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NASA Ball NASA
Procedural
Requirements
NPR 7123.1B
Effective Date: April 18, 2013
Expiration Date: April 18, 2018
COMPLIANCE IS MANDATORY
Printable Format (PDF)

(NASA Only)

Subject: NASA Systems Engineering Processes and Requirements

Responsible Office: Office of the Chief Engineer


| TOC | ChangeHistory | Preface | Chapter1 | Chapter2 | Chapter3 | Chapter4 | Chapter5 | Chapter6 | AppendixA | AppendixB | AppendixC | AppendixD | AppendixE | AppendixF | AppendixG | AppendixH | AppendixI | AppendixJ | ALL |

Appendix E. Technology Readiness Levels

TRL Definition Hardware Description Software Description Exit Criteria
1 Basic principles observed and reported Scientific knowledge generated underpinning hardware technology concepts/applications. Scientific knowledge generated underpinning basic properties of software architecture and mathematical formulation. Peer reviewed publication of research underlying the proposed concept/application.
2 Technology concept and/or application formulated Invention begins, practical applications is identified but is speculative, no experimental proof or detailed analysis is available to support the conjecture. Practical application is identified but is speculative; no experimental proof or detailed analysis is available to support the conjecture. Basic properties of algorithms, representations, and concepts defined. Basic principles coded. Experiments performed with synthetic data. Documented description of the application/concept that addresses feasibility and benefit.
3 -Analytical and experimental critical function and/or characteristic proof-of- concept Analytical studies place the technology in an appropriate context and laboratory demonstrations, modeling and simulation validate analytical prediction. Development of limited functionality to validate critical properties and predictions using non-integrated software components. Documented analytical/experimental results validating predictions of key parameters.
4 Component and/or breadboard validation in laboratory environment. A low fidelity system/component breadboard is built and operated to demonstrate basic functionality and critical test environments, and associated performance predictions are defined relative to final operating environment. Key, functionality critical software components are integrated and functionally validated to establish interoperability and begin architecture development. Relevant environments defined and performance in the environment predicted. Documented test performance demonstrating agreement with analytical predictions. Documented definition of relevant environment.
5 Component and/or breadboard validation in relevant environment. A medium fidelity system/component brassboard is built and operated to demonstrate overall performance in a simulated operational environment with realistic support elements that demonstrate overall performance in critical areas. Performance predictions are made for subsequent development phases. End-to-end software elements implemented and interfaced with existing systems/simulations conforming to target environment. End-to-end software system tested in relevant environment, meeting predicted performance. Operational environment performance predicted. Prototype implementations developed. Documented test performance demonstrating agreement with analytical predictions. Documented definition of scaling requirements.
6 System/sub-system model or prototype demonstration in an operational environment. A high fidelity system/component prototype that adequately addresses all critical scaling issues is built and operated in a relevant environment to demonstrate operations under critical environmental conditions. Prototype implementations of the software demonstrated on full-scale, realistic problems. Partially integrated with existing hardware/software systems. Limited documentation available. Engineering feasibility fully demonstrated. Documented test performance demonstrating agreement with analytical predictions.
7 System prototype demonstration in an operational environment. A high fidelity engineering unit that adequately addresses all critical scaling issues is built and operated in a relevant environment to demonstrate performance in the actual operational environment and platform (ground, airborne, or space). Prototype software exists having all key functionality available for demonstration and test. Well integrated with operational hardware/software systems demonstrating operational feasibility. Most software bugs removed. Limited documentation available. Documented test performance demonstrating agreement with analytical predictions.
8 Actual system completed and "flight qualified" through test and demonstration. The final product in its final configuration is successfully demonstrated through test and analysis for its intended operational environment and platform (ground, airborne, or space). All software has been thoroughly debugged and fully integrated with all operational hardware and software systems. All user documentation, training documentation, and maintenance documentation completed. All functionality successfully demonstrated in simulated operational scenarios. Verification and validation completed. Documented test performance verifying analytical predictions.
9 Actual system flight proven through successful mission operations. The final product is successfully operated in an actual mission. All software has been thoroughly debugged and fully integrated with all operational hardware and software systems. All documentation has been completed. Sustaining software support is in place. System has been successfully operated in the operational environment. Documented mission operational results.

Note: In cases of conflict between NASA directives concerning TRL definitions, NPR 7123.1 will take precedence.



| TOC | ChangeHistory | Preface | Chapter1 | Chapter2 | Chapter3 | Chapter4 | Chapter5 | Chapter6 | AppendixA | AppendixB | AppendixC | AppendixD | AppendixE | AppendixF | AppendixG | AppendixH | AppendixI | AppendixJ | ALL |
 
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