Peregrine Falcon Corp
CAGE Code: 084E5
NCAGE Code: 084E5
Status: Active
Type: Manufacturer
Dun & Bradstreet (DUNS): 963306857
Summary
Peregrine Falcon Corp is an Active Manufacturer with the Cage Code 084E5 and is tracked by Dun & Bradstreet under DUNS Number 963306857..
Address
1051 Serpentine Ln Ste 100
Pleasanton CA 94566-8451
United States
Points of Contact
No Points of Contact...
Related Information
People who viewed this 'CAGE Code' also viewed...
M S R California Tactec, Inc. Elsag-Bailey Fitch Electric Inc Supreme Facility Services Llc Tudor Charles E Consultant Unisource Worldwide Inc Fauver J N Co Q-Chem Inc International Research Associates Siemens Medical Systems Inc Dillingham/Holmes And Narver Thoratec Corporation Dsp Construction Inc Apex Data Inc Metro Services Inc. Univerd Marketing And Services Apax Data Inc Riedel Environmental Service Inc Anixter Inc
Frequently Asked Questions (FAQ) for CAGE 084E5
- What is CAGE Code 084E5?
- 084E5 is the unique identifier used by NATO Organizations to reference the physical entity known as Peregrine Falcon Corp located at 1051 Serpentine Ln Ste 100, Pleasanton CA 94566-8451, United States.
- Who is CAGE Code 084E5?
- 084E5 refers to Peregrine Falcon Corp located at 1051 Serpentine Ln Ste 100, Pleasanton CA 94566-8451, United States.
- Where is CAGE Code 084E5 Located?
- CAGE Code 084E5 is located in Pleasanton, CA, USA.
Contracting History for CAGE 084E5 Most Recent 25 Records
- SP470123P0065
- P00001 - Modification To Re Align Clin Structure.
- 8 Sep 2023
- P00001 - Modification To Re Align Clin Structure.
- Dcso Philadelphia
- Department Of Defense (Dod)
- $98,269.00
- Department Of Defense (Dod)
- SP470123P0065
- Peregrine Falcon Sbir Phase I Proposal L23a-003-0025 Award Sp4701-23-P-0065
- 22 Aug 2023
- Peregrine Falcon Sbir Phase I Proposal L23a-003-0025 Award Sp4701-23-P-0065
- Dcso Philadelphia
- Department Of Defense (Dod)
- $98,269.00
- Department Of Defense (Dod)
- FA239423CB058
- Conversion Coatings For High Temperature Protection Of Niobium Alloys
- 23 Aug 2023
- Conversion Coatings For High Temperature Protection Of Niobium Alloys
- Fa2394 Usaf Afmc Afrl Pzl Afrl Rxkm
- Department Of Defense (Dod)
- $1,219,790.00
- Department Of Defense (Dod)
- SP470123C0063
- Sbir Phase Ii Proposal #L2-0413 Tendered Under Topic # Dla22.2-007 For Conversion Coated Surfaces For Hypersonic Environments Phase Ii Proposal.
- 6 Sep 2023
- Sbir Phase Ii Proposal #L2-0413 Tendered Under Topic # Dla22.2-007 For Conversion Coated Surfaces For Hypersonic Environments Phase Ii Proposal.
- Dcso Philadelphia
- Department Of Defense (Dod)
- $998,018.00
- Department Of Defense (Dod)
- N6833521C0232
- Exercise The Option And Incrementally Fund Clin 0003 Slin 01 And Related Data Clin 0004.
- 24 Feb 2022
- Exercise The Option And Incrementally Fund Clin 0003 Slin 01 And Related Data Clin 0004.
