Tendeg Llc
CAGE Code: 58WC8
NCAGE Code: 58WC8
Status: Active
Type: Commercial Supplier
Dun & Bradstreet (DUNS): 828820659
Summary
Tendeg Llc is an Active Commercial Supplier with the Cage Code 58WC8 and is tracked by Dun & Bradstreet under DUNS Number 828820659..
Address
1772 Prairie Way
Unit A
Louisville CO 80027-8902
United States
Points of Contact
- Telephone:
- 3039294466
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Frequently Asked Questions (FAQ) for CAGE 58WC8
- What is CAGE Code 58WC8?
- 58WC8 is the unique identifier used by NATO Organizations to reference the physical entity known as Tendeg Llc located at 1772 Prairie Way, Unit A, Louisville CO 80027-8902, United States.
- Who is CAGE Code 58WC8?
- 58WC8 refers to Tendeg Llc located at 1772 Prairie Way, Unit A, Louisville CO 80027-8902, United States.
- Where is CAGE Code 58WC8 Located?
- CAGE Code 58WC8 is located in Louisville, CO, USA.
Contracting History for CAGE 58WC8 Most Recent 25 Records
- 80NSSC23CA039
- High Aspect Ratio Cylindrical Parabolic Antenna For Microsats.
- 13 Jun 2023
- High Aspect Ratio Cylindrical Parabolic Antenna For Microsats.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $300,000.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC23CA039
- High Aspect Ratio Cylindrical Parabolic Antenna For Microsats.
- 17 Nov 2023
- High Aspect Ratio Cylindrical Parabolic Antenna For Microsats.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $300,000.00
- National Aeronautics And Space Administration (Nasa)
- N0001418C2062
- Cubesat Fully Polarimetric Imaging Radiometer
- 24 Aug 2018
- Cubesat Fully Polarimetric Imaging Radiometer
- Office Of Naval Research
- Department Of Defense (Dod)
- $284,060.00
- Department Of Defense (Dod)
- NNX17CP09C
- The Proposed Phase Ii Program Will Refine And Mature The Design Of The Optical Edge, Optical Shield And Snubber Assemblies Within A Starshade Petal. Prototypes Of Each Sub-Assembly Will Be Built And Tested After A Rigorous Trade Study. The Final Sub-Assembly Designs Will Be Built And Integrated To A Complete Petal Assembly That Utilizes Flight-Like Materials And Fabrication Processes. The Full Petal Assembly Will Be Tested To Demonstrate Survival To Launch Packaging And Temperature Extremes. A Segment Of A Petal Will Be Delivered To Nasa Jpl For Thermal Distortion And Stability Tests. More Specifically, The Optical Edge Assembly Efforts Will Address The Integration Of A Micro-Thin Metal Alloy To A Low Cte Composite Substrate And The Alignment And Handling Procedures Required To Accurately Position Each Segment To The Petal Structure. The Optical Shield Effort Will Address Opacity, Thermal Expansion, Micrometeoroid Mitigation And Venting. The Snubber Effort Will Address Preload, Alignment And Support For The Petals In The Furled And Launch Configuration.
