The Boeing Company
Div Engineering, Test & Technology
CAGE Code: 4JTK8
NCAGE Code: 4JTK8
Status: Active
Type: Manufacturer
Dun & Bradstreet (DUNS): 622390818
Stock Symbol: BA
Summary
The Boeing Company, Div Engineering, Test & Technology is an Active Manufacturer with the Cage Code 4JTK8 and is tracked by Dun & Bradstreet under DUNS Number 622390818..
Address
14441 Astronautics Ln
Huntington Beach CA 92647-2080
United States
Points of Contact
- Telephone:
- 3148826934
-
http://www.boeing.com/INDEX.HTML
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Frequently Asked Questions (FAQ) for CAGE 4JTK8
- What is CAGE Code 4JTK8?
- 4JTK8 is the unique identifier used by NATO Organizations to reference the physical entity known as The Boeing Company Div Engineering, Test & Technology located at 14441 Astronautics Ln, Huntington Beach CA 92647-2080, United States.
- Who is CAGE Code 4JTK8?
- 4JTK8 refers to The Boeing Company Div Engineering, Test & Technology located at 14441 Astronautics Ln, Huntington Beach CA 92647-2080, United States.
- Where is CAGE Code 4JTK8 Located?
- CAGE Code 4JTK8 is located in Huntington Beach, CA, USA.
Contracting History for CAGE 4JTK8 Most Recent 25 Records
- W900KK21F0103
- National Cyber Range Complex Innovation And Technology Council
- 30 Jul 2021
- National Cyber Range Complex Innovation And Technology Council
- W6qk Acc-Orlando
- Department Of Defense (Dod)
- $36,828.00
- Department Of Defense (Dod)
- W900KK21D0008
- This Multiple Award Indefinite-Delivery, Indefinite-Quantity Contract Is In Support Of The National Cyber Range Complex (Ncrc) Event Planning, Operations, And Support (Epos) Requirement. There Are 14 Awardees Across Two Lots.
- 27 Jul 2021
- This Multiple Award Indefinite-Delivery, Indefinite-Quantity Contract Is In Support Of The National Cyber Range Complex (Ncrc) Event Planning, Operations, And Support (Epos) Requirement. There Are 14 Awardees Across Two Lots.
- W6qk Acc-Orlando
- Department Of Defense (Dod)
- $0.00
- Department Of Defense (Dod)
- W900KK21F0103
- Ncrc Innovation And Technology Council Exercise Of Option Year One
- 25 Oct 2022
- Ncrc Innovation And Technology Council Exercise Of Option Year One
- W6qk Acc-Orlando
- Department Of Defense (Dod)
- $50,034.63
- Department Of Defense (Dod)
- W900KK21F0103
- Ncrc Innovation And Technology Council (Nitc) Clean Up Mod
- 26 May 2022
- Ncrc Innovation And Technology Council (Nitc) Clean Up Mod
- W6qk Acc-Orlando
- Department Of Defense (Dod)
- $36,828.00
- Department Of Defense (Dod)
- W900KK21F0103
- Ncrc Innovation And Technology Council Nitc Supports The Test Resource Management Centers Trmc Mission To Provide Realistic Cybersecurity Environments For Test And Evaluation Of Major Department Of Defense Acquisition Programs
- 6 Sep 2023
- Ncrc Innovation And Technology Council Nitc Supports The Test Resource Management Centers Trmc Mission To Provide Realistic Cybersecurity Environments For Test And Evaluation Of Major Department Of Defense Acquisition Programs
- W6qk Acc-Orlando
- Department Of Defense (Dod)
- $30,000.00
- Department Of Defense (Dod)
- 80HQTR17C0011
- Eo 14042 Under This Effort, Boeing Will Team With The Nanofabrication Group At The California Institute Of Technology To Perform The Following Efforts Relative To Research And Development Field Emission Vacuum Electronic Devices For Operation Above 500 Degrees Celsius. (1) Demonstrate Nanotride Devices Based On Field Emission Vacuum (Fev) Electronics Technology (2) Design And Fabricate Small Integrated Circuit (Oscillator For Frequencies Corresponding To S-Band, 2Ghz) (3) Verify The Operation Of Devices And Oscillator Circuit At 500 C In Vacuum, For Over 1,500 Hours (60 Days). Most Semiconductor Devices Operate Up To 250 C. Recent Advances In Carbide And Nitride Semiconductors Hold Promise For Higher Temperatures, Yet Are Associated With High R&D Costs. There Is A Need For Technology With The Simplicity Of Vacuum Tubes And With Micron Sizes. This Contract Is For The Development And Fabrication Of Field Emission Vacuum (Fev) Devices And An Oscillator Circuit For 2 Ghx (S-Band). Implementation Will Be Complimented By Theoretical/Simulation Analysis Of The Path To X-Band. Additionally, The Effort Will Include The Following (1) Development Of A Device Model For Hspice Circuit Simulations And (2) Simulation Using First-Principles Modeling Tools, Of Metal Migration For Tungsten And Derivatives At High Temperatures.
- 21 Oct 2021
- Eo 14042 Under This Effort, Boeing Will Team With The Nanofabrication Group At The California Institute Of Technology To Perform The Following Efforts Relative To Research And Development Field Emission Vacuum Electronic Devices For Operation Above 500 Degrees Celsius. (1) Demonstrate Nanotride Devices Based On Field Emission Vacuum (Fev) Electronics Technology (2) Design And Fabricate Small Integrated Circuit (Oscillator For Frequencies Corresponding To S-Band, 2Ghz) (3) Verify The Operation Of Devices And Oscillator Circuit At 500 C In Vacuum, For Over 1,500 Hours (60 Days). Most Semiconductor Devices Operate Up To 250 C. Recent Advances In Carbide And Nitride Semiconductors Hold Promise For Higher Temperatures, Yet Are Associated With High R&D Costs. There Is A Need For Technology With The Simplicity Of Vacuum Tubes And With Micron Sizes. This Contract Is For The Development And Fabrication Of Field Emission Vacuum (Fev) Devices And An Oscillator Circuit For 2 Ghx (S-Band). Implementation Will Be Complimented By Theoretical/Simulation Analysis Of The Path To X-Band. Additionally, The Effort Will Include The Following (1) Development Of A Device Model For Hspice Circuit Simulations And (2) Simulation Using First-Principles Modeling Tools, Of Metal Migration For Tungsten And Derivatives At High Temperatures.
- Nasa Headquarters
- National Aeronautics And Space Administration (Nasa)
- $599,558.00
- National Aeronautics And Space Administration (Nasa)
- NNL15AB47T
- Task Order - Statement Of Work - Task Title: Advanced Composites Project (Acp) For Certification Timeline Reduction. 1.0 Introduction/Background: The Nasa Advanced Composites Project (Acp) Is Focused On Reducing The Timeline For Devel
- 23 Jun 2023
- Task Order - Statement Of Work - Task Title: Advanced Composites Project (Acp) For Certification Timeline Reduction. 1.0 Introduction/Background: The Nasa Advanced Composites Project (Acp) Is Focused On Reducing The Timeline For Devel
- Nasa Langley Research Center
- National Aeronautics And Space Administration (Nasa)
- $6,291,683.98
- National Aeronautics And Space Administration (Nasa)
- 80HQTR17C0011
- Under This Effort, Boeing Will Team With The Nanofabrication Group At The California Institute Of Technology To Perform The Following Efforts Relative To Research And Development Field Emission Vacuum Electronic Devices For Operation Above 500 Degrees Celsius. (1) Demonstrate Nanotride Devices Based On Field Emission Vacuum (Fev) Electronics Technology (2) Design And Fabricate Small Integrated Circuit (Oscillator For Frequencies Corresponding To S-Band, 2Ghz) (3) Verify The Operation Of Devices And Oscillator Circuit At 500 C In Vacuum, For Over 1,500 Hours (60 Days). Most Semiconductor Devices Operate Up To 250 C. Recent Advances In Carbide And Nitride Semiconductors Hold Promise For Higher Temperatures, Yet Are Associated With High R&D Costs. There Is A Need For Technology With The Simplicity Of Vacuum Tubes And With Micron Sizes. This Contract Is For The Development And Fabrication Of Field Emission Vacuum (Fev) Devices And An Oscillator Circuit For 2 Ghx (S-Band). Implementation Will Be Complimented By Theoretical/Simulation Analysis Of The Path To X-Band. Additionally, The Effort Will Include The Following (1) Development Of A Device Model For Hspice Circuit Simulations And (2) Simulation Using First-Principles Modeling Tools, Of Metal Migration For Tungsten And Derivatives At High Temperatures.
