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  • Spacecraft Propulsion and Power  (3)
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  • 1
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    Thermal Integration of a Liquid Acquisition Device into a Cryogenic Feed System (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Primary objectives of this effort were to define the following: (1) Approaches for quantification of the accumulation of thermal energy within a capillary screen liquid acquisition device (LAD) for a lunar lander upper stage during periods of up to 210 days on the lunar surface, (2) techniques for mitigating heat entrapment, and (3) perform initial testing, data evaluation. The technical effort was divided into the following categories: (1) Detailed thermal modeling of the LAD/feed system interactions using both COMSOL computational fluid device and standard codes, (2) FLOW-3D modeling of bulk liquid to provide interfacing conditions for the LAD thermal modeling, (3) condensation conditioning of capillary screens to stabilize surface tension retention capability, and (4) subscale testing of an integrated LAD/feed system. Substantial progress was achieved in the following technical areas: (1) Thermal modeling and experimental approaches for evaluating integrated cryogen LAD/feed systems, at both the system and component levels, (2) reduced gravity pressure control analyses, (3) analytical modeling and testing for capillary screen conditioning using condensation and wicking, and (4) development of rapid turnaround testing techniques for evaluating LAD/feed system thermal and fluid integration. A comprehensive effort, participants included a diverse cross section of representatives from academia, contractors, and multiple Marshall Space Flight Center organizations.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/TP-2011-216474 , M-1323
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Summary of the 2012 Inductive Pulsed Plasma Thruster Development and Testing Program (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Inductive pulsed plasma thrusters are spacecraft propulsion devices in which energy is capacitively stored and then discharged through an inductive coil. While these devices have shown promise for operation at high efficiency on a range of propellants, many technical issues remain before they can be used in flight applications. A conical theta-pinch thruster geometry was fabricated and tested to investigate potential improvements in propellant utilization relative to more common, flat-plate planar coil designs. A capacitor charging system is used to permit repetitive discharging of thrusters at multiple cycles per second, with successful testing accomplished at a repetition-rate of 5 Hz at power levels of 0.9, 1.6, and 2.5 kW. The conical theta-pinch thruster geometry was tested at cone angles of 20deg, 38deg, and 60deg, with single-pulse operation at 500 J/pulse and repetitionrate operation with the 38deg model quantified through direct thrust measurement using a hanging pendulum thrust stand. A long-lifetime valve was designed and fabricated, and initial testing was performed to measure the valve response and quantify the leak rate at beginning-of-life. Subscale design and testing of a capacitor charging system required for operation on a spacecraft is reported, providing insights into the types of components needed in the circuit topology employed. On a spacecraft, this system would accept as input a lower voltage from the spacecraft DC bus and boost the output to the high voltage required to charge the capacitors of the thruster.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/TP-2013-217488 , M-1364
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Single and Multi-Pulse Low-Energy Conical Theta Pinch Inductive Pulsed Plasma Thruster Performance (2013)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Impulse bits produced by conical theta-pinch inductive pulsed plasma thrusters possessing cone angles of 20deg, 38deg, and 60deg, were quantified for 500J/pulse operation by direct measurement using a hanging-pendulum thrust stand. All three cone angles were tested in single-pulse mode, with the 38deg model producing the highest impulse bits at roughly 1 mN-s operating on both argon and xenon propellants. A capacitor charging system, assembled to support repetitively-pulsed thruster operation, permitted testing of the 38deg thruster at a repetition-rate of 5 Hz at power levels of 0.9, 1.6, and 2.5 kW. The average thrust measured during multiple-pulse operation exceeded the value obtained when the single-pulse impulse bit is multiplied by the repetition rate.
    Keywords: Spacecraft Propulsion and Power
    Type: M13-2466 , 6th Space Propulsion Subcommittee Meeting (SPS); Apr 29, 2013 - May 03, 2013; Colorado Springs, CO; United States|9th Modelling and Simulation Subcommittee Meeting (MSS); Apr 29, 2013 - May 03, 2013; Colorado Springs, CO; United States|7th Liquid Propulsion Subcommittee Meeting (LPS); Apr 29, 2013 - May 03, 2013; Colorado Springs, CO; United States|60th JANNAF Propulsion Meeting; Apr 29, 2013 - May 03, 2013; Colorado Springs, CO; United States
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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