S. D. Miller And Associates P.L.L.C.
CAGE Code: 4LCQ5
NCAGE Code: 4LCQ5
Status: Active
Type: Commercial Supplier
Dun & Bradstreet (DUNS): 932699192
Summary
S. D. Miller And Associates P.L.L.C. is an Active Commercial Supplier with the Cage Code 4LCQ5 and is tracked by Dun & Bradstreet under DUNS Number 932699192..
Address
216 W Cherry Ave
Flagstaff AZ 86001-4424
United States
Points of Contact
No Points of Contact...
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Frequently Asked Questions (FAQ) for CAGE 4LCQ5
- What is CAGE Code 4LCQ5?
- 4LCQ5 is the unique identifier used by NATO Organizations to reference the physical entity known as S. D. Miller And Associates P.L.L.C. located at 216 W Cherry Ave, Flagstaff AZ 86001-4424, United States.
- Who is CAGE Code 4LCQ5?
- 4LCQ5 refers to S. D. Miller And Associates P.L.L.C. located at 216 W Cherry Ave, Flagstaff AZ 86001-4424, United States.
- Where is CAGE Code 4LCQ5 Located?
- CAGE Code 4LCQ5 is located in Flagstaff, AZ, USA.
Contracting History for CAGE 4LCQ5 Most Recent 25 Records
- 80NSSC19C0052
- The Current Effort To Demonstrate That A Thin, Flexible Aerogel Insulation Can Be Produced Using Paper-Making Methods Has Gone Quite Well. Recent Data Indicates That A 100 Foot Length Of Insulation Made By This Method Is Consistent From Start To Finish, And That The Same Insulation Can Be Duplicated Several Months Later In A Separate Run. The Thermal Conductivity Appears To Be As Good Or Better Than Offthe- Shelf (Ots) Aerogel Insulations That Are Thicker And Less Flexible. This Success Follows Hundreds Of Experiments To First Demonstrate A Good Insulation Recipe Using Single Sheet Molds In The Laboratory, Followed By Pilot Runs On A 12-Inch Wide System To Demonstrate That The Recipe Could Be Run In A Continuous Process. Because The Insulation Is Only 0.5 Mm Thick, Its Not Nearly As Strong As The 5 Mm Thick Ots Insulation Used As Our Benchmark. As A Remedy, We Have Added Scrim To The Insulation In Short Sections By Hand In The Manufacturing Process. While This Solved The Strength Problem, It Is A Step Backwards In Terms Of Manufacturing Readiness Because Scrim Is Now Fed By Hand Into A Process That Is Otherwise Machine Controlled. The Final Steps Needed To Demonstrate That The Technology Can Be Scaled Is To A) Produce The Insulation With A Scrim In A Continuous Process And B) Produce The Insulation In A Wider Width On A Production System. Demonstrating These Capabilities Is The Goal Of This Proposed Phase Ii-X Effort.
- 14 Apr 2020
- The Current Effort To Demonstrate That A Thin, Flexible Aerogel Insulation Can Be Produced Using Paper-Making Methods Has Gone Quite Well. Recent Data Indicates That A 100 Foot Length Of Insulation Made By This Method Is Consistent From Start To Finish, And That The Same Insulation Can Be Duplicated Several Months Later In A Separate Run. The Thermal Conductivity Appears To Be As Good Or Better Than Offthe- Shelf (Ots) Aerogel Insulations That Are Thicker And Less Flexible. This Success Follows Hundreds Of Experiments To First Demonstrate A Good Insulation Recipe Using Single Sheet Molds In The Laboratory, Followed By Pilot Runs On A 12-Inch Wide System To Demonstrate That The Recipe Could Be Run In A Continuous Process. Because The Insulation Is Only 0.5 Mm Thick, Its Not Nearly As Strong As The 5 Mm Thick Ots Insulation Used As Our Benchmark. As A Remedy, We Have Added Scrim To The Insulation In Short Sections By Hand In The Manufacturing Process. While This Solved The Strength Problem, It Is A Step Backwards In Terms Of Manufacturing Readiness Because Scrim Is Now Fed By Hand Into A Process That Is Otherwise Machine Controlled. The Final Steps Needed To Demonstrate That The Technology Can Be Scaled Is To A) Produce The Insulation With A Scrim In A Continuous Process And B) Produce The Insulation In A Wider Width On A Production System. Demonstrating These Capabilities Is The Goal Of This Proposed Phase Ii-X Effort.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $75,000.00
- National Aeronautics And Space Administration (Nasa)
- NNX16CL26C
- Igf::Ot::Igf Gas Conduction And Radiation Are The Two Important Heat Transfer Mechanisms In Highly Porous Reusable Thermal Protection Systems Used For Planetary Entry Of Space Vehicles. The Relative Magnitude Of The Two Varies Depending On Altitude, Temperature And The Planet. Usually Radiation Is More Significant At Lower Pressures And At Higher Temperatures. Gas Conduction Is More Dominant At Higher Pressures And Lower Temperatures. In Most Planetary Entries, Both Modes Of Heat Transfer Are Significant. Typical Flexible Or Rigid Refractory Ceramic Fiber Thermal Protection System (Tps) Such As Advanced Flexible Reusable Surface Insulation (Afrsi) And Shuttle Tiles Can Take High Temperatures, Can Reduce Gas Conduction At Lower Pressures, And Scatter Radiation At Higher Temperatures. There Is A Need For More Efficient Tps With Lower Mass, Reduced Thickness And Significantly Lower Thermal Conductivity To Make Inter Planetary Missions Possible. In Order To Achieve This Goal, Insulations Need To Be Developed That Can Further Reduce Gas Conduction And Radiation Heat Transfer Compared To Standard Refractory Ceramic Fiber Insulations. The Overall Objective Of The Phase Ii Program Is To Migrate And Optimize Proven Paper Making Concepts To Fabricate Robust, Flexible And Cost Efficient, Fiber Reinforced Aerogels, Without Sacrificing The Thermal And Mechanical Qualities, In Large Sections Suitable For Application On High Speed Vehicles (Hsv?S). Further Investigation In Phase Ii Would Focus On Production Methods And Recipe Optimization For This New Class Of Thermal Insulations. Embedding Materials With Advantageous Properties Into Fibrous Mats Allows Tailoring The Temperature And Flexibility Requirements To Meet The Needs Of Specific Missions.