- 9 Jun 2022
- Under This Effort, Boeing Will Team With The Nanofabrication Group At The California Institute Of Technology To Perform The Following Efforts Relative To Research And Development Field Emission Vacuum Electronic Devices For Operation Above 500 Degrees Celsius. (1) Demonstrate Nanotride Devices Based On Field Emission Vacuum (Fev) Electronics Technology (2) Design And Fabricate Small Integrated Circuit (Oscillator For Frequencies Corresponding To S-Band, 2Ghz) (3) Verify The Operation Of Devices And Oscillator Circuit At 500 C In Vacuum, For Over 1,500 Hours (60 Days). Most Semiconductor Devices Operate Up To 250 C. Recent Advances In Carbide And Nitride Semiconductors Hold Promise For Higher Temperatures, Yet Are Associated With High R&D Costs. There Is A Need For Technology With The Simplicity Of Vacuum Tubes And With Micron Sizes. This Contract Is For The Development And Fabrication Of Field Emission Vacuum (Fev) Devices And An Oscillator Circuit For 2 Ghx (S-Band). Implementation Will Be Complimented By Theoretical/Simulation Analysis Of The Path To X-Band. Additionally, The Effort Will Include The Following (1) Development Of A Device Model For Hspice Circuit Simulations And (2) Simulation Using First-Principles Modeling Tools, Of Metal Migration For Tungsten And Derivatives At High Temperatures.
- Nasa Headquarters
- National Aeronautics And Space Administration (Nasa)
- $599,558.00
- National Aeronautics And Space Administration (Nasa)
- W91ZLK13P0089
- Boeing Support Igf::Ot::Igf
- 15 Dec 2017
- Boeing Support Igf::Ot::Igf
- W6qk Acc-Apg Dir
- Department Of Defense (Dod)
- $19,999.99
- Department Of Defense (Dod)
- W56HZV11C0333
- Laser Hardened Optics
- 15 Jun 2021
- Laser Hardened Optics
- Dcma Carson
- Department Of Defense (Dod)
- $9,472,125.32
- Department Of Defense (Dod)
- 0043
- 200406!000069!5700!Gu30 !Asc/Yck !F3365701d2000 !A!N! !N!0025 ! !20040312!20060301!781650619!781650619!009256819!N!Mcdonnell Douglas Corporation !2401 E Wardlow Road !Long Beach !Ca!90807!43000!037!06!Long Beach !Los Angeles !California!+000011000000!N!N!000000000000!Ac15!Rdte/Aircraft-Eng/Manuf Develop !A1c!Other Aircraft Equipment !200 !C-17A !336411!E! !5!B!S! ! ! !99990909!B! ! !A! !D!U!R!1!001!N!1B!A!N!Z! ! !N!C!N! ! ! !A!A!A!A!000!A!C!N! ! ! !Y! ! !0001! !
- 27 May 2021
- 200406!000069!5700!Gu30 !Asc/Yck !F3365701d2000 !A!N! !N!0025 ! !20040312!20060301!781650619!781650619!009256819!N!Mcdonnell Douglas Corporation !2401 E Wardlow Road !Long Beach !Ca!90807!43000!037!06!Long Beach !Los Angeles !California!+000011000000!N!N!000000000000!Ac15!Rdte/Aircraft-Eng/Manuf Develop !A1c!Other Aircraft Equipment !200 !C-17A !336411!E! !5!B!S! ! ! !99990909!B! ! !A! !D!U!R!1!001!N!1B!A!N!Z! ! !N!C!N! ! ! !A!A!A!A!000!A!C!N! ! ! !Y! ! !0001! !
- Dcma Carson
- Department Of Defense (Dod)
- $245,480.44
- Department Of Defense (Dod)
- 0045
- Power And Thermal Advanced Demonstration Design (Ptadd) - New Task Order
- 21 Jun 2022
- Power And Thermal Advanced Demonstration Design (Ptadd) - New Task Order
- Dcma Carson
- Department Of Defense (Dod)
- $12,807,965.00
- Department Of Defense (Dod)
- NNL10AA05B
- Structures, Materials, Aerodynamics, Aerothermodynamics And Acoustics Research And Technology (Smaaart). This Contract Is For Structures, Materials, Aerodynamics, Aerothermodynamics, And Acoustics Research And Technology For Aerospace Vehicles. The Contractor Shall Furnish All Personnel, Facilities, Equipment, Material, Supplies, And Services, Except As May Be Expressly Set Forth In The Contract Task Orders As Government Furnished, And Otherwise Do All Things Necessary To, Or Incident To, Perform And Provide The Work Efforts Described In The Pws. The Contractor Shall Perform Task Orders That Are Issued By The Langley Research Center Contracting Officer. This Contract May Be Used To Support All Nasa Centers That Require Work Within The Scope Of The Pws. Structures And Materials - Support Research And Development In Materials And Structures Technology Related To Aerospace Vehicles, With Emphasis In The Research Areas Of Structural Mechanics And Concepts, Durability, Damage Tolerance, And Reliability, Structural Dynamics, Aeroelasticity, Advanced Materials And Processing, And Nondestructive Evaluation Sciences. Durability, Damage Tolerance, And Reliability - Investigate Stability, Strength, Damage Tolerance, And Structural Integrity Of Aircraft And Spacecraft Structures, And Tailor Structures Made From Composite, Metallic Or Hybrid Metallic-Composite Materials. Structural Dynamics - Analytical And Experimental Research For The Purpose Of Developing And Validating Improved Methods To Predict, Verify, And Control Complex Aircraft And Space Structures Dynamic Responses, And To The Validity Of Approaches By Conducting Tests On Full-Scale Structures, Structural Elements, And Scaled Structural Models. Aeroelasticity - Study Aeroelastic Phenomena And Prediction Capabilities Needed To Apply New Aerodynamics And Structural Concepts To Future Flight Vehicles And To Determine And Solve The Aeroelastic Problems Of Current Designs. Structural Mechanics And Concepts - Analytical And Experimental Research To Study The Behavior Of Complex Structures Subject To Static And Time-Varying Mechanical And Thermal Loads. Advanced Materials And Processing - Fundamental And Applied Materials And Processing Research Studies That Cover The Development And Integration Of The Full Range Of Aerospace Materials (Polymers, Metals, Ceramics, Composites Derived From Combinations Of Any Of The Three Areas And Emerging Materials Technologies) Into Aerospace Systems. Nondestructive Evaluation Sciences - Research, Develop, And Apply Advanced Measurement Techniques That Relate Quantitative Nondestructive Evaluation Sciences To Physical/Engineering Materials And Structures Characterization. Aerodynamic, Aerothermodynamic And Acoustics - Support Research And Development In Aerodynamics, Aerothermodynamics, And Acoustics Technology Related To Aerospace Vehicles, With Emphasis In The Research Areas Of Configuration Aerodynamics, Computational Modeling And Simulation, Flow Physics And Control, Aircraft And Spacecraft Noise And Vibration Prediction And Control, Aerothermodynamics, Hypersonic Airbreathing Propulsion, Advanced Measurement, Diagnostics, And Instrument Systems, And Model Systems. Configuration Aerodynamics - Applied Experimental And Computational Research Focused On The Development Of Advanced Configuration Concepts For All Classes Of Fixed-Wing Aircraft At Subsonic, Transonic, And Supersonic Speeds. Computational Modeling And Simulation - Develop Computational Methods That Can Be Used To Improve Fundamental Understanding Of Physics Associated With The Fluid Mechanics And Noise Generation For Complex Airframe Systems. Flow Physics And Control - Conduct Fundamental Experimental And Computational Research To Enhance The Knowledge And Understanding Of The Physics Underlying Boundary-Layer Transition, Active And Passive Flow Control, Three-Dimensional Flow Physics, Turbulence, Vortical And Separated Flows. Aircraft And Spacecraft Noise Predictio
- 9 Oct 2015
- Structures, Materials, Aerodynamics, Aerothermodynamics And Acoustics Research And Technology (Smaaart). This Contract Is For Structures, Materials, Aerodynamics, Aerothermodynamics, And Acoustics Research And Technology For Aerospace Vehicles. The Contractor Shall Furnish All Personnel, Facilities, Equipment, Material, Supplies, And Services, Except As May Be Expressly Set Forth In The Contract Task Orders As Government Furnished, And Otherwise Do All Things Necessary To, Or Incident To, Perform And Provide The Work Efforts Described In The Pws. The Contractor Shall Perform Task Orders That Are Issued By The Langley Research Center Contracting Officer. This Contract May Be Used To Support All Nasa Centers That Require Work Within The Scope Of The Pws. Structures And Materials - Support Research And Development In Materials And Structures Technology Related To Aerospace Vehicles, With Emphasis In The Research Areas Of Structural Mechanics And Concepts, Durability, Damage Tolerance, And Reliability, Structural Dynamics, Aeroelasticity, Advanced Materials And Processing, And Nondestructive Evaluation Sciences. Durability, Damage Tolerance, And Reliability - Investigate Stability, Strength, Damage Tolerance, And Structural Integrity Of Aircraft And Spacecraft Structures, And Tailor Structures Made From Composite, Metallic Or Hybrid Metallic-Composite Materials. Structural Dynamics - Analytical And Experimental Research For The Purpose Of Developing And Validating Improved Methods To Predict, Verify, And Control Complex Aircraft And Space Structures Dynamic Responses, And To The Validity Of Approaches By Conducting Tests On Full-Scale Structures, Structural Elements, And Scaled Structural Models. Aeroelasticity - Study Aeroelastic Phenomena And Prediction Capabilities Needed To Apply New Aerodynamics And Structural Concepts To Future Flight Vehicles And To Determine And Solve The Aeroelastic Problems Of Current Designs. Structural Mechanics And Concepts - Analytical And Experimental Research To Study The Behavior Of Complex Structures Subject To Static And Time-Varying Mechanical And Thermal Loads. Advanced Materials And Processing - Fundamental And Applied Materials And Processing Research Studies That Cover The Development And Integration Of The Full Range Of Aerospace Materials (Polymers, Metals, Ceramics, Composites Derived From Combinations Of Any Of The Three Areas And Emerging Materials Technologies) Into Aerospace Systems. Nondestructive Evaluation Sciences - Research, Develop, And