Terves, Llc
CAGE Code: 6ZU51
NCAGE Code: 6ZU51
Status: Active
Type: Manufacturer
Dun & Bradstreet (DUNS): 079112219
Summary
Terves, Llc is an Active Manufacturer with the Cage Code 6ZU51 and is tracked by Dun & Bradstreet under DUNS Number 079112219..
Address
24112 Rockwell Dr Ste C
Euclid OH 44117-1252
United States
Points of Contact
No Points of Contact...
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Frequently Asked Questions (FAQ) for CAGE 6ZU51
- What is CAGE Code 6ZU51?
- 6ZU51 is the unique identifier used by NATO Organizations to reference the physical entity known as Terves, Llc located at 24112 Rockwell Dr Ste C, Euclid OH 44117-1252, United States.
- Who is CAGE Code 6ZU51?
- 6ZU51 refers to Terves, Llc located at 24112 Rockwell Dr Ste C, Euclid OH 44117-1252, United States.
- Where is CAGE Code 6ZU51 Located?
- CAGE Code 6ZU51 is located in Euclid, OH, USA.
Contracting History for CAGE 6ZU51 Most Recent 25 Records
- FA864922P0489
- Rapid Casting Of Legacy Aluminum Components By 3D Printed Sand Molds
- 2 Nov 2021
- Rapid Casting Of Legacy Aluminum Components By 3D Printed Sand Molds
- Fa8649 Usaf Sbir Sttr Contracting
- Department Of Defense (Dod)
- $49,588.00
- Department Of Defense (Dod)
- FA864922P0489
- Rapid Casting Of Legacy Aluminum Components By 3D Printed Sand Molds
- 29 Oct 2021
- Rapid Casting Of Legacy Aluminum Components By 3D Printed Sand Molds
- Fa8649 Usaf Sbir Sttr Contracting
- Department Of Defense (Dod)
- $49,588.00
- Department Of Defense (Dod)
- SP470122C0066
- Terves Sbir Ii Proposal L2-0359 Entitled "Low Cost Domestic Gadolinium Production For Defense Critical Applications"
- 6 Jul 2022
- Terves Sbir Ii Proposal L2-0359 Entitled "Low Cost Domestic Gadolinium Production For Defense Critical Applications"
- Dcso Philadelphia
- Department Of Defense (Dod)
- $1,355,690.00
- Department Of Defense (Dod)
- FA864921P0011
- Rare Earth Free, High Strength, Formable Magnesium Alloys For Lightweight Aircraft Components.
- 18 Nov 2020
- Rare Earth Free, High Strength, Formable Magnesium Alloys For Lightweight Aircraft Components.
- Fa8649 Usaf Sbir Sttr Contracting
- Department Of Defense (Dod)
- $149,721.00
- Department Of Defense (Dod)
- W911QX20C0001
- Eo14042 - The Purpose Of This Modification Is To Incorporate Dfars Clause 252.223-7999 To Implement E.O. 14042 Ensuring Adequate Covid-19 Safety Protocols For Federal Contractors. Extension To Pop And Update To Acc-Apg Poc Will Also Be Completed.
- 10 Dec 2021
- Eo14042 - The Purpose Of This Modification Is To Incorporate Dfars Clause 252.223-7999 To Implement E.O. 14042 Ensuring Adequate Covid-19 Safety Protocols For Federal Contractors. Extension To Pop And Update To Acc-Apg Poc Will Also Be Completed.
