and Propulsion Element will be subject to the SLS launch mass constraints associated with an Orion co-manifest launch. The PPE will also be capable of accommodating SLS Block 1B induced environments.

L4-PPE-112 Co-Manifest Payload

The PPE shall launch as a co-manifested payload with Orion.

Rationale: The Power and Propulsion Element will be subject to the SLS constraints documented in the SLS Mission Planners Guide (document reference) and additional constraints associated with launch on EM-2.

L4-PPE-111 Launch Volume

The PPE shall launch in the Space Launch System, Upper Stage Adapter (USA).

Rationale: The Power and Propulsion Element will be subject to the SLS constraints documented in the SLS Mission Planners Guide (document reference) and additional constraints associated with launch on EM-2.

L3-PPE-06 Power and Propulsion Element Attitude Control

The Power and Propulsion Element shall provide attitude control for all crewed and un-crewed configurations of Exploration Elements with maximum masses and center of masses shown in Table 2 (TBR), with the center of masses relative to the coordinate system in Figure 1 with the exception of rendezvous and docking when the Power and Propulsion Element is the passive element and will enter a state of free drift.

Rationale: The Power and Propulsion Element will provide attitude control using RCS, momentum wheels, SEP thrust vectoring (TBD-021) for the entire stack. The control authority requirements for attitude control will change over time as exploration elements are added.

Table 2: Orbit Maintenance and Attitude Control (All values TBR)

L4-PPE-113 Non-propulsive Attitude Control

The PPE shall be capable of providing non-propulsive attitude control for all configurations of Exploration Elements with maximum masses shown in Table 2 (TBR) up to (TBD-005) rates in each axis.

L4-PPE-114 Propulsive Attitude Control

The PPE shall be capable of providing propulsive attitude control for all configurations of Exploration Elements with maximum masses shown in Table 2 (TBR) up to (TBD-009) rates in each axis.

L4-PPE-115 Mass and Center of Mass

The PPE shall be capable of providing attitude control for all configurations of Exploration Elements up to stack mass per Table 2 (TBR) and stack center of mass, with the center of mass relative to the coordinate system in Figure 1.

L4-PPE-NEW Rendezvous and Docking The PPE shall be capable of entering into a stable free-drift state as the passive element during rendezvous and docking.

L3-PPE-07 Power and Propulsion Element Interfaces The Power and Propulsion Element shall provide two International Docking System Standard compliant interfaces one forward and one aft.

Rationale: The Power and Propulsion Element will be equipped with two International Docking System Standard (IDSS) compliant systems one forward and one aft. The IDSS specification will include interfaces for power, C&DH and fluids as standard interfaces.

L3 New: The Power and Propulsion Element shall provide one storage port interface.

L3 New: The PPE shall provide one to two (TBR) passive base interface plate (PBIP) for robot arm operations for complete inspection coverage of the PPE except for the solar arrays.

L4 New: The PPE shall provide one to two (TBR) passive base interface plate(s) (PBIP) with power, data, and video interfaces for complete inspection coverage of the PPE except for the solar arrays.

L3 New: The PPE shall provide (TBD) wedge mounting interface (WMI).

Rationale: Examples include payload EVA attachment, science or other external accommodations.

L4 New: The PPE shall provide (TBD) wedge mounting interface (WMI) with power, data and command interfaces. Rationale: Examples include payload EVA attachment, science or other external accommodations.

L3 New: PPE shall utilize data interfaces of IDSS to connect to software systems on other elements.

Rationale: At minimum, the PPE must interface with a common flight software approach to integrate with the stack.

L4-PPE-116 IDSS Interface

The Power and Propulsion Element shall provide passive docking capability forward and aft through IDSS compliant systems.

L3-PPE-08 Power and Propulsion Element Communication

The Power and Propulsion Element shall provide X-Band, Ka-Band, S-Band and UHF communications.