Apply Advanced Measurement Techniques That Relate Quantitative Nondestructive Evaluation Sciences To Physical/Engineering Materials And Structures Characterization. Aerodynamic, Aerothermodynamic And Acoustics - Support Research And Development In Aerodynamics, Aerothermodynamics, And Acoustics Technology Related To Aerospace Vehicles, With Emphasis In The Research Areas Of Configuration Aerodynamics, Computational Modeling And Simulation, Flow Physics And Control, Aircraft And Spacecraft Noise And Vibration Prediction And Control, Aerothermodynamics, Hypersonic Airbreathing Propulsion, Advanced Measurement, Diagnostics, And Instrument Systems, And Model Systems. Configuration Aerodynamics - Applied Experimental And Computational Research Focused On The Development Of Advanced Configuration Concepts For All Classes Of Fixed-Wing Aircraft At Subsonic, Transonic, And Supersonic Speeds. Computational Modeling And Simulation - Develop Computational Methods That Can Be Used To Improve Fundamental Understanding Of Physics Associated With The Fluid Mechanics And Noise Generation For Complex Airframe Systems. Flow Physics And Control - Conduct Fundamental Experimental And Computational Research To Enhance The Knowledge And Understanding Of The Physics Underlying Boundary-Layer Transition, Active And Passive Flow Control, Three-Dimensional Flow Physics, Turbulence, Vortical And Separated Flows. Aircraft And Spacecraft Noise Predictio
- Langley Research Center
- National Aeronautics And Space Administration (Nasa)
- $0.00
- National Aeronautics And Space Administration (Nasa)
- NNL14AC00T
- Smaaart Task Order Sow - Slit-Tape Buckling Afp Process Characterization. 1.0 Introduction And Background: As Part Of The Advanced Composites Project (Acp), Nasa Is Partnering With The Aerospace Industry To Significantly Reduce The Timeline To Certify Composite Structure For Commercial And Military Aeronautic Vehicles. Three Main Focus Areas, Or Technical Challenges, Have Been Identified By Nasa And Industry As Having Major Impact On The Current Certification Timeline. The Acp Third Technical Challenge (Tc3), Manufacturing Process And Simulation, Is Concerned With Reducing The Occurrence Of Defects Which Commonly Occur In Aerospace Composite Structures As A Result Of The Processing Methods Utilized To Fabricate These Large, Highly Complex Vehicles. One Of The Objectives In Tc3 Is To Develop Physics-Based Process Models Which Are Capable Of Accurately Predicting The Formation Of Defects During Robotic, Automated Fiber Placement (Afp) Of Composite Structure. While The Efficiency Demonstrated In Afp Has Led To Its Adoption By The Aerospace Industry For Fabrication Of Aircraft Fuselage, Wing, And Engine Nacelle Primary Composite Structures, The Potential Advantages Have Not Been Fully Realized Due To The Occurrence Of Performance Reducing Defects Which Result In Costly And Time-Consuming Rework. The Development Of Accurate Afp Process Models Will Give Aircraft Manufacturers The Ability To Predict Defects Which Occur Due To The Physical Relationship Between The Material, The Part Tooling, And The Afp Processing Parameters. This Science-Based Approach To Maximizing Part Quality Has Proven Successful In Other Composite Processing Methodologies Such As Infusion Flow Prediction And Cure Process Defects Such As Residual Stress. However, Currently No Validated Physics-Based Process Model Exists To Predict Defects Such As Fiber / Tape Buckling, Also Referred To As Fiber Waviness, Wrinkling, Puckering, Or Window-Shading. An Afp Process Model Which Accurately Predicts Process Defects Will Significantly Reduce The Trial And Error Fabrication Effort Required To Meet Production Certification Of Aerospace Composite Structure. The Work Described In This Sow Is Intended To Address Fabrication Issues That Have A Negative Impact On The Timeline Required To Certify Composite Structures. The Intention Of This Task Order Is To Characterize The Afp Process Parameters During The Fabrication Of Parts Which In The Past Have Been Demonstrated To Contain Defects Such As Wrinkling Or Puckering. The Government Will Utilize A Well Characterized Aerospace Toughened Epoxy Material, Hexcel Im7 / 8552-1 Prepreg, So That The Characterization Study Is Focused On The Afp Placement Parameters Which Affect The Formation Of The Wrinkling / Puckering Defects. These Processing Parameters, For Example, Include But Are Not Limited To: Placement Speed, Compaction Load, Material Temperature, And/Or Head Turning Radius. The Geometry Used To Evaluate The Various Afp Processing Parameters Will Be Limited To The Type And Form Which Has Been Demonstrated In Previous Builds By The Fabricator To Result In Formation Of The Wrinkling / Puckering Defects. The Results Of This Afp Processing Characterization Effort Will Be Utilized In The Future Development Of An Afp Physics-Based Process Model To Predict These Types Of Defects. 2.0 Scope&Objective(S): 2.1 The Scope Of This Task Order Is To Fabricate Composite Panels Using The Afp Process And Characterize The Afp Process By Measuring The Processing Parameters Which Result In Fiber / Tape Buckling Defects (Wrinkling / Puckering). 2.2 The Objectives Of This Task Order Are To: A. Determine Afp Placement Parameters And Placement Parameter Interactions Which Influence The Formation And Magnitude Of Wrinkling / Puckering Defects For The Fixed Part Geometry Fabricated Using 0.25 Wide Hexcel Im7 / 8552-1 Slit-Tape Prepreg. B. Empirically Characterize The Afp Processing Parameters And Quantify
- 9 Dec 2020
- Smaaart Task Order Sow - Slit-Tape Buckling Afp Process Characterization. 1.0 Introduction And Background: As Part Of The Advanced Composites Project (Acp), Nasa Is Partnering With The Aerospace Industry To Significantly Reduce The Timeline To Certify Composite Structure For Commercial And Military Aeronautic Vehicles. Three Main Focus Areas, Or Technical Challenges, Have Been Identified By Nasa And Industry As Having Major Impact On The Current Certification Timeline. The Acp Third Technical Challenge (Tc3), Manufacturing Process And Simulation, Is Concerned With Reducing The Occurrence Of Defects Which Commonly Occur In Aerospace Composite Structures As A Result Of The Processing Methods Utilized To Fabricate These Large, Highly Complex Vehicles. One Of The Objectives In Tc3 Is To Develop Physics-Based Process Models Which Are Capable Of Accurately Predicting The Formation Of Defects During Robotic, Automated Fiber Placement (Afp) Of Composite Structure. While The Efficiency Demonstrated In Afp Has Led To Its Adoption By The Aerospace Industry For Fabrication Of Aircraft Fuselage, Wing, And Engine Nacelle Primary Composite Structures, The Potential Advantages Have Not Been Fully Realized Due To The Occurrence Of Performance Reducing Defects Which Result In Costly And Time-Consuming Rework. The Development Of Accurate Afp Process Models Will Give Aircraft Manufacturers The Ability To Predict Defects Which Occur Due To The Physical Relationship Between The Material, The Part Tooling, And The Afp Processing Parameters. This Science-Based Approach To Maximizing Part Quality Has Proven Successful In Other Composite Processing Methodologies Such As Infusion Flow Prediction And Cure Process Defects Such As Residual Stress. However, Currently No Validated Physics-Based Process Model Exists To Predict Defects Such As Fiber / Tape Buckling, Also Referred To As Fiber Waviness, Wrinkling, Puckering, Or Window-Shading. An Afp Process Model Which Accurately Predicts Process Defects Will Significantly Reduce The Trial And Error Fabrication Effort Required To Meet Production Certification Of Aerospace Composite Structure. The Work Described In This Sow Is Intended To Address Fabrication Issues That Have A Negative Impact On The Timeline Required To Certify Composite Structures. The Intention Of This Task Order Is To Characterize The Afp Process Parameters During The Fabrication Of Parts Which In The Past Have Been Demonstrated To Contain Defects Such As Wrinkling Or Puckering. The Government Will Utilize A Well Characterized Aerospace Toughened Epoxy Material, Hexcel Im7 / 8552-1 Prepreg, So That The Characterization Study Is Focused On The Afp Placement Parameters Which Affect The Formation Of The Wrinkling / Puckering Defects. These Processing Parameters, For Example, Include But Are Not Limited To: Placement Speed, Compaction Load, Material Temperature, And/Or Head Turning Radius. The Geometry Used To Evaluate The Various Afp Processing Parameters Will Be Limited To The Type And Form Which Has Been Demonstrated In Previous Builds By The Fabricator To Result In Formation Of The Wrinkling / Puckering Defects. The Results Of This Afp Processing Characterization Effort Will Be Utilized In The Future Development Of An Afp Physics-Based Process Model To Predict These Types Of Defects. 2.0 Scope&Objective(S): 2.1 The Scope Of This Task Order Is To Fabricate Composite Panels Using The Afp Process And Characterize The Afp Process By Measuring The Processing Parameters Which Result In Fiber / Tape Buckling Defects (Wrinkling / Puckering). 2.2 The Objectives Of This Task Order Are To: A. Determine Afp Placement Parameters And Placement Parameter Interactions Which Influence The Formation And Magnitude Of Wrinkling / Puckering Defects For The Fixed Part Geometry Fabricated Using 0.25 Wide Hexcel Im7 / 8552-1 Slit-Tape Prepreg. B. Empirically Characterize The Afp Processing Parameters And Quantify
- Nasa Langley Research Center
- National Aeronautics And Space Administration (Nasa)
- $492,748.31
- National Aeronautics And Space Administration (Nasa)
