Composites Automation Llc
CAGE Code: 1RLQ2
NCAGE Code: 1RLQ2
Status: Active
Type: Commercial Supplier
Dun & Bradstreet (DUNS): 848699810
Summary
Composites Automation Llc is an Active Commercial Supplier with the Cage Code 1RLQ2 and is tracked by Dun & Bradstreet under DUNS Number 848699810..
Address
9 Adelaide Ct
Newark DE 19702-2068
United States
Points of Contact
- Telephone:
- 3025844184
- Fax:
- 3028318525
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Frequently Asked Questions (FAQ) for CAGE 1RLQ2
- What is CAGE Code 1RLQ2?
- 1RLQ2 is the unique identifier used by NATO Organizations to reference the physical entity known as Composites Automation Llc located at 9 Adelaide Ct, Newark DE 19702-2068, United States.
- Who is CAGE Code 1RLQ2?
- 1RLQ2 refers to Composites Automation Llc located at 9 Adelaide Ct, Newark DE 19702-2068, United States.
- Where is CAGE Code 1RLQ2 Located?
- CAGE Code 1RLQ2 is located in Newark, DE, USA.
Contracting History for CAGE 1RLQ2 Most Recent 25 Records
- 80NSSC22CA107
- Sbir Phase Ii Manufacturing Assessment Of Tailorable And Ultra-Thin Tuff Composites
- 22 Apr 2022
- Sbir Phase Ii Manufacturing Assessment Of Tailorable And Ultra-Thin Tuff Composites
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $749,957.00
- National Aeronautics And Space Administration (Nasa)
- W911NF21C0034
- Mod To Exercise Option
- 3 Mar 2022
- Mod To Exercise Option
- W6qk Acc-Apg Durham
- Department Of Defense (Dod)
- $1,099,991.94
- Department Of Defense (Dod)
- W911NF21C0034
- Add Clause-
- 25 May 2021
- Add Clause-
- W6qk Acc-Apg Durham
- Department Of Defense (Dod)
- $569,691.66
- Department Of Defense (Dod)
- W911NF21C0034
- Sttr Phase Ii Award To Composites Automation Llc For Throughput Optimization For The Tailorable Universal Feedstock For Forming (Tuff0 Process.
- 4 Mar 2021
- Sttr Phase Ii Award To Composites Automation Llc For Throughput Optimization For The Tailorable Universal Feedstock For Forming (Tuff0 Process.
- W6qk Acc-Apg Durham
- Department Of Defense (Dod)
- $569,691.66
- Department Of Defense (Dod)
- 80NSSC18C0213
- Composites Automation Llc (Ca), Our Academic Partner University Of Delaware Center For Composite Materials (Ud-Ccm) Are Teaming Up In This Sttr Phase Ii Project To Evaluate Automated Tape Placement (Atp) Processing Of Thin-Ply Composites, Including Material And Process Development, Creation Of A Modeling Foundation Capturing Thin-Ply Placement, Test Panel Fabrication And Mechanical Performance Evaluation. Keys To Successful Transition Of Standard Ply To Thin-Ply Atp Processing, Is The Ability To Fabricate Uniform High Fiber Volume And Fiber Distribution Composite Parts At Or Below 1% Void Content Phase Ii Will Investigate Other Material Options Beyond The North Thin Ply Technology (Ntpt) Material Investigated In Phase I, Evaluate Their Microstructure And Down-Select For Further Investigation. Our Atp Robotic System Will Be Reconfigured To Include A Material Handling System That Eliminates Tape Geometry Changes During Placement Of Thin-Ply Material. A Key Innovation Will Be The Development Of A Comprehensive Modeling Approach Capturing The Complete Placement, Debulking And Autoclave Cure Process For Thin-Ply Material Addressing The Critical Challenges Found In Phase I. This Will Allow Definition Of Material Requirements And Optimization Of The Placement Conditions Such As Speed And Head Pressure For Any Thin Ply Material, Recommend The Number Of Debulking Steps For Thicker Geometry Parts And Provide Cure Cycle Guidance In Particular For Complex Geometry Components. The Comprehensive Software Will Evaluate The Sensitivity Of Incoming Tape Material Quality On Production Rate And Performance, And Enable A Virtual Modeling Environment For Thin-Ply Material. We Will Demonstrate The Approach By Building And Testing Standard Coupons As Well As Complex Geometry Components To Validate And Transition The Technology To Nasa.