- W6qk Acc-Apg Adelphi
- Department Of Defense (Dod)
- $1,095,460.75
- Department Of Defense (Dod)
- 80NSSC19C0007
- This Sttr Program Will Mature High Density, High Regression Rate Hybrid Rocket Motor Technology Through Trl6 Through The Design, Fabrication, And Testing Of Third And Fourth Stage Nanosatellite Motors, While Preparing Designs And Sizing For Booster Stages. Hybrid Rockets Offer Substantially Lower Cost Compared To Storable And Cryogenic Bipropellant Systems, But Currently Suffer From Poor Packaging Efficiency. During Proof Of Concept Work, The Use Of A High Density, Han Based Oxidizer System Combined With A High Density And High Regression Rate Solid Fuel Were Demonstrated As Solutions To Packaging Efficiency, O/F Ratio Sensitivity, And Regression Rate Limitations Of Hybrid Motors. The Han Based Oxidizer Has Low Freezing Temperature And No Appreciable Vapor Pressure, Being Safe, Storable, And Eliminating The Need For Special Handling And Shipping Precautions. The High Density Oxidizer Combined With The High Density, High Performance Fuel, Creates A Hybrid Engine System With The Density Impulse Performance Of A Solid Rocket Motor, But The Throttleability Of A Bipropellant System, With The Safety Approaching An Inert System. An Electrically Enhanced Ignition System Was Demonstrated Which Improved C*, And Enables Higher Performance To Be Met With Shorter Motor Grains, With The Potential For Multiple Start Capabilities. This Phase Ii Program Will Continue The Development Of High Density, Safe, Storable, Non-Toxic Hybrid Motors To Optimize Isp And Motor Design, Improve Injector And Igniter Performance, And Mature Third And Fourth Stage Motor Maturity Through Full Scale Motor Burns.
- 19 Dec 2023
- This Sttr Program Will Mature High Density, High Regression Rate Hybrid Rocket Motor Technology Through Trl6 Through The Design, Fabrication, And Testing Of Third And Fourth Stage Nanosatellite Motors, While Preparing Designs And Sizing For Booster Stages. Hybrid Rockets Offer Substantially Lower Cost Compared To Storable And Cryogenic Bipropellant Systems, But Currently Suffer From Poor Packaging Efficiency. During Proof Of Concept Work, The Use Of A High Density, Han Based Oxidizer System Combined With A High Density And High Regression Rate Solid Fuel Were Demonstrated As Solutions To Packaging Efficiency, O/F Ratio Sensitivity, And Regression Rate Limitations Of Hybrid Motors. The Han Based Oxidizer Has Low Freezing Temperature And No Appreciable Vapor Pressure, Being Safe, Storable, And Eliminating The Need For Special Handling And Shipping Precautions. The High Density Oxidizer Combined With The High Density, High Performance Fuel, Creates A Hybrid Engine System With The Density Impulse Performance Of A Solid Rocket Motor, But The Throttleability Of A Bipropellant System, With The Safety Approaching An Inert System. An Electrically Enhanced Ignition System Was Demonstrated Which Improved C*, And Enables Higher Performance To Be Met With Shorter Motor Grains, With The Potential For Multiple Start Capabilities. This Phase Ii Program Will Continue The Development Of High Density, Safe, Storable, Non-Toxic Hybrid Motors To Optimize Isp And Motor Design, Improve Injector And Igniter Performance, And Mature Third And Fourth Stage Motor Maturity Through Full Scale Motor Burns.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $747,824.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC19C0007
- Eo14042 This Sttr Program Will Mature High Density, High Regression Rate Hybrid Rocket Motor Technology Through Trl6 Through The Design, Fabrication, And Testing Of Third And Fourth Stage Nanosatellite Motors, While Preparing Designs And Sizing For Booster Stages. Hybrid Rockets Offer Substantially Lower Cost Compared To Storable And Cryogenic Bipropellant Systems, But Currently Suffer From Poor Packaging Efficiency. During Proof Of Concept Work, The Use Of A High Density, Han Based Oxidizer System Combined With A High Density And High Regression Rate Solid Fuel Were Demonstrated As Solutions To Packaging Efficiency, O/F Ratio Sensitivity, And Regression Rate Limitations Of Hybrid Motors. The Han Based Oxidizer Has Low Freezing Temperature And No Appreciable Vapor Pressure, Being Safe, Storable, And Eliminating The Need For Special Handling And Shipping Precautions. The High Density Oxidizer Combined With The High Density, High Performance Fuel, Creates A Hybrid Engine System With The Density Impulse Performance Of A Solid Rocket Motor, But The Throttleability Of A Bipropellant System, With The Safety Approaching An Inert System. An Electrically Enhanced Ignition System Was Demonstrated Which Improved C*, And Enables Higher Performance To Be Met With Shorter Motor Grains, With The Potential For Multiple Start Capabilities. This Phase Ii Program Will Continue The Development Of High Density, Safe, Storable, Non-Toxic Hybrid Motors To Optimize Isp And Motor Design, Improve Injector And Igniter Performance, And Mature Third And Fourth Stage Motor Maturity Through Full Scale Motor Burns.