- NNL14AB65T
- Smaaart Era Structural Concept And Trailing Edge Evaluation 1.0 Introduction/Background: Nasa Created The Environmentally Responsible Aviation (Era) Project To Explore And Document The Feasibility, Benefits, And Technical Risk Of Vehicle Concepts And Enabling Technologies That Will Reduce The Impact Of Aviation On The Environment. Today's Current Generation Of Aircraft Has Benefitted From Nasa Investments In Aeronautical Research That Have Improved Fuel Efficiencies, Lowered Noise Levels, And Reduced Harmful Emissions. Although Substantial Progress Has Been Made, Much More Needs To Be Done. The Nation's Air Transportation System Will Expand By A Factor Of Two Or Three Within The Next Two Decades, Potentially Increasing Aviation's Impact On Climate Change. The Era Project Works To Reduce The Environmental Harm That Could Result From Such An Expansion. The Era Project Is Focusing On Environmental Issues Associated With Aircraft, Including Fuel Burn, Emissions, And Noise. The Project Is Exploring And Documenting The Feasibility, Benefits, And Technical Risk Of Vehicle Concepts And Enabling Technologies Identified To Have The Potential To Mitigate The Impact Of Aviation On The Environment. This Technology Development Directly Supports The National Aeronautics Research And Development Policy To Develop Appropriate Environmental Protection Measures To Ensure Continued Growth In Air Transportation. The Primary Structural Concept Being Developed Under The Era Project In The Airframe Technology Element Is The Pultruded Rod Stitched Efficient Unitized Structure (Prseus) Design. The Prseus Design Approach Is Part Of The Era Effort To Address Fuel Burn (C02 Emissions) By Reducing The Weight Of Advanced Structures. Reducing Fuel Burn Reduces The Need To Use Resources And Reduces Pollution. Prseus Represents A New Concept In Composite Design Theory And Manufacturing Methods. It Is A Conscious Progression Away From Conventional Laminated And Bonded Assemblies Toward Larger One-Piece Panel Designs With Seamless Transitions And Damage-Arrest Interfaces Such As Stitch Rows And Tear Straps. It Focuses On A New Structural Concept That Integrates Skin, Stringers, And Frame Elements Into A Single Large Panel In Which All Elements Are Simultaneously Cured (Or Co-Cured) In One High-Temperature Cure Cycle. The Resulting Structure Is A Novel Solution For Addressing The Demanding Fuselage Loading Requirements Inherent In A Pressurized Shaped Vehicle Like The Hybrid Wing Body (Hwb) Concept. The Prseus Concept Builds Upon, Extends, And Tailors These Structural Technologies In Order To Meet The Demanding Challenges Associated With Vehicles With Shapes And Load Paths Different From Today S Traditional Wing And Circular Fuselage Structures. 2.0 Scope&Objective(S): 2.1 The Scope Of This Task Order Is To Conduct Analytical Evaluations Based On A Stitched Unitized Composite Structural Concept And Advanced Aerodynamics To Commercial Transport Aircraft Structures To Determine Weight Reductions And Aerodynamic Performance Improvements Compared To State-Of-The-Art Aircraft With Wings Attached To A Barrel Fuselage Section. Advances Beyond Traditional Tube-With-Wings Aircraft Under Consideration Include (1) The Concept Change To Go To A Hwb Design, (2) To Use High Aspect Ratio Composite Wings Attached To A Barrel Fuselage, And (3) To Add Adaptive Compliant Elements Such As A Flexible Composite Trailing Edge To Either The Wing Of A Traditional Shaped Aircraft Or To The Wing Of A Hwb Aircraft. All Of These Concepts Improve The Aerodynamic Performance. 2.2 The Objectives Of This Task Order Are As Follows: 1. Describe The Benefits Of The Prseus Concept, And Other Stitched Resin Infused Concepts, To A Conventional Twin-Aisle Tube-And-Wing Transport Vehicle. 2. Update The Performance Benefits Of The Prseus Concept To A Hwb Vehicle Based On The Test Results Obtained Since The Original Study Was Performed Under Co
- 26 May 2015
- Smaaart Era Structural Concept And Trailing Edge Evaluation 1.0 Introduction/Background: Nasa Created The Environmentally Responsible Aviation (Era) Project To Explore And Document The Feasibility, Benefits, And Technical Risk Of Vehicle Concepts And Enabling Technologies That Will Reduce The Impact Of Aviation On The Environment. Today's Current Generation Of Aircraft Has Benefitted From Nasa Investments In Aeronautical Research That Have Improved Fuel Efficiencies, Lowered Noise Levels, And Reduced Harmful Emissions. Although Substantial Progress Has Been Made, Much More Needs To Be Done. The Nation's Air Transportation System Will Expand By A Factor Of Two Or Three Within The Next Two Decades, Potentially Increasing Aviation's Impact On Climate Change. The Era Project Works To Reduce The Environmental Harm That Could Result From Such An Expansion. The Era Project Is Focusing On Environmental Issues Associated With Aircraft, Including Fuel Burn, Emissions, And Noise. The Project Is Exploring And Documenting The Feasibility, Benefits, And Technical Risk Of Vehicle Concepts And Enabling Technologies Identified To Have The Potential To Mitigate The Impact Of Aviation On The Environment. This Technology Development Directly Supports The National Aeronautics Research And Development Policy To Develop Appropriate Environmental Protection Measures To Ensure Continued Growth In Air Transportation. The Primary Structural Concept Being Developed Under The Era Project In The Airframe Technology Element Is The Pultruded Rod Stitched Efficient Unitized Structure (Prseus) Design. The Prseus Design Approach Is Part Of The Era Effort To Address Fuel Burn (C02 Emissions) By Reducing The Weight Of Advanced Structures. Reducing Fuel Burn Reduces The Need To Use Resources And Reduces Pollution. Prseus Represents A New Concept In Composite Design Theory And Manufacturing Methods. It Is A Conscious Progression Away From Conventional Laminated And Bonded Assemblies Toward Larger One-Piece Panel Designs With Seamless Transitions And Damage-Arrest Interfaces Such As Stitch Rows And Tear Straps. It Focuses On A New Structural Concept That Integrates Skin, Stringers, And Frame Elements Into A Single Large Panel In Which All Elements Are Simultaneously Cured (Or Co-Cured) In One High-Temperature Cure Cycle. The Resulting Structure Is A Novel Solution For Addressing The Demanding Fuselage Loading Requirements Inherent In A Pressurized Shaped Vehicle Like The Hybrid Wing Body (Hwb) Concept. The Prseus Concept Builds Upon, Extends, And Tailors These Structural Technologies In Order To Meet The Demanding Challenges Associated With Vehicles With Shapes And Load Paths Different From Today S Traditional Wing And Circular Fuselage Structures. 2.0 Scope&Objective(S): 2.1 The Scope Of This Task Order Is To Conduct Analytical Evaluations Based On A Stitched Unitized Composite Structural Concept And Advanced Aerodynamics To Commercial Transport Aircraft Structures To Determine Weight Reductions And Aerodynamic Performance Improvements Compared To State-Of-The-Art Aircraft With Wings Attached To A Barrel Fuselage Section. Advances Beyond Traditional Tube-With-Wings Aircraft Under Consideration Include (1) The Concept Change To Go To A Hwb Design, (2) To Use High Aspect Ratio Composite Wings Attached To A Barrel Fuselage, And (3) To Add Adaptive Compliant Elements Such As A Flexible Composite Trailing Edge To Either The Wing Of A Traditional Shaped Aircraft Or To The Wing Of A Hwb Aircraft. All Of These Concepts Improve The Aerodynamic Performance. 2.2 The Objectives Of This Task Order Are As Follows: 1. Describe The Benefits Of The Prseus Concept, And Other Stitched Resin Infused Concepts, To A Conventional Twin-Aisle Tube-And-Wing Transport Vehicle. 2. Update The Performance Benefits Of The Prseus Concept To A Hwb Vehicle Based On The Test Results Obtained Since The Original Study Was Performed Under Co
- Langley Research Center
- National Aeronautics And Space Administration (Nasa)
- $1,083,076.11
- National Aeronautics And Space Administration (Nasa)
- IND12PC00367
- Neurofeedback Testbed And Narrative Architect(N2 Baa12-03)
- 11 Aug 2021
- Neurofeedback Testbed And Narrative Architect(N2 Baa12-03)
- Ibc Acq Svcs Directorate (00004)
- Department Of The Interior (Doi)
- $2,557,995.48
- Department Of The Interior (Doi)
- 80HQTR17C0011
- Under This Effort, Boeing Will Team With The Nanofabrication Group At The California Institute Of Technology To Perform The Following Efforts Relative To Research And Development Field Emission Vacuum Electronic Devices For Operation Above 500 Degrees Celsius. (1) Demonstrate Nanotride Devices Based On Field Emission Vacuum (Fev) Electronics Technology (2) Design And Fabricate Small Integrated Circuit (Oscillator For Frequencies Corresponding To S-Band, 2Ghz) (3) Verify The Operation Of Devices And Oscillator Circuit At 500 C In Vacuum, For Over 1,500 Hours (60 Days). Most Semiconductor Devices Operate Up To 250 C. Recent Advances In Carbide And Nitride Semiconductors Hold Promise For Higher Temperatures, Yet Are Associated With High R&D Costs. There Is A Need For Technology With The Simplicity Of Vacuum Tubes And With Micron Sizes. This Contract Is For The Development And Fabrication Of Field Emission Vacuum (Fev) Devices And An Oscillator Circuit For 2 Ghx (S-Band). Implementation Will Be Complimented By Theoretical/Simulation Analysis Of The Path To X-Band. Additionally, The Effort Will Include The Following (1) Development Of A Device Model For Hspice Circuit Simulations And (2) Simulation Using First-Principles Modeling Tools, Of Metal Migration For Tungsten And Derivatives At High Temperatures.