- 28 Jul 2020
- The Proposed Phase Ii Program Will Refine And Mature The Design Of The Optical Edge, Optical Shield And Snubber Assemblies Within A Starshade Petal. Prototypes Of Each Sub-Assembly Will Be Built And Tested After A Rigorous Trade Study. The Final Sub-Assembly Designs Will Be Built And Integrated To A Complete Petal Assembly That Utilizes Flight-Like Materials And Fabrication Processes. The Full Petal Assembly Will Be Tested To Demonstrate Survival To Launch Packaging And Temperature Extremes. A Segment Of A Petal Will Be Delivered To Nasa Jpl For Thermal Distortion And Stability Tests. More Specifically, The Optical Edge Assembly Efforts Will Address The Integration Of A Micro-Thin Metal Alloy To A Low Cte Composite Substrate And The Alignment And Handling Procedures Required To Accurately Position Each Segment To The Petal Structure. The Optical Shield Effort Will Address Opacity, Thermal Expansion, Micrometeoroid Mitigation And Venting. The Snubber Effort Will Address Preload, Alignment And Support For The Petals In The Furled And Launch Configuration.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $1,124,951.00
- National Aeronautics And Space Administration (Nasa)
- NNX17CP18C
- Modification Of Pop And Amount
- 20 Feb 2019
- Modification Of Pop And Amount
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $1,124,835.00
- National Aeronautics And Space Administration (Nasa)
- NNX17CP18C
- Modification Of Pop And Amount
- 25 Jun 2019
- Modification Of Pop And Amount
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $1,124,835.00
- National Aeronautics And Space Administration (Nasa)
- N0001418C2062
- Cubesat Fully Polarimetric Imaging Radiometer
- 19 Sep 2018
- Cubesat Fully Polarimetric Imaging Radiometer
- Office Of Naval Research
- Department Of Defense (Dod)
- $284,060.00
- Department Of Defense (Dod)
- 80NSSC19C0146
- The National Academies Decadal Strategy And Nasa Have Identified Critical Earth Observations Including Surface Deformation And Change And Clouds, Convection And Precipitation.
- 21 May 2021
- The National Academies Decadal Strategy And Nasa Have Identified Critical Earth Observations Including Surface Deformation And Change And Clouds, Convection And Precipitation.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $749,968.00
- National Aeronautics And Space Administration (Nasa)
- NNX16CP04C
- Igf::Ot::Igf In These Days Of Tight Budgets And Limited Funding, Nasa Is Constantly Looking For New Ways To Reduce Development Time And Costs Of Future Spacecraft. This Is The Driving Spirit Behind Nasa's Increasing Interest In The Cubesat Platform, And The Vision That Is Guiding Development And Demonstration Of Higher-Risk Technologies That Can Eventually Lead To Low-Cost Atmospheric Science From Cubesats. For Example, A Tantalizing Next-Generation Cubesat System Would Combine A High-Gain Deployable Antenna With A High-Frequency Ka-Band Transponder To Support Very High Bandwidth Communications On The Order Of 10S Of Mbps And/Or Very High-Resolution Radiometric Remote Sensing Of Atmospheric Phenomenon. To Address This Need, Tendeg Proposes To Develop A Ka-Band Deployable Mesh Antenna That Can Package Within A 3U Cubesat Volume And Deploy To Diameters Of 0.8-1.5M. The Antenna Employs A Backing Structure That Is A Hybrid Wrap-Rib/Perimeter-Truss Design. A Net Supports A Reflective Mesh While The Entire Assembly Provides The Structural Depth And Surface Accuracy Needed For Ka-Band Operation.
- 3 Jun 2018
- Igf::Ot::Igf In These Days Of Tight Budgets And Limited Funding, Nasa Is Constantly Looking For New Ways To Reduce Development Time And Costs Of Future Spacecraft. This Is The Driving Spirit Behind Nasa's Increasing Interest In The Cubesat Platform, And The Vision That Is Guiding Development And Demonstration Of Higher-Risk Technologies That Can Eventually Lead To Low-Cost Atmospheric Science From Cubesats. For Example, A Tantalizing Next-Generation Cubesat System Would Combine A High-Gain Deployable Antenna With A High-Frequency Ka-Band Transponder To Support Very High Bandwidth Communications On The Order Of 10S Of Mbps And/Or Very High-Resolution Radiometric Remote Sensing Of Atmospheric Phenomenon. To Address This Need, Tendeg Proposes To Develop A Ka-Band Deployable Mesh Antenna That Can Package Within A 3U Cubesat Volume And Deploy To Diameters Of 0.8-1.5M. The Antenna Employs A Backing Structure That Is A Hybrid Wrap-Rib/Perimeter-Truss Design. A Net Supports A Reflective Mesh While The Entire Assembly Provides The Structural Depth And Surface Accuracy Needed For Ka-Band Operation.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $749,968.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC18C0140