- 17 Jun 2020
- Composites Automation Llc (Ca), Our Academic Partner University Of Delaware Center For Composite Materials (Ud-Ccm) Are Teaming Up In This Sttr Phase Ii Project To Evaluate Automated Tape Placement (Atp) Processing Of Thin-Ply Composites, Including Material And Process Development, Creation Of A Modeling Foundation Capturing Thin-Ply Placement, Test Panel Fabrication And Mechanical Performance Evaluation. Keys To Successful Transition Of Standard Ply To Thin-Ply Atp Processing, Is The Ability To Fabricate Uniform High Fiber Volume And Fiber Distribution Composite Parts At Or Below 1% Void Content Phase Ii Will Investigate Other Material Options Beyond The North Thin Ply Technology (Ntpt) Material Investigated In Phase I, Evaluate Their Microstructure And Down-Select For Further Investigation. Our Atp Robotic System Will Be Reconfigured To Include A Material Handling System That Eliminates Tape Geometry Changes During Placement Of Thin-Ply Material. A Key Innovation Will Be The Development Of A Comprehensive Modeling Approach Capturing The Complete Placement, Debulking And Autoclave Cure Process For Thin-Ply Material Addressing The Critical Challenges Found In Phase I. This Will Allow Definition Of Material Requirements And Optimization Of The Placement Conditions Such As Speed And Head Pressure For Any Thin Ply Material, Recommend The Number Of Debulking Steps For Thicker Geometry Parts And Provide Cure Cycle Guidance In Particular For Complex Geometry Components. The Comprehensive Software Will Evaluate The Sensitivity Of Incoming Tape Material Quality On Production Rate And Performance, And Enable A Virtual Modeling Environment For Thin-Ply Material. We Will Demonstrate The Approach By Building And Testing Standard Coupons As Well As Complex Geometry Components To Validate And Transition The Technology To Nasa.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $749,962.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC18C0055
- Composites Automation (Ca) Proposes To Collaborate With The University Of Delaware Center For Composite Materials (Ud-Ccm) And Our Industry Transition Partner Ilc Dover, To Develop Innovative Material And Structure Concepts For Next Generation Space Suit Hard Composite Components. The Sbir Goals Are Develop Material Systems That Survive An Impact Of 300 J At≪0.125 Thickness And≪1.7 G/Cc Density With No Leaks. Phase I Demonstrated A Material Solution That Met These Requirements And The Ability To Balance Impact And Structural Performance With Composite Design. Phase Ii Will Study Additional Material Choices, Develop And Optimize Composite Architectures, And Demonstrate Impact, Structure And Joint/Interface Performance. A Complete Material Specification Including Material Composition, Process Methods And Properties Will Be Developed For The Optimized Solution(S) For Use In Product Design. Phase Ii Will Culminate In The Design, Analysis And Manufacture Of A Full-Scale Hatch, Based On Nasa Requirements, With The Optimized Composite Material Solutions.
- 18 Mar 2020
- Composites Automation (Ca) Proposes To Collaborate With The University Of Delaware Center For Composite Materials (Ud-Ccm) And Our Industry Transition Partner Ilc Dover, To Develop Innovative Material And Structure Concepts For Next Generation Space Suit Hard Composite Components. The Sbir Goals Are Develop Material Systems That Survive An Impact Of 300 J At≪0.125 Thickness And≪1.7 G/Cc Density With No Leaks. Phase I Demonstrated A Material Solution That Met These Requirements And The Ability To Balance Impact And Structural Performance With Composite Design. Phase Ii Will Study Additional Material Choices, Develop And Optimize Composite Architectures, And Demonstrate Impact, Structure And Joint/Interface Performance. A Complete Material Specification Including Material Composition, Process Methods And Properties Will Be Developed For The Optimized Solution(S) For Use In Product Design. Phase Ii Will Culminate In The Design, Analysis And Manufacture Of A Full-Scale Hatch, Based On Nasa Requirements, With The Optimized Composite Material Solutions.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $749,997.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC18C0055
- Composites Automation (Ca) Proposes To Collaborate With The University Of Delaware Center For Composite Materials (Ud-Ccm) And Our Industry Transition Partner Ilc Dover, To Develop Innovative Material And Structure Concepts For Next Generation Space Suit Hard Composite Components. The Sbir Goals Are Develop Material Systems That Survive An Impact Of 300 J At≪0.125 Thickness And≪1.7 G/Cc Density With No Leaks. Phase I Demonstrated A Material Solution That Met These Requirements And The Ability To Balance Impact And Structural Performance With Composite Design. Phase Ii Will Study Additional Material Choices, Develop And Optimize Composite Architectures, And Demonstrate Impact, Structure And Joint/Interface Performance. A Complete Material Specification Including Material Composition, Process Methods And Properties Will Be Developed For The Optimized Solution(S) For Use In Product Design. Phase Ii Will Culminate In The Design, Analysis And Manufacture Of A Full-Scale Hatch, Based On Nasa Requirements, With The Optimized Composite Material Solutions.
