Atk Space Systems Inc.
Dba Atk
CAGE Code: 8V543
NCAGE Code: 8V543
Status: Active
Type: Manufacturer
Dun & Bradstreet (DUNS): 032516361
Summary
Atk Space Systems Inc., Dba Atk is an Active Manufacturer with the Cage Code 8V543 and is tracked by Dun & Bradstreet under DUNS Number 032516361..
Address
11310 Frederick Ave
Beltsville MD 20705-2005
United States
Points of Contact
No Points of Contact...
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Frequently Asked Questions (FAQ) for CAGE 8V543
- What is CAGE Code 8V543?
- 8V543 is the unique identifier used by NATO Organizations to reference the physical entity known as Atk Space Systems Inc. Dba Atk located at 11310 Frederick Ave, Beltsville MD 20705-2005, United States.
- Who is CAGE Code 8V543?
- 8V543 refers to Atk Space Systems Inc. Dba Atk located at 11310 Frederick Ave, Beltsville MD 20705-2005, United States.
- Where is CAGE Code 8V543 Located?
- CAGE Code 8V543 is located in Beltsville, MD, USA.
Contracting History for CAGE 8V543 Most Recent 25 Records
- NNL12AA49T
- Statement Of Work (Sow) - Task Title: Hypervelocity Mixing Project 1.0 Introduction/Background: The Propulsion Discipline Of The Nasa Hypersonics Project Has Initiated A New Research Project To Investigate The Injection And Mixing Of Fuel And Air For Scramjet Engines At Hypervelocity Flight Speeds (Generally Considered Mach 10 And Greater). This Research Project Will Enhance Our Understanding Of Scramjet Injection And Mixing Devices And Will Provide A Controlled Test Environment To Evaluate Innovative Ideas. One Of The Milestones For The Hypersonics Project Is To Develop An Air-Breathing Combined Cycle Space Launch Vehicle. To Achieve This Milestone, A Scramjet Engine Which Can Operate At Hypervelocity Flight Speeds Is Critical. Since The Scramjet Mixing And Combustion Processes Are Known To Have The Greatest Potential For Improving Scramjet Engine Performance And Efficiency, This Research Project Is Intended To Provide A Major Step Towards Reaching The Hypersonics Project Milestone. The Hypervelocity Mixing Project, Which Is Scheduled To Begin In Fy12, Will Involve Ground-Based Experiments In The Nasa Langley Research Center (Larc) Arc-Heated Scramjet Test Facility (Ahstf). Candidate Injector Concepts Will Be Fabricated At Langley Using The Selective Laser Melting Process And Will Be Mounted To A Common Plate In The Test Facility. Flowfield Measurements Will Be Made Using Laser-Based Optical Diagnostics And With In-Stream Pressure And Gas Sampling Rakes Positioned Downstream Of The Injector Hardware. The Expected Outcome Of The Hypervelocity Mixing Project Is High-Speed Injectors That Significantly Improve Scramjet Performance (I.E., Faster Mixing With Decreased Drag) In The Hypervelocity Speed Range. This Task Order Is Intended To Provide Design And Fabrication Support Of The Major Hardware Components Necessary To Successfully Complete The Goals Of This Project. 2.0 Scope / Objective(S): The Scope Of This Task Order Is To Obtain The Design, Analysis, Fabrication, And Manufacturing Schedules Of The Hardware Necessary To Test And Evaluate Various Fuel Injection Devices That Will Be Tested In The Langley Ahstf. The Objectives Of This Task Order Are To: 1) Obtain Detailed Engineering Designs, Analysis, And Engineering Drawings Of The Test Hardware. 2) Delivery Of Test Hardware.
- 1 Aug 2012
- Statement Of Work (Sow) - Task Title: Hypervelocity Mixing Project 1.0 Introduction/Background: The Propulsion Discipline Of The Nasa Hypersonics Project Has Initiated A New Research Project To Investigate The Injection And Mixing Of Fuel And Air For Scramjet Engines At Hypervelocity Flight Speeds (Generally Considered Mach 10 And Greater). This Research Project Will Enhance Our Understanding Of Scramjet Injection And Mixing Devices And Will Provide A Controlled Test Environment To Evaluate Innovative Ideas. One Of The Milestones For The Hypersonics Project Is To Develop An Air-Breathing Combined Cycle Space Launch Vehicle. To Achieve This Milestone, A Scramjet Engine Which Can Operate At Hypervelocity Flight Speeds Is Critical. Since The Scramjet Mixing And Combustion Processes Are Known To Have The Greatest Potential For Improving Scramjet Engine Performance And Efficiency, This Research Project Is Intended To Provide A Major Step Towards Reaching The Hypersonics Project Milestone. The Hypervelocity Mixing Project, Which Is Scheduled To Begin In Fy12, Will Involve Ground-Based Experiments In The Nasa Langley Research Center (Larc) Arc-Heated Scramjet Test Facility (Ahstf). Candidate Injector Concepts Will Be Fabricated At Langley Using The Selective Laser Melting Process And Will Be Mounted To A Common Plate In The Test Facility. Flowfield Measurements Will Be Made Using Laser-Based Optical Diagnostics And With In-Stream Pressure And Gas Sampling Rakes Positioned Downstream Of The Injector Hardware. The Expected Outcome Of The Hypervelocity Mixing Project Is High-Speed Injectors That Significantly Improve Scramjet Performance (I.E., Faster Mixing With Decreased Drag) In The Hypervelocity Speed Range. This Task Order Is Intended To Provide Design And Fabrication Support Of The Major Hardware Components Necessary To Successfully Complete The Goals Of This Project. 2.0 Scope / Objective(S): The Scope Of This Task Order Is To Obtain The Design, Analysis, Fabrication, And Manufacturing Schedules Of The Hardware Necessary To Test And Evaluate Various Fuel Injection Devices That Will Be Tested In The Langley Ahstf. The Objectives Of This Task Order Are To: 1) Obtain Detailed Engineering Designs, Analysis, And Engineering Drawings Of The Test Hardware. 2) Delivery Of Test Hardware.