- 25 Jun 2021
- Under This Effort, Boeing Will Team With The Nanofabrication Group At The California Institute Of Technology To Perform The Following Efforts Relative To Research And Development Field Emission Vacuum Electronic Devices For Operation Above 500 Degrees Celsius. (1) Demonstrate Nanotride Devices Based On Field Emission Vacuum (Fev) Electronics Technology (2) Design And Fabricate Small Integrated Circuit (Oscillator For Frequencies Corresponding To S-Band, 2Ghz) (3) Verify The Operation Of Devices And Oscillator Circuit At 500 C In Vacuum, For Over 1,500 Hours (60 Days). Most Semiconductor Devices Operate Up To 250 C. Recent Advances In Carbide And Nitride Semiconductors Hold Promise For Higher Temperatures, Yet Are Associated With High R&D Costs. There Is A Need For Technology With The Simplicity Of Vacuum Tubes And With Micron Sizes. This Contract Is For The Development And Fabrication Of Field Emission Vacuum (Fev) Devices And An Oscillator Circuit For 2 Ghx (S-Band). Implementation Will Be Complimented By Theoretical/Simulation Analysis Of The Path To X-Band. Additionally, The Effort Will Include The Following (1) Development Of A Device Model For Hspice Circuit Simulations And (2) Simulation Using First-Principles Modeling Tools, Of Metal Migration For Tungsten And Derivatives At High Temperatures.
- Nasa Headquarters
- National Aeronautics And Space Administration (Nasa)
- $599,558.00
- National Aeronautics And Space Administration (Nasa)
- 0035
- 200406!000069!5700!Gu30 !Asc/Yck !F3365701d2000 !A!N! !N!0025 ! !20040312!20060301!781650619!781650619!009256819!N!Mcdonnell Douglas Corporation !2401 E Wardlow Road !Long Beach !Ca!90807!43000!037!06!Long Beach !Los Angeles !California!+000011000000!N!N!000000000000!Ac15!Rdte/Aircraft-Eng/Manuf Develop !A1c!Other Aircraft Equipment !200 !C-17A !336411!E! !5!B!S! ! ! !99990909!B! ! !A! !D!U!R!1!001!N!1B!A!N!Z! ! !N!C!N! ! ! !A!A!A!A!000!A!C!N! ! ! !Y! ! !0001! !
- 27 May 2021
- 200406!000069!5700!Gu30 !Asc/Yck !F3365701d2000 !A!N! !N!0025 ! !20040312!20060301!781650619!781650619!009256819!N!Mcdonnell Douglas Corporation !2401 E Wardlow Road !Long Beach !Ca!90807!43000!037!06!Long Beach !Los Angeles !California!+000011000000!N!N!000000000000!Ac15!Rdte/Aircraft-Eng/Manuf Develop !A1c!Other Aircraft Equipment !200 !C-17A !336411!E! !5!B!S! ! ! !99990909!B! ! !A! !D!U!R!1!001!N!1B!A!N!Z! ! !N!C!N! ! ! !A!A!A!A!000!A!C!N! ! ! !Y! ! !0001! !
- Dcma Carson
- Department Of Defense (Dod)
- $693,159.38
- Department Of Defense (Dod)
- 0001
- 200406!000069!5700!Gu30 !Asc/Yck !F3365701d2000 !A!N! !N!0025 ! !20040312!20060301!781650619!781650619!009256819!N!Mcdonnell Douglas Corporation !2401 E Wardlow Road !Long Beach !Ca!90807!43000!037!06!Long Beach !Los Angeles !California!+000011000000!N!N!000000000000!Ac15!Rdte/Aircraft-Eng/Manuf Develop !A1c!Other Aircraft Equipment !200 !C-17A !336411!E! !5!B!S! ! ! !99990909!B! ! !A! !D!U!R!1!001!N!1B!A!N!Z! ! !N!C!N! ! ! !A!A!A!A!000!A!C!N! ! ! !Y! ! !0001! !
- 2 Jun 2021
- 200406!000069!5700!Gu30 !Asc/Yck !F3365701d2000 !A!N! !N!0025 ! !20040312!20060301!781650619!781650619!009256819!N!Mcdonnell Douglas Corporation !2401 E Wardlow Road !Long Beach !Ca!90807!43000!037!06!Long Beach !Los Angeles !California!+000011000000!N!N!000000000000!Ac15!Rdte/Aircraft-Eng/Manuf Develop !A1c!Other Aircraft Equipment !200 !C-17A !336411!E! !5!B!S! ! ! !99990909!B! ! !A! !D!U!R!1!001!N!1B!A!N!Z! ! !N!C!N! ! ! !A!A!A!A!000!A!C!N! ! ! !Y! ! !0001! !
- Dcma Carson
- Department Of Defense (Dod)
- $317,555.62
- Department Of Defense (Dod)
- NNL11AD26T
- Smaaart Task Order Task Title: Aeroacoustic Measurements Of A Leading-Edge Slat
- 30 Aug 2017
- Smaaart Task Order Task Title: Aeroacoustic Measurements Of A Leading-Edge Slat
- Nasa Langley Research Center
- National Aeronautics And Space Administration (Nasa)
- $102,389.84
- National Aeronautics And Space Administration (Nasa)
- 0041
- 200406!000069!5700!Gu30 !Asc/Yck !F3365701d2000 !A!N! !N!0025 ! !20040312!20060301!781650619!781650619!009256819!N!Mcdonnell Douglas Corporation !2401 E Wardlow Road !Long Beach !Ca!90807!43000!037!06!Long Beach !Los Angeles !California!+000011000000!N!N!000000000000!Ac15!Rdte/Aircraft-Eng/Manuf Develop !A1c!Other Aircraft Equipment !200 !C-17A !336411!E! !5!B!S! ! ! !99990909!B! ! !A! !D!U!R!1!001!N!1B!A!N!Z! ! !N!C!N! ! ! !A!A!A!A!000!A!C!N! ! ! !Y! ! !0001! !
- 7 May 2021
- 200406!000069!5700!Gu30 !Asc/Yck !F3365701d2000 !A!N! !N!0025 ! !20040312!20060301!781650619!781650619!009256819!N!Mcdonnell Douglas Corporation !2401 E Wardlow Road !Long Beach !Ca!90807!43000!037!06!Long Beach !Los Angeles !California!+000011000000!N!N!000000000000!Ac15!Rdte/Aircraft-Eng/Manuf Develop !A1c!Other Aircraft Equipment !200 !C-17A !336411!E! !5!B!S! ! ! !99990909!B! ! !A! !D!U!R!1!001!N!1B!A!N!Z! ! !N!C!N! ! ! !A!A!A!A!000!A!C!N! ! ! !Y! ! !0001! !