- The Proposed Innovations Are As Follows: 1) A Fully Redundant Electrical And Mechanical Motor/Cable Deployment Assembly 2) A Redundant Motor/Cable Deployment Assembly That Is Integrated And Deploys A Perimeter Truss For A Starshade 3) A Truss Strut Mechanism That Allows Petal And Truss Deployment And Provides A Stiff And Repeatable Support 4) A Truss Node Light Seal The Suppressess All Sun And Starlight Through A Truss Node With Articulatinig Truss Elements And Inner Disk And Petal Interfaces. The Significance And Relevance Of The Proposed Innovations Is To Meet The Technical Challenges Of Deploying A Large Scale Perimeter Truss (10-30M Diameter) For A Starshade. The Stdt's "Exo-S Final Report" Identified An Open Issue To "Mature Perimeter Truss Technology Readiness." This Is Part Of A Defined Starshade Technology Gap S-5 That Is Titled "Demonstrate Inner Disk Deployment With Optical Shield." In The Nasa Jpl Starshade Design The Petals Are Placed Into Their Precise Position By The Deploying Truss And Truss Strut. The Truss Also Deploys The Spiral Wrapped Inner Disk And At The End Tensions The Precision Spokes. If The Truss Was Not Able To Fully Deploy Or Meet The On-Orbit Load (Deployment And Deployed) And Positioning Requirements Then The Mission Would Fail. Obviously The Truss Deployment Mechanism Needs To Be A Robust And Reliable System.
- 21 Sep 2018
- The Proposed Innovations Are As Follows: 1) A Fully Redundant Electrical And Mechanical Motor/Cable Deployment Assembly 2) A Redundant Motor/Cable Deployment Assembly That Is Integrated And Deploys A Perimeter Truss For A Starshade 3) A Truss Strut Mechanism That Allows Petal And Truss Deployment And Provides A Stiff And Repeatable Support 4) A Truss Node Light Seal The Suppressess All Sun And Starlight Through A Truss Node With Articulatinig Truss Elements And Inner Disk And Petal Interfaces. The Significance And Relevance Of The Proposed Innovations Is To Meet The Technical Challenges Of Deploying A Large Scale Perimeter Truss (10-30M Diameter) For A Starshade. The Stdt's "Exo-S Final Report" Identified An Open Issue To "Mature Perimeter Truss Technology Readiness." This Is Part Of A Defined Starshade Technology Gap S-5 That Is Titled "Demonstrate Inner Disk Deployment With Optical Shield." In The Nasa Jpl Starshade Design The Petals Are Placed Into Their Precise Position By The Deploying Truss And Truss Strut. The Truss Also Deploys The Spiral Wrapped Inner Disk And At The End Tensions The Precision Spokes. If The Truss Was Not Able To Fully Deploy Or Meet The On-Orbit Load (Deployment And Deployed) And Positioning Requirements Then The Mission Would Fail. Obviously The Truss Deployment Mechanism Needs To Be A Robust And Reliable System.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $749,898.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC19C0146
- High Aspect Ratio Cylindrical Parabolic Antenna For Microsats
- 22 Jul 2021
- High Aspect Ratio Cylindrical Parabolic Antenna For Microsats
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $1,124,968.00
- National Aeronautics And Space Administration (Nasa)
- NNX16CP04C
- Igf::Ot::Igf In These Days Of Tight Budgets And Limited Funding, Nasa Is Constantly Looking For New Ways To Reduce Development Time And Costs Of Future Spacecraft. This Is The Driving Spirit Behind Nasa's Increasing Interest In The Cubesat Platform, And The Vision That Is Guiding Development And Demonstration Of Higher-Risk Technologies That Can Eventually Lead To Low-Cost Atmospheric Science From Cubesats. For Example, A Tantalizing Next-Generation Cubesat System Would Combine A High-Gain Deployable Antenna With A High-Frequency Ka-Band Transponder To Support Very High Bandwidth Communications On The Order Of 10S Of Mbps And/Or Very High-Resolution Radiometric Remote Sensing Of Atmospheric Phenomenon. To Address This Need, Tendeg Proposes To Develop A Ka-Band Deployable Mesh Antenna That Can Package Within A 3U Cubesat Volume And Deploy To Diameters Of 0.8-1.5M. The Antenna Employs A Backing Structure That Is A Hybrid Wrap-Rib/Perimeter-Truss Design. A Net Supports A Reflective Mesh While The Entire Assembly Provides The Structural Depth And Surface Accuracy Needed For Ka-Band Operation.