- 31 May 2019
- Igf::Ot::Igf Gas Conduction And Radiation Are The Two Important Heat Transfer Mechanisms In Highly Porous Reusable Thermal Protection Systems Used For Planetary Entry Of Space Vehicles. The Relative Magnitude Of The Two Varies Depending On Altitude, Temperature And The Planet. Usually Radiation Is More Significant At Lower Pressures And At Higher Temperatures. Gas Conduction Is More Dominant At Higher Pressures And Lower Temperatures. In Most Planetary Entries, Both Modes Of Heat Transfer Are Significant. Typical Flexible Or Rigid Refractory Ceramic Fiber Thermal Protection System (Tps) Such As Advanced Flexible Reusable Surface Insulation (Afrsi) And Shuttle Tiles Can Take High Temperatures, Can Reduce Gas Conduction At Lower Pressures, And Scatter Radiation At Higher Temperatures. There Is A Need For More Efficient Tps With Lower Mass, Reduced Thickness And Significantly Lower Thermal Conductivity To Make Inter Planetary Missions Possible. In Order To Achieve This Goal, Insulations Need To Be Developed That Can Further Reduce Gas Conduction And Radiation Heat Transfer Compared To Standard Refractory Ceramic Fiber Insulations. The Overall Objective Of The Phase Ii Program Is To Migrate And Optimize Proven Paper Making Concepts To Fabricate Robust, Flexible And Cost Efficient, Fiber Reinforced Aerogels, Without Sacrificing The Thermal And Mechanical Qualities, In Large Sections Suitable For Application On High Speed Vehicles (Hsv?S). Further Investigation In Phase Ii Would Focus On Production Methods And Recipe Optimization For This New Class Of Thermal Insulations. Embedding Materials With Advantageous Properties Into Fibrous Mats Allows Tailoring The Temperature And Flexibility Requirements To Meet The Needs Of Specific Missions.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $904,609.00
- National Aeronautics And Space Administration (Nasa)
- FA955018C0003
- Igf::Ot::Igf "Sbir Phase 2- Heterogeneous Porous Media For Thermal Transport Mitigation In Hypersonics"
- 30 Nov 2017
- Igf::Ot::Igf "Sbir Phase 2- Heterogeneous Porous Media For Thermal Transport Mitigation In Hypersonics"
- Fa9550 Afrl Afosr
- Department Of Defense (Dod)
- $749,877.00
- Department Of Defense (Dod)
- 80NSSC19C0052
- The Current Effort To Demonstrate That A Thin, Flexible Aerogel Insulation Can Be Produced Using Paper-Making Methods Has Gone Quite Well. Recent Data Indicates That A 100 Foot Length Of Insulation Made By This Method Is Consistent From Start To Finish, And That The Same Insulation Can Be Duplicated Several Months Later In A Separate Run. The Thermal Conductivity Appears To Be As Good Or Better Than Offthe- Shelf (Ots) Aerogel Insulations That Are Thicker And Less Flexible. This Success Follows Hundreds Of Experiments To First Demonstrate A Good Insulation Recipe Using Single Sheet Molds In The Laboratory, Followed By Pilot Runs On A 12-Inch Wide System To Demonstrate That The Recipe Could Be Run In A Continuous Process. Because The Insulation Is Only 0.5 Mm Thick, Its Not Nearly As Strong As The 5 Mm Thick Ots Insulation Used As Our Benchmark. As A Remedy, We Have Added Scrim To The Insulation In Short Sections By Hand In The Manufacturing Process. While This Solved The Strength Problem, It Is A Step Backwards In Terms Of Manufacturing Readiness Because Scrim Is Now Fed By Hand Into A Process That Is Otherwise Machine Controlled. The Final Steps Needed To Demonstrate That The Technology Can Be Scaled Is To A) Produce The Insulation With A Scrim In A Continuous Process And B) Produce The Insulation In A Wider Width On A Production System. Demonstrating These Capabilities Is The Goal Of This Proposed Phase Ii-X Effort.