- 13 Oct 2021
- Eo14042 This Sttr Program Will Mature High Density, High Regression Rate Hybrid Rocket Motor Technology Through Trl6 Through The Design, Fabrication, And Testing Of Third And Fourth Stage Nanosatellite Motors, While Preparing Designs And Sizing For Booster Stages. Hybrid Rockets Offer Substantially Lower Cost Compared To Storable And Cryogenic Bipropellant Systems, But Currently Suffer From Poor Packaging Efficiency. During Proof Of Concept Work, The Use Of A High Density, Han Based Oxidizer System Combined With A High Density And High Regression Rate Solid Fuel Were Demonstrated As Solutions To Packaging Efficiency, O/F Ratio Sensitivity, And Regression Rate Limitations Of Hybrid Motors. The Han Based Oxidizer Has Low Freezing Temperature And No Appreciable Vapor Pressure, Being Safe, Storable, And Eliminating The Need For Special Handling And Shipping Precautions. The High Density Oxidizer Combined With The High Density, High Performance Fuel, Creates A Hybrid Engine System With The Density Impulse Performance Of A Solid Rocket Motor, But The Throttleability Of A Bipropellant System, With The Safety Approaching An Inert System. An Electrically Enhanced Ignition System Was Demonstrated Which Improved C*, And Enables Higher Performance To Be Met With Shorter Motor Grains, With The Potential For Multiple Start Capabilities. This Phase Ii Program Will Continue The Development Of High Density, Safe, Storable, Non-Toxic Hybrid Motors To Optimize Isp And Motor Design, Improve Injector And Igniter Performance, And Mature Third And Fourth Stage Motor Maturity Through Full Scale Motor Burns.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $747,824.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC19C0007
- This Sttr Program Will Mature High Density, High Regression Rate Hybrid Rocket Motor Technology Through Trl6 Through The Design, Fabrication, And Testing Of Third And Fourth Stage Nanosatellite Motors, While Preparing Designs And Sizing For Booster Stages. Hybrid Rockets Offer Substantially Lower Cost Compared To Storable And Cryogenic Bipropellant Systems, But Currently Suffer From Poor Packaging Efficiency. During Proof Of Concept Work, The Use Of A High Density, Han Based Oxidizer System Combined With A High Density And High Regression Rate Solid Fuel Were Demonstrated As Solutions To Packaging Efficiency, O/F Ratio Sensitivity, And Regression Rate Limitations Of Hybrid Motors. The Han Based Oxidizer Has Low Freezing Temperature And No Appreciable Vapor Pressure, Being Safe, Storable, And Eliminating The Need For Special Handling And Shipping Precautions. The High Density Oxidizer Combined With The High Density, High Performance Fuel, Creates A Hybrid Engine System With The Density Impulse Performance Of A Solid Rocket Motor, But The Throttleability Of A Bipropellant System, With The Safety Approaching An Inert System. An Electrically Enhanced Ignition System Was Demonstrated Which Improved C*, And Enables Higher Performance To Be Met With Shorter Motor Grains, With The Potential For Multiple Start Capabilities. This Phase Ii Program Will Continue The Development Of High Density, Safe, Storable, Non-Toxic Hybrid Motors To Optimize Isp And Motor Design, Improve Injector And Igniter Performance, And Mature Third And Fourth Stage Motor Maturity Through Full Scale Motor Burns.