- Langley Research Center
- National Aeronautics And Space Administration (Nasa)
- $296,888.00
- National Aeronautics And Space Administration (Nasa)
- 0002
- 199909!1700!2950!E3230!Naval Research Laboratory !N0001497d2020 !A!*!000204 !19981222!19990910!032516361!032516361!032516361!N!8V543!Swales And Associates, Inc !5050 Powder Mill Rd !Beltsville !Md!20705!06400!033!24!Beltsville !Prince George S !Maryland !0001!+000000424774!N!N!000000000000!Ac22!Rdte/Missile And Space Systems-Applied Research !S1 !Services !2000!Not Discernable Or Classified !8731!5!B!S!C!B!A!*!A !N!U!1!001!B!* !Z!N!Z!* !* !N!B!*!Z!*!A!A!A!*!* !*!N!A!B!N!*!*!*!*!*!
- 22 Dec 1998
- 199909!1700!2950!E3230!Naval Research Laboratory !N0001497d2020 !A!*!000204 !19981222!19990910!032516361!032516361!032516361!N!8V543!Swales And Associates, Inc !5050 Powder Mill Rd !Beltsville !Md!20705!06400!033!24!Beltsville !Prince George S !Maryland !0001!+000000424774!N!N!000000000000!Ac22!Rdte/Missile And Space Systems-Applied Research !S1 !Services !2000!Not Discernable Or Classified !8731!5!B!S!C!B!A!*!A !N!U!1!001!B!* !Z!N!Z!* !* !N!B!*!Z!*!A!A!A!*!* !*!N!A!B!N!*!*!*!*!*!
- Naval Research Laboratory
- Department Of Defense (Dod)
- $2,247,211.00
- Department Of Defense (Dod)
- NNL12AD04T
- Igf::0T::Igf Statement Of Work (Sow) Smaaart Task Title: Ahstf Enhanced Mixing Research Project 1.0 Introduction/Background: The Hypersonic Airbreathing Propulsion Branch (Hapb) At Nasa Langley Research Center (Larc) Recently Initiated The Ahstf Enhanced Mixing Research Project Which Seeks To Meet Future Hypersonic Research Requirements. The Purpose Of This Project Is To Investigate And Develop Flight Simulation Capability And Improve The Ability To Assess Flow Quality For Hypersonic Research. Improved Diagnostics And Measurement Systems Are Needed To Routinely Quantify The Flow Properties Delivered To The Test Articles. This Project Also Includes Investigating Fuel Injection And Mixing For Scramjet Engines To Enhance Our Understanding Of Scramjet Fuel Injection And Mixing Devices In A Controlled Test Environment To Evaluate Innovative Concepts. Since The Scramjet Mixing And Combustion Processes Are Known To Have The Greatest Potential For Improving Scramjet Engine Performance And Efficiency, This Project Seeks To Provide A Major Step Towards Developing Practical Propulsion Systems For Aerospace Vehicles Operating In The Hypersonic Speed Regime. The Ahstf Enhanced Mixing Research Project, Scheduled To Be Implemented In Fiscal Year (Fy) 13, Involves The Research, Development, And Installation Of Two New Facility Nozzles (I.E., Mach 3.5 And Mach 2.2) To Demonstrate Mach 2.5 To 4.0 Flight Simulated Conditions. 2.0 Scope And Objective(S): The Scope Of This Task Order Is To Research, Procure, And Develop The Ahstf With Major Hardware Components Necessary To Successfully Complete The Ahstf Enhanced Mixing Project. The Objectives Of This Task Order Are To Obtain: 1) Procure Facility Test Hardware. 2) Test And Evaluate Various Fuel Injection And Mixing Devices In The Ahstf. 3.0 Description Of The Work/Tasks To Be Performed: The Contactor Shall Design, Analyze, And Fabricate The Following Component(S): 1) A Mach 3.5 Facility Nozzle. 2) A Mach 2.2 Facility Nozzle. 3) A Rake Traverse System. 4) Three (3) In-Stream Rakes For The Facility Nozzle Exit. 5) Three (3) In-Stream Rakes For The Mixing Test Apparatus. 6) A Gas Composition Measurement System. 7) Four (4) Facility Nozzle Jet Stretchers. Note: Larc Will Be Responsible For The Installation And Integration Of This Hardware Into The Ahsft. A Cad Image Of The Ahstf, With Its Mixing Test Apparatus Installed In The Test Cabin Is Shown In Sow 8.1. The Rake Traverse System And In-Stream Rakes Will Be Used To Survey The Flow Over A Range Of Axial Locations Along The Test Cabin From The Nozzle Exit To The End Of The Mixing Region. General Requirements: A) All Hardware Shall Integrate/Install Within The Ahstf. B) All Hardware Shall Incorporate Design Features That Reduce Maintenance Time. Design Choices That Allow Day Shift Configuration Changes Are Preferred As Long As They Do Not Compromise The Functionality Or Design Life. C) All Fluid, Electrical, And Instrumentation Lines Shall Incorporate Matching Connection To The Adjoining Facility Interface. D) All Hardware Shall Comply With Langley Procedural Requirement (Lpr) 1710.15 Entitled Wind Tunnel Model Systems Criteria (Gfi 5.1). The Contractor Shall Perform The Following Tasks: 3.1 Mach 3.5 And Mach 2.2 Facility Nozzles The Government Has Developed The Requirements For The Facility Nozzles With The Intent To Minimize Hardware Design And Fabrication Costs By Limiting The Maximum Operating Temperature To Levels Consistent With Un-Cooled Hardware. The Design Shall Take Advantage Of Materials And Thermal Management That Provides The Best Trade-Off Between Cost And Dimensional Tolerance. 3.1.1 The Contractor Shall Design, Analyze, And Deliver Engineering Drawings For A Mach 3.5 Facility Nozzle And A Mach 2.2 Facility Nozzle Which Deliver Flow To The Test Cabin/Experiment Hardware. A. Each Nozzle Shall Mate With Existin
- 3 Sep 2013
- Igf::0T::Igf Statement Of Work (Sow) Smaaart Task Title: Ahstf Enhanced Mixing Research Project 1.0 Introduction/Background: The Hypersonic Airbreathing Propulsion Branch (Hapb) At Nasa Langley Research Center (Larc) Recently Initiated The Ahstf Enhanced Mixing Research Project Which Seeks To Meet Future Hypersonic Research Requirements. The Purpose Of This Project Is To Investigate And Develop Flight Simulation Capability And Improve The Ability To Assess Flow Quality For Hypersonic Research. Improved Diagnostics And Measurement Systems Are Needed To Routinely Quantify The Flow Properties Delivered To The Test Articles. This Project Also Includes Investigating Fuel Injection And Mixing For Scramjet Engines To Enhance Our Understanding Of Scramjet Fuel Injection And Mixing Devices In A Controlled Test Environment To Evaluate Innovative Concepts. Since The Scramjet Mixing And Combustion Processes Are Known To Have The Greatest Potential For Improving Scramjet Engine Performance And Efficiency, This Project Seeks To Provide A Major Step Towards Developing Practical Propulsion Systems For Aerospace Vehicles Operating In The Hypersonic Speed Regime. The Ahstf Enhanced Mixing Research Project, Scheduled To Be Implemented In Fiscal Year (Fy) 13, Involves The Research, Development, And Installation Of Two New Facility Nozzles (I.E., Mach 3.5 And Mach 2.2) To Demonstrate Mach 2.5 To 4.0 Flight Simulated Conditions. 