- 6 Aug 2018
- Igf::Ot::Igf In These Days Of Tight Budgets And Limited Funding, Nasa Is Constantly Looking For New Ways To Reduce Development Time And Costs Of Future Spacecraft. This Is The Driving Spirit Behind Nasa's Increasing Interest In The Cubesat Platform, And The Vision That Is Guiding Development And Demonstration Of Higher-Risk Technologies That Can Eventually Lead To Low-Cost Atmospheric Science From Cubesats. For Example, A Tantalizing Next-Generation Cubesat System Would Combine A High-Gain Deployable Antenna With A High-Frequency Ka-Band Transponder To Support Very High Bandwidth Communications On The Order Of 10S Of Mbps And/Or Very High-Resolution Radiometric Remote Sensing Of Atmospheric Phenomenon. To Address This Need, Tendeg Proposes To Develop A Ka-Band Deployable Mesh Antenna That Can Package Within A 3U Cubesat Volume And Deploy To Diameters Of 0.8-1.5M. The Antenna Employs A Backing Structure That Is A Hybrid Wrap-Rib/Perimeter-Truss Design. A Net Supports A Reflective Mesh While The Entire Assembly Provides The Structural Depth And Surface Accuracy Needed For Ka-Band Operation.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $749,968.00
- National Aeronautics And Space Administration (Nasa)
- NNX17CP18C
- Igf::Ot::Igf This Phaseii Program Will Focus On Integrating Viable Solar Cell Blanket Assemblies Onto The Inner Disk Of A Starshade Needed For Potential Exoplanet Discovery Missions. The Phase Ii Will Design And Analyze Structural Interfaces, Harness Requirements, Harness Routing, Survival And Durability For Packaging, Launch And On-Orbit Environmental Requirements. The Program Will Involve Numerous Hardware Demonstration Units And Testing And Culminate In A Full Scale Demonstration Unit With A Portion Of Active Solar Cells. This Will Move The Inner Disk With Solar Cells To Trl 5. The Inner Disk Of The Baseline Starshade Is Approximately 10 M In Diameter. This Large Surface Area Is An Ideal Location For Solar Arrays Which Will Allow For Solar Electric Propulsion. Sep Will Allow The Starshade To Transition To New Orbit Positions Relative To The Telescope More Efficiently Which Will Expand The Exoplanet Science During The Mission Lifetime.
- 3 Jun 2018
- Igf::Ot::Igf This Phaseii Program Will Focus On Integrating Viable Solar Cell Blanket Assemblies Onto The Inner Disk Of A Starshade Needed For Potential Exoplanet Discovery Missions. The Phase Ii Will Design And Analyze Structural Interfaces, Harness Requirements, Harness Routing, Survival And Durability For Packaging, Launch And On-Orbit Environmental Requirements. The Program Will Involve Numerous Hardware Demonstration Units And Testing And Culminate In A Full Scale Demonstration Unit With A Portion Of Active Solar Cells. This Will Move The Inner Disk With Solar Cells To Trl 5. The Inner Disk Of The Baseline Starshade Is Approximately 10 M In Diameter. This Large Surface Area Is An Ideal Location For Solar Arrays Which Will Allow For Solar Electric Propulsion. Sep Will Allow The Starshade To Transition To New Orbit Positions Relative To The Telescope More Efficiently Which Will Expand The Exoplanet Science During The Mission Lifetime.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $749,884.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC19C0146
- The National Academies Decadal Strategy And Nasa Have Identified Critical Earth Observations Including Surface Deformation And Change And Clouds, Convection And Precipitation.