- 8 Jul 2020
- The Current Effort To Demonstrate That A Thin, Flexible Aerogel Insulation Can Be Produced Using Paper-Making Methods Has Gone Quite Well. Recent Data Indicates That A 100 Foot Length Of Insulation Made By This Method Is Consistent From Start To Finish, And That The Same Insulation Can Be Duplicated Several Months Later In A Separate Run. The Thermal Conductivity Appears To Be As Good Or Better Than Offthe- Shelf (Ots) Aerogel Insulations That Are Thicker And Less Flexible. This Success Follows Hundreds Of Experiments To First Demonstrate A Good Insulation Recipe Using Single Sheet Molds In The Laboratory, Followed By Pilot Runs On A 12-Inch Wide System To Demonstrate That The Recipe Could Be Run In A Continuous Process. Because The Insulation Is Only 0.5 Mm Thick, Its Not Nearly As Strong As The 5 Mm Thick Ots Insulation Used As Our Benchmark. As A Remedy, We Have Added Scrim To The Insulation In Short Sections By Hand In The Manufacturing Process. While This Solved The Strength Problem, It Is A Step Backwards In Terms Of Manufacturing Readiness Because Scrim Is Now Fed By Hand Into A Process That Is Otherwise Machine Controlled. The Final Steps Needed To Demonstrate That The Technology Can Be Scaled Is To A) Produce The Insulation With A Scrim In A Continuous Process And B) Produce The Insulation In A Wider Width On A Production System. Demonstrating These Capabilities Is The Goal Of This Proposed Phase Ii-X Effort.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $125,000.00
- National Aeronautics And Space Administration (Nasa)
- NNX16CL26C
- Gas Conduction And Radiation Are The Two Important Heat Transfer Mechanisms In Highly Porous Reusable Thermal Protection Systems Used For Planetary Entry Of Space Vehicles. The Relative Magnitude Of The Two Varies Depending On Altitude, Temperature And The Planet. Usually Radiation Is More Significant At Lower Pressures And At Higher Temperatures. Gas Conduction Is More Dominant At Higher Pressures And Lower Temperatures. In Most Planetary Entries, Both Modes Of Heat Transfer Are Significant. Typical Flexible Or Rigid Refractory Ceramic Fiber Thermal Protection System (Tps) Such As Advanced Flexible Reusable Surface Insulation (Afrsi) And Shuttle Tiles Can Take High Temperatures, Can Reduce Gas Conduction At Lower Pressures, And Scatter Radiation At Higher Temperatures. There Is A Need For More Efficient Tps With Lower Mass, Reduced Thickness And Significantly Lower Thermal Conductivity To Make Inter Planetary Missions Possible. In Order To Achieve This Goal, Insulations Need To Be Developed That Can Further Reduce Gas Conduction And Radiation Heat Transfer Compared To Standard Refractory Ceramic Fiber Insulations. The Overall Objective Of The Phase Ii Program Is To Migrate And Optimize Proven Paper Making Concepts To Fabricate Robust, Flexible And Cost Efficient, Fiber Reinforced Aerogels, Without Sacrificing The Thermal And Mechanical Qualities, In Large Sections Suitable For Application On High Speed Vehicles (Hsv?S). Further Investigation In Phase Ii Would Focus On Production Methods And Recipe Optimization For This New Class Of Thermal Insulations. Embedding Materials With Advantageous Properties Into Fibrous Mats Allows Tailoring The Temperature And Flexibility Requirements To Meet The Needs Of Specific Missions.