- 27 Oct 2020
- Composites Automation (Ca) Proposes To Collaborate With The University Of Delaware Center For Composite Materials (Ud-Ccm) And Our Industry Transition Partner Ilc Dover, To Develop Innovative Material And Structure Concepts For Next Generation Space Suit Hard Composite Components. The Sbir Goals Are Develop Material Systems That Survive An Impact Of 300 J At≪0.125 Thickness And≪1.7 G/Cc Density With No Leaks. Phase I Demonstrated A Material Solution That Met These Requirements And The Ability To Balance Impact And Structural Performance With Composite Design. Phase Ii Will Study Additional Material Choices, Develop And Optimize Composite Architectures, And Demonstrate Impact, Structure And Joint/Interface Performance. A Complete Material Specification Including Material Composition, Process Methods And Properties Will Be Developed For The Optimized Solution(S) For Use In Product Design. Phase Ii Will Culminate In The Design, Analysis And Manufacture Of A Full-Scale Hatch, Based On Nasa Requirements, With The Optimized Composite Material Solutions.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $749,997.00
- National Aeronautics And Space Administration (Nasa)
- N6833517C0093
- Igf::Ot::Igf
- 14 Feb 2019
- Igf::Ot::Igf
- Navair Warfare Ctr Aircraft Div Lke
- Department Of Defense (Dod)
- $989,709.00
- Department Of Defense (Dod)
- 80NSSC18P2117
- This Project Develops An Ultra-Thin And Formable Prepreg Material From Reusable Short Carbon Fiber Composites (Cfc), Including Process And Material Development, Test Panel Fabrication And Mechanical Performance Evaluation. Key To Superior Performance Of Ultra-Thin Ply Materials Is The Ability To Fabricate High Fiber Volume And Uniform Fiber Distribution Prepreg With Low Void Content And Layer Thicknesses≤20 M. Our Prepreg Is Made From Short, Aligned Carbon Fiber (Cf) Sheets And Polymer Film Impregnation. We Have Demonstrated Successful Fabrication Of 30Gsm Areal Weight Fabric Material And Recently Proved Ultra-Thin Ply Prepreg Impregnation With A Low Areal Weight Polymer Film. The Process Is Unique As It Is Not Relying On Spreading Of Large Fiber Tows But Assembles Individual Short Fibers Creating Better Control Of Fiber Content And Thickness Uniformity. The Materials Can Be Processed Using Conventional Autoclave With Mechanical Properties Equivalent To Continuous Cfc. Key Advantages Of Short Cf Thin-Ply Material Compared To Traditional Continuous Prepreg Are The Lower Variability Of The Microstructure, The Ability Of In-Plane Stretching Of Short Cfcs, The Ability To Hybridize At The Fiber Level And To Reclaim The Cf Material For Fabrication Of New High-Performance Parts Or As Feedstock For Additive Manufacturing Processes. The Phase I Will Demonstrate Highquality Thin-Ply Uni And Qi Prepregs Made From Short Cfs And A Potential Phase Ii Will Consider Evaluation Of The Multi-Functional Aspect Of The Material Including Hybridization, Improved Processability And Recovery Of Short Cfcs.
- 22 Jul 2019
- This Project Develops An Ultra-Thin And Formable Prepreg Material From Reusable Short Carbon Fiber Composites (Cfc), Including Process And Material Development, Test Panel Fabrication And Mechanical Performance Evaluation. Key To Superior Performance Of Ultra-Thin Ply Materials Is The Ability To Fabricate High Fiber Volume And Uniform Fiber Distribution Prepreg With Low Void Content And Layer Thicknesses≤20 M. Our Prepreg Is Made From Short, Aligned Carbon Fiber (Cf) Sheets And Polymer Film Impregnation. We Have Demonstrated Successful Fabrication Of 30Gsm Areal Weight Fabric Material And Recently Proved Ultra-Thin Ply Prepreg Impregnation With A Low Areal Weight Polymer Film. The Process Is Unique As It Is Not Relying On Spreading Of Large Fiber Tows But Assembles Individual Short Fibers Creating Better Control Of Fiber Content And Thickness Uniformity. The Materials Can Be Processed Using Conventional Autoclave With Mechanical Properties Equivalent To Continuous Cfc. Key Advantages Of Short Cf Thin-Ply Material Compared To Traditional Continuous Prepreg Are The Lower Variability Of The Microstructure, The Ability Of In-Plane Stretching Of Short Cfcs, The Ability To Hybridize At The Fiber Level And To Reclaim The Cf Material For Fabrication Of New High-Performance Parts Or As Feedstock For Additive Manufacturing Processes. The Phase I Will Demonstrate Highquality Thin-Ply Uni And Qi Prepregs Made From Short Cfs And A Potential Phase Ii Will Consider Evaluation Of The Multi-Functional Aspect Of The Material Including Hybridization, Improved Processability And Recovery Of Short Cfcs.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $124,993.00
- National Aeronautics And Space Administration (Nasa)
- W911NF20P0014
- Sttr Phase I- Composites Automation -"Throughput Optimization For The Tailorable Universal Feedstock For Forming (Tuff) Process"
- 30 Dec 2019
- Sttr Phase I- Composites Automation -"Throughput Optimization For The Tailorable Universal Feedstock For Forming (Tuff) Process"
- W6qk Acc-Apg Durham
- Department Of Defense (Dod)
- $166,473.91
- Department Of Defense (Dod)
- FA865019P5186
- Modeling Simulation Framework
- 15 Apr 2020
- Modeling Simulation Framework
- Fa8650 Usaf Afmc Afrl Pzl Rak Rxk
- Department Of Defense (Dod)
- $149,976.00
- Department Of Defense (Dod)
- N6833517C0093
- Research And Development
- 17 Mar 2021
- Research And Development
- Navair Warfare Ctr Aircraft Div
- Department Of Defense (Dod)
- $989,709.00
- Department Of Defense (Dod)
- 80NSSC21C0395
- Manufacturing Assessment Of Tailorable And Ultra-Thin Tuff Composites
- 17 May 2021
- Manufacturing Assessment Of Tailorable And Ultra-Thin Tuff Composites
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $124,956.00
- National Aeronautics And Space Administration (Nasa)
- FA865019P5186
- Modeling&Simulation Framework For Robust Process Design Of Thermoset Prepegs
- 10 Jul 2019
- Modeling&Simulation Framework For Robust Process Design Of Thermoset Prepegs
- Fa8650 Usaf Afmc Afrl Pzl Rak Rxk
- Department Of Defense (Dod)
- $149,976.00
- Department Of Defense (Dod)
- 80NSSC18C0055
- Composites Automation (Ca) Proposes To Collaborate With The University Of Delaware Center For Composite Materials (Ud-Ccm) And Our Industry Transition Partner Ilc Dover, To Develop Innovative Material And Structure Concepts For Next Generation Space Suit Hard Composite Components. The Sbir Goals Are Develop Material Systems That Survive An Impact Of 300 J At<0.125 Thickness And<1.7 G/Cc Density With No Leaks. Phase I Demonstrated A Material Solution That Met These Requirements And The Ability To Balance Impact And Structural Performance With Composite Design. Phase Ii Will Study Additional Material Choices, Develop And Optimize Composite Architectures, And Demonstrate Impact, Structure And Joint/Interface Performance. A Complete Material Specification Including Material Composition, Process Methods And Properties Will Be Developed For The Optimized Solution(S) For Use In Product Design. Phase Ii Will Culminate In The Design, Analysis And Manufacture Of A Full-Scale Hatch, Based On Nasa Requirements, With The Optimized Composite Material Solutions.