- Dcma Carson
- Department Of Defense (Dod)
- $767,705.39
- Department Of Defense (Dod)
- NNL15AC21T
- Reducing Risk To Achieving The Nasa N2 Noise Goal. Nasas Environmentally Responsible Aviation (Era) Project Has Focused On Developing And Demonstrating Technologies For Integrated Aircraft Systems. The Fuel Burn Goal Is A Reduction By 50 Relative To A Best In Fleet Aircraft In 2005, The Noise Goal Is 42 Decibels (Db) Cumulative Relative To The Federal Aviation Administrations Stage 4 Requirement, And The Emissions Goal Is For A Reduction Of 75 In Nitrous Oxide Below The Committee On Aviation Environmental Protection Standard Number 6 (Caep6). The Target Date Is 2020 For Key Technologies To Be At A Technology Readiness Level (Trl) Of Four To Six (I.E., System Or Sub-System Prototype Demonstrated In A Relevant Environment). This Corresponds To A Projected Aircraft Entry Into Service No Earlier Than 2025. These Goals And Timeframe Are Defined By Nasa As N21. This Effort Builds Upon Previous Contract Work By Boeing. The Hybrid Wing Body (Hwb) Aircraft Was Previously Identified As One Concept That Has The Potential To Meet The Era Projects Aircraft Noise Goal. Nasa Published In American Institute Of Aeronautics And Astronautics (Aiaa) Paper Numbers 2010-3912 And 2010-3913 Results Showing A Technical Path For The Hwb Concept To Meet The 42 Db Goal. Under The Era Advanced Vehicle Configurations (Avc) Task The Advanced Hwb Aircraft Concept Proposed By Boeing Was Shown To Meet All Three Of The Era N2 Goals Simultaneously. Nasa Has Participated In A Detailed And Updated Noise Assessment That Was Published As Aiaa Paper 2014-0365 (Guo, Burley, And Thomas) Including Comparison With The Previous Nasa Noise Assessment. Finally, Under Smaaart Task Order Nnl13ab86t, Boeing Is Currently Working With An Updated Design Of Its Hwb Preferred System Concept (Psc) Aircraft With Improved Design Features Including A Krueger Flap Leading Edge, An Improved Engine Selection, And Improved Engine/Airframe Integration. In Review Of The Above Research, Nasa Has Identified Four Critical Areas Needed To Improve Nasas Current System Noise Assessment Methodology. Also, Investigation Of Noise Reduction Approaches In These Four Areas Will Result In Higher Confidence Noise Assessments Relative To Meeting The 42 Db Goal. It Is Of Additional Value To Nasa That The Results From This Task Will Also Be Applicable To Assessments Of Other Advanced Aircraft Concepts. The Overall Purpose Of This Task Order Is To Reduce The Risk To Achieving The 42 Db Goal Based On The Most Advanced Assessments To Be Done By Nasa On The Era Vehicle Concepts. _______________ 1. Nasas Research Focuses On Future Aircraft Design Concepts And Technology That Could Be Introduced Into Service In 2020, 2025 And 2030. The First "Next" Generation For 2020 Is Referred To As "N1." The Second Generation Is "N2." The Third And Farthest Out Generation Is "N3." Each Design Generation Offers Technology Features More Sophisticated Than Those Of The Generation Before.  2.0 Scope&Objective(S): 2.1 The Scope Of This Task Order Is Limited To Using Boeings Hwb Psc In The Following Four Technical Areas That Have Been Identified As Critical To Improving The Current State Of The Art Of Nasas Aircraft System Noise Assessments, To Achieve The 42 Db Noise Goal. 1. High Fidelity Ultra-High Bypass (Uhb) Fan Noise Shielding Effectiveness. 2. Airframe System Database With Component Noise Ranking. 3. Krueger Flap Noise. 4. Flight Path And System Noise Optimization. The Contractor Shall Utilize Computational And Analytical Modeling Methods And Analysis Of Existing Experimental And Simulation Data In Conducting The Work Under This Sow. 2.2 The Objectives Of This Task Order Are To: 1. Develop Shielding Suppression Maps From High Fidelity Simulations Of Uhb Aft Radiated Fan Noise That Are To Be Used In System Noise Assessments. 2. Develop And Predict The Performance Of A Conc
- 22 Jun 2021
- Reducing Risk To Achieving The Nasa N2 Noise Goal. Nasas Environmentally Responsible Aviation (Era) Project Has Focused On Developing And Demonstrating Technologies For Integrated Aircraft Systems. The Fuel Burn Goal Is A Reduction By 50 Relative To A Best In Fleet Aircraft In 2005, The Noise Goal Is 42 Decibels (Db) Cumulative Relative To The Federal Aviation Administrations Stage 4 Requirement, And The Emissions Goal Is For A Reduction Of 75 In Nitrous Oxide Below The Committee On Aviation Environmental Protection Standard Number 6 (Caep6). The Target Date Is 2020 For Key Technologies To Be At A Technology Readiness Level (Trl) Of Four To Six (I.E., System Or Sub-System Prototype Demonstrated In A Relevant Environment). This Corresponds To A Projected Aircraft Entry Into Service No Earlier Than 2025. These Goals And Timeframe Are Defined By Nasa As N21. This Effort Builds Upon Previous Contract Work By Boeing. The Hybrid Wing Body (Hwb) Aircraft Was Previously Identified As One Concept That Has The Potential To Meet The Era Projects Aircraft Noise Goal. Nasa Published In American Institute Of Aeronautics And Astronautics (Aiaa) Paper Numbers 2010-3912 And 2010-3913 Results Showing A Technical Path For The Hwb Concept To Meet The 42 Db Goal. Under The Era Advanced Vehicle Configurations (Avc) Task The Advanced Hwb Aircraft Concept Proposed By Boeing Was Shown To Meet All Three Of The Era N2 Goals Simultaneously. Nasa Has Participated In A Detailed And Updated Noise Assessment That Was Published As Aiaa Paper 2014-0365 (Guo, Burley, And Thomas) Including Comparison With The Previous Nasa Noise Assessment. Finally, Under Smaaart Task Order Nnl13ab86t, Boeing Is Currently Working With An Updated Design Of Its Hwb Preferred System Concept (Psc) Aircraft With Improved Design Features Including A Krueger Flap Leading Edge, An Improved Engine Selection, And Improved Engine/Airframe Integration. In Review Of The Above Research, Nasa Has Identified Four Critical Areas Needed To Improve Nasas Current System Noise Assessment Methodology. Also, Investigation Of Noise Reduction Approaches In These Four Areas Will Result In Higher Confidence Noise Assessments Relative To Meeting The 42 Db Goal. It Is Of Additional Value To Nasa That The Results From This Task Will Also Be Applicable To Assessments Of Other Advanced Aircraft Concepts. The Overall Purpose Of This Task Order Is To Reduce The Risk To Achieving The 42 Db Goal Based On The Most Advanced Assessments To Be Done By Nasa On The Era Vehicle Concepts. _______________ 1. Nasas Research Focuses On Future Aircraft Design Concepts And Technology That Could Be Introduced Into Service In 2020, 2025 And 2030. The First "Next" Generation For 2020 Is Referred To As "N1." The Second Generation Is "N2." The Third And Farthest Out Generation Is "N3." Each Design Generation Offers Technology Features More Sophisticated Than Those Of The Generation Before.  2.0 Scope&Objective(S): 2.1 The Scope Of This Task Order Is Limited To Using Boeings Hwb Psc In The Following Four Technical Areas That Have Been Identified As Critical To Improving The Current State Of The Art Of Nasas Aircraft System Noise Assessments, To Achieve The 42 Db Noise Goal. 1. High Fidelity Ultra-High Bypass (Uhb) Fan Noise Shielding Effectiveness. 2. Airframe System Database With Component Noise Ranking. 3. Krueger Flap Noise. 4. Flight Path And System Noise Optimization. The Contractor Shall Utilize Computational And Analytical Modeling Methods And Analysis Of Existing Experimental And Simulation Data In Conducting The Work Under This Sow. 2.2 The Objectives Of This Task Order Are To: 1. Develop Shielding Suppression Maps From High Fidelity Simulations Of Uhb Aft Radiated Fan Noise That Are To Be Used In System Noise Assessments. 2. Develop And Predict The Performance Of A Conc
- Nasa Langley Research Center
- National Aeronautics And Space Administration (Nasa)
- $2,337,153.91
- National Aeronautics And Space Administration (Nasa)
- NNL15AC21T
