Fission Surface Power System - Technical Library

Form / Attachment / Pricing Sheet

This document is a form for "Obtaining Access to Export Controlled Content." It requires individuals requesting access to export-controlled scientific and technical information to provide specific company and contact details to the Contracting Officer. The form aims to ensure that the provided information is accurate and that companies are compliant with U.S. export regulations.

• Full Company Name
• Company Address
• Confirmation of incorporation to do business in the United States (Yes/No)
• Commercial and Government Entity (CAGE) Code
• Company Security or Human Resources Point of Contact information (Name, Title, Phone Number, Email)
• Certification regarding foreign persons and designated countries.
• Requirements for foreign nationals from designated and non-designated countries, including Programmatic Technology Transfer Control Plans (P-TTCP) and Individual Technology Transfer Control Plans (I-TTCP) with Non-Disclosure Agreements (NDA).

Bidders who require access to export-controlled content must complete and submit this form. It outlines the necessary information and certifications to ensure compliance with export control regulations, which is a prerequisite for accessing sensitive technical data related to the opportunity.

Amendment / Modification

This document, SLS-SPEC-159, "Cross-Program Design Specification for Natural Environments (DSNE)", has undergone several revisions:

• Revision I, Effective Date: October 27, 2021
  • This revision incorporates updates to Design Reference Missions (DRMs) for NASA Exploration Systems Development (ESD) Programs.
  • The document is derived from a previous Constellation Program (CxP) document (CxP 70023, Revision C).
  • The specifications are intended to provide a unified set of natural environment parameters for all ESD Programs.
  • The document defines parameter limits, energy spectra, and model inputs for all ESD Programs.
  • It is developed by the NASA Marshall Space Flight Center (MSFC) Natural Environments Branch (EV44).
  • Parameter limits are based on experience with previous programs, such as the Space Shuttle Program, and contain no margin.
  • The specifications are intended to be accounted for by robust design, but operational mitigation or risk acceptance may be used.
  • The DSNE is not intended as a definition of operational models or constraints, nor is it adequate alone for ground facilities.
  • "Natural environments" are defined as those not resulting from human activity or intervention.
  • The document specifies terrestrial environments (launch, abort, landing sites) and space environments (radiation, debris, meteoroids, thermosphere density, plasma, solar, Earth, and lunar-emitted thermal radiation).
  • Destination environments (Lunar surface/orbit, Mars atmosphere/surface, near-Earth asteroids) are also covered.
  • Environmental specifications are based on models, data, and descriptions from NASA/TM 2016-218229, Natural Environment Definition for Design (NEDD).
  • Validation of models, data, and design limits are provided in Appendix B.
  • Environmental specifications are tied to ESD DRMs in ESD-10012, Revision E, Exploration Systems Development Concept of Operations (ConOps).
  • Table 1.3-1 maps DRMs in ESD-10012, Revision E to corresponding sections in the DSNE.

This revision impacts the entire document by updating the underlying Design Reference Missions (DRMs) and incorporating a unified specification for natural environments.

This revision does not appear to modify proposal deadlines or submission rules. It provides updated environmental data and models for design and analysis.

Statement of Work (SOW) / Performance Work Statement (PWS)

This document defines the interface requirements for the Human-class Delivery Lander (HDL) system to deliver cargo to the lunar surface. It outlines the accommodations, functions, and utilities provided by the HDL for various cargo types, including the Lunar Surface Habitat (SH) and Pressurized Rover (PR), supporting the Artemis Sustained Mission Phases.

• Defines the interface requirements between the HDL and the Cargo.

• Specifies HDL-side interface requirements for structural/mechanical, thermal control, command and data handling, electrical power, environmental, fire protection, human factors, and safety.

• Outlines HDL interface functions including structural/mechanical attachment, thermal control, command and data handling, electrical power supply, crew access, and environmental protection.

• Details cargo interface functions including structural/mechanical attachment, receiving thermal control and electrical power, and providing crew access.

• Addresses cargo offloading capabilities and transit time limitations.

• Specifies a minimum of 2 kW continuous electrical power from launch to 2 days post-offloading.

• Defines a maximum cargo transit time of 210 days from Earth launch to lunar touchdown.

• Requires active thermal control heat transport of at least 2 kW.

• Mandates electromagnetic compatibility between HDL and Cargo.

• Requires single fault tolerance to catastrophic hazards during mated operations.

• The document applies to cargo launched and delivered by the HDL to the lunar surface.

• The period of performance for certain interface functions (e.g., power, thermal) extends up to 2 days (48 hours) after the HDL is ready for cargo post-offloading checkouts.

• Cargo must fit within defined volumetric envelopes (two options provided).

• Cargo mass must not exceed 15 t (inclusive of adapters).