- 30 May 2018
- Composites Automation (Ca) Proposes To Collaborate With The University Of Delaware Center For Composite Materials (Ud-Ccm) And Our Industry Transition Partner Ilc Dover, To Develop Innovative Material And Structure Concepts For Next Generation Space Suit Hard Composite Components. The Sbir Goals Are Develop Material Systems That Survive An Impact Of 300 J At<0.125 Thickness And<1.7 G/Cc Density With No Leaks. Phase I Demonstrated A Material Solution That Met These Requirements And The Ability To Balance Impact And Structural Performance With Composite Design. Phase Ii Will Study Additional Material Choices, Develop And Optimize Composite Architectures, And Demonstrate Impact, Structure And Joint/Interface Performance. A Complete Material Specification Including Material Composition, Process Methods And Properties Will Be Developed For The Optimized Solution(S) For Use In Product Design. Phase Ii Will Culminate In The Design, Analysis And Manufacture Of A Full-Scale Hatch, Based On Nasa Requirements, With The Optimized Composite Material Solutions.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $749,997.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC18P2117
- This Project Develops An Ultra-Thin And Formable Prepreg Material From Reusable Short Carbon Fiber Composites (Cfc), Including Process And Material Development, Test Panel Fabrication And Mechanical Performance Evaluation. Key To Superior Performance Of Ultra-Thin Ply Materials Is The Ability To Fabricate High Fiber Volume And Uniform Fiber Distribution Prepreg With Low Void Content And Layer Thicknesses≤20 M. Our Prepreg Is Made From Short, Aligned Carbon Fiber (Cf) Sheets And Polymer Film Impregnation. We Have Demonstrated Successful Fabrication Of 30Gsm Areal Weight Fabric Material And Recently Proved Ultra-Thin Ply Prepreg Impregnation With A Low Areal Weight Polymer Film. The Process Is Unique As It Is Not Relying On Spreading Of Large Fiber Tows But Assembles Individual Short Fibers Creating Better Control Of Fiber Content And Thickness Uniformity. The Materials Can Be Processed Using Conventional Autoclave With Mechanical Properties Equivalent To Continuous Cfc. Key Advantages Of Short Cf Thin-Ply Material Compared To Traditional Continuous Prepreg Are The Lower Variability Of The Microstructure, The Ability Of In-Plane Stretching Of Short Cfcs, The Ability To Hybridize At The Fiber Level And To Reclaim The Cf Material For Fabrication Of New High-Performance Parts Or As Feedstock For Additive Manufacturing Processes. The Phase I Will Demonstrate Highquality Thin-Ply Uni And Qi Prepregs Made From Short Cfs And A Potential Phase Ii Will Consider Evaluation Of The Multi-Functional Aspect Of The Material Including Hybridization, Improved Processability And Recovery Of Short Cfcs.