- 18 Aug 2020
- Gas Conduction And Radiation Are The Two Important Heat Transfer Mechanisms In Highly Porous Reusable Thermal Protection Systems Used For Planetary Entry Of Space Vehicles. The Relative Magnitude Of The Two Varies Depending On Altitude, Temperature And The Planet. Usually Radiation Is More Significant At Lower Pressures And At Higher Temperatures. Gas Conduction Is More Dominant At Higher Pressures And Lower Temperatures. In Most Planetary Entries, Both Modes Of Heat Transfer Are Significant. Typical Flexible Or Rigid Refractory Ceramic Fiber Thermal Protection System (Tps) Such As Advanced Flexible Reusable Surface Insulation (Afrsi) And Shuttle Tiles Can Take High Temperatures, Can Reduce Gas Conduction At Lower Pressures, And Scatter Radiation At Higher Temperatures. There Is A Need For More Efficient Tps With Lower Mass, Reduced Thickness And Significantly Lower Thermal Conductivity To Make Inter Planetary Missions Possible. In Order To Achieve This Goal, Insulations Need To Be Developed That Can Further Reduce Gas Conduction And Radiation Heat Transfer Compared To Standard Refractory Ceramic Fiber Insulations. The Overall Objective Of The Phase Ii Program Is To Migrate And Optimize Proven Paper Making Concepts To Fabricate Robust, Flexible And Cost Efficient, Fiber Reinforced Aerogels, Without Sacrificing The Thermal And Mechanical Qualities, In Large Sections Suitable For Application On High Speed Vehicles (Hsv?S). Further Investigation In Phase Ii Would Focus On Production Methods And Recipe Optimization For This New Class Of Thermal Insulations. Embedding Materials With Advantageous Properties Into Fibrous Mats Allows Tailoring The Temperature And Flexibility Requirements To Meet The Needs Of Specific Missions.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $904,609.00
- National Aeronautics And Space Administration (Nasa)
- NNX16CL26C
- Gas Conduction And Radiation Are The Two Important Heat Transfer Mechanisms In Highly Porous Reusable Thermal Protection Systems Used For Planetary Entry Of Space Vehicles.
- 29 Nov 2020
- Gas Conduction And Radiation Are The Two Important Heat Transfer Mechanisms In Highly Porous Reusable Thermal Protection Systems Used For Planetary Entry Of Space Vehicles.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $904,609.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC19C0052
- The Current Effort To Demonstrate That A Thin, Flexible Aerogel Insulation Can Be Produced Using Paper-Making Methods Has Gone Quite Well. Recent Data Indicates That A 100 Foot Length Of Insulation Made By This Method Is Consistent From Start To Finish, And That The Same Insulation Can Be Duplicated Several Months Later In A Separate Run. The Thermal Conductivity Appears To Be As Good Or Better Than Offthe- Shelf (Ots) Aerogel Insulations That Are Thicker And Less Flexible. This Success Follows Hundreds Of Experiments To First Demonstrate A Good Insulation Recipe Using Single Sheet Molds In The Laboratory, Followed By Pilot Runs On A 12-Inch Wide System To Demonstrate That The Recipe Could Be Run In A Continuous Process. Because The Insulation Is Only 0.5 Mm Thick, Its Not Nearly As Strong As The 5 Mm Thick Ots Insulation Used As Our Benchmark. As A Remedy, We Have Added Scrim To The Insulation In Short Sections By Hand In The Manufacturing Process. While This Solved The Strength Problem, It Is A Step Backwards In Terms Of Manufacturing Readiness Because Scrim Is Now Fed By Hand Into A Process That Is Otherwise Machine Controlled. The Final Steps Needed To Demonstrate That The Technology Can Be Scaled Is To A) Produce The Insulation With A Scrim In A Continuous Process And B) Produce The Insulation In A Wider Width On A Production System. Demonstrating These Capabilities Is The Goal Of This Proposed Phase Ii-X Effort.
- 9 May 2019
- The Current Effort To Demonstrate That A Thin, Flexible Aerogel Insulation Can Be Produced Using Paper-Making Methods Has Gone Quite Well. Recent Data Indicates That A 100 Foot Length Of Insulation Made By This Method Is Consistent From Start To Finish, And That The Same Insulation Can Be Duplicated Several Months Later In A Separate Run. The Thermal Conductivity Appears To Be As Good Or Better Than Offthe- Shelf (Ots) Aerogel Insulations That Are Thicker And Less Flexible. This Success Follows Hundreds Of Experiments To First Demonstrate A Good Insulation Recipe Using Single Sheet Molds In The Laboratory, Followed By Pilot Runs On A 12-Inch Wide System To Demonstrate That The Recipe Could Be Run In A Continuous Process. Because The Insulation Is Only 0.5 Mm Thick, Its Not Nearly As Strong As The 5 Mm Thick Ots Insulation Used As Our Benchmark. As A Remedy, We Have Added Scrim To The Insulation In Short Sections By Hand In The Manufacturing Process. While This Solved The Strength Problem, It Is A Step Backwards In Terms Of Manufacturing Readiness Because Scrim Is Now Fed By Hand Into A Process That Is Otherwise Machine Controlled. The Final Steps Needed To Demonstrate That The Technology Can Be Scaled Is To A) Produce The Insulation With A Scrim In A Continuous Process And B) Produce The Insulation In A Wider Width On A Production System. Demonstrating These Capabilities Is The Goal Of This Proposed Phase Ii-X Effort.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $125,000.00
- National Aeronautics And Space Administration (Nasa)
- NNX16CL26C