• HDL and Cargo must mechanically mate.

• MMOD risk to cargo must be limited as specified in the Cargo-specific ICD.

• HDL must provide cybersecurity risk management.

• Crew access to cargo is facilitated by the HDL.

• Specifies verification methods for interface requirements, including inspection, analysis, demonstration, and test.

Other / Unclassified

This document is NASA-STD-6016C w/CHANGE 1, titled "STANDARD MATERIALS AND PROCESSES REQUIREMENTS FOR SPACECRAFT." It establishes minimum requirements for materials and processes (M&P) and provides a general control specification for incorporation into NASA program/project hardware procurements and technical programs.

This standard is critical for any bidder involved in designing, fabricating, or testing space program flight hardware for NASA. It outlines the mandatory requirements for materials and processes, including:

• Materials and Processes Selection, Control, and Implementation Plan: Requires a formal plan detailing how M&P requirements will be managed, controlled, and verified throughout the program lifecycle.
• Detailed Requirements: Covers a wide range of specific material and process requirements, including:
  • Flammability, offgassing, and compatibility
  • Metals (Aluminum, Steel, Titanium, Magnesium, Beryllium, Cadmium, Zinc, Mercury, Refractory Metals, Superalloys, Tin)
  • Nonmetallic Materials (Elastomeric Materials, Polyvinyl Chloride, Composite Materials, Lubricants, Limited-Life Items, Thermal Vacuum Stability, External Environment Survivability, Fungus Resistance, Glycols, Etching Fluorocarbons)
  • Processes (Heat Treatment, Forging, Castings, Formed Panels, Adhesive Bonding, Welding, Brazing, Electrical Discharge Machining, Nickel Plating, Additive Manufacturing)
  • Material Nondestructive Evaluation (NDE)
  • Special Materials Requirements (Residual Stresses, Sandwich Assemblies, Corrosion Prevention and Control, Hydrogen Embrittlement, Intermetallic Compounds, Fastener Installation, Contamination Control, Packaging)
• Material Usage Agreements (MUAs): Outlines the process for accepting materials or processes that do not strictly meet the standard's requirements but are deemed acceptable for specific applications.
• Appendices: Include a requirements compliance matrix, typical MUA forms, retired rationale codes, and recommended data requirements documents.

Bidders must ensure their proposed materials and processes comply with this standard or have a documented and approved deviation (MUA) to be considered for NASA spaceflight hardware opportunities.

Statement of Work (SOW) / Performance Work Statement (PWS)

This document outlines the requirements for the Lunar Communications Relay and Navigation Systems (LCRNS) project, which aims to provide relay services for lunar orbiting and surface assets to support Artemis missions and other NASA science and technology missions in the lunar regime.

• Initial Operating Capability (IOC): Expected to cover 2025-2028, with phased increments (Alpha, Bravo, Charlie) building up capabilities.

• Enhanced Operating Capability (EOC): Expected to begin in 2030, offering more complex network services.

• Services Offered: Includes communication, navigation (PNT), data relay (real-time and store-and-forward), and search and rescue (LunarSAR).

• Coverage: Defined by three service volumes (SV1, SV2, SV3) encompassing different lunar surface areas and altitudes.

• Key Technologies: Utilizes S-band and Ka-band frequencies, optical communications, Augmented Forward Signal (AFS) for PNT, and LunaNet Interoperability Specification (LNIS).

• Availability: Specified for both nominal and critical services during IOC and EOC phases.

• Latency: Real-time data latency to the NSN interface point is targeted at less than 1.0 second.

• Data Rates: Requirements for S-band and Ka-band services are detailed, including aggregate data rates for Artemis missions.

• PNT Accuracy: Specific performance requirements for position, velocity, and time knowledge are outlined for various user scenarios.

• LunarSAR: Requires a 99% probability of detection within 5 minutes and 99% service availability during EVA periods.

• Period: IOC phase from 2025-2028, with EOC phase starting in 2030.

• Place: Lunar proximity, including lunar orbit and surface, with an interface to the NASA Near Space Network (NSN) on Earth.

• Interoperability: Compliance with LunaNet Interoperability Specification (LNIS) is mandatory.

• Security: Command data encryption using FIPS 140-3 certified encryption is required.

• Cybersecurity: Information system authorization, project protection plans, service authentication, and anti-jamming capabilities are specified.

• Configuration Control: Changes to the requirements document are managed by the LCRNS Project Configuration Control Board (CCB).

Other / Unclassified

This document, "EHP-10028 BASELINE: EXPLORATION EVA (XEVA) SYSTEM COMPATIBILITY STANDARDS," establishes design standards for hardware and systems that interface with the xEVA suit or facilitate Extravehicular Activity (EVA) at Exploration Destinations. It consolidates requirements from previous programs (Shuttle, ISS, Constellation) and applies them to current and future Artemis missions, including Gateway, Human Landing System (HLS), Lunar Terrain Vehicle (LTV), and Pressurized Rover (PR).