- 18 Jul 2018
- This Project Develops An Ultra-Thin And Formable Prepreg Material From Reusable Short Carbon Fiber Composites (Cfc), Including Process And Material Development, Test Panel Fabrication And Mechanical Performance Evaluation. Key To Superior Performance Of Ultra-Thin Ply Materials Is The Ability To Fabricate High Fiber Volume And Uniform Fiber Distribution Prepreg With Low Void Content And Layer Thicknesses≤20 M. Our Prepreg Is Made From Short, Aligned Carbon Fiber (Cf) Sheets And Polymer Film Impregnation. We Have Demonstrated Successful Fabrication Of 30Gsm Areal Weight Fabric Material And Recently Proved Ultra-Thin Ply Prepreg Impregnation With A Low Areal Weight Polymer Film. The Process Is Unique As It Is Not Relying On Spreading Of Large Fiber Tows But Assembles Individual Short Fibers Creating Better Control Of Fiber Content And Thickness Uniformity. The Materials Can Be Processed Using Conventional Autoclave With Mechanical Properties Equivalent To Continuous Cfc. Key Advantages Of Short Cf Thin-Ply Material Compared To Traditional Continuous Prepreg Are The Lower Variability Of The Microstructure, The Ability Of In-Plane Stretching Of Short Cfcs, The Ability To Hybridize At The Fiber Level And To Reclaim The Cf Material For Fabrication Of New High-Performance Parts Or As Feedstock For Additive Manufacturing Processes. The Phase I Will Demonstrate Highquality Thin-Ply Uni And Qi Prepregs Made From Short Cfs And A Potential Phase Ii Will Consider Evaluation Of The Multi-Functional Aspect Of The Material Including Hybridization, Improved Processability And Recovery Of Short Cfcs.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $124,993.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC18C0055
- Composites Automation (Ca) Proposes To Collaborate With The University Of Delaware Center For Composite Materials (Ud-Ccm) And Our Industry Transition Partner Ilc Dover, To Develop Innovative Material And Structure Concepts For Next Generation Space Suit Hard Composite Components. The Sbir Goals Are Develop Material Systems That Survive An Impact Of 300 J At<0.125 Thickness And<1.7 G/Cc Density With No Leaks. Phase I Demonstrated A Material Solution That Met These Requirements And The Ability To Balance Impact And Structural Performance With Composite Design. Phase Ii Will Study Additional Material Choices, Develop And Optimize Composite Architectures, And Demonstrate Impact, Structure And Joint/Interface Performance. A Complete Material Specification Including Material Composition, Process Methods And Properties Will Be Developed For The Optimized Solution(S) For Use In Product Design. Phase Ii Will Culminate In The Design, Analysis And Manufacture Of A Full-Scale Hatch, Based On Nasa Requirements, With The Optimized Composite Material Solutions.
- 27 Sep 2018
- Composites Automation (Ca) Proposes To Collaborate With The University Of Delaware Center For Composite Materials (Ud-Ccm) And Our Industry Transition Partner Ilc Dover, To Develop Innovative Material And Structure Concepts For Next Generation Space Suit Hard Composite Components. The Sbir Goals Are Develop Material Systems That Survive An Impact Of 300 J At<0.125 Thickness And<1.7 G/Cc Density With No Leaks. Phase I Demonstrated A Material Solution That Met These Requirements And The Ability To Balance Impact And Structural Performance With Composite Design. Phase Ii Will Study Additional Material Choices, Develop And Optimize Composite Architectures, And Demonstrate Impact, Structure And Joint/Interface Performance. A Complete Material Specification Including Material Composition, Process Methods And Properties Will Be Developed For The Optimized Solution(S) For Use In Product Design. Phase Ii Will Culminate In The Design, Analysis And Manufacture Of A Full-Scale Hatch, Based On Nasa Requirements, With The Optimized Composite Material Solutions.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $749,997.00
- National Aeronautics And Space Administration (Nasa)
- W911NF20P0014
- Nce For 2 Months Covid-19 Related Delays
- 29 Jun 2020
- Nce For 2 Months Covid-19 Related Delays
- W6qk Acc-Apg Durham
- Department Of Defense (Dod)
- $166,473.91
- Department Of Defense (Dod)
- 80NSSC18C0213
- Composites Automation Llc (Ca), Our Academic Partner University Of Delaware Center For Composite Materials (Ud-Ccm) Are Teaming Up In This Sttr Phase Ii Project To Evaluate Automated Tape Placement (Atp) Processing Of Thin-Ply Composites, Including Material And Process Development, Creation Of A Modeling Foundation Capturing Thin-Ply Placement, Test Panel Fabrication And Mechanical Performance Evaluation. Keys To Successful Transition Of Standard Ply To Thin-Ply Atp Processing, Is The Ability To Fabricate Uniform High Fiber Volume And Fiber Distribution Composite Parts At Or Below 1% Void Content Phase Ii Will Investigate Other Material Options Beyond The North Thin Ply Technology (Ntpt) Material Investigated In Phase I, Evaluate Their Microstructure And Down-Select For Further Investigation. Our Atp Robotic System Will Be Reconfigured To Include A Material Handling System That Eliminates Tape Geometry Changes During Placement Of Thin-Ply Material. A Key Innovation Will Be The Development Of A Comprehensive Modeling Approach Capturing The Complete Placement, Debulking And Autoclave Cure Process For Thin-Ply Material Addressing The Critical Challenges Found In Phase I. This Will Allow Definition Of Material Requirements And Optimization Of The Placement Conditions Such As Speed And Head Pressure For Any Thin Ply Material, Recommend The Number Of Debulking Steps For Thicker Geometry Parts And Provide Cure Cycle Guidance In Particular For Complex Geometry Components. The Comprehensive Software Will Evaluate The Sensitivity Of Incoming Tape Material Quality On Production Rate And Performance, And Enable A Virtual Modeling Environment For Thin-Ply Material. We Will Demonstrate The Approach By Building And Testing Standard Coupons As Well As Complex Geometry Components To Validate And Transition The Technology To Nasa.