- Igf::Ot::Igf Gas Conduction And Radiation Are The Two Important Heat Transfer Mechanisms In Highly Porous Reusable Thermal Protection Systems Used For Planetary Entry Of Space Vehicles. The Relative Magnitude Of The Two Varies Depending On Altitude, Temperature And The Planet. Usually Radiation Is More Significant At Lower Pressures And At Higher Temperatures. Gas Conduction Is More Dominant At Higher Pressures And Lower Temperatures. In Most Planetary Entries, Both Modes Of Heat Transfer Are Significant. Typical Flexible Or Rigid Refractory Ceramic Fiber Thermal Protection System (Tps) Such As Advanced Flexible Reusable Surface Insulation (Afrsi) And Shuttle Tiles Can Take High Temperatures, Can Reduce Gas Conduction At Lower Pressures, And Scatter Radiation At Higher Temperatures. There Is A Need For More Efficient Tps With Lower Mass, Reduced Thickness And Significantly Lower Thermal Conductivity To Make Inter Planetary Missions Possible. In Order To Achieve This Goal, Insulations Need To Be Developed That Can Further Reduce Gas Conduction And Radiation Heat Transfer Compared To Standard Refractory Ceramic Fiber Insulations. The Overall Objective Of The Phase Ii Program Is To Migrate And Optimize Proven Paper Making Concepts To Fabricate Robust, Flexible And Cost Efficient, Fiber Reinforced Aerogels, Without Sacrificing The Thermal And Mechanical Qualities, In Large Sections Suitable For Application On High Speed Vehicles (Hsv?S). Further Investigation In Phase Ii Would Focus On Production Methods And Recipe Optimization For This New Class Of Thermal Insulations. Embedding Materials With Advantageous Properties Into Fibrous Mats Allows Tailoring The Temperature And Flexibility Requirements To Meet The Needs Of Specific Missions.
- 27 Aug 2018
- Igf::Ot::Igf Gas Conduction And Radiation Are The Two Important Heat Transfer Mechanisms In Highly Porous Reusable Thermal Protection Systems Used For Planetary Entry Of Space Vehicles. The Relative Magnitude Of The Two Varies Depending On Altitude, Temperature And The Planet. Usually Radiation Is More Significant At Lower Pressures And At Higher Temperatures. Gas Conduction Is More Dominant At Higher Pressures And Lower Temperatures. In Most Planetary Entries, Both Modes Of Heat Transfer Are Significant. Typical Flexible Or Rigid Refractory Ceramic Fiber Thermal Protection System (Tps) Such As Advanced Flexible Reusable Surface Insulation (Afrsi) And Shuttle Tiles Can Take High Temperatures, Can Reduce Gas Conduction At Lower Pressures, And Scatter Radiation At Higher Temperatures. There Is A Need For More Efficient Tps With Lower Mass, Reduced Thickness And Significantly Lower Thermal Conductivity To Make Inter Planetary Missions Possible. In Order To Achieve This Goal, Insulations Need To Be Developed That Can Further Reduce Gas Conduction And Radiation Heat Transfer Compared To Standard Refractory Ceramic Fiber Insulations. The Overall Objective Of The Phase Ii Program Is To Migrate And Optimize Proven Paper Making Concepts To Fabricate Robust, Flexible And Cost Efficient, Fiber Reinforced Aerogels, Without Sacrificing The Thermal And Mechanical Qualities, In Large Sections Suitable For Application On High Speed Vehicles (Hsv?S). Further Investigation In Phase Ii Would Focus On Production Methods And Recipe Optimization For This New Class Of Thermal Insulations. Embedding Materials With Advantageous Properties Into Fibrous Mats Allows Tailoring The Temperature And Flexibility Requirements To Meet The Needs Of Specific Missions.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $754,609.00
- National Aeronautics And Space Administration (Nasa)
- NNX16CL26C
- Igf::Ot::Igf Gas Conduction And Radiation Are The Two Important Heat Transfer Mechanisms In Highly Porous Reusable Thermal Protection Systems Used For Planetary Entry Of Space Vehicles. The Relative Magnitude Of The Two Varies Depending On Altitude, Temperature And The Planet. Usually Radiation Is More Significant At Lower Pressures And At Higher Temperatures. Gas Conduction Is More Dominant At Higher Pressures And Lower Temperatures. In Most Planetary Entries, Both Modes Of Heat Transfer Are Significant. Typical Flexible Or Rigid Refractory Ceramic Fiber Thermal Protection System (Tps) Such As Advanced Flexible Reusable Surface Insulation (Afrsi) And Shuttle Tiles Can Take High Temperatures, Can Reduce Gas Conduction At Lower Pressures, And Scatter Radiation At Higher Temperatures. There Is A Need For More Efficient Tps With Lower Mass, Reduced Thickness And Significantly Lower Thermal Conductivity To Make Inter Planetary Missions Possible. In Order To Achieve This Goal, Insulations Need To Be Developed That Can Further Reduce Gas Conduction And Radiation Heat Transfer Compared To Standard Refractory Ceramic Fiber Insulations. The Overall Objective Of The Phase Ii Program Is To Migrate And Optimize Proven Paper Making Concepts To Fabricate Robust, Flexible And Cost Efficient, Fiber Reinforced Aerogels, Without Sacrificing The Thermal And Mechanical Qualities, In Large Sections Suitable For Application On High Speed Vehicles (Hsv?S). Further Investigation In Phase Ii Would Focus On Production Methods And Recipe Optimization For This New Class Of Thermal Insulations. Embedding Materials With Advantageous Properties Into Fibrous Mats Allows Tailoring The Temperature And Flexibility Requirements To Meet The Needs Of Specific Missions.