Rationale: The Power and Propulsion Element will provide communications X-band uplink and downlink and Ka-band downlink with the Ground, and S-band with the external hardware. PPE will support UHF communications with EVA.

L4-PPE-118 X-Band Communication

The PPE shall communicate with the Earth using X-band for uplink and downlink.

L4-PPE-119 Ka-Band Communication

The PPE shall communicate with the Earth using Ka-band for downlink.

L4-PPE-117 S-Band Communication

The PPE shall communicate with visiting vehicles using S-Band.

L4-PPE-120 EVA Communication

The PPE shall provide RF, data, power and mounting interfaces to support communications during EVAs.

L4 New: Nominal un-crewed operations of PPE shall utilize 8 hours of communication coverage per week.

Rationale: Uncrewed phases are intended to minimize ground control for nominal operations. Schedule constraints prevent extensive communications coverage during unmanned periods.

L4 New: The PPE shall support contingency operations with up to 3 (TBR) weeks without communication with ground controllers.

L3-PPE-09 Power and Propulsion Element Human Rating

The Power and Propulsion Element shall be an element of the human rated Deep Space Gateway system.

Rationale: Compliance with Certification Requirements for NASA Deep Space Missions HEOMD-XX–1000X (TBR-002). The specific requirements drive aspects of crew safety. This drives hazard controls and interoperability requirements.

The Power and Propulsion Element will be capable of supporting EVA but will not be EVA/EVR maintainable.

L4 New: The PPE shall comply with the DSG allocation of HEOMD-003 Deep Space Exploration Systems Certification Requirements and Standards (TBD).

L3-PPE-010 Power and Propulsion Element Refuelablility

The Power and Propulsion Element shall be on-orbit refuelable both forward and aft.

Rationale: The Power and Propulsion Element will have refuel capability incorporated with/near the forward and aft IDSS compliant interfaces for both xenon and hydrazine.

L4-PPE-128 RCS Refueling

The PPE shall be capable of being refueled up to (TBD-007) kg of reaction control system propellant with an IDSS-compliant Interface

L4-PPE-127 Xenon Refueling

The PPE shall be capable of being refueled up to 2000 kg (TBR-012) of xenon propellant with an IDSS-compliant Interface.

L3-PPE-011 Power and Propulsion Element Extensibility

The Power and Propulsion Element shall demonstrate an advanced integrated 50-kW-class Solar Electric Propulsion system that is extensible to future human Mars-class missions.

Rationale: The advanced solar electric propulsion system employs elements that have solar arrays with a high power-to-mass ratio, stowed volume efficiency, deployed strength and radiation tolerance. It has high-power electric propulsion with the specific impulse and total impulse needed for future Mars missions.

Addresses Human Exploration and Operations Exploration Objective P1-06 to demonstrate operation of long-duration high power solar arrays and solar electric propulsion (SEP) transportation of in-space propulsion elements.

L4-PPE-129 Xenon Processing Capacity

The PPE shall be capable of processing 5000 kg (TBR-014) of xenon propellant.

Rationale: This is a lifetime requirement for extensibility. This demonstrates lifetime of the EP string.

L4-PPE-131 Solar Array Technology Demonstration

The PPE shall demonstrate solar array technology with the power-to-mass ratio, stowed volume efficiency, deployed strength and radiation tolerance that is extensible for future human missions to Mars at a 300 kW class power level.

L4-PPE-130 High-Power Solar Electric Propulsion (SEP) System

The PPE shall demonstrate inflight performance of an integrated 50 kW-class Solar Electric Propulsion (SEP) System.

L3-PPE-012 Power and Propulsion Element Lunar Orbit

The Power and Propulsion Element shall be capable of inserting into a crew-accessible Near Rectilinear Halo Orbit (NRHO) in no longer than 100 days (TBR-003) after launch.

Rationale: Identification of the NRHO orbit is needed to scope the mission.