- 17 Sep 2018
- Composites Automation Llc (Ca), Our Academic Partner University Of Delaware Center For Composite Materials (Ud-Ccm) Are Teaming Up In This Sttr Phase Ii Project To Evaluate Automated Tape Placement (Atp) Processing Of Thin-Ply Composites, Including Material And Process Development, Creation Of A Modeling Foundation Capturing Thin-Ply Placement, Test Panel Fabrication And Mechanical Performance Evaluation. Keys To Successful Transition Of Standard Ply To Thin-Ply Atp Processing, Is The Ability To Fabricate Uniform High Fiber Volume And Fiber Distribution Composite Parts At Or Below 1% Void Content Phase Ii Will Investigate Other Material Options Beyond The North Thin Ply Technology (Ntpt) Material Investigated In Phase I, Evaluate Their Microstructure And Down-Select For Further Investigation. Our Atp Robotic System Will Be Reconfigured To Include A Material Handling System That Eliminates Tape Geometry Changes During Placement Of Thin-Ply Material. A Key Innovation Will Be The Development Of A Comprehensive Modeling Approach Capturing The Complete Placement, Debulking And Autoclave Cure Process For Thin-Ply Material Addressing The Critical Challenges Found In Phase I. This Will Allow Definition Of Material Requirements And Optimization Of The Placement Conditions Such As Speed And Head Pressure For Any Thin Ply Material, Recommend The Number Of Debulking Steps For Thicker Geometry Parts And Provide Cure Cycle Guidance In Particular For Complex Geometry Components. The Comprehensive Software Will Evaluate The Sensitivity Of Incoming Tape Material Quality On Production Rate And Performance, And Enable A Virtual Modeling Environment For Thin-Ply Material. We Will Demonstrate The Approach By Building And Testing Standard Coupons As Well As Complex Geometry Components To Validate And Transition The Technology To Nasa.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $749,962.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC18C0213
- Composites Automation Llc (Ca), Our Academic Partner University Of Delaware Center For Composite Materials (Ud-Ccm) Are Teaming Up In This Sttr Phase Ii Project To Evaluate Automated Tape Placement (Atp) Processing Of Thin-Ply Composites, Including Material And Process Development, Creation Of A Modeling Foundation Capturing Thin-Ply Placement, Test Panel Fabrication And Mechanical Performance Evaluation. Keys To Successful Transition Of Standard Ply To Thin-Ply Atp Processing, Is The Ability To Fabricate Uniform High Fiber Volume And Fiber Distribution Composite Parts At Or Below 1% Void Content Phase Ii Will Investigate Other Material Options Beyond The North Thin Ply Technology (Ntpt) Material Investigated In Phase I, Evaluate Their Microstructure And Down-Select For Further Investigation. Our Atp Robotic System Will Be Reconfigured To Include A Material Handling System That Eliminates Tape Geometry Changes During Placement Of Thin-Ply Material. A Key Innovation Will Be The Development Of A Comprehensive Modeling Approach Capturing The Complete Placement, Debulking And Autoclave Cure Process For Thin-Ply Material Addressing The Critical Challenges Found In Phase I. This Will Allow Definition Of Material Requirements And Optimization Of The Placement Conditions Such As Speed And Head Pressure For Any Thin Ply Material, Recommend The Number Of Debulking Steps For Thicker Geometry Parts And Provide Cure Cycle Guidance In Particular For Complex Geometry Components. The Comprehensive Software Will Evaluate The Sensitivity Of Incoming Tape Material Quality On Production Rate And Performance, And Enable A Virtual Modeling Environment For Thin-Ply Material. We Will Demonstrate The Approach By Building And Testing Standard Coupons As Well As Complex Geometry Components To Validate And Transition The Technology To Nasa.
- 20 Jan 2021
- Composites Automation Llc (Ca), Our Academic Partner University Of Delaware Center For Composite Materials (Ud-Ccm) Are Teaming Up In This Sttr Phase Ii Project To Evaluate Automated Tape Placement (Atp) Processing Of Thin-Ply Composites, Including Material And Process Development, Creation Of A Modeling Foundation Capturing Thin-Ply Placement, Test Panel Fabrication And Mechanical Performance Evaluation. Keys To Successful Transition Of Standard Ply To Thin-Ply Atp Processing, Is The Ability To Fabricate Uniform High Fiber Volume And Fiber Distribution Composite Parts At Or Below 1% Void Content Phase Ii Will Investigate Other Material Options Beyond The North Thin Ply Technology (Ntpt) Material Investigated In Phase I, Evaluate Their Microstructure And Down-Select For Further Investigation. Our Atp Robotic System Will Be Reconfigured To Include A Material Handling System That Eliminates Tape Geometry Changes During Placement Of Thin-Ply Material. A Key Innovation Will Be The Development Of A Comprehensive Modeling Approach Capturing The Complete Placement, Debulking And Autoclave Cure Process For Thin-Ply Material Addressing The Critical Challenges Found In Phase I. This Will Allow Definition Of Material Requirements And Optimization Of The Placement Conditions Such As Speed And Head Pressure For Any Thin Ply Material, Recommend The Number Of Debulking Steps For Thicker Geometry Parts And Provide Cure Cycle Guidance In Particular For Complex Geometry Components. The Comprehensive Software Will Evaluate The Sensitivity Of Incoming Tape Material Quality On Production Rate And Performance, And Enable A Virtual Modeling Environment For Thin-Ply Material. We Will Demonstrate The Approach By Building And Testing Standard Coupons As Well As Complex Geometry Components To Validate And Transition The Technology To Nasa.