- 6 Jan 2021
- The National Academies Decadal Strategy And Nasa Have Identified Critical Earth Observations Including Surface Deformation And Change And Clouds, Convection And Precipitation.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $749,968.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC18P2011
- The Subtopic Requests Advanced Deployable Parabolic Antennas With An Effective Aperture Of 4M2 That Operate At Frequencies Up To 36Ghz. Tendeg Will Produce A Flight Antenna Design To Meet A Nasa Specific Science Mission. Various Feed Systems Will Be Explored Including A Beam Scanning Phased Array Feed Along With Multi-Array Feeds. The Primary Goal Of This Phase I Program Will Be To Design And Develop The Primary Reflector Deployment Mechanism And Shape Forming Net. This Will Include Construction Of A Proof Of Concept Prototype Which Will Contain A Deployment Mechanism, Parabolic Shaped Slit Tube Back Support, Bulkhead Rear Supports, Reflector Netting, And Mesh Net Back Structure. This Will Demonstrate The Ability For High Packaging Efficiencies For Smallsat And Cubesat Buses.
- 26 Jul 2018
- The Subtopic Requests Advanced Deployable Parabolic Antennas With An Effective Aperture Of 4M2 That Operate At Frequencies Up To 36Ghz. Tendeg Will Produce A Flight Antenna Design To Meet A Nasa Specific Science Mission. Various Feed Systems Will Be Explored Including A Beam Scanning Phased Array Feed Along With Multi-Array Feeds. The Primary Goal Of This Phase I Program Will Be To Design And Develop The Primary Reflector Deployment Mechanism And Shape Forming Net. This Will Include Construction Of A Proof Of Concept Prototype Which Will Contain A Deployment Mechanism, Parabolic Shaped Slit Tube Back Support, Bulkhead Rear Supports, Reflector Netting, And Mesh Net Back Structure. This Will Demonstrate The Ability For High Packaging Efficiencies For Smallsat And Cubesat Buses.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $124,860.00
- National Aeronautics And Space Administration (Nasa)
- NNX17CP01C
- Igf::Ot::Igf The Proposed Phase Ii Program Would Develop And Prototype A High Frequency, High Performance Reflective Mesh That Is Well Suited To The Emerging Small Aperture Antenna Designs. The Program Will Build On The Testing Knowledge Of The Phase I Prototyped Mesh. 40 Opi Gold Mesh Will Be Prototyped And Integrated To A Cubesat Ka-Band Reflector. Carbon Nanotube Yarn Will Also Be Knitted Into A 30 Opi Mesh And Tested On A Similar Antenna. The Phase Ii Program Will Move The Mesh To Trl 6. The Goal Is To Make Cost Effective And Robust Mesh For The Small Aperture Antenna Community. Rf Test Samples And A Complete Deployable Ka-Band Antenna Will Be Delivered To Nasa Jpl For Rf Testing.
- 3 Jun 2018
- Igf::Ot::Igf The Proposed Phase Ii Program Would Develop And Prototype A High Frequency, High Performance Reflective Mesh That Is Well Suited To The Emerging Small Aperture Antenna Designs. The Program Will Build On The Testing Knowledge Of The Phase I Prototyped Mesh. 40 Opi Gold Mesh Will Be Prototyped And Integrated To A Cubesat Ka-Band Reflector. Carbon Nanotube Yarn Will Also Be Knitted Into A 30 Opi Mesh And Tested On A Similar Antenna. The Phase Ii Program Will Move The Mesh To Trl 6. The Goal Is To Make Cost Effective And Robust Mesh For The Small Aperture Antenna Community. Rf Test Samples And A Complete Deployable Ka-Band Antenna Will Be Delivered To Nasa Jpl For Rf Testing.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $749,991.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC19C0146
- Eo14042 The National Academies Decadal Strategy And Nasa Have Identified Critical Earth Observations Including Surface Deformation And Change And Clouds, Convection And Precipitation.