- 8 Dec 2022
- This Sttr Program Will Mature High Density, High Regression Rate Hybrid Rocket Motor Technology Through Trl6 Through The Design, Fabrication, And Testing Of Third And Fourth Stage Nanosatellite Motors, While Preparing Designs And Sizing For Booster Stages. Hybrid Rockets Offer Substantially Lower Cost Compared To Storable And Cryogenic Bipropellant Systems, But Currently Suffer From Poor Packaging Efficiency. During Proof Of Concept Work, The Use Of A High Density, Han Based Oxidizer System Combined With A High Density And High Regression Rate Solid Fuel Were Demonstrated As Solutions To Packaging Efficiency, O/F Ratio Sensitivity, And Regression Rate Limitations Of Hybrid Motors. The Han Based Oxidizer Has Low Freezing Temperature And No Appreciable Vapor Pressure, Being Safe, Storable, And Eliminating The Need For Special Handling And Shipping Precautions. The High Density Oxidizer Combined With The High Density, High Performance Fuel, Creates A Hybrid Engine System With The Density Impulse Performance Of A Solid Rocket Motor, But The Throttleability Of A Bipropellant System, With The Safety Approaching An Inert System. An Electrically Enhanced Ignition System Was Demonstrated Which Improved C*, And Enables Higher Performance To Be Met With Shorter Motor Grains, With The Potential For Multiple Start Capabilities. This Phase Ii Program Will Continue The Development Of High Density, Safe, Storable, Non-Toxic Hybrid Motors To Optimize Isp And Motor Design, Improve Injector And Igniter Performance, And Mature Third And Fourth Stage Motor Maturity Through Full Scale Motor Burns.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $747,824.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC19C0007
- Eo14042 This Sttr Program Will Mature High Density, High Regression Rate Hybrid Rocket Motor Technology Through Trl6 Through The Design, Fabrication, And Testing Of Third And Fourth Stage Nanosatellite Motors, While Preparing Designs And Sizing For Booster Stages. Hybrid Rockets Offer Substantially Lower Cost Compared To Storable And Cryogenic Bipropellant Systems, But Currently Suffer From Poor Packaging Efficiency. During Proof Of Concept Work, The Use Of A High Density, Han Based Oxidizer System Combined With A High Density And High Regression Rate Solid Fuel Were Demonstrated As Solutions To Packaging Efficiency, O/F Ratio Sensitivity, And Regression Rate Limitations Of Hybrid Motors. The Han Based Oxidizer Has Low Freezing Temperature And No Appreciable Vapor Pressure, Being Safe, Storable, And Eliminating The Need For Special Handling And Shipping Precautions. The High Density Oxidizer Combined With The High Density, High Performance Fuel, Creates A Hybrid Engine System With The Density Impulse Performance Of A Solid Rocket Motor, But The Throttleability Of A Bipropellant System, With The Safety Approaching An Inert System. An Electrically Enhanced Ignition System Was Demonstrated Which Improved C*, And Enables Higher Performance To Be Met With Shorter Motor Grains, With The Potential For Multiple Start Capabilities. This Phase Ii Program Will Continue The Development Of High Density, Safe, Storable, Non-Toxic Hybrid Motors To Optimize Isp And Motor Design, Improve Injector And Igniter Performance, And Mature Third And Fourth Stage Motor Maturity Through Full Scale Motor Burns.