- Navair Warfare Ctr Aircraft Div
- Department Of Defense (Dod)
- $1,185,536.00
- Department Of Defense (Dod)
- N6833521C0232
- Exercise The Option And Fully Fund Clin 0005 Slin 01 And Related Data Clin 0006
- 1 Feb 2023
- Exercise The Option And Fully Fund Clin 0005 Slin 01 And Related Data Clin 0006
- Navair Warfare Ctr Aircraft Div
- Department Of Defense (Dod)
- $1,680,244.00
- Department Of Defense (Dod)
- N6833521C0232
- Research And Development
- 4 Feb 2021
- Research And Development
- Navair Warfare Ctr Aircraft Div
- Department Of Defense (Dod)
- $692,922.00
- Department Of Defense (Dod)
- 80NSSC21C0007
- Consolidation Of Heat Pipes Within A U-8Mo Core For High Efficiency And Long-Term Reliability. Thermal Energy Conversion. Liquid Interface Diffusion Bonding Of Fps Heat Pipes To Core
- 8 Jul 2021
- Consolidation Of Heat Pipes Within A U-8Mo Core For High Efficiency And Long-Term Reliability. Thermal Energy Conversion. Liquid Interface Diffusion Bonding Of Fps Heat Pipes To Core
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $3,588,755.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC21C0007
- Consolidation Of Heat Pipes Within A U-8Mo Core For High Efficiency And Long-Term Reliability. Thermal Energy Conversion. Liquid Interface Diffusion Bonding Of Fps Heat Pipes To Core
- 22 Dec 2020
- Consolidation Of Heat Pipes Within A U-8Mo Core For High Efficiency And Long-Term Reliability. Thermal Energy Conversion. Liquid Interface Diffusion Bonding Of Fps Heat Pipes To Core
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $3,588,755.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC21C0007
- Eo14042 Consolidation Of Heat Pipes Within A U-8Mo Core For High Efficiency And Long-Term Reliability. Thermal Energy Conversion. Liquid Interface Diffusion Bonding Of Fps Heat Pipes To Core
- 16 Dec 2022
- Eo14042 Consolidation Of Heat Pipes Within A U-8Mo Core For High Efficiency And Long-Term Reliability. Thermal Energy Conversion. Liquid Interface Diffusion Bonding Of Fps Heat Pipes To Core
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $3,588,755.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC21C0007
- Consolidation Of Heat Pipes Within A U-8Mo Core For High Efficiency And Long-Term Reliability. Thermal Energy Conversion. Liquid Interface Diffusion Bonding Of Fps Heat Pipes To Core
- 13 Feb 2021
- Consolidation Of Heat Pipes Within A U-8Mo Core For High Efficiency And Long-Term Reliability. Thermal Energy Conversion. Liquid Interface Diffusion Bonding Of Fps Heat Pipes To Core
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $3,588,755.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC21C0007
- Eo14042 Consolidation Of Heat Pipes Within A U-8Mo Core For High Efficiency And Long-Term Reliability. Thermal Energy Conversion. Liquid Interface Diffusion Bonding Of Fps Heat Pipes To Core
- 15 Oct 2021
- Eo14042 Consolidation Of Heat Pipes Within A U-8Mo Core For High Efficiency And Long-Term Reliability. Thermal Energy Conversion. Liquid Interface Diffusion Bonding Of Fps Heat Pipes To Core
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $3,588,755.00
- National Aeronautics And Space Administration (Nasa)
- 80NSSC21C0007
- Consolidation Of Heat Pipes Within A U-8Mo Core For High Efficiency And Long-Term Reliability. Thermal Energy Conversion. Liquid Interface Diffusion Bonding Of Fps Heat Pipes To Core
- 14 Oct 2021
- Consolidation Of Heat Pipes Within A U-8Mo Core For High Efficiency And Long-Term Reliability. Thermal Energy Conversion. Liquid Interface Diffusion Bonding Of Fps Heat Pipes To Core
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $3,588,755.00
- National Aeronautics And Space Administration (Nasa)
- N6833520C0214
- Exercise The Option And Fully Fund Clins 0004, 0005, And 0006. Pr # 1300867363. Reduce Clin 0004 To Reflect $45,000.00 To Match The Proposed Total $238,438.00.
- 20 Jul 2020
- Exercise The Option And Fully Fund Clins 0004, 0005, And 0006. Pr # 1300867363. Reduce Clin 0004 To Reflect $45,000.00 To Match The Proposed Total $238,438.00.