This document is critical for any vendor developing hardware or systems intended for use in conjunction with or in proximity to the xEVA suit and EVA activities. It outlines the minimum requirements and constraints for performance, design, interoperability, maintainability, and safety. Bidders must ensure their designs comply with these standards, which cover aspects such as clearances, translation paths, handling features, worksite outfitting, loads, connectors, fasteners, and safety considerations applicable to microgravity and partial gravity environments.

Key sections relevant to bidders include:

• Section 3.0 Requirements: Details specific standards for clearances, translation, EVA handling, worksite outfitting, loads, connectors, fasteners, hardware design, and safety.
• Section 4.0 Verification: Outlines the methods and responsibilities for verifying compliance with the requirements.
• Appendices: Provide definitions, best practices, and system allocations.

Form / Attachment / Pricing Sheet

This document, "Moon to Mars (M2M) Graphical User Interface (GUI) Standard," establishes the standards for developing GUIs across the Artemis program. Its purpose is to create a usable design framework that promotes consistency, ease of learning, reduced operator workload, error reduction, increased situation awareness, and improved mission safety. It aims to simplify GUI design and increase development efficiency.

• Scope: Applies to Human-Rated Spaceflight vehicles, Contractor Furnished Equipment (CFE), Government Furnished Equipment (GFE), and items provided by International Partners. It covers displays on fixed units and portable computers. Commercial-Off-the-Shelf (COTS) applications providing vehicle insight or commanding must adhere to these requirements.
• Key Sections: The standard covers general GUI principles, layout and appearance, interaction with the vehicle (data display, commanding, system messages), GUI components (text, labels, menus, buttons, inputs, numbers, icons, graphs, schematics, color, flashing), and special purpose elements (time, automation, electronic procedures, alerts).
• Requirements: Details specific requirements for visual design, information presentation, user interaction, error handling, and feedback mechanisms.
• Appendices: Includes sections for Acronyms and Abbreviations, Glossary of Terms, Open Work (To Be Determined, To Be Resolved, Forward Work), and a Payload Mapping Matrix.

Vendors developing GUIs for Artemis programs must adhere to these standards to ensure compatibility, usability, and safety. Understanding these requirements is crucial for designing interfaces that meet NASA's specifications for crewed spaceflight missions. This document will guide the development and evaluation of user interfaces for any systems that will be integrated into the M2M program.

Other / Unclassified

This document is the Johnson Space Center (JSC) Contamination Control Requirements Manual (JPR No. 5322.1H), effective January 25, 2016, and expiring January 25, 2026. It establishes the minimum requirements and controls for an effective contamination control system for space flight equipment and associated ground support equipment.

While not a solicitation, this manual outlines critical requirements for contamination control that may be referenced or incorporated into future solicitations for space flight hardware, testing facilities, precision-cleaned packaging, and garment services. Bidders involved in such procurements should be aware of these standards, which cover areas such as:

• Foreign Object Damage (FOD) Prevention: Procedures for identifying and mitigating FOD risks.
• Surface Cleanliness Levels: Definitions and requirements for Generally Clean (GC), Visibly Clean (VC), and Precision Clean levels.
• Environmentally Controlled Areas (ECAs): Requirements for cleanrooms, laminar flow clean workstations, and controlled work areas, including personnel discipline, garmenting, and certification.
• Packaging: Standards for packaging precision-cleaned and visibly clean items.
• Microbiological Contamination Control: Requirements for managing microbial contamination.
• Electrostatic Discharge (ESD) Control: Program requirements for ESD sensitive equipment.

Understanding these requirements is crucial for developing proposals that meet NASA's stringent contamination control standards for space hardware.

Form / Attachment / Pricing Sheet

This document, the "Moon to Mars (M2M) Lunar Surface Data Book Baseline," serves as a comprehensive reference for lunar surface data, products, and analytical assumptions. It is intended to support Artemis mission science, exploration, and operational objectives by providing a common set of data sources and assumptions for mission planners, hardware designers, and potential vendors. The book aims to supplement high-level requirements documents by offering detailed information on lunar terrain and other characteristics.

• Scope: Focuses on the lunar south pole region, defined as within six degrees latitude of the geographic lunar south pole.
• Data Sources: Compiles data from various NASA missions (e.g., Apollo, Lunar Reconnaissance Orbiter) and international missions, with an emphasis on data from the Lunar Reconnaissance Orbiter.
• Data Products: Details foundational data products, visible imagery and altimetry, derived imagery and altimetry products, topographic data products, and modeling analyses.
• Terrain Characteristics: Includes general characteristics, plume-surface interactions, trafficability, illumination, and hazards.
• Example Use Cases: Provides representative traverses and associated data for the lunar south pole.
• Appendices: Includes acronyms, abbreviations, glossaries, open work items, reference materials, and data request processes.

