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  • 1
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    Small-Scale Metal Tanks for High Pressure Storage of Fluids (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Small scale metal tanks for high-pressure storage of fluids having tank factors of more than 5000 meters and volumes of ten cubic inches or less featuring arrays of interconnected internal chambers having at least inner walls thinner than gage limitations allow. The chambers may be arranged as multiple internal independent vessels. Walls of chambers that are also portions of external tank walls may be arcuate on the internal and/or external surfaces, including domed. The tanks may be shaped adaptively and/or conformally to an application, including, for example, having one or more flat outer walls and/or having an annular shape. The tanks may have dual-purpose inlet/outlet conduits of may have separate inlet and outlet conduits. The tanks are made by fusion bonding etched metal foil layers patterned from slices of a CAD model of the tank. The fusion bonded foil stack may be further machined.
    Keywords: Metals and Metallic Materials
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Technology Development and Design of an Electrically Driven Pump Fed (EDPF) Bi-Propellant Propulsion System for a Mars Ascent Vehicle (MAV) (2017)
    In:  Other Sources
    Details
    Publication Date: 2019-08-06
    Description: A Mars Ascent Vehicle (MAV), as part of a potential Mars Sample Return (MSR) campaign, is a very unique challenge and has been the focus of technology development and design efforts at JPL (Jet Propulsion Lab.) for several decades. Recent trajectory studies, for the current range of notional MAV payloads (6-25 kilograms), evaluated performance using propulsion systems in the 2.5 kiloNewton to 4.5 kiloNewton (600-1000 pounds-force) thrust range. The study examined several propulsion system approaches - solid rocket, bi-propellant and hybrid propulsion systems - and developed a ranking based on several key figures of merit. This paper focuses on the evaluations conducted for the two bi-propellant propulsion system options considered for a potential MAV. Historically, bi-propellant propulsion systems have been considered for this application; this study took a fresh look at both a conventional State of the Art (SOA) pressure fed bi-propellant propulsion system and recent developments using small EDPF (Electrically-Driven Pump-Fed) bi-propellant propulsion systems.
    Keywords: Launch Vehicles and Launch Operations
    Type: JPL-CL-CL#17-5410 , International Astronautical Congress (IAC 2018); Sep 25, 2017 - Sep 29, 2017; Adelaide; Australia
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Small Scale High Speed Turbomachinery (2018)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: A small scale, high speed turbomachine is described, as well as a process for manufacturing the turbomachine. The turbomachine is manufactured by diffusion bonding stacked sheets of metal foil, each of which has been pre-formed to correspond to a cross section of the turbomachine structure. The turbomachines include rotating elements as well as static structures. Using this process, turbomachines may be manufactured with rotating elements that have outer diameters of less than four inches in size, and/or blading heights of less than 0.1 inches. The rotating elements of the turbomachines are capable of rotating at speeds in excess of 150 feet per second. In addition, cooling features may be added internally to blading to facilitate cooling in high temperature operations.
    Keywords: Aircraft Propulsion and Power
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Small Scale High Speed Turbomachinery (2015)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: A small scale, high speed turbomachine is described, as well as a process for manufacturing the turbomachine. The turbomachine is manufactured by diffusion bonding stacked sheets of metal foil, each of which has been pre-formed to correspond to a cross section of the turbomachine structure. The turbomachines include rotating elements as well as static structures. Using this process, turbomachines may be manufactured with rotating elements that have outer diameters of less than four inches in size, and/or blading heights of less than 0.1 inches. The rotating elements of the turbomachines are capable of rotating at speeds in excess of 150 feet per second. In addition, cooling features may be added internally to blading to facilitate cooling in high temperature operations.
    Keywords: Mechanical Engineering
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Regeneratively Cooled Porous Media Jacket (2013)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: The fluid and heat transfer theory for regenerative cooling of a rocket combustion chamber with a porous media coolant jacket is presented. This model is used to design a regeneratively cooled rocket or other high temperature engine cooling jacket. Cooling jackets comprising impermeable inner and outer walls, and porous media channels are disclosed. Also disclosed are porous media coolant jackets with additional structures designed to transfer heat directly from the inner wall to the outer wall, and structures designed to direct movement of the coolant fluid from the inner wall to the outer wall. Methods of making such jackets are also disclosed.
    Keywords: Spacecraft Propulsion and Power
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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