L4-PPE-132 Missed Thrust Outage

The PPE shall recover from missed thrust outages.

L4-PPE-135 Transport to NRHO The PPE shall be capable of inserting from Translunar injection into a Near Rectilinear Halo Orbit (NRHO).

L4-PPE-134 Orbit Insertion Timeframe

The PPE shall be capable of inserting into a Near Rectilinear Halo Orbit (NRHO) within 100 days (TBR-003) after launch vehicle separation.

L3 New: The PPE shall operate in cislunar space after translunar injection.

Rationale: PPE will operate from EUS separation post TLI, through translation to a NRHO and operations in various cislunar orbits. The PPE is not intended for interplanetary transfers or operation in LLO. Applies after insertion phase.

L3-PPE-013 Power and Propulsion Element Orbit Maintenance

The Power and Propulsion Element shall provide orbit maintenance for all crewed and un-crewed configurations of the Exploration Elements with maximum masses and center of masses shown in Table 2 (TBR), with the center of mass relative to the coordinate system in Figure 1.

Rationale: The capability of the Power and Propulsion Element provides in-space transportation for the external hardware.

L4-PPE-108 Orbit Maintenance

The PPE shall provide orbit maintenance for all configurations of the Exploration Elements with maximum masses and center of masses for the cases shown in Table 2 (TBR), with the center of mass relative to the coordinate system in Figure 1.

L3-PPE-014 Power and Propulsion Element Mass

The Power and Propulsion Element shall not exceed a mass of 7500 kg including the payload adapter.

Rationale: 7500 kg includes Payload Adaptor (which includes Payload Interface Adaptor and Payload fitting) but does not include 500kg being held at the management level above the Power and Propulsion Element. Currently this would constrain the Power and Propulsion Element to 7,500 kg total launch mass (wet) including the Payload Adapter and any partner provided hardware or systems. The total mass includes a minimum of 1200 kg of xenon propellant as specified in L3-PPE-017 and L4-PPE-136.

L4-PPE-110 Launch Mass

The PPE shall have a launch mass of less than or equal to 7500 kg including the Payload Adapter.

Rationale: 7500 kg includes Payload Adaptor (which includes Payload Interface Adaptor and Payload Attach Fitting) but does not include 500kg being held at the management level above the Power and Propulsion Element. Currently this would constrain the Power and Propulsion Element to 7,500 kg total launch mass (wet) including the Payload Adapter and any partner provided hardware or systems.

The total mass includes a minimum of 1200 kg of xenon propellant as specified in L3-PPE-017 and L4-PPE-136.

L3-PPE-015 Power and Propulsion Element Optical Communication

The Power and Propulsion Element shall accommodate optical communication demonstration.

Rationale: The Power and Propulsion Element will accommodate an optical communication demonstration by providing attachment to a Passive Base Interface Plate.

L4-PPE-121 Optical Communication

The Power and Propulsion Element shall provide a Passive Base Interface Plate attachment point for accommodation of an optical communication demonstration.

Rationale: The PBIP includes structural, data and power interfaces.

L3-PPE-016 Power and Propulsion Element Translation Path

The Power and Propulsion Element shall provide a translation path for EVA.

Rationale: The translation path refers to a quantifiable translation path for EVA. PPE to assess if significant driver. DSG to determine EVA needs relating to PPE.

L4-PPE-124 EVA Compatibility

The PPE shall provide a translation corridor for EVAs.

L3-PPE-017 Power and Propulsion Element Xenon Loading

The Power and Propulsion Element shall launch with a minimum of 1200kg (TBR-020) of Xenon.

Rationale: Specifying the tank loading allocates mass for translation capability without refueling.

L4-PPE-136 Xenon Tank Loading

The PPE shall launch with a minimum of 1200kg (TBR-020) of Xenon.

[END OF ATTACHMENT B]

Attachment C: Model Contract

The Model Contract is provided as a separate file on FedBizOps.