- 13 Oct 2021
- Eo14042 The National Academies Decadal Strategy And Nasa Have Identified Critical Earth Observations Including Surface Deformation And Change And Clouds, Convection And Precipitation.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $1,124,968.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC19C0146
- The National Academies Decadal Strategy And Nasa Have Identified Critical Earth Observations Including Surface Deformation And Change And Clouds, Convection And Precipitation. These Observations Are Well Suited To Synthetic Aperture Radar Instruments. The Missions Span Operating Frequencies From L To Ka Band. Precision Mesh Reflectors Are Uniquely Suited To Provide Large Frequency Bandwidth While Maintaining Small Packaging Forms With Low Mass. Tendeg Proposes To Create A Cylindrical Parabolic Reflector That Can Be Used Across Many Missions. This Will Include The Ability To Operate At Frequencies Up To 36 Ghz While Maintaining The Ability To Operate At Frequencies Down To L-Band. This Will Allow The Proposed Reflector To Operate With Current Multi Array Feeds, Or Scanning Phased Array Feeds, Of Different Frequencies On The Same Vehicle. This In Turn Will Allow Buses Equipped With This Reflector To Carry Out Several Of The Decadal Proposed Missions Which Require Sar Technologies. The Proposed Baseline Design Is A 5:1 Aspect Ratio Aperture That Will Be A 1 X 5M Deployed Effective Aperture. The Proposed Design Is Scalable To Larger Apertures And Can Accommodate A Fixed Feed With Either Center Fed Or Offset Fed Apertures. The Antenna Has High Structural Stability Which Results In High On-Orbit Resonance Frequencies, Precision Deployment Repeatability, Low Distortions Due To On-Orbit Temperatures And Ability To Accurately Rf Test In 1G. The Proposed Design Would Leverage Technologies Already Developed By Tendeg As Part Of Previous Sbir Activities.
- 14 Aug 2019
- The National Academies Decadal Strategy And Nasa Have Identified Critical Earth Observations Including Surface Deformation And Change And Clouds, Convection And Precipitation. These Observations Are Well Suited To Synthetic Aperture Radar Instruments. The Missions Span Operating Frequencies From L To Ka Band. Precision Mesh Reflectors Are Uniquely Suited To Provide Large Frequency Bandwidth While Maintaining Small Packaging Forms With Low Mass. Tendeg Proposes To Create A Cylindrical Parabolic Reflector That Can Be Used Across Many Missions. This Will Include The Ability To Operate At Frequencies Up To 36 Ghz While Maintaining The Ability To Operate At Frequencies Down To L-Band. This Will Allow The Proposed Reflector To Operate With Current Multi Array Feeds, Or Scanning Phased Array Feeds, Of Different Frequencies On The Same Vehicle. This In Turn Will Allow Buses Equipped With This Reflector To Carry Out Several Of The Decadal Proposed Missions Which Require Sar Technologies. The Proposed Baseline Design Is A 5:1 Aspect Ratio Aperture That Will Be A 1 X 5M Deployed Effective Aperture. The Proposed Design Is Scalable To Larger Apertures And Can Accommodate A Fixed Feed With Either Center Fed Or Offset Fed Apertures. The Antenna Has High Structural Stability Which Results In High On-Orbit Resonance Frequencies, Precision Deployment Repeatability, Low Distortions Due To On-Orbit Temperatures And Ability To Accurately Rf Test In 1G. The Proposed Design Would Leverage Technologies Already Developed By Tendeg As Part Of Previous Sbir Activities.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $749,968.00
- National Aeronautics And Space Administration (Nasa)
- NNX17CP01C
- The Proposed Phase Ii Program Would Develop And Prototype A High Frequency, High Performance Reflective Mesh That Is Well Suited To The Emerging Small Aperture Antenna Designs.