- 13 May 2019
- Igf::Ot::Igf Gas Conduction And Radiation Are The Two Important Heat Transfer Mechanisms In Highly Porous Reusable Thermal Protection Systems Used For Planetary Entry Of Space Vehicles. The Relative Magnitude Of The Two Varies Depending On Altitude, Temperature And The Planet. Usually Radiation Is More Significant At Lower Pressures And At Higher Temperatures. Gas Conduction Is More Dominant At Higher Pressures And Lower Temperatures. In Most Planetary Entries, Both Modes Of Heat Transfer Are Significant. Typical Flexible Or Rigid Refractory Ceramic Fiber Thermal Protection System (Tps) Such As Advanced Flexible Reusable Surface Insulation (Afrsi) And Shuttle Tiles Can Take High Temperatures, Can Reduce Gas Conduction At Lower Pressures, And Scatter Radiation At Higher Temperatures. There Is A Need For More Efficient Tps With Lower Mass, Reduced Thickness And Significantly Lower Thermal Conductivity To Make Inter Planetary Missions Possible. In Order To Achieve This Goal, Insulations Need To Be Developed That Can Further Reduce Gas Conduction And Radiation Heat Transfer Compared To Standard Refractory Ceramic Fiber Insulations. The Overall Objective Of The Phase Ii Program Is To Migrate And Optimize Proven Paper Making Concepts To Fabricate Robust, Flexible And Cost Efficient, Fiber Reinforced Aerogels, Without Sacrificing The Thermal And Mechanical Qualities, In Large Sections Suitable For Application On High Speed Vehicles (Hsv?S). Further Investigation In Phase Ii Would Focus On Production Methods And Recipe Optimization For This New Class Of Thermal Insulations. Embedding Materials With Advantageous Properties Into Fibrous Mats Allows Tailoring The Temperature And Flexibility Requirements To Meet The Needs Of Specific Missions.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $754,609.00
- National Aeronautics And Space Administration (Nasa)
- NNX16CL26C
- Gas Conduction And Radiation Are The Two Important Heat Transfer Mechanisms In Highly Porous Reusable Thermal Protection Systems Used For Planetary Entry Of Space Vehicles. The Relative Magnitude Of The Two Varies Depending On Altitude, Temperature And The Planet. Usually Radiation Is More Significant At Lower Pressures And At Higher Temperatures. Gas Conduction Is More Dominant At Higher Pressures And Lower Temperatures. In Most Planetary Entries, Both Modes Of Heat Transfer Are Significant. Typical Flexible Or Rigid Refractory Ceramic Fiber Thermal Protection System (Tps) Such As Advanced Flexible Reusable Surface Insulation (Afrsi) And Shuttle Tiles Can Take High Temperatures, Can Reduce Gas Conduction At Lower Pressures, And Scatter Radiation At Higher Temperatures. There Is A Need For More Efficient Tps With Lower Mass, Reduced Thickness And Significantly Lower Thermal Conductivity To Make Inter Planetary Missions Possible. In Order To Achieve This Goal, Insulations Need To Be Developed That Can Further Reduce Gas Conduction And Radiation Heat Transfer Compared To Standard Refractory Ceramic Fiber Insulations. The Overall Objective Of The Phase Ii Program Is To Migrate And Optimize Proven Paper Making Concepts To Fabricate Robust, Flexible And Cost Efficient, Fiber Reinforced Aerogels, Without Sacrificing The Thermal And Mechanical Qualities, In Large Sections Suitable For Application On High Speed Vehicles (Hsv?S). Further Investigation In Phase Ii Would Focus On Production Methods And Recipe Optimization For This New Class Of Thermal Insulations. Embedding Materials With Advantageous Properties Into Fibrous Mats Allows Tailoring The Temperature And Flexibility Requirements To Meet The Needs Of Specific Missions.