- 5 Apr 2022
- Eo14042 This Sttr Program Will Mature High Density, High Regression Rate Hybrid Rocket Motor Technology Through Trl6 Through The Design, Fabrication, And Testing Of Third And Fourth Stage Nanosatellite Motors, While Preparing Designs And Sizing For Booster Stages. Hybrid Rockets Offer Substantially Lower Cost Compared To Storable And Cryogenic Bipropellant Systems, But Currently Suffer From Poor Packaging Efficiency. During Proof Of Concept Work, The Use Of A High Density, Han Based Oxidizer System Combined With A High Density And High Regression Rate Solid Fuel Were Demonstrated As Solutions To Packaging Efficiency, O/F Ratio Sensitivity, And Regression Rate Limitations Of Hybrid Motors. The Han Based Oxidizer Has Low Freezing Temperature And No Appreciable Vapor Pressure, Being Safe, Storable, And Eliminating The Need For Special Handling And Shipping Precautions. The High Density Oxidizer Combined With The High Density, High Performance Fuel, Creates A Hybrid Engine System With The Density Impulse Performance Of A Solid Rocket Motor, But The Throttleability Of A Bipropellant System, With The Safety Approaching An Inert System. An Electrically Enhanced Ignition System Was Demonstrated Which Improved C*, And Enables Higher Performance To Be Met With Shorter Motor Grains, With The Potential For Multiple Start Capabilities. This Phase Ii Program Will Continue The Development Of High Density, Safe, Storable, Non-Toxic Hybrid Motors To Optimize Isp And Motor Design, Improve Injector And Igniter Performance, And Mature Third And Fourth Stage Motor Maturity Through Full Scale Motor Burns.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $747,824.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC19C0007
- This Sttr Program Will Mature High Density, High Regression Rate Hybrid Rocket Motor Technology Through Trl6 Through The Design, Fabrication, And Testing Of Third And Fourth Stage Nanosatellite Motors, While Preparing Designs And Sizing For Booster Stages. Hybrid Rockets Offer Substantially Lower Cost Compared To Storable And Cryogenic Bipropellant Systems, But Currently Suffer From Poor Packaging Efficiency. During Proof Of Concept Work, The Use Of A High Density, Han Based Oxidizer System Combined With A High Density And High Regression Rate Solid Fuel Were Demonstrated As Solutions To Packaging Efficiency, O/F Ratio Sensitivity, And Regression Rate Limitations Of Hybrid Motors. The Han Based Oxidizer Has Low Freezing Temperature And No Appreciable Vapor Pressure, Being Safe, Storable, And Eliminating The Need For Special Handling And Shipping Precautions. The High Density Oxidizer Combined With The High Density, High Performance Fuel, Creates A Hybrid Engine System With The Density Impulse Performance Of A Solid Rocket Motor, But The Throttleability Of A Bipropellant System, With The Safety Approaching An Inert System. An Electrically Enhanced Ignition System Was Demonstrated Which Improved C*, And Enables Higher Performance To Be Met With Shorter Motor Grains, With The Potential For Multiple Start Capabilities. This Phase Ii Program Will Continue The Development Of High Density, Safe, Storable, Non-Toxic Hybrid Motors To Optimize Isp And Motor Design, Improve Injector And Igniter Performance, And Mature Third And Fourth Stage Motor Maturity Through Full Scale Motor Burns.
- 11 Oct 2022
- This Sttr Program Will Mature High Density, High Regression Rate Hybrid Rocket Motor Technology Through Trl6 Through The Design, Fabrication, And Testing Of Third And Fourth Stage Nanosatellite Motors, While Preparing Designs And Sizing For Booster Stages. Hybrid Rockets Offer Substantially Lower Cost Compared To Storable And Cryogenic Bipropellant Systems, But Currently Suffer From Poor Packaging Efficiency. During Proof Of Concept Work, The Use Of A High Density, Han Based Oxidizer System Combined With A High Density And High Regression Rate Solid Fuel Were Demonstrated As Solutions To Packaging Efficiency, O/F Ratio Sensitivity, And Regression Rate Limitations Of Hybrid Motors. The Han Based Oxidizer Has Low Freezing Temperature And No Appreciable Vapor Pressure, Being Safe, Storable, And Eliminating The Need For Special Handling And Shipping Precautions. The High Density Oxidizer Combined With The High Density, High Performance Fuel, Creates A Hybrid Engine System With The Density Impulse Performance Of A Solid Rocket Motor, But The Throttleability Of A Bipropellant System, With The Safety Approaching An Inert System. An Electrically Enhanced Ignition System Was Demonstrated Which Improved C*, And Enables Higher Performance To Be Met With Shorter Motor Grains, With The Potential For Multiple Start Capabilities. This Phase Ii Program Will Continue The Development Of High Density, Safe, Storable, Non-Toxic Hybrid Motors To Optimize Isp And Motor Design, Improve Injector And Igniter Performance, And Mature Third And Fourth Stage Motor Maturity Through Full Scale Motor Burns.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $747,824.00
- National Aeronautics And Space Administration (Nasa)
- W911QX18P0038
- Igf::Ot::Igf Sbir Phase 1 Topic A18-031. The Contractor Shall Perform Research And Development Efforts In The Area Of Improved Method For High Strength Magnesium Alloys In The As-Cast Condition.