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $749,962.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC18P2117
- This Project Develops An Ultra-Thin And Formable Prepreg Material From Reusable Short Carbon Fiber Composites (Cfc), Including Process And Material Development, Test Panel Fabrication And Mechanical Performance Evaluation. Key To Superior Performance Of Ultra-Thin Ply Materials Is The Ability To Fabricate High Fiber Volume And Uniform Fiber Distribution Prepreg With Low Void Content And Layer Thicknesses󖼤 M. Our Prepreg Is Made From Short, Aligned Carbon Fiber (Cf) Sheets And Polymer Film Impregnation. We Have Demonstrated Successful Fabrication Of 30Gsm Areal Weight Fabric Material And Recently Proved Ultra-Thin Ply Prepreg Impregnation With A Low Areal Weight Polymer Film. The Process Is Unique As It Is Not Relying On Spreading Of Large Fiber Tows But Assembles Individual Short Fibers Creating Better Control Of Fiber Content And Thickness Uniformity. The Materials Can Be Processed Using Conventional Autoclave With Mechanical Properties Equivalent To Continuous Cfc. Key Advantages Of Short Cf Thin-Ply Material Compared To Traditional Continuous Prepreg Are The Lower Variability Of The Microstructure, The Ability Of In-Plane Stretching Of Short Cfcs, The Ability To Hybridize At The Fiber Level And To Reclaim The Cf Material For Fabrication Of New High-Performance Parts Or As Feedstock For Additive Manufacturing Processes. The Phase I Will Demonstrate Highquality Thin-Ply Uni And Qi Prepregs Made From Short Cfs And A Potential Phase Ii Will Consider Evaluation Of The Multi-Functional Aspect Of The Material Including Hybridization, Improved Processability And Recovery Of Short Cfcs.
- 5 May 2020
- This Project Develops An Ultra-Thin And Formable Prepreg Material From Reusable Short Carbon Fiber Composites (Cfc), Including Process And Material Development, Test Panel Fabrication And Mechanical Performance Evaluation. Key To Superior Performance Of Ultra-Thin Ply Materials Is The Ability To Fabricate High Fiber Volume And Uniform Fiber Distribution Prepreg With Low Void Content And Layer Thicknesses󖼤 M. Our Prepreg Is Made From Short, Aligned Carbon Fiber (Cf) Sheets And Polymer Film Impregnation. We Have Demonstrated Successful Fabrication Of 30Gsm Areal Weight Fabric Material And Recently Proved Ultra-Thin Ply Prepreg Impregnation With A Low Areal Weight Polymer Film. The Process Is Unique As It Is Not Relying On Spreading Of Large Fiber Tows But Assembles Individual Short Fibers Creating Better Control Of Fiber Content And Thickness Uniformity. The Materials Can Be Processed Using Conventional Autoclave With Mechanical Properties Equivalent To Continuous Cfc. Key Advantages Of Short Cf Thin-Ply Material Compared To Traditional Continuous Prepreg Are The Lower Variability Of The Microstructure, The Ability Of In-Plane Stretching Of Short Cfcs, The Ability To Hybridize At The Fiber Level And To Reclaim The Cf Material For Fabrication Of New High-Performance Parts Or As Feedstock For Additive Manufacturing Processes. The Phase I Will Demonstrate Highquality Thin-Ply Uni And Qi Prepregs Made From Short Cfs And A Potential Phase Ii Will Consider Evaluation Of The Multi-Functional Aspect Of The Material Including Hybridization, Improved Processability And Recovery Of Short Cfcs.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $124,992.00
- National Aeronautics And Space Administration (Nasa)
- NNX17CL52P
- Igf::Ot::Igf This Project Evaluates Automated Tape Placement (Atp) Processing Of Thin Ply Composites, Including Process And Design Modeling, Test Panel Fabrication And Mechanical Performance Evaluation. Key To Successful Transition Of Standard Ply To Thin Ply Atp Processing Is The Ability To Fabricate Uniform High Fiber Volume And Fiber Distribution Composite Parts With Below 1% Void Content. Our Atp Robotic System Will Be Adapted To Handle Thin Ply Materials, Including Accurate Placement And Consolidation To Minimize Potential Defects (Adjacent Tape Gaps Creating Voids, Non-Uniform Compaction Of Plies, Etc.). Existing Modeling Of The Placement Process At Our Academic Partner Will Support Hardware Optimization. Coupon Fabrication And Testing Will Provide Validation Of The Process To Produce High Quality Parts And Initiate The Development Of A Property Database (Microstructure, Mechanical Performance, Etc.).