2.0 Scope And Objective(S): The Scope Of This Task Order Is To Research, Procure, And Develop The Ahstf With Major Hardware Components Necessary To Successfully Complete The Ahstf Enhanced Mixing Project. The Objectives Of This Task Order Are To Obtain: 1) Procure Facility Test Hardware. 2) Test And Evaluate Various Fuel Injection And Mixing Devices In The Ahstf. 3.0 Description Of The Work/Tasks To Be Performed: The Contactor Shall Design, Analyze, And Fabricate The Following Component(S): 1) A Mach 3.5 Facility Nozzle. 2) A Mach 2.2 Facility Nozzle. 3) A Rake Traverse System. 4) Three (3) In-Stream Rakes For The Facility Nozzle Exit. 5) Three (3) In-Stream Rakes For The Mixing Test Apparatus. 6) A Gas Composition Measurement System. 7) Four (4) Facility Nozzle Jet Stretchers. Note: Larc Will Be Responsible For The Installation And Integration Of This Hardware Into The Ahsft. A Cad Image Of The Ahstf, With Its Mixing Test Apparatus Installed In The Test Cabin Is Shown In Sow 8.1. The Rake Traverse System And In-Stream Rakes Will Be Used To Survey The Flow Over A Range Of Axial Locations Along The Test Cabin From The Nozzle Exit To The End Of The Mixing Region. General Requirements: A) All Hardware Shall Integrate/Install Within The Ahstf. B) All Hardware Shall Incorporate Design Features That Reduce Maintenance Time. Design Choices That Allow Day Shift Configuration Changes Are Preferred As Long As They Do Not Compromise The Functionality Or Design Life. C) All Fluid, Electrical, And Instrumentation Lines Shall Incorporate Matching Connection To The Adjoining Facility Interface. D) All Hardware Shall Comply With Langley Procedural Requirement (Lpr) 1710.15 Entitled Wind Tunnel Model Systems Criteria (Gfi 5.1). The Contractor Shall Perform The Following Tasks: 3.1 Mach 3.5 And Mach 2.2 Facility Nozzles The Government Has Developed The Requirements For The Facility Nozzles With The Intent To Minimize Hardware Design And Fabrication Costs By Limiting The Maximum Operating Temperature To Levels Consistent With Un-Cooled Hardware. The Design Shall Take Advantage Of Materials And Thermal Management That Provides The Best Trade-Off Between Cost And Dimensional Tolerance. 3.1.1 The Contractor Shall Design, Analyze, And Deliver Engineering Drawings For A Mach 3.5 Facility Nozzle And A Mach 2.2 Facility Nozzle Which Deliver Flow To The Test Cabin/Experiment Hardware. A. Each Nozzle Shall Mate With Existin
- Langley Research Center
- National Aeronautics And Space Administration (Nasa)
- $2,546,027.00
- National Aeronautics And Space Administration (Nasa)
- GSFC0200101DNAS501090
- Mechanical Engineering Support Services
- 20 Sep 2007
- Mechanical Engineering Support Services
- Goddard Space Flight Center
- National Aeronautics And Space Administration (Nasa)
- $596,800,894.22
- National Aeronautics And Space Administration (Nasa)
- GSFC0200101DNAS501090
- Mechanical Engineering Support Services
- 29 Feb 2008
- Mechanical Engineering Support Services
- Goddard Space Flight Center
- National Aeronautics And Space Administration (Nasa)
- $596,800,894.22
- National Aeronautics And Space Administration (Nasa)
- GSFC0200101DNAS501090
- Mechanical Engineering Support Services
- 1 Oct 2003
- Mechanical Engineering Support Services
- Goddard Space Flight Center
- National Aeronautics And Space Administration (Nasa)
- $596,800,894.22
- National Aeronautics And Space Administration (Nasa)
- NNL10AA04B
- 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 Confirm 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
- 13 May 2014
- 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 Confirm 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)
- GSFC0200101DNAS501090
- Mechanical Engineering Support Services
- 31 Dec 2007
- Mechanical Engineering Support Services
- Goddard Space Flight Center
- National Aeronautics And Space Administration (Nasa)
- $596,800,894.22
- National Aeronautics And Space Administration (Nasa)
- GSFC0200101DNAS501090
- Mechanical Engineering Support Services
- 22 Jun 2005
- Mechanical Engineering Support Services
- Goddard Space Flight Center
- National Aeronautics And Space Administration (Nasa)
- $596,800,894.22
- National Aeronautics And Space Administration (Nasa)
- GSFC0200101DNAS501090
- Mechanical Engineering Support Services
- 24 Aug 2005
- Mechanical Engineering Support Services
- Goddard Space Flight Center
- National Aeronautics And Space Administration (Nasa)
- $596,800,894.22
- National Aeronautics And Space Administration (Nasa)
- GSFC0200101DNAS501090
- Mechanical Engineering Support Services
- 1 Oct 2003
- Mechanical Engineering Support Services
- Goddard Space Flight Center
- National Aeronautics And Space Administration (Nasa)
- $596,800,894.22
- National Aeronautics And Space Administration (Nasa)
- GSFC0200101DNAS501090
- Mechanical Engineering Support Services
- 27 Mar 2006
- Mechanical Engineering Support Services
- Goddard Space Flight Center
- National Aeronautics And Space Administration (Nasa)
- $596,800,894.22
- National Aeronautics And Space Administration (Nasa)
- IND12PC00381
- Defense Advanced Research Projects Agency, Tactical Technology Office Darpa-Baa-12-02 "Phoenix" Program - Property Transfer
- 8 Sep 2023
- Defense Advanced Research Projects Agency, Tactical Technology Office Darpa-Baa-12-02 "Phoenix" Program - Property Transfer
- Ibc Acq Svcs Directorate (00004)
- Department Of The Interior (Doi)
- $1,729,231.48
- Department Of The Interior (Doi)
- 0003
- 199911!1700!4688!E3230!Naval Research Laboratory !N0001497d2020 !A!*!000303 !19990827!20000602!032516361!032516361!032516361!N!8V543!Swales And Associates, Inc !5050 Powder Mill Rd !Beltsville !Md!20705!06400!033!24!Beltsville !Prince George S !Maryland !0001!+000000123864!N!N!000000000000!Ac22!Rdte/Missile And Space Systems-Applied Research !S1 !Services !2000!Not Discernable Or Classified !8731!5!B!S!C!B!A!*!A !N!U!1!001!B!* !Z!N!Z!* !* !N!B!*!Z!*!A!A!A!*!* !*!N!A!B!N!*!*!*!*!*!
- 27 Aug 1999
- 199911!1700!4688!E3230!Naval Research Laboratory !N0001497d2020 !A!*!000303 !19990827!20000602!032516361!032516361!032516361!N!8V543!Swales And Associates, Inc !5050 Powder Mill Rd !Beltsville !Md!20705!06400!033!24!Beltsville !Prince George S !Maryland !0001!+000000123864!N!N!000000000000!Ac22!Rdte/Missile And Space Systems-Applied Research !S1 !Services !2000!Not Discernable Or Classified !8731!5!B!S!C!B!A!*!A !N!U!1!001!B!* !Z!N!Z!* !* !N!B!*!Z!*!A!A!A!*!* !*!N!A!B!N!*!*!*!*!*!
- Naval Research Laboratory
- Department Of Defense (Dod)
- $3,560,211.00
- Department Of Defense (Dod)
- NNL12AD04T
- Igf::Ot::Igf Statement Of Work (Sow) Smaaart Task Title: Ahstf Enhanced Mixing Research Project 1.0 Introduction/Background: The Hypersonic Airbreathing Propulsion Branch (Hapb) At Nasa Langley Research Center (Larc) Recently Initiated The Ahstf Enhanced Mixing Research Project Which Seeks To Meet Future Hypersonic Research Requirements. The Purpose Of This Project Is To Investigate And Develop Flight Simulation Capability And Improve The Ability To Assess Flow Quality For Hypersonic Research. Improved Diagnostics And Measurement Systems Are Needed To Routinely Quantify The Flow Properties Delivered To The Test Articles. This Project Also Includes Investigating Fuel Injection And Mixing For Scramjet Engines To Enhance Our Understanding Of Scramjet Fuel Injection And Mixing Devices In A Controlled Test Environment To Evaluate Innovative Concepts. Since The Scramjet Mixing And Combustion Processes Are Known To Have The Greatest Potential For Improving Scramjet Engine Performance And Efficiency, This Project Seeks To Provide A Major Step Towards Developing Practical Propulsion Systems For Aerospace Vehicles Operating In The Hypersonic Speed Regime. The Ahstf Enhanced Mixing Research Project, Scheduled To Be Implemented In Fiscal Year (Fy) 13, Involves The Research, Development, And Installation Of Two New Facility Nozzles (I.E., Mach 3.5 And Mach 2.2) To Demonstrate Mach 2.5 To 4.0 Flight Simulated Conditions. 2.0 Scope And Objective(S): The Scope Of This Task Order Is To Research, Procure, And Develop The Ahstf With Major Hardware Components Necessary To Successfully Complete The Ahstf Enhanced Mixing Project. The Objectives Of This Task Order Are To Obtain: 1) Procure Facility Test Hardware. 2) Test And Evaluate Various Fuel Injection And Mixing Devices In The Ahstf.  3.0 Description Of The Work/Tasks To Be Performed: The Contactor Shall Design, Analyze, And Fabricate The Following Component(S): 1) A Mach 3.5 Facility Nozzle. 2) A Mach 2.2 Facility Nozzle. 3) A Rake Traverse System. 4) Three (3) In-Stream Rakes For The Facility Nozzle Exit. 5) Three (3) In-Stream Rakes For The Mixing Test Apparatus. 6) A Gas Composition Measurement System. 7) Four (4) Facility Nozzle Jet Stretchers. Note: Larc Will Be Responsible For The Installation And Integration Of This Hardware Into The Ahsft. A Cad Image Of The Ahstf, With Its Mixing Test Apparatus Installed In The Test Cabin Is Shown In Sow 8.1. The Rake Traverse System And In-Stream Rakes Will Be Used To Survey The Flow Over A Range Of Axial Locations Along The Test Cabin From The Nozzle Exit To The End Of The Mixing Region. General Requirements: A) All Hardware Shall Integrate/Install Within The Ahstf. B) All Hardware Shall Incorporate Design Features That Reduce Maintenance Time. Design Choices That Allow Day Shift Configuration Changes Are Preferred As Long As They Do Not Compromise The Functionality Or Design Life. C) All Fluid, Electrical, And Instrumentation Lines Shall Incorporate Matching Connection To The Adjoining Facility Interface. D) All Hardware Shall Comply With Langley Procedural Requirement (Lpr) 1710.15 Entitled Wind Tunnel Model Systems Criteria (Gfi 5.1). The Contractor Shall Perform The Following Tasks: 3.1 Mach 3.5 And Mach 2.2 Facility Nozzles The Government Has Developed The Requirements For The Facility Nozzles With The Intent To Minimize Hardware Design And Fabrication Costs By Limiting The Maximum Operating Temperature To Levels Consistent With Un-Cooled Hardware. The Design Shall Take Advantage Of Materials And Thermal Management That Provides The Best Trade-Off Between Cost And Dimensional Tolerance. 3.1.1 The Contractor Shall Design, Analyze, And Deliver Engineering Drawings For A Mach 3.5 Facility Nozzle And A Mach 2.2 Facility Nozzle Which Deliver Flow To The Test Cabin/Experiment Hardware. A. Each Nozzle Shall Mate With Existin
- 28 May 2014
- Igf::Ot::Igf Statement Of Work (Sow) Smaaart Task Title: Ahstf Enhanced Mixing Research Project 1.0 Introduction/Background: The Hypersonic Airbreathing Propulsion Branch (Hapb) At Nasa Langley Research Center (Larc) Recently Initiated The Ahstf Enhanced Mixing Research Project Which Seeks To Meet Future Hypersonic Research Requirements. The Purpose Of This Project Is To Investigate And Develop Flight Simulation Capability And Improve The Ability To Assess Flow Quality For Hypersonic Research. Improved Diagnostics And Measurement Systems Are Needed To Routinely Quantify The Flow Properties Delivered To The Test Articles. This Project Also Includes Investigating Fuel Injection And Mixing For Scramjet Engines To Enhance Our Understanding Of Scramjet Fuel Injection And Mixing Devices In A Controlled Test Environment To Evaluate Innovative Concepts. Since The Scramjet Mixing And Combustion Processes Are Known To Have The Greatest Potential For Improving Scramjet Engine Performance And Efficiency, This Project Seeks To Provide A Major Step Towards Developing Practical Propulsion Systems For Aerospace Vehicles Operating In The Hypersonic Speed Regime. The Ahstf Enhanced Mixing Research Project, Scheduled To Be Implemented In Fiscal Year (Fy) 13, Involves The Research, Development, And Installation Of Two New Facility Nozzles (I.E., Mach 3.5 And Mach 2.2) To Demonstrate Mach 2.5 To 4.0 Flight Simulated Conditions. 2.0 Scope And Objective(S): The Scope Of This Task Order Is To Research, Procure, And Develop The Ahstf With Major Hardware Components Necessary To Successfully Complete The Ahstf Enhanced Mixing Project. The Objectives Of This Task Order Are To Obtain: 1) Procure Facility Test Hardware. 2) Test And Evaluate Various Fuel Injection And Mixing Devices In The Ahstf.  3.0 Description Of The Work/Tasks To Be Performed: The Contactor Shall Design, Analyze, And Fabricate The Following Component(S): 1) A Mach 3.5 Facility Nozzle. 2) A Mach 2.2 Facility Nozzle. 3) A Rake Traverse System. 4) Three (3) In-Stream Rakes For The Facility Nozzle Exit. 5) Three (3) In-Stream Rakes For The Mixing Test Apparatus. 6) A Gas Composition Measurement System. 7) Four (4) Facility Nozzle Jet Stretchers. Note: Larc Will Be Responsible For The Installation And Integration Of This Hardware Into The Ahsft. A Cad Image Of The Ahstf, With Its Mixing Test Apparatus Installed In The Test Cabin Is Shown In Sow 8.1. The Rake Traverse System And In-Stream Rakes Will Be Used To Survey The Flow Over A Range Of Axial Locations Along The Test Cabin From The Nozzle Exit To The End Of The Mixing Region. General Requirements: A) All Hardware Shall Integrate/Install Within The Ahstf. B) All Hardware Shall Incorporate Design Features That Reduce Maintenance Time. Design Choices That Allow Day Shift Configuration Changes Are Preferred As Long As They Do Not Compromise The Functionality Or Design Life. C) All Fluid, Electrical, And Instrumentation Lines Shall Incorporate Matching Connection To The Adjoining Facility Interface. D) All Hardware Shall Comply With Langley Procedural Requirement (Lpr) 1710.15 Entitled Wind Tunnel Model Systems Criteria (Gfi 5.1). The Contractor Shall Perform The Following Tasks: 3.1 Mach 3.5 And Mach 2.2 Facility Nozzles The Government Has Developed The Requirements For The Facility Nozzles With The Intent To Minimize Hardware Design And Fabrication Costs By Limiting The Maximum Operating Temperature To Levels Consistent With Un-Cooled Hardware. The Design Shall Take Advantage Of Materials And Thermal Management That Provides The Best Trade-Off Between Cost And Dimensional Tolerance. 3.1.1 The Contractor Shall Design, Analyze, And Deliver Engineering Drawings For A Mach 3.5 Facility Nozzle And A Mach 2.2 Facility Nozzle Which Deliver Flow To The Test Cabin/Experiment Hardware. A. Each Nozzle Shall Mate With Existin
- Langley Research Center
- National Aeronautics And Space Administration (Nasa)
- $2,546,027.00
- National Aeronautics And Space Administration (Nasa)
- NNL10AA04B
- 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 Confirm 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
- 21 Apr 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 Confirm 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)
- NNL15AA18T
- Igf::Ot::Igf Statement Of Work. Task: 8-Foot High Temperature Tunnel Mixer Liner And Mach 5 High Dynamic Pressure Thermal Analysis. 1.0 Introduction/Background: Planned Future Testing In The Nasa Langley 8 Htt Requires Operation Of The Existing Facility Mixer And Mach 5 High Dynamic Pressure (M5hiq) Nozzle At Temperature Levels Exceeding The Design Value For That Hardware. The 8 Htt Mixer Is The Low Velocity Region Immediately Upstream Of The M5hiq Nozzle. Inside The Facility Mixer, Dilution Air And Hot Flow From The Facility Combustor Are Mixed Together To Form The Entrance Flow To The M5hiq Nozzle. For A Nominal Mach 5 Test, The Mixed Flow Temperature Is Approximately 2150 Rankine. The Facility Has Conducted Numerous Tests At This Nominal Mach 5 Condition And Is Capable Of Delivering Steady Operational Conditions For Period Of 100 Seconds Without Exceeding High Temperature Interlocks Installed At Key Locations On The Mixer Liner And M5hiq Nozzle. Future Customers Have Identified Test Requirements At Conditions Simulating Flight At Mach 5.5. This Simulation Requires That Both The Mixer Liner And The Existing Mach 5 Nozzle Be Operated At Temperatures That Exceed The Design Value. It Is Known That Exceeding The Design Temperature Is Acceptable As Long As The Run Time Is Shortened So That Red-Line Temperature Limits Are Not Violated During A Test Run. However, The Allowable Run Duration Is Not Known. The Allowable Run Time Duration At Temperatures Exceeding The Nominal Design Value Must Be Known So That Future Facility Users Can Determine How Many Runs Are Required For Them To Complete Their Required Test Matrix. 2.0 Scope&Objective(S): 2.1 The Scope Of This Task Order Is To Conduct An Analytical Study To Determine The Allowable Run Time (Seconds) For The Mixer And The M5hiq Nozzle At Stagnation Temperature Levels Exceeding The Nominal Design Level At Nozzle Inlet Stagnation Pressure Levels Provided As Government Furnished Information (Gfi) Under This Task Order. 2.2 The Objectives Of This Task Order Are To: 2.2.1 Analytically Determine The Allowable Run Time For The Existing 8 Htt Mixer And M5hiq Nozzle At Two Conditions Exceeding The Nominal Design Temperature Level. 2.2.2 Identify The Limiting Factor On Run Time For Each Mach Condition And Investigate Design Modifications That Would Extend The Run Time Limits. 3.0 Description Of The Work/Tasks To Be Performed: The Contractor Shall Perform The Following Tasks: 3.1 Mixer Liner And M5hiq Transient Thermal Analysis: (Deliverable Item 4.3) 3.1.1 The Contractor Shall Construct A Single Transient Thermal Model Of The Mixer And M5hiq Nozzle. The Thermal Model Shall Be Constructed From Mixer Liner And M5hiq Hardware Geometry And Material Information Furnished By The Government (Gfi 5.1). 3.1.2 The Contractor Shall Utilize The Transient Thermal Model Developed In Sow Task 3.1.1 To Conduct Transient Thermal Analyses At Two Different Conditions Specified By The Nasa Tech Poc. The Two Different Analysis Conditions Provided By The Government (Gfi 5.2) Will Consist Of The Mixer Stagnation Pressure, The Mixer Stagnation Temperature, And The Total Flow Rate Through The Mixer And M5hiq Nozzle. The Conditions Provided As Gfi 5.2 Will Be Representative Of Flight Simulation At Mach 5.3 And Mach 5.5. The Transient Thermal Analysis Shall Be Utilized By The Contractor To Predict The Time Required For The Mixer And / Or M5hiq Nozzle To Exceed Red-Line Temperature Limits At The Two Flight Simulation Conditions. 3.1.3 The Contractor Shall Identify The Axial Locations In The Mixer / Nozzle Assembly Where The Temperature Exceeds Material Limits. Approaches To Mitigate The Limiting Condition Shall Be Identified And Presented As Part Of The Final Presentation.
- 24 Feb 2015
- Igf::Ot::Igf Statement Of Work. Task: 8-Foot High Temperature Tunnel Mixer Liner And Mach 5 High Dynamic Pressure Thermal Analysis. 1.0 Introduction/Background: Planned Future Testing In The Nasa Langley 8 Htt Requires Operation Of The Existing Facility Mixer And Mach 5 High Dynamic Pressure (M5hiq) Nozzle At Temperature Levels Exceeding The Design Value For That Hardware. The 8 Htt Mixer Is The Low Velocity Region Immediately Upstream Of The M5hiq Nozzle. Inside The Facility Mixer, Dilution Air And Hot Flow From The Facility Combustor Are Mixed Together To Form The Entrance Flow To The M5hiq Nozzle. For A Nominal Mach 5 Test, The Mixed Flow Temperature Is Approximately 2150 Rankine. The Facility Has Conducted Numerous Tests At This Nominal Mach 5 Condition And Is Capable Of Delivering Steady Operational Conditions For Period Of 100 Seconds Without Exceeding High Temperature Interlocks Installed At Key Locations On The Mixer Liner And M5hiq Nozzle. Future Customers Have Identified Test Requirements At Conditions Simulating Flight At Mach 5.5. This Simulation Requires That Both The Mixer Liner And The Existing Mach 5 Nozzle Be Operated At Temperatures That Exceed The Design Value. It Is Known That Exceeding The Design Temperature Is Acceptable As Long As The Run Time Is Shortened So That Red-Line Temperature Limits Are Not Violated During A Test Run. However, The Allowable Run Duration Is Not Known. The Allowable Run Time Duration At Temperatures Exceeding The Nominal Design Value Must Be Known So That Future Facility Users Can Determine How Many Runs Are Required For Them To Complete Their Required Test Matrix. 2.0 Scope&Objective(S): 2.1 The Scope Of This Task Order Is To Conduct An Analytical Study To Determine The Allowable Run Time (Seconds) For The Mixer And The M5hiq Nozzle At Stagnation Temperature Levels Exceeding The Nominal Design Level At Nozzle Inlet Stagnation Pressure Levels Provided As Government Furnished Information (Gfi) Under This Task Order. 2.2 The Objectives Of This Task Order Are To: 2.2.1 Analytically Determine The Allowable Run Time For The Existing 8 Htt Mixer And M5hiq Nozzle At Two Conditions Exceeding The Nominal Design Temperature Level. 2.2.2 Identify The Limiting Factor On Run Time For Each Mach Condition And Investigate Design Modifications That Would Extend The Run Time Limits. 3.0 Description Of The Work/Tasks To Be Performed: The Contractor Shall Perform The Following Tasks: 3.1 Mixer Liner And M5hiq Transient Thermal Analysis: (Deliverable Item 4.3) 3.1.1 The Contractor Shall Construct A Single Transient Thermal Model Of The Mixer And M5hiq Nozzle. The Thermal Model Shall Be Constructed From Mixer Liner And M5hiq Hardware Geometry And Material Information Furnished By The Government (Gfi 5.1). 3.1.2 The Contractor Shall Utilize The Transient Thermal Model Developed In Sow Task 3.1.1 To Conduct Transient Thermal Analyses At Two Different Conditions Specified By The Nasa Tech Poc. The Two Different Analysis Conditions Provided By The Government (Gfi 5.2) Will Consist Of The Mixer Stagnation Pressure, The Mixer Stagnation Temperature, And The Total Flow Rate Through The Mixer And M5hiq Nozzle. The Conditions Provided As Gfi 5.2 Will Be Representative Of Flight Simulation At Mach 5.3 And Mach 5.5. The Transient Thermal Analysis Shall Be Utilized By The Contractor To Predict The Time Required For The Mixer And / Or M5hiq Nozzle To Exceed Red-Line Temperature Limits At The Two Flight Simulation Conditions. 3.1.3 The Contractor Shall Identify The Axial Locations In The Mixer / Nozzle Assembly Where The Temperature Exceeds Material Limits. Approaches To Mitigate The Limiting Condition Shall Be Identified And Presented As Part Of The Final Presentation.
- Langley Research Center
- National Aeronautics And Space Administration (Nasa)
- $107,890.00
- National Aeronautics And Space Administration (Nasa)
- GSFC0200101DNAS501090
- Mechanical Engineering Support Services
- 22 Jun 2006
- Mechanical Engineering Support Services
- Goddard Space Flight Center
- National Aeronautics And Space Administration (Nasa)
- $596,800,894.22
- National Aeronautics And Space Administration (Nasa)
- GSFC0200101DNAS501090
- Mechanical Engineering Support Services
- 1 Oct 2003
- Mechanical Engineering Support Services
- Goddard Space Flight Center
- National Aeronautics And Space Administration (Nasa)
- $596,800,894.22
- National Aeronautics And Space Administration (Nasa)
- GSFC0200101DNAS501090
- Mechanical Engineering Support Services
- 15 May 2002
- Mechanical Engineering Support Services
- Goddard Space Flight Center
- National Aeronautics And Space Administration (Nasa)
- $596,800,894.22
- National Aeronautics And Space Administration (Nasa)
- 0003
- 200010!1700!000248!E3230 !Naval Research Laboratory !N0001497d2020 !A!*!000306 !19991129!20000602!032516361!032516361!032516361!N!8V543!Swales And Associates, Inc !5050 Powder Mill Rd !Beltsville !Md!20705!06400!033!24!Beltsville !Prince George S !Maryland !0001!+000000221739!N!N!000000000000!Ac22!Rdte/Missile And Space Systems-Applied Research !S1 !Services !2000!Not Discernable Or Classified !8731!5!B!S!C!B!A!*!A !N!U!2!001!B!* !Z!N!Z!* !* !N!B!N!Z!*!A!A!A!A!* !*!N!A!B!N!*!*!*!*!*!
- 29 Nov 1999
- 200010!1700!000248!E3230 !Naval Research Laboratory !N0001497d2020 !A!*!000306 !19991129!20000602!032516361!032516361!032516361!N!8V543!Swales And Associates, Inc !5050 Powder Mill Rd !Beltsville !Md!20705!06400!033!24!Beltsville !Prince George S !Maryland !0001!+000000221739!N!N!000000000000!Ac22!Rdte/Missile And Space Systems-Applied Research !S1 !Services !2000!Not Discernable Or Classified !8731!5!B!S!C!B!A!*!A !N!U!2!001!B!* !Z!N!Z!* !* !N!B!N!Z!*!A!A!A!A!* !*!N!A!B!N!*!*!*!*!*!
- Naval Research Laboratory
- Department Of Defense (Dod)
- $3,560,211.00
- Department Of Defense (Dod)
- GSFC0200101DNAS501090
- Mechanical Engineering Support Services
- 26 Sep 2008
- Mechanical Engineering Support Services
- Goddard Space Flight Center
- National Aeronautics And Space Administration (Nasa)
- $596,800,894.22
- National Aeronautics And Space Administration (Nasa)
- GSFC0200101DNAS501090
- Mechanical Engineering Support Services
- 21 Dec 2004
- Mechanical Engineering Support Services
- Goddard Space Flight Center
- National Aeronautics And Space Administration (Nasa)
- $596,800,894.22
- National Aeronautics And Space Administration (Nasa)
- GSFC0200101DNAS501090
- Mechanical Engineering Support Services
- 18 May 2006
- Mechanical Engineering Support Services
- Goddard Space Flight Center
- National Aeronautics And Space Administration (Nasa)
- $596,800,894.22
- National Aeronautics And Space Administration (Nasa)
- NNL11AB41T
- Smaaart Task Order: Statement Of Work (Sow) Task Title: 8-Foot High Temperature Tunnel (8 Htt) Large-Scale Scramjet Engine Test Techniques (Lsett) Test Engineering Support 1.0 Introduction/Background: Nasas Hypersonic Project, The Air Force Research Laboratory (Afrl), And The Department Of Defenses (Dods) Test Resource Management Centers Advanced Propulsion Test Technology Focus Area Have Entered Into A Collaborative Test Effort To Quantify Large Scale Scramjet To Facility Interactions That Affect The Test Article Performance. Future Programs From All Three Agencies Focus On The Development Of Increasingly Large Scramjet Engines. There Are Two Existing National Hypersonic Test Facilities Used To Perform Freejet Testing Of Scramjet Engines. The First Is The Arnold Engineering Development Centers Aerodynamic And Propulsion Test Unit (Aptu) Which Has A 42 Diameter Hypersonic Test Stream. The Second Is The Nasa Langley Research Center 8-Foot High Temperature Tunnel Which Has A 96 Diameter Test Stream. The Development Of Larger Scramjet Engines Places New Demands On These Two Test Facilities And Results In Significant Interaction Between The Test Engine And The Test Facility. It Is Critical That These Interactions And The Impact They Have On The Measured Engine Performance Are Predictable And Well Understood. The Increasing Size Of Future Scramjet Engines Will Result In Blocking A Large Portion Of The Test Facility Hypersonic Flow And Will Also Require Truncation Of The Engine Inlet And Exit Nozzle To Physically Fit Into The Existing Test Facilities. The Truncation Of The Inlet And Nozzle, As Well As The Large Fraction Of Flow Blockage For These Future Large Engines, Will Result In Facility Induced Impacts On The Measured Engine Performance. The Future Development And Production Of Large Scale Scramjets Depend Heavily On The Ability To Accurately Predict The Impact Of The Test Facility On The Measured Data. The Collaborative Testing Effort Between The Three Organizations Will Produce Experimental Data Assessing These Impacts And Providing A Benchmark Data Set Relative To Test Facility / Scramjet Interactions. 2.0 Scope / Objective(S): The Scope Of This Task Is To Provide Test Engineering Support For The Lsett Test In The Nasa Langley 8 Htt. The Testing Is Scheduled To Occur During The Second Half Of Fy 2011, But Test Preparation Is Required To Begin In January 2011 In Order To Meet The Test Schedule. The Objective Of Lsett Testing In The 8 Htt Is To Test A Contractor Designed Scramjet Engine With A Full Inlet And Nozzle In The 8 Htt At Mach 5 Flight Conditions. 3.0 Description Of The Work/Tasks To Be Performed: The Contractor Shall Perform The Following Tasks: 3.1 Test Planning And Documentation. 3.1.1 The Contractor Shall Participate In Weekly Telecons To Define The Integrated Run Sequence Required For Safe Execution Of The Lsett Test In The 8 Htt. The Definition Of The Integrated Run Sequence Shall Be A Collaborative Effort And Will Be Mutually Agreed Upon By The Contractor And Nasa. The Completed Integrated Run Sequence Shall Satisfy All Nasa Langley Test Safety Requirements And The Contractor Engine Operating Limits. Final Approval Will Be Given By The Nasa Task Monitor (Tm) Via Email To The Contractors Project Manager (Pm). The Contractor Shall Update And Maintain The Detailed Integrated Run Sequence Document (Irsd) For Weekly Review During The Telecons. (Deliverable Item 4.3). The Initial Irsd Draft Will Be Provided To The Contractor As Specified Under Government Furnished Information (Gfi) Sow 5.1. 3.1.2 The Contractor Shall Develop, At A Minimum, The Following Facility Systems Verification Check Lists (Deliverable Item 4.4): - Engine Fuel Delivery System. - Water Cooling System Performance. - Silane Ignitor Gas System Performance. - Angle Of Attach/Model Elevator Coordination. - Normal Stop Sequence Of Events. - Abnormal Stop Sequence
- 7 Mar 2011
- Smaaart Task Order: Statement Of Work (Sow) Task Title: 8-Foot High Temperature Tunnel (8 Htt) Large-Scale Scramjet Engine Test Techniques (Lsett) Test Engineering Support 1.0 Introduction/Background: Nasas Hypersonic Project, The Air Force Research Laboratory (Afrl), And The Department Of Defenses (Dods) Test Resource Management Centers Advanced Propulsion Test Technology Focus Area Have Entered Into A Collaborative Test Effort To Quantify Large Scale Scramjet To Facility Interactions That Affect The Test Article Performance. Future Programs From All Three Agencies Focus On The Development Of Increasingly Large Scramjet Engines. There Are Two Existing National Hypersonic Test Facilities Used To Perform Freejet Testing Of Scramjet Engines. The First Is The Arnold Engineering Development Centers Aerodynamic And Propulsion Test Unit (Aptu) Which Has A 42 Diameter Hypersonic Test Stream. The Second Is The Nasa Langley Research Center 8-Foot High Temperature Tunnel Which Has A 96 Diameter Test Stream. The Development Of Larger Scramjet Engines Places New Demands On These Two Test Facilities And Results In Significant Interaction Between The Test Engine And The Test Facility. It Is Critical That These Interactions And The Impact They Have On The Measured Engine Performance Are Predictable And Well Understood. The Increasing Size Of Future Scramjet Engines Will Result In Blocking A Large Portion Of The Test Facility Hypersonic Flow And Will Also Require Truncation Of The Engine Inlet And Exit Nozzle To Physically Fit Into The Existing Test Facilities. The Truncation Of The Inlet And Nozzle, As Well As The Large Fraction Of Flow Blockage For These Future Large Engines, Will Result In Facility Induced Impacts On The Measured Engine Performance. The Future Development And Production Of Large Scale Scramjets Depend Heavily On The Ability To Accurately Predict The Impact Of The Test Facility On The Measured Data. The Collaborative Testing Effort Between The Three Organizations Will Produce Experimental Data Assessing These Impacts And Providing A Benchmark Data Set Relative To Test Facility / Scramjet Interactions. 2.0 Scope / Objective(S): The Scope Of This Task Is To Provide Test Engineering Support For The Lsett Test In The Nasa Langley 8 Htt. The Testing Is Scheduled To Occur During The Second Half Of Fy 2011, But Test Preparation Is Required To Begin In January 2011 In Order To Meet The Test Schedule. The Objective Of Lsett Testing In The 8 Htt Is To Test A Contractor Designed Scramjet Engine With A Full Inlet And Nozzle In The 8 Htt At Mach 5 Flight Conditions. 3.0 Description Of The Work/Tasks To Be Performed: The Contractor Shall Perform The Following Tasks: 3.1 Test Planning And Documentation. 3.1.1 The Contractor Shall Participate In Weekly Telecons To Define The Integrated Run Sequence Required For Safe Execution Of The Lsett Test In The 8 Htt. The Definition Of The Integrated Run Sequence Shall Be A Collaborative Effort And Will Be Mutually Agreed Upon By The Contractor And Nasa. The Completed Integrated Run Sequence Shall Satisfy All Nasa Langley Test Safety Requirements And The Contractor Engine Operating Limits. Final Approval Will Be Given By The Nasa Task Monitor (Tm) Via Email To The Contractors Project Manager (Pm). The Contractor Shall Update And Maintain The Detailed Integrated Run Sequence Document (Irsd) For Weekly Review During The Telecons. (Deliverable Item 4.3). The Initial Irsd Draft Will Be Provided To The Contractor As Specified Under Government Furnished Information (Gfi) Sow 5.1. 3.1.2 The Contractor Shall Develop, At A Minimum, The Following Facility Systems Verification Check Lists (Deliverable Item 4.4): - Engine Fuel Delivery System. - Water Cooling System Performance. - Silane Ignitor Gas System Performance. - Angle Of Attach/Model Elevator Coordination. - Normal Stop Sequence Of Events. - Abnormal Stop Sequence
- Langley Research Center
- National Aeronautics And Space Administration (Nasa)
- $196,964.51
- National Aeronautics And Space Administration (Nasa)