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  • Other Sources  (242)
  • Spacecraft Propulsion and Power  (240)
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  • 2000-2004  (242)
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  • 2003  (242)
  • 11
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    Comparison of On-Orbit and Ground Based Hollow Cathode Operation (2003)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The Plasma Contactor Unit (PCU) was developed by the Rocketdyne division of Boeing to control charging of the International Space Station (ISS). Each PCU contains a Hollow Cathode Assembly (HCA), which emits the charge control electrons. The HCAs were designed and fabricated at NASA's Glenn Research Center (GRC). GRC's HCA development program included manufacture of engineering, qualification, and flight model HCAs as well as wear tests and qualification tests. GRC is currently tracking the on-orbit data for the flight HCAs. This data will be discussed with comparison to operating parameters verified by ground based HCA tests. The flight HCAs continue to operate flawlessly. The first unit has accumulated more than 3650 hours of on-orbit operation and the second unit has accumulated over 5550 hours.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/CR-2003-212585 , E-14140 , NAS 1.26:212585 , AIAA Paper 2003-5145 , 39th Joint Propulsion Conference and Exhibit; Jul 20, 2003 - Jul 23, 2003; Huntsville, AL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 12
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    Hall Effect Thruster Interactions Data From the Russian Express-A2 and Express-A3 Satellites (2003)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: This 12-part report documents the data obtained from various sensor measurements taken aboard the Russian Express-A2 and Express-A3 spacecraft in Geosynchronous Earth Orbit (GEO). These GEO communications satellites, which were designed and built by NPO Prikladnoy Mekhaniki (NPO PM) of Zheleznogorsk, Russia, utilize Hall thruster propulsion systems for north-south and east-west stationkeeping and as of June 2002, were still operating at 80 E. and 11 W., respectively. Express-A2 was launched on March 12, 2000, while Express-A3 was launched on June 24, 2000. The diagnostic equipment from which these data were taken includes electric field strength sensors, ion current and energy sensors, and pressure sensors. The diagnostics and the Hall thruster propulsion systems are described in detail along with lists of tabular data from those diagnostics and propulsion system and other satellite systems. Space Power, Inc., now part of Pratt & Whitney's Chemical Systems Division, under contract NAS3 99151 to the NASA Glenn Research Center, obtained these data over several periods from March 12, 2000, through September 30, 2001. Each of the 12 individual reports describe, in detail, the propulsion systems as well as the diagnostic sensors utilized. Finally, parts 11 and 12 include the requirements to which NPO PM prepared and delivered these data.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/CR-2003-212005/PT10 , E-13691-10/PT10 , NAS 1.26:212005/PT10
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 13
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    Hall Effect Thruster Interactions Data from the Russian Express-A2 and Express-A3 Satellites (2003)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: This 12-part report documents the data obtained from various sensor measurements taken aboard the Russian Express-A2 and Express-A3 spacecraft in Geosynchronous Earth Orbit (GEO). These GEO communications satellites, which were designed and built by NPO Prikladnoy Mekhaniki (NPO PM) of Zheleznogorsk, Russia, utilize Hall thruster propulsion systems for north-south and east-west stationkeeping and as of June 2002, were still operating at 80deg E. and 11deg W., respectively. Express-A2 was launched on March 12, 2000, while Express-A3 was launched on June 24, 2000. The diagnostic equipment from which these data were taken includes electric field strength sensors, ion current and energy sensors, and pressure sensors. The diagnostics and the Hall thruster propulsion systems are described in detail along with lists of tabular data from those diagnostics and propulsion system and other satellite systems. Space Power, Inc., now part of Pratt & Whitney's Chemical Systems Division, under contract NAS3 99151 to the NASA Glenn Research Center, obtained these data over several periods from March 12, 2000, through September 30, 2001. Each of the 12 individual reports describe, in detail, the propulsion systems as well as the diagnostic sensors utilized. Finally, parts 11 and 12 include the requirements to which NPO PM prepared and delivered these data.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/CR-2003-212005/PT8 , E-13691-8/PT8 , NAS 1.26:212005/PT8
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 14
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    Long Term Performance Retention Test Using High Power COTS NiCd and NiMH Cells (2003)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: This slide presentation reviews the tests and results for performance retention of high powered commercial off the shelf (COTS) NiCd, and NiMH cells. Electromechanical actuators for space flight requires short duration high power batteries. The concern is that NiCd battery designs demonstrate an unfavorable power degradation after long periods of inactivity. Cycling can recover some of the decay, but this reduces the readiness that these batteries must have. Two 5-cell SubC stick test batteries ere chosen using NiCd and NiMH were tested and then the differences for charge maintenance were compared.
    Keywords: Spacecraft Propulsion and Power
    Type: JSC-CN-8284 , 2003 NASA Aerospace Battery Workshop; Nov 16, 2003 - Nov 18, 2003; Huntsville, AL; United States
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    NASA TECHNICAL REPORTS
  • 15
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    Combination Solar Sail and Electrodynamic Tether Propulsion System (2003)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: A propulsion system for a spacecraft includes a solar sail system and an electrodynamic tether system is presented. The solar sail system is used to generate propulsion to propel the spacecraft through space using solar photons and the electrodynamic tether system is used to generate propulsion to steer the spacecraft into orbit and to perform orbital maneuvers around a planet using the planet's magnetic field. The electrodynamic tether system can also be used to generate power for the spacecraft using the planet's magnetic field.
    Keywords: Spacecraft Propulsion and Power
    Format: text
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    NASA TECHNICAL REPORTS
  • 16
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    Comparison of On-orbit and Ground Based Hollow Cathode Operation (2003)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The Plasma Contactor Units (PCUs) were developed at NASA Glenn Research Center (GRC) and Boeing for charge control on board the International Space Station (ISS). Since the first ignition of a PCU on 10/16/2000 over 3,900 hours of operation have been demonstrated on a single unit. In order to guarantee that the PCUs hollow cathode assemblies (HCAs), which emit the electrons used for charge control, would satisfy the life requirement of 18,000 hours, a ground based hollow cathode life test program was initiated at GRC. The life test program aimed at 27,000 hours of operation on a single unit to demonstrate the industry standard 1.5 times operational life requirement. As of this printing, over 18,000 hours of operation have been accumulated on a single hollow cathode. By comparing the data received from the on-orbit HCAs to the data obtained for the life test cathodes, a comparison may be drawn to determine if the on-orbit HCAs are operating normally, with a final goal of predicting lifetime. Based on the data taken thus far, it can be concluded that the on-orbit HCAs are operating within their design specifications.