- 8 Jun 2018
- Igf::Ot::Igf This Project Evaluates Automated Tape Placement (Atp) Processing Of Thin Ply Composites, Including Process And Design Modeling, Test Panel Fabrication And Mechanical Performance Evaluation. Key To Successful Transition Of Standard Ply To Thin Ply Atp Processing Is The Ability To Fabricate Uniform High Fiber Volume And Fiber Distribution Composite Parts With Below 1% Void Content. Our Atp Robotic System Will Be Adapted To Handle Thin Ply Materials, Including Accurate Placement And Consolidation To Minimize Potential Defects (Adjacent Tape Gaps Creating Voids, Non-Uniform Compaction Of Plies, Etc.). Existing Modeling Of The Placement Process At Our Academic Partner Will Support Hardware Optimization. Coupon Fabrication And Testing Will Provide Validation Of The Process To Produce High Quality Parts And Initiate The Development Of A Property Database (Microstructure, Mechanical Performance, Etc.).
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $124,956.00
- National Aeronautics And Space Administration (Nasa)
- N6833517C0059
- Igf::Ot::Igf
- 7 Nov 2018
- Igf::Ot::Igf
- Navair Warfare Ctr Aircraft Div Lke
- Department Of Defense (Dod)
- $746,130.60
- Department Of Defense (Dod)
- 80NSSC18C0055
- Composites Automation (Ca) Proposes To Collaborate With The University Of Delaware Center For Composite Materials (Ud-Ccm) And Our Industry Transition Partner Ilc Dover, To Develop Innovative Material And Structure Concepts For Next Generation Space Suit Hard Composite Components. The Sbir Goals Are Develop Material Systems That Survive An Impact Of 300 J At≪0.125 Thickness And≪1.7 G/Cc Density With No Leaks. Phase I Demonstrated A Material Solution That Met These Requirements And The Ability To Balance Impact And Structural Performance With Composite Design. Phase Ii Will Study Additional Material Choices, Develop And Optimize Composite Architectures, And Demonstrate Impact, Structure And Joint/Interface Performance. A Complete Material Specification Including Material Composition, Process Methods And Properties Will Be Developed For The Optimized Solution(S) For Use In Product Design. Phase Ii Will Culminate In The Design, Analysis And Manufacture Of A Full-Scale Hatch, Based On Nasa Requirements, With The Optimized Composite Material Solutions.
- 8 Oct 2019
- Composites Automation (Ca) Proposes To Collaborate With The University Of Delaware Center For Composite Materials (Ud-Ccm) And Our Industry Transition Partner Ilc Dover, To Develop Innovative Material And Structure Concepts For Next Generation Space Suit Hard Composite Components. The Sbir Goals Are Develop Material Systems That Survive An Impact Of 300 J At≪0.125 Thickness And≪1.7 G/Cc Density With No Leaks. Phase I Demonstrated A Material Solution That Met These Requirements And The Ability To Balance Impact And Structural Performance With Composite Design. Phase Ii Will Study Additional Material Choices, Develop And Optimize Composite Architectures, And Demonstrate Impact, Structure And Joint/Interface Performance. A Complete Material Specification Including Material Composition, Process Methods And Properties Will Be Developed For The Optimized Solution(S) For Use In Product Design. Phase Ii Will Culminate In The Design, Analysis And Manufacture Of A Full-Scale Hatch, Based On Nasa Requirements, With The Optimized Composite Material Solutions.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $749,997.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC18C0055
- Composites Automation (Ca) Proposes To Collaborate With The University Of Delaware Center For Composite Materials (Ud-Ccm) And Our Industry Transition Partner Ilc Dover, To Develop Innovative Material And Structure Concepts For Next Generation Space Suit Hard Composite Components. The Sbir Goals Are Develop Material Systems That Survive An Impact Of 300 J At≪0.125 Thickness And≪1.7 G/Cc Density With No Leaks. Phase I Demonstrated A Material Solution That Met These Requirements And The Ability To Balance Impact And Structural Performance With Composite Design. Phase Ii Will Study Additional Material Choices, Develop And Optimize Composite Architectures, And Demonstrate Impact, Structure And Joint/Interface Performance. A Complete Material Specification Including Material Composition, Process Methods And Properties Will Be Developed For The Optimized Solution(S) For Use In Product Design. Phase Ii Will Culminate In The Design, Analysis And Manufacture Of A Full-Scale Hatch, Based On Nasa Requirements, With The Optimized Composite Material Solutions.
- 20 Jan 2021
- Composites Automation (Ca) Proposes To Collaborate With The University Of Delaware Center For Composite Materials (Ud-Ccm) And Our Industry Transition Partner Ilc Dover, To Develop Innovative Material And Structure Concepts For Next Generation Space Suit Hard Composite Components. The Sbir Goals Are Develop Material Systems That Survive An Impact Of 300 J At≪0.125 Thickness And≪1.7 G/Cc Density With No Leaks. Phase I Demonstrated A Material Solution That Met These Requirements And The Ability To Balance Impact And Structural Performance With Composite Design. Phase Ii Will Study Additional Material Choices, Develop And Optimize Composite Architectures, And Demonstrate Impact, Structure And Joint/Interface Performance. A Complete Material Specification Including Material Composition, Process Methods And Properties Will Be Developed For The Optimized Solution(S) For Use In Product Design. Phase Ii Will Culminate In The Design, Analysis And Manufacture Of A Full-Scale Hatch, Based On Nasa Requirements, With The Optimized Composite Material Solutions.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $749,997.00
- National Aeronautics And Space Administration (Nasa)