- 22 Jul 2019
- The Proposed Phase Ii Program Would Develop And Prototype A High Frequency, High Performance Reflective Mesh That Is Well Suited To The Emerging Small Aperture Antenna Designs.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $749,991.00
- National Aeronautics And Space Administration (Nasa)
- NNX17CP09C
- Igf::Ot::Igf The Proposed Phase Ii Program Will Refine And Mature The Design Of The Optical Edge, Optical Shield And Snubber Assemblies Within A Starshade Petal. Prototypes Of Each Sub-Assembly Will Be Built And Tested After A Rigorous Trade Study. The Final Sub-Assembly Designs Will Be Built And Integrated To A Complete Petal Assembly That Utilizes Flight-Like Materials And Fabrication Processes. The Full Petal Assembly Will Be Tested To Demonstrate Survival To Launch Packaging And Temperature Extremes. A Segment Of A Petal Will Be Delivered To Nasa Jpl For Thermal Distortion And Stability Tests. More Specifically, The Optical Edge Assembly Efforts Will Address The Integration Of A Micro-Thin Metal Alloy To A Low Cte Composite Substrate And The Alignment And Handling Procedures Required To Accurately Position Each Segment To The Petal Structure. The Optical Shield Effort Will Address Opacity, Thermal Expansion, Micrometeoroid Mitigation And Venting. The Snubber Effort Will Address Preload, Alignment And Support For The Petals In The Furled And Launch Configuration.
- 3 Jun 2018
- Igf::Ot::Igf The Proposed Phase Ii Program Will Refine And Mature The Design Of The Optical Edge, Optical Shield And Snubber Assemblies Within A Starshade Petal. Prototypes Of Each Sub-Assembly Will Be Built And Tested After A Rigorous Trade Study. The Final Sub-Assembly Designs Will Be Built And Integrated To A Complete Petal Assembly That Utilizes Flight-Like Materials And Fabrication Processes. The Full Petal Assembly Will Be Tested To Demonstrate Survival To Launch Packaging And Temperature Extremes. A Segment Of A Petal Will Be Delivered To Nasa Jpl For Thermal Distortion And Stability Tests. More Specifically, The Optical Edge Assembly Efforts Will Address The Integration Of A Micro-Thin Metal Alloy To A Low Cte Composite Substrate And The Alignment And Handling Procedures Required To Accurately Position Each Segment To The Petal Structure. The Optical Shield Effort Will Address Opacity, Thermal Expansion, Micrometeoroid Mitigation And Venting. The Snubber Effort Will Address Preload, Alignment And Support For The Petals In The Furled And Launch Configuration.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $1,124,951.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC19C0146
- Eo14042 Phase Ii P00006 High Aspect Ratio Cylindrical Parabolic Antenna For Microsats
- 15 Sep 2022
- Eo14042 Phase Ii P00006 High Aspect Ratio Cylindrical Parabolic Antenna For Microsats
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $1,124,968.00
- National Aeronautics And Space Administration (Nasa)
- NNX17CP09C
- Igf::Ot::Igf The Proposed Phase Ii Program Will Refine And Mature The Design Of The Optical Edge, Optical Shield And Snubber Assemblies Within A Starshade Petal. Prototypes Of Each Sub-Assembly Will Be Built And Tested After A Rigorous Trade Study. The Final Sub-Assembly Designs Will Be Built And Integrated To A Complete Petal Assembly That Utilizes Flight-Like Materials And Fabrication Processes. The Full Petal Assembly Will Be Tested To Demonstrate Survival To Launch Packaging And Temperature Extremes. A Segment Of A Petal Will Be Delivered To Nasa Jpl For Thermal Distortion And Stability Tests. More Specifically, The Optical Edge Assembly Efforts Will Address The Integration Of A Micro-Thin Metal Alloy To A Low Cte Composite Substrate And The Alignment And Handling Procedures Required To Accurately Position Each Segment To The Petal Structure. The Optical Shield Effort Will Address Opacity, Thermal Expansion, Micrometeoroid Mitigation And Venting. The Snubber Effort Will Address Preload, Alignment And Support For The Petals In The Furled And Launch Configuration.