This document is crucial for bidders involved in Artemis missions, particularly those focused on lunar surface operations in the south pole region. It provides essential background information, data sources, and analytical assumptions that underpin mission planning and requirements. Understanding this data book will help bidders align their proposals with NASA's established data frameworks and operational considerations for lunar exploration.

Form / Attachment / Pricing Sheet

This document, "LunaNet Interoperability Specification (LNIS V4)", defines the standard services and interfaces for LunaNet service providers to administer interoperable services for missions operating in the lunar vicinity. It is intended to enable interoperability within the LunaNet architecture, which includes Earth ground stations and orbiting spacecraft, and to provide services for various missions.

• Scope: Defines standards and specifications for interoperations within LunaNet on the lunar surface and in cislunar space.
• Services: Details communications services (real-time, store-and-forward, messaging), Position, Navigation, and Timing (PNT) services, and detection and information services.
• Interfaces: Outlines interfaces between LunaNet Service Providers (LNSPs) and users, as well as between LNSPs themselves (crosslink, DTE, terrestrial).
• Appendices: Includes detailed signal definitions (Augmented Forward Signal Structure - PFS5), acronyms and abbreviations, and phase allocations for different service capabilities.
• To Be Determined (TBD) / To Be Refined (TBR) Items: A significant portion of the document identifies areas where specifications are still under development or require further definition, indicating an evolving standard.

This document is crucial for any potential bidder involved in lunar communications, navigation, or PNT services. It outlines the technical requirements, standards, and interfaces that systems must adhere to for interoperability within the LunaNet framework. Bidders should pay close attention to the defined services, interfaces, and the numerous TBD/TBR items, as these represent areas for potential development, standardization, and future requirements. Understanding these specifications is essential for designing compatible systems and proposing relevant solutions for lunar missions.

Other / Unclassified

This document, NASA-STD-4003A w/CHANGE 1, is a NASA Technical Standard that establishes requirements for electrical bonding for NASA launch vehicles, spacecraft, payloads, and flight equipment. It provides a framework for consistent electrical bonding practices across NASA programs.

This standard defines the technical requirements for electrical bonding. If an opportunity requires compliance with NASA standards for spacecraft or launch vehicle hardware, this document would be a critical reference for understanding the specific bonding requirements, including:

• Scope: Defines basic electrical bonding requirements and classifies bonds by purpose (e.g., power current return, shock/fault protection, radio frequency, lightning protection, electrostatic discharge).
• Applicable Documents: Lists other relevant NASA and industry standards.
• Definitions: Provides key terms and definitions related to electrical bonding.
• General Requirements: Details specific requirements for various bonding classes (Class C, H, L, R, S).
• Detailed Requirements: Outlines bonding methods (metal-to-metal, bond straps, fasteners), surface cleaning, galvanic corrosion considerations, and requirements for specific materials like carbon fiber reinforced plastic and multilayer insulation.
• Verification: Describes methods for verifying compliance with bonding requirements (tests, analysis, inspection).

Vendors responding to opportunities that involve hardware requiring electrical bonding will need to adhere to the specifications outlined in this standard.

Other / Unclassified

This document, "International Software System Interoperability Standards (ISwSIS) Baseline - September 2020," establishes a standard interface to enable collaborative endeavors utilizing different spacecraft in deep space. It defines syntactic and semantic software system interface standards, as well as software production, product, and process standards. The document also defines a Software Framework Standard for use by NASA, International Partners, and commercial entities developing cislunar spacecraft software systems.

This document is relevant to bidders involved in developing software for cislunar and deep space missions. It outlines the required standards for software compatibility, data exchange, and interpretation to ensure interoperability between different spacecraft systems and modules. Key areas covered include:

• Syntactic Interoperability Standards: Based on Consultative Committee for Space Data Systems (CCSDS) standards such as Space Packet Protocol (CCSDS 133.0-B-1) and Encapsulation Service (CCSDS 133.1-B-2).
• Semantic Interoperability Standards: Including XML Specification for Electronic Data Sheets (CCSDS 876.0-B-1) and XML Telemetric and Command Exchange (XTCE) (CCSDS 660.0-B-2).
• Flight Software Framework Standard: Recommends NASA's Core Flight System (cFS) as the standard software framework for application hosting and implementation of interoperability standards.

Bidders should review these standards to ensure their proposed software solutions align with the ISwSIS requirements for seamless data exchange and interpretation in collaborative space exploration efforts.