- 17 Jul 2018
- Igf::Ot::Igf Sbir Phase 1 Topic A18-031. The Contractor Shall Perform Research And Development Efforts In The Area Of Improved Method For High Strength Magnesium Alloys In The As-Cast Condition.
- W6qk Acc-Apg Adelphi
- Department Of Defense (Dod)
- $154,597.48
- Department Of Defense (Dod)
- 80NSSC19C0007
- This Sttr Program Will Mature High Density, High Regression Rate Hybrid Rocket Motor Technology Through Trl6 Through The Design, Fabrication, And Testing Of Third And Fourth Stage Nanosatellite Motors, While Preparing Designs And Sizing For Booster Stages. Hybrid Rockets Offer Substantially Lower Cost Compared To Storable And Cryogenic Bipropellant Systems, But Currently Suffer From Poor Packaging Efficiency. During Proof Of Concept Work, The Use Of A High Density, Han Based Oxidizer System Combined With A High Density And High Regression Rate Solid Fuel Were Demonstrated As Solutions To Packaging Efficiency, O/F Ratio Sensitivity, And Regression Rate Limitations Of Hybrid Motors. The Han Based Oxidizer Has Low Freezing Temperature And No Appreciable Vapor Pressure, Being Safe, Storable, And Eliminating The Need For Special Handling And Shipping Precautions. The High Density Oxidizer Combined With The High Density, High Performance Fuel, Creates A Hybrid Engine System With The Density Impulse Performance Of A Solid Rocket Motor, But The Throttleability Of A Bipropellant System, With The Safety Approaching An Inert System. An Electrically Enhanced Ignition System Was Demonstrated Which Improved C*, And Enables Higher Performance To Be Met With Shorter Motor Grains, With The Potential For Multiple Start Capabilities. This Phase Ii Program Will Continue The Development Of High Density, Safe, Storable, Non-Toxic Hybrid Motors To Optimize Isp And Motor Design, Improve Injector And Igniter Performance, And Mature Third And Fourth Stage Motor Maturity Through Full Scale Motor Burns.
- 9 Aug 2021
- This Sttr Program Will Mature High Density, High Regression Rate Hybrid Rocket Motor Technology Through Trl6 Through The Design, Fabrication, And Testing Of Third And Fourth Stage Nanosatellite Motors, While Preparing Designs And Sizing For Booster Stages. Hybrid Rockets Offer Substantially Lower Cost Compared To Storable And Cryogenic Bipropellant Systems, But Currently Suffer From Poor Packaging Efficiency. During Proof Of Concept Work, The Use Of A High Density, Han Based Oxidizer System Combined With A High Density And High Regression Rate Solid Fuel Were Demonstrated As Solutions To Packaging Efficiency, O/F Ratio Sensitivity, And Regression Rate Limitations Of Hybrid Motors. The Han Based Oxidizer Has Low Freezing Temperature And No Appreciable Vapor Pressure, Being Safe, Storable, And Eliminating The Need For Special Handling And Shipping Precautions. The High Density Oxidizer Combined With The High Density, High Performance Fuel, Creates A Hybrid Engine System With The Density Impulse Performance Of A Solid Rocket Motor, But The Throttleability Of A Bipropellant System, With The Safety Approaching An Inert System. An Electrically Enhanced Ignition System Was Demonstrated Which Improved C*, And Enables Higher Performance To Be Met With Shorter Motor Grains, With The Potential For Multiple Start Capabilities. This Phase Ii Program Will Continue The Development Of High Density, Safe, Storable, Non-Toxic Hybrid Motors To Optimize Isp And Motor Design, Improve Injector And Igniter Performance, And Mature Third And Fourth Stage Motor Maturity Through Full Scale Motor Burns.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $747,824.00
- National Aeronautics And Space Administration (Nasa)
- SP470121P0096
- 8508436112 - Basic Research
- 14 Sep 2021
- 8508436112 - Basic Research
- Dcso Philadelphia
- Department Of Defense (Dod)
- $99,959.00
- Department Of Defense (Dod)