- 14 Apr 2020
- Gas Conduction And Radiation Are The Two Important Heat Transfer Mechanisms In Highly Porous Reusable Thermal Protection Systems Used For Planetary Entry Of Space Vehicles. The Relative Magnitude Of The Two Varies Depending On Altitude, Temperature And The Planet. Usually Radiation Is More Significant At Lower Pressures And At Higher Temperatures. Gas Conduction Is More Dominant At Higher Pressures And Lower Temperatures. In Most Planetary Entries, Both Modes Of Heat Transfer Are Significant. Typical Flexible Or Rigid Refractory Ceramic Fiber Thermal Protection System (Tps) Such As Advanced Flexible Reusable Surface Insulation (Afrsi) And Shuttle Tiles Can Take High Temperatures, Can Reduce Gas Conduction At Lower Pressures, And Scatter Radiation At Higher Temperatures. There Is A Need For More Efficient Tps With Lower Mass, Reduced Thickness And Significantly Lower Thermal Conductivity To Make Inter Planetary Missions Possible. In Order To Achieve This Goal, Insulations Need To Be Developed That Can Further Reduce Gas Conduction And Radiation Heat Transfer Compared To Standard Refractory Ceramic Fiber Insulations. The Overall Objective Of The Phase Ii Program Is To Migrate And Optimize Proven Paper Making Concepts To Fabricate Robust, Flexible And Cost Efficient, Fiber Reinforced Aerogels, Without Sacrificing The Thermal And Mechanical Qualities, In Large Sections Suitable For Application On High Speed Vehicles (Hsv?S). Further Investigation In Phase Ii Would Focus On Production Methods And Recipe Optimization For This New Class Of Thermal Insulations. Embedding Materials With Advantageous Properties Into Fibrous Mats Allows Tailoring The Temperature And Flexibility Requirements To Meet The Needs Of Specific Missions.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $904,609.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC19C0052
- The Current Effort To Demonstrate That A Thin, Flexible Aerogel Insulation Can Be Produced Using Paper-Making Methods Has Gone Quite Well. Recent Data Indicates That A 100 Foot Length Of Insulation Made By This Method Is Consistent From Start To Finish, And That The Same Insulation Can Be Duplicated Several Months Later In A Separate Run. The Thermal Conductivity Appears To Be As Good Or Better Than Offthe- Shelf (Ots) Aerogel Insulations That Are Thicker And Less Flexible. This Success Follows Hundreds Of Experiments To First Demonstrate A Good Insulation Recipe Using Single Sheet Molds In The Laboratory, Followed By Pilot Runs On A 12-Inch Wide System To Demonstrate That The Recipe Could Be Run In A Continuous Process. Because The Insulation Is Only 0.5 Mm Thick, Its Not Nearly As Strong As The 5 Mm Thick Ots Insulation Used As Our Benchmark. As A Remedy, We Have Added Scrim To The Insulation In Short Sections By Hand In The Manufacturing Process. While This Solved The Strength Problem, It Is A Step Backwards In Terms Of Manufacturing Readiness Because Scrim Is Now Fed By Hand Into A Process That Is Otherwise Machine Controlled. The Final Steps Needed To Demonstrate That The Technology Can Be Scaled Is To A) Produce The Insulation With A Scrim In A Continuous Process And B) Produce The Insulation In A Wider Width On A Production System. Demonstrating These Capabilities Is The Goal Of This Proposed Phase Ii-X Effort.
- 27 Oct 2020
- The Current Effort To Demonstrate That A Thin, Flexible Aerogel Insulation Can Be Produced Using Paper-Making Methods Has Gone Quite Well. Recent Data Indicates That A 100 Foot Length Of Insulation Made By This Method Is Consistent From Start To Finish, And That The Same Insulation Can Be Duplicated Several Months Later In A Separate Run. The Thermal Conductivity Appears To Be As Good Or Better Than Offthe- Shelf (Ots) Aerogel Insulations That Are Thicker And Less Flexible. This Success Follows Hundreds Of Experiments To First Demonstrate A Good Insulation Recipe Using Single Sheet Molds In The Laboratory, Followed By Pilot Runs On A 12-Inch Wide System To Demonstrate That The Recipe Could Be Run In A Continuous Process. Because The Insulation Is Only 0.5 Mm Thick, Its Not Nearly As Strong As The 5 Mm Thick Ots Insulation Used As Our Benchmark. As A Remedy, We Have Added Scrim To The Insulation In Short Sections By Hand In The Manufacturing Process. While This Solved The Strength Problem, It Is A Step Backwards In Terms Of Manufacturing Readiness Because Scrim Is Now Fed By Hand Into A Process That Is Otherwise Machine Controlled. The Final Steps Needed To Demonstrate That The Technology Can Be Scaled Is To A) Produce The Insulation With A Scrim In A Continuous Process And B) Produce The Insulation In A Wider Width On A Production System. Demonstrating These Capabilities Is The Goal Of This Proposed Phase Ii-X Effort.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $125,000.00
- National Aeronautics And Space Administration (Nasa)
- NNX16CL26C
- Gas Conduction And Radiation Are The Two Important Heat Transfer Mechanisms In Highly Porous Reusable Thermal Protection Systems Used For Planetary Entry Of Space Vehicles.