- Reducing Risk To Achieving The Nasa N2 Noise Goal. Nasas Environmentally Responsible Aviation (Era) Project Has Focused On Developing And Demonstrating Technologies For Integrated Aircraft Systems. The Fuel Burn Goal Is A Reduction By 50 Relative To A Best In Fleet Aircraft In 2005, The Noise Goal Is 42 Decibels (Db) Cumulative Relative To The Federal Aviation Administrations Stage 4 Requirement, And The Emissions Goal Is For A Reduction Of 75 In Nitrous Oxide Below The Committee On Aviation Environmental Protection Standard Number 6 (Caep6). The Target Date Is 2020 For Key Technologies To Be At A Technology Readiness Level (Trl) Of Four To Six (I.E., System Or Sub-System Prototype Demonstrated In A Relevant Environment). This Corresponds To A Projected Aircraft Entry Into Service No Earlier Than 2025. These Goals And Timeframe Are Defined By Nasa As N21. This Effort Builds Upon Previous Contract Work By Boeing. The Hybrid Wing Body (Hwb) Aircraft Was Previously Identified As One Concept That Has The Potential To Meet The Era Projects Aircraft Noise Goal. Nasa Published In American Institute Of Aeronautics And Astronautics (Aiaa) Paper Numbers 2010-3912 And 2010-3913 Results Showing A Technical Path For The Hwb Concept To Meet The 42 Db Goal. Under The Era Advanced Vehicle Configurations (Avc) Task The Advanced Hwb Aircraft Concept Proposed By Boeing Was Shown To Meet All Three Of The Era N2 Goals Simultaneously. Nasa Has Participated In A Detailed And Updated Noise Assessment That Was Published As Aiaa Paper 2014-0365 (Guo, Burley, And Thomas) Including Comparison With The Previous Nasa Noise Assessment. Finally, Under Smaaart Task Order Nnl13ab86t, Boeing Is Currently Working With An Updated Design Of Its Hwb Preferred System Concept (Psc) Aircraft With Improved Design Features Including A Krueger Flap Leading Edge, An Improved Engine Selection, And Improved Engine/Airframe Integration. In Review Of The Above Research, Nasa Has Identified Four Critical Areas Needed To Improve Nasas Current System Noise Assessment Methodology. Also, Investigation Of Noise Reduction Approaches In These Four Areas Will Result In Higher Confidence Noise Assessments Relative To Meeting The 42 Db Goal. It Is Of Additional Value To Nasa That The Results From This Task Will Also Be Applicable To Assessments Of Other Advanced Aircraft Concepts. The Overall Purpose Of This Task Order Is To Reduce The Risk To Achieving The 42 Db Goal Based On The Most Advanced Assessments To Be Done By Nasa On The Era Vehicle Concepts. _______________ 1. Nasas Research Focuses On Future Aircraft Design Concepts And Technology That Could Be Introduced Into Service In 2020, 2025 And 2030. The First "Next" Generation For 2020 Is Referred To As "N1." The Second Generation Is "N2." The Third And Farthest Out Generation Is "N3." Each Design Generation Offers Technology Features More Sophisticated Than Those Of The Generation Before.  2.0 Scope&Objective(S): 2.1 The Scope Of This Task Order Is Limited To Using Boeings Hwb Psc In The Following Four Technical Areas That Have Been Identified As Critical To Improving The Current State Of The Art Of Nasas Aircraft System Noise Assessments, To Achieve The 42 Db Noise Goal. 1. High Fidelity Ultra-High Bypass (Uhb) Fan Noise Shielding Effectiveness. 2. Airframe System Database With Component Noise Ranking. 3. Krueger Flap Noise. 4. Flight Path And System Noise Optimization. The Contractor Shall Utilize Computational And Analytical Modeling Methods And Analysis Of Existing Experimental And Simulation Data In Conducting The Work Under This Sow. 2.2 The Objectives Of This Task Order Are To: 1. Develop Shielding Suppression Maps From High Fidelity Simulations Of Uhb Aft Radiated Fan Noise That Are To Be Used In System Noise Assessments. 2. Develop And Predict The Performance Of A Conc
- 22 Sep 2023
- Reducing Risk To Achieving The Nasa N2 Noise Goal. Nasas Environmentally Responsible Aviation (Era) Project Has Focused On Developing And Demonstrating Technologies For Integrated Aircraft Systems. The Fuel Burn Goal Is A Reduction By 50 Relative To A Best In Fleet Aircraft In 2005, The Noise Goal Is 42 Decibels (Db) Cumulative Relative To The Federal Aviation Administrations Stage 4 Requirement, And The Emissions Goal Is For A Reduction Of 75 In Nitrous Oxide Below The Committee On Aviation Environmental Protection Standard Number 6 (Caep6). The Target Date Is 2020 For Key Technologies To Be At A Technology Readiness Level (Trl) Of Four To Six (I.E., System Or Sub-System Prototype Demonstrated In A Relevant Environment). This Corresponds To A Projected Aircraft Entry Into Service No Earlier Than 2025. These Goals And Timeframe Are Defined By Nasa As N21. This Effort Builds Upon Previous Contract Work By Boeing. The Hybrid Wing Body (Hwb) Aircraft Was Previously Identified As One Concept That Has The Potential To Meet The Era Projects Aircraft Noise Goal. Nasa Published In American Institute Of Aeronautics And Astronautics (Aiaa) Paper Numbers 2010-3912 And 2010-3913 Results Showing A Technical Path For The Hwb Concept To Meet The 42 Db Goal. Under The Era Advanced Vehicle Configurations (Avc) Task The Advanced Hwb Aircraft Concept Proposed By Boeing Was Shown To Meet All Three Of The Era N2 Goals Simultaneously. Nasa Has Participated In A Detailed And Updated Noise Assessment That Was Published As Aiaa Paper 2014-0365 (Guo, Burley, And Thomas) Including Comparison With The Previous Nasa Noise Assessment. Finally, Under Smaaart Task Order Nnl13ab86t, Boeing Is Currently Working With An Updated Design Of Its Hwb Preferred System Concept (Psc) Aircraft With Improved Design Features Including A Krueger Flap Leading Edge, An Improved Engine Selection, And Improved Engine/Airframe Integration. In Review Of The Above Research, Nasa Has Identified Four Critical Areas Needed To Improve Nasas Current System Noise Assessment Methodology. Also, Investigation Of Noise Reduction Approaches In These Four Areas Will Result In Higher Confidence Noise Assessments Relative To Meeting The 42 Db Goal. It Is Of Additional Value To Nasa That The Results From This Task Will Also Be Applicable To Assessments Of Other Advanced Aircraft Concepts. The Overall Purpose Of This Task Order Is To Reduce The Risk To Achieving The 42 Db Goal Based On The Most Advanced Assessments To Be Done By Nasa On The Era Vehicle Concepts. _______________ 1. Nasas Research Focuses On Future Aircraft Design Concepts And Technology That Could Be Introduced Into Service In 2020, 2025 And 2030. The First "Next" Generation For 2020 Is Referred To As "N1." The Second Generation Is "N2." The Third And Farthest Out Generation Is "N3." Each Design Generation Offers Technology Features More Sophisticated Than Those Of The Generation Before.  2.0 Scope&Objective(S): 2.1 The Scope Of This Task Order Is Limited To Using Boeings Hwb Psc In The Following Four Technical Areas That Have Been Identified As Critical To Improving The Current State Of The Art Of Nasas Aircraft System Noise Assessments, To Achieve The 42 Db Noise Goal. 1. High Fidelity Ultra-High Bypass (Uhb) Fan Noise Shielding Effectiveness. 2. Airframe System Database With Component Noise Ranking. 3. Krueger Flap Noise. 4. Flight Path And System Noise Optimization. The Contractor Shall Utilize Computational And Analytical Modeling Methods And Analysis Of Existing Experimental And Simulation Data In Conducting The Work Under This Sow. 2.2 The Objectives Of This Task Order Are To: 1. Develop Shielding Suppression Maps From High Fidelity Simulations Of Uhb Aft Radiated Fan Noise That Are To Be Used In System Noise Assessments. 2. Develop And Predict The Performance Of A Conc
- Nasa Langley Research Center
- National Aeronautics And Space Administration (Nasa)
- $2,382,031.79
- National Aeronautics And Space Administration (Nasa)
- NNL14AB13T
- Statement Of Work (Sow) Smaaart Task Title: Low-Boom Flight Demonstrator (Lbfd) Concept Refinement Study 1.0 Introduction/Background: The Overall Goal Of The Nasa Fundamental Aeronautics Programs High Speed Project Is To Develop And Validate The Tools, Technologies, And Concepts To Overcome The Barriers To Practical High-Speed Vehicles. During The 2013 - 2017 Time Period, The High Speed Project Has Placed A Priority On The Development Of Tools And Integrated Concepts That Will Enable Demonstration Of Overland Supersonic Flight With An Acceptable Sonic Boom. Two Of The High Speed Projects Technical Challenges In This Time Frame Relate To This Priority. They Are Low Sonic Boom Design Tools And The Development Of Sonic Boom Community Response Metrics And Methodologies. The High Speed Project Also Has A Technical Challenge Of Achieving Acceptable Airport Community Noise. In Addition To These Near-Term Technical Challenges, The High Speed Project Continues To Invest In Longer-Term Research On Other Barriers To High-Speed Aircraft Such As High Altitude Emissions, Cruise Efficiency, Aeroservoelasticity, Flight Systems, And Scramjet Propulsion. The Selection Of These Technical Challenges Described Above Was Based On Successful Fundamental Aeronautics Supersonics Project Research Conducted Over The Previous Several Years. Although Broader In Overall Scope Than The High Speed Project, The Supersonics Project Also Contained Elements That Focused On Low Sonic Boom Design And Sonic Boom Community Response. This Work Culminated In The 2009 Award Of The N+2 Systems Validation Contracts. The Objective Of These Nasa Research Announcement (Nra)-Funded Efforts Was To Evaluate Tools And Technologies For Supersonic Civil Aircraft Design. The Studies Have Helped Validate These Tool Sets And Technologies Through Successful Wind Tunnel Testing Of Scale Models. The Next Critical Steps In Overcoming The Barrier To Overland Supersonic Flight Are