- 3 Jun 2018
- Igf::Ot::Igf The Proposed Phase Ii Program Will Refine And Mature The Design Of The Optical Edge, Optical Shield And Snubber Assemblies Within A Starshade Petal. Prototypes Of Each Sub-Assembly Will Be Built And Tested After A Rigorous Trade Study. The Final Sub-Assembly Designs Will Be Built And Integrated To A Complete Petal Assembly That Utilizes Flight-Like Materials And Fabrication Processes. The Full Petal Assembly Will Be Tested To Demonstrate Survival To Launch Packaging And Temperature Extremes. A Segment Of A Petal Will Be Delivered To Nasa Jpl For Thermal Distortion And Stability Tests. More Specifically, The Optical Edge Assembly Efforts Will Address The Integration Of A Micro-Thin Metal Alloy To A Low Cte Composite Substrate And The Alignment And Handling Procedures Required To Accurately Position Each Segment To The Petal Structure. The Optical Shield Effort Will Address Opacity, Thermal Expansion, Micrometeoroid Mitigation And Venting. The Snubber Effort Will Address Preload, Alignment And Support For The Petals In The Furled And Launch Configuration.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $749,980.00
- National Aeronautics And Space Administration (Nasa)
- NNX17CP09C
- The Proposed Phase Ii Program Will Refine And Mature The Design Of The Optical Edge, Optical Shield And Snubber Assemblies Within A Starshade Petal. Prototypes Of Each Sub-Assembly Will Be Built And Tested After A Rigorous Trade Study. The Final Sub-Assembly Designs Will Be Built And Integrated To A Complete Petal Assembly That Utilizes Flight-Like Materials And Fabrication Processes. The Full Petal Assembly Will Be Tested To Demonstrate Survival To Launch Packaging And Temperature Extremes. A Segment Of A Petal Will Be Delivered To Nasa Jpl For Thermal Distortion And Stability Tests. More Specifically, The Optical Edge Assembly Efforts Will Address The Integration Of A Micro-Thin Metal Alloy To A Low Cte Composite Substrate And The Alignment And Handling Procedures Required To Accurately Position Each Segment To The Petal Structure. The Optical Shield Effort Will Address Opacity, Thermal Expansion, Micrometeoroid Mitigation And Venting. The Snubber Effort Will Address Preload, Alignment And Support For The Petals In The Furled And Launch Configuration.
- 27 Sep 2019
- The Proposed Phase Ii Program Will Refine And Mature The Design Of The Optical Edge, Optical Shield And Snubber Assemblies Within A Starshade Petal. Prototypes Of Each Sub-Assembly Will Be Built And Tested After A Rigorous Trade Study. The Final Sub-Assembly Designs Will Be Built And Integrated To A Complete Petal Assembly That Utilizes Flight-Like Materials And Fabrication Processes. The Full Petal Assembly Will Be Tested To Demonstrate Survival To Launch Packaging And Temperature Extremes. A Segment Of A Petal Will Be Delivered To Nasa Jpl For Thermal Distortion And Stability Tests. More Specifically, The Optical Edge Assembly Efforts Will Address The Integration Of A Micro-Thin Metal Alloy To A Low Cte Composite Substrate And The Alignment And Handling Procedures Required To Accurately Position Each Segment To The Petal Structure. The Optical Shield Effort Will Address Opacity, Thermal Expansion, Micrometeoroid Mitigation And Venting. The Snubber Effort Will Address Preload, Alignment And Support For The Petals In The Furled And Launch Configuration.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $1,124,951.00
- National Aeronautics And Space Administration (Nasa)
- NNX17CP18C
- Modification Of Pop And Amount
- 29 Feb 2020
- Modification Of Pop And Amount
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $1,124,835.00
- National Aeronautics And Space Administration (Nasa)
- NNX16CP04C
- In These Days Of Tight Budgets And Limited Funding, Nasa Is Constantly Looking For New Ways To Reduce Development Time And Costs Of Future Spacecraft.
- 27 Mar 2020
- In These Days Of Tight Budgets And Limited Funding, Nasa Is Constantly Looking For New Ways To Reduce Development Time And Costs Of Future Spacecraft.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $749,968.00
- National Aeronautics And Space Administration (Nasa)