- 14 Jan 2021
- Gas Conduction And Radiation Are The Two Important Heat Transfer Mechanisms In Highly Porous Reusable Thermal Protection Systems Used For Planetary Entry Of Space Vehicles.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $904,609.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC20C0667
- High Temperature Flexible Aerogel Insulation For Extreme Hiad Environments
- 20 Aug 2020
- High Temperature Flexible Aerogel Insulation For Extreme Hiad Environments
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $124,998.00
- National Aeronautics And Space Administration (Nasa)
- NNX16CL26C
- Igf::Ot::Igf Gas Conduction And Radiation Are The Two Important Heat Transfer Mechanisms In Highly Porous Reusable Thermal Protection Systems Used For Planetary Entry Of Space Vehicles. The Relative Magnitude Of The Two Varies Depending On Altitude, Temperature And The Planet. Usually Radiation Is More Significant At Lower Pressures And At Higher Temperatures. Gas Conduction Is More Dominant At Higher Pressures And Lower Temperatures. In Most Planetary Entries, Both Modes Of Heat Transfer Are Significant. Typical Flexible Or Rigid Refractory Ceramic Fiber Thermal Protection System (Tps) Such As Advanced Flexible Reusable Surface Insulation (Afrsi) And Shuttle Tiles Can Take High Temperatures, Can Reduce Gas Conduction At Lower Pressures, And Scatter Radiation At Higher Temperatures. There Is A Need For More Efficient Tps With Lower Mass, Reduced Thickness And Significantly Lower Thermal Conductivity To Make Inter Planetary Missions Possible. In Order To Achieve This Goal, Insulations Need To Be Developed That Can Further Reduce Gas Conduction And Radiation Heat Transfer Compared To Standard Refractory Ceramic Fiber Insulations. The Overall Objective Of The Phase Ii Program Is To Migrate And Optimize Proven Paper Making Concepts To Fabricate Robust, Flexible And Cost Efficient, Fiber Reinforced Aerogels, Without Sacrificing The Thermal And Mechanical Qualities, In Large Sections Suitable For Application On High Speed Vehicles (Hsv?S). Further Investigation In Phase Ii Would Focus On Production Methods And Recipe Optimization For This New Class Of Thermal Insulations. Embedding Materials With Advantageous Properties Into Fibrous Mats Allows Tailoring The Temperature And Flexibility Requirements To Meet The Needs Of Specific Missions.
- 4 Jun 2018
- Igf::Ot::Igf Gas Conduction And Radiation Are The Two Important Heat Transfer Mechanisms In Highly Porous Reusable Thermal Protection Systems Used For Planetary Entry Of Space Vehicles. The Relative Magnitude Of The Two Varies Depending On Altitude, Temperature And The Planet. Usually Radiation Is More Significant At Lower Pressures And At Higher Temperatures. Gas Conduction Is More Dominant At Higher Pressures And Lower Temperatures. In Most Planetary Entries, Both Modes Of Heat Transfer Are Significant. Typical Flexible Or Rigid Refractory Ceramic Fiber Thermal Protection System (Tps) Such As Advanced Flexible Reusable Surface Insulation (Afrsi) And Shuttle Tiles Can Take High Temperatures, Can Reduce Gas Conduction At Lower Pressures, And Scatter Radiation At Higher Temperatures. There Is A Need For More Efficient Tps With Lower Mass, Reduced Thickness And Significantly Lower Thermal Conductivity To Make Inter Planetary Missions Possible. In Order To Achieve This Goal, Insulations Need To Be Developed That Can Further Reduce Gas Conduction And Radiation Heat Transfer Compared To Standard Refractory Ceramic Fiber Insulations. The Overall Objective Of The Phase Ii Program Is To Migrate And Optimize Proven Paper Making Concepts To Fabricate Robust, Flexible And Cost Efficient, Fiber Reinforced Aerogels, Without Sacrificing The Thermal And Mechanical Qualities, In Large Sections Suitable For Application On High Speed Vehicles (Hsv?S). Further Investigation In Phase Ii Would Focus On Production Methods And Recipe Optimization For This New Class Of Thermal Insulations. Embedding Materials With Advantageous Properties Into Fibrous Mats Allows Tailoring The Temperature And Flexibility Requirements To Meet The Needs Of Specific Missions.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $754,609.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC19C0052
- The Current Effort To Demonstrate That A Thin, Flexible Aerogel Insulation Can Be Produced Using Paper-Making Methods Has Gone Quite Well.
- 29 Nov 2020
- The Current Effort To Demonstrate That A Thin, Flexible Aerogel Insulation Can Be Produced Using Paper-Making Methods Has Gone Quite Well.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $125,000.00
- National Aeronautics And Space Administration (Nasa)
- FA955018C0003
- Sttr Phase Ii. Igf Ot Igf Sbir Phase 2 Heterogeneous Porous Media For Thermal Transport Mitigation In Hypersonics
- 14 Nov 2019
- Sttr Phase Ii. Igf Ot Igf Sbir Phase 2 Heterogeneous Porous Media For Thermal Transport Mitigation In Hypersonics
- Fa9550 Afrl Afosr
- Department Of Defense (Dod)
- $749,877.00
- Department Of Defense (Dod)