Flight Validation Of These Tools And Technologies Coupled With Community Response Studies And Research Flights That Will Provide Data To Support The Development Of A Noise-Based Regulatory Standard To Replace The Current Prohibition Of Civil Overland Supersonic Flight. Based On Recent Successful Efforts, The High Speed Project Was Directed To Focus On Ensuring The Readiness Of Low-Boom Design Tools For Application In A Manned Flight Demonstration Project And On The Validation Of Field Study Methodologies, Survey Tools, And The Test Protocols Required To Support Community Overflight Studies. The High Speed Project Was Also Tasked With Conducting Concept Studies And Research To Inform The Decision Process Regarding A Potential Flight Demonstration Program Including The Development And Definition Of Programmatic, Technical, And Cost Requirements For A Low-Boom Flight Demonstration (Lbfd) Project. The Primary Objectives Of The Lbfd Project Would Be Two-Fold: The Flight Validation Of Design Tools&Technologies Applicable To Low Sonic Boom Aircraft And The Creation Of Community Response Data That Will Support The Development Of A Noise-Based Standard For Supersonic Overland Flight. To Investigate The Potential Lbfd, Nasa Initiated A Lbfd Concept Formulation Study In March 2013. The Goals Of The Lbfd Concept Formulation Study Were To Define The Initial Lbfd Mission Requirements, Provide A Concept Definition Consistent With The Mission Requirements, And Provide Concept Formulation Planning And Documentation Required For The Lbfd Effort. For The Purposes Of The Lbfd Concept Formulation Study, The Lbfd Project Was Envisioned As Three Distinct Phases. Phase 1 Included All Required Lbfd Aircraft Development Activities From System Definition And Preliminary Design Through Fabrication, Checkout, And First Flight Through Supersonic Envelope Expansion. Phases 1&2 Were Expected To Include Minimal Technology Development And Not Exceed 5 Years In Duration. Phase 2 Transitioned From E
- 17 Aug 2021
- Statement Of Work (Sow) Smaaart Task Title: Low-Boom Flight Demonstrator (Lbfd) Concept Refinement Study 1.0 Introduction/Background: The Overall Goal Of The Nasa Fundamental Aeronautics Programs High Speed Project Is To Develop And Validate The Tools, Technologies, And Concepts To Overcome The Barriers To Practical High-Speed Vehicles. During The 2013 - 2017 Time Period, The High Speed Project Has Placed A Priority On The Development Of Tools And Integrated Concepts That Will Enable Demonstration Of Overland Supersonic Flight With An Acceptable Sonic Boom. Two Of The High Speed Projects Technical Challenges In This Time Frame Relate To This Priority. They Are Low Sonic Boom Design Tools And The Development Of Sonic Boom Community Response Metrics And Methodologies. The High Speed Project Also Has A Technical Challenge Of Achieving Acceptable Airport Community Noise. In Addition To These Near-Term Technical Challenges, The High Speed Project Continues To Invest In Longer-Term Research On Other Barriers To High-Speed Aircraft Such As High Altitude Emissions, Cruise Efficiency, Aeroservoelasticity, Flight Systems, And Scramjet Propulsion. The Selection Of These Technical Challenges Described Above Was Based On Successful Fundamental Aeronautics Supersonics Project Research Conducted Over The Previous Several Years. Although Broader In Overall Scope Than The High Speed Project, The Supersonics Project Also Contained Elements That Focused On Low Sonic Boom Design And Sonic Boom Community Response. This Work Culminated In The 2009 Award Of The N+2 Systems Validation Contracts. The Objective Of These Nasa Research Announcement (Nra)-Funded Efforts Was To Evaluate Tools And Technologies For Supersonic Civil Aircraft Design. The Studies Have Helped Validate These Tool Sets And Technologies Through Successful Wind Tunnel Testing Of Scale Models. The Next Critical Steps In Overcoming The Barrier To Overland Supersonic Flight Are Flight Validation Of These Tools And Technologies Coupled With Community Response Studies And Research Flights That Will Provide Data To Support The Development Of A Noise-Based Regulatory Standard To Replace The Current Prohibition Of Civil Overland Supersonic Flight. Based On Recent Successful Efforts, The High Speed Project Was Directed To Focus On Ensuring The Readiness Of Low-Boom Design Tools For Application In A Manned Flight Demonstration Project And On The Validation Of Field Study Methodologies, Survey Tools, And The Test Protocols Required To Support Community Overflight Studies. The High Speed Project Was Also Tasked With Conducting Concept Studies And Research To Inform The Decision Process Regarding A Potential Flight Demonstration Program Including The Development And Definition Of Programmatic, Technical, And Cost Requirements For A Low-Boom Flight Demonstration (Lbfd) Project. The Primary Objectives Of The Lbfd Project Would Be Two-Fold: The Flight Validation Of Design Tools&Technologies Applicable To Low Sonic Boom Aircraft And The Creation Of Community Response Data That Will Support The Development Of A Noise-Based Standard For Supersonic Overland Flight. To Investigate The Potential Lbfd, Nasa Initiated A Lbfd Concept Formulation Study In March 2013. The Goals Of The Lbfd Concept Formulation Study Were To Define The Initial Lbfd Mission Requirements, Provide A Concept Definition Consistent With The Mission Requirements, And Provide Concept Formulation Planning And Documentation Required For The Lbfd Effort. For The Purposes Of The Lbfd Concept Formulation Study, The Lbfd Project Was Envisioned As Three Distinct Phases. Phase 1 Included All Required Lbfd Aircraft Development Activities From System Definition And Preliminary Design Through Fabrication, Checkout, And First Flight Through Supersonic Envelope Expansion. Phases 1&2 Were Expected To Include Minimal Technology Development And Not Exceed 5 Years In Duration. Phase 2 Transitioned From E
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $4,638,466.71
- National Aeronautics And Space Administration (Nasa)
- 80HQTR17C0011
- Under This Effort, Boeing Will Team With The Nanofabrication Group At The California Institute Of Technology To Perform The Following Efforts Relative To Research And Development Field Emission Vacuum Electronic Devices For Operation Above 500 Degrees Celsius. (1) Demonstrate Nanotride Devices Based On Field Emission Vacuum (Fev) Electronics Technology (2) Design And Fabricate Small Integrated Circuit (Oscillator For Frequencies Corresponding To S-Band, 2Ghz) (3) Verify The Operation Of Devices And Oscillator Circuit At 500 C In Vacuum, For Over 1,500 Hours (60 Days). Most Semiconductor Devices Operate Up To 250 C. Recent Advances In Carbide And Nitride Semiconductors Hold Promise For Higher Temperatures, Yet Are Associated With High R&D Costs. There Is A Need For Technology With The Simplicity Of Vacuum Tubes And With Micron Sizes. This Contract Is For The Development And Fabrication Of Field Emission Vacuum (Fev) Devices And An Oscillator Circuit For 2 Ghx (S-Band). Implementation Will Be Complimented By Theoretical/Simulation Analysis Of The Path To X-Band. Additionally, The Effort Will Include The Following (1) Development Of A Device Model For Hspice Circuit Simulations And (2) Simulation Using First-Principles Modeling Tools, Of Metal Migration For Tungsten And Derivatives At High Temperatures.
- 29 Jun 2022
- Under This Effort, Boeing Will Team With The Nanofabrication Group At The California Institute Of Technology To Perform The Following Efforts Relative To Research And Development Field Emission Vacuum Electronic Devices For Operation Above 500 Degrees Celsius. (1) Demonstrate Nanotride Devices Based On Field Emission Vacuum (Fev) Electronics Technology (2) Design And Fabricate Small Integrated Circuit (Oscillator For Frequencies Corresponding To S-Band, 2Ghz) (3) Verify The Operation Of Devices And Oscillator Circuit At 500 C In Vacuum, For Over 1,500 Hours (60 Days). Most Semiconductor Devices Operate Up To 250 C. Recent Advances In Carbide And Nitride Semiconductors Hold Promise For Higher Temperatures, Yet Are Associated With High R&D Costs. There Is A Need For Technology With The Simplicity Of Vacuum Tubes And With Micron Sizes. This Contract Is For The Development And Fabrication Of Field Emission Vacuum (Fev) Devices And An Oscillator Circuit For 2 Ghx (S-Band). Implementation Will Be Complimented By Theoretical/Simulation Analysis Of The Path To X-Band. Additionally, The Effort Will Include The Following (1) Development Of A Device Model For Hspice Circuit Simulations And (2) Simulation Using First-Principles Modeling Tools, Of Metal Migration For Tungsten And Derivatives At High Temperatures.
- Nasa Headquarters
- National Aeronautics And Space Administration (Nasa)
- $599,558.00
- National Aeronautics And Space Administration (Nasa)