- Navair Warfare Ctr Aircraft Div Lke
- Department Of Defense (Dod)
- $238,438.00
- Department Of Defense (Dod)
- N6833520C0214
- Progress Report
- 7 Nov 2019
- Progress Report
- Navair Warfare Ctr Aircraft Div
- Department Of Defense (Dod)
- $238,438.00
- Department Of Defense (Dod)
- 80NSSC19C0462
- Multi-Layer Metal Insulation With Aerostructure For Hot Structure
- 31 Jul 2019
- Multi-Layer Metal Insulation With Aerostructure For Hot Structure
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $124,791.00
- National Aeronautics And Space Administration (Nasa)
- FA865019P5169
- Improved Seals For Hypersonic Vehicles
- 19 Jul 2019
- Improved Seals For Hypersonic Vehicles
- Fa8650 Usaf Afmc Afrl Pzl Rak Rxk
- Department Of Defense (Dod)
- $149,662.00
- Department Of Defense (Dod)
- FA865018P5075
- Peregrine Advanced Machining Of Aerospace Materials Sbir Phase I
- 25 Jul 2018
- Peregrine Advanced Machining Of Aerospace Materials Sbir Phase I
- Fa8650 Usaf Afmc Afrl Pzl Rak Rxk
- Department Of Defense (Dod)
- $149,542.00
- Department Of Defense (Dod)
- HQ086021C7152
- Sbir/Sttr Phase Ii R&D
- 11 May 2021
- Sbir/Sttr Phase Ii R&D
- Missile Defense Agency (Mda)
- Department Of Defense (Dod)
- $1,699,932.00
- Department Of Defense (Dod)
- HQ086021C7152
- Sbir/Sttr Phase Ii R&D
- 8 Aug 2023
- Sbir/Sttr Phase Ii R&D
- Missile Defense Agency (Mda)
- Department Of Defense (Dod)
- $2,720,705.00
- Department Of Defense (Dod)
- HQ086021C7152
- Sbir/Sttr Phase Ii R&D
- 8 Aug 2022
- Sbir/Sttr Phase Ii R&D
- Missile Defense Agency (Mda)
- Department Of Defense (Dod)
- $2,720,705.00
- Department Of Defense (Dod)
- NNX17CC06C
- Igf::Ot::Igf A Key Challenge To Producing 10Kwe Fission Power Systems (Fps) Is Embedding And Joining Heat Pipes Internally To The U-7Mo Core. A Successful Phase I Effort Has Demonstrated The Feasibility Of Applying The Technology Of Liquid Interface Diffusion (Lid) Bonding To Embed And Join Heat Pipes (Haynes 230) To The Core. An Added Bonus Is That This Lid Bonding Technology Will Simultaneously Eliminate The Seams And Voids Created From A Core Made From Pieces Of U-7Mo Thereby Providing An Integrated Heat Pipe / U-7Mo Core Sub-Assembly With No Internal Voids Or Separations Between Core Pieces Or From The Core To The Heat Pipes. Lid Bonding Will Even Allow For The Core To Be Built Up By Various Horizontal And Asymmetric Pieces Such As Split Heat Pipe Channels To Easily Receive Heat Pipes, Consolidating The Core Material Around The Heat Pipes During The Lid Bonding Process. Phase Ii Will Allow Nasa To Produce Fps Up To 10 Kwe And Beyond To Meet The Power Requirements For Landing Astronauts On Mars, And Also To Provide Power To A Host Of Other Programs, Including Programs Such As Neptune Systems Explorer, Kuiper Belt Optic, Trojan Tour, And Jupiter Europa Orbiter.
- 4 Jun 2018
- Igf::Ot::Igf A Key Challenge To Producing 10Kwe Fission Power Systems (Fps) Is Embedding And Joining Heat Pipes Internally To The U-7Mo Core. A Successful Phase I Effort Has Demonstrated The Feasibility Of Applying The Technology Of Liquid Interface Diffusion (Lid) Bonding To Embed And Join Heat Pipes (Haynes 230) To The Core. An Added Bonus Is That This Lid Bonding Technology Will Simultaneously Eliminate The Seams And Voids Created From A Core Made From Pieces Of U-7Mo Thereby Providing An Integrated Heat Pipe / U-7Mo Core Sub-Assembly With No Internal Voids Or Separations Between Core Pieces Or From The Core To The Heat Pipes. Lid Bonding Will Even Allow For The Core To Be Built Up By Various Horizontal And Asymmetric Pieces Such As Split Heat Pipe Channels To Easily Receive Heat Pipes, Consolidating The Core Material Around The Heat Pipes During The Lid Bonding Process. Phase Ii Will Allow Nasa To Produce Fps Up To 10 Kwe And Beyond To Meet The Power Requirements For Landing Astronauts On Mars, And Also To Provide Power To A Host Of Other Programs, Including Programs Such As Neptune Systems Explorer, Kuiper Belt Optic, Trojan Tour, And Jupiter Europa Orbiter.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $744,354.00
- National Aeronautics And Space Administration (Nasa)
- HQ014717C7409
- Sbir/Sttr Phase Ii R & D Enhancement
- 8 Apr 2021
- Sbir/Sttr Phase Ii R & D Enhancement
- Missile Defense Agency (Mda)
- Department Of Defense (Dod)
- $1,696,296.71
- Department Of Defense (Dod)
- 80NSSC18P0161
- Multi-Layer Insulation (Mli) Package
- 21 Jun 2018
- Multi-Layer Insulation (Mli) Package
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $63,177.66
- National Aeronautics And Space Administration (Nasa)
- NNX16CC19C
- Igf::Ot::Igf Large Radiator Panels, Based Upon State Of The Art Conventional Heat Pipes With Attached Fins For Thermal Load Distribution And Dissipation Is The Current Baseline Design For Nasa?S Fission Power System. The Initial 1 Kwe Fps Requires A Total Radiating Surface Of 2.5 M2. Higher Power Designs Will Require Corresponding Larger Radiating Surfaces. In Order To Achieve Optimum Radiator Performance, The Face Sheets Of These Radiators Should Present Waste Heat Loads As Isothermal Sheets Pointed To The Sink Of Space. The Current State Of The Art Designs Do Not Meet This Requirement And Rely Upon Heat Pipes To Axially Carry The Waste Thermal Loads While Radiating Fins, With Typical Thermal Gradients And Losses, Provide Thermal Distribution Away From The Heat Pipes Via Simple Conduction. Under Phase I, Peregrine Has Successfully Demonstrated An Alternative Design Which Promises To Be Lower In Mass While Improving Performance Based Upon Pulsating Heat Pipes (Phps). Phps Can Directly Acquire And Then Readily Distribute Thermal Loads Across The Face Of Radiator Panels To Create Highly Efficient Near Isothermal Designs. Phps Are An Autonomous, Self-Contained, Low Profile, Lightweight, High Performance Thermal Transport System Based Upon Heat Of Vaporization. Phase Ii Will Characterize A Titanium/Water Pulsating Heat Pipe System, Build Prototypes Of A Pulsating Heat Pipe (Php) Radiator For A 1 Kwe Fps, And Also Build A Conventional Heat Pipe Design In Order To Provide A Side By Side Comparison Of Performance Increases Of Phps Versus The Conventional Design. Phase Ii Will Provide Objective Data Through Empirical Results For Future Efficient Lightweight, Isothermal Radiator Designs.
- 4 Sep 2018
- Igf::Ot::Igf Large Radiator Panels, Based Upon State Of The Art Conventional Heat Pipes With Attached Fins For Thermal Load Distribution And Dissipation Is The Current Baseline Design For Nasa?S Fission Power System. The Initial 1 Kwe Fps Requires A Total Radiating Surface Of 2.5 M2. Higher Power Designs Will Require Corresponding Larger Radiating Surfaces. In Order To Achieve Optimum Radiator Performance, The Face Sheets Of These Radiators Should Present Waste Heat Loads As Isothermal Sheets Pointed To The Sink Of Space. The Current State Of The Art Designs Do Not Meet This Requirement And Rely Upon Heat Pipes To Axially Carry The Waste Thermal Loads While Radiating Fins, With Typical Thermal Gradients And Losses, Provide Thermal Distribution Away From The Heat Pipes Via Simple Conduction. Under Phase I, Peregrine Has Successfully Demonstrated An Alternative Design Which Promises To Be Lower In Mass While Improving Performance Based Upon Pulsating Heat Pipes (Phps). Phps Can Directly Acquire And Then Readily Distribute Thermal Loads Across The Face Of Radiator Panels To Create Highly Efficient Near Isothermal Designs. Phps Are An Autonomous, Self-Contained, Low Profile, Lightweight, High Performance Thermal Transport System Based Upon Heat Of Vaporization. Phase Ii Will Characterize A Titanium/Water Pulsating Heat Pipe System, Build Prototypes Of A Pulsating Heat Pipe (Php) Radiator For A 1 Kwe Fps, And Also Build A Conventional Heat Pipe Design In Order To Provide A Side By Side Comparison Of Performance Increases Of Phps Versus The Conventional Design. Phase Ii Will Provide Objective Data Through Empirical Results For Future Efficient Lightweight, Isothermal Radiator Designs.
- Nasa Shared Services Center
- National Aeronautics And Space Administration (Nasa)
- $747,469.00
- National Aeronautics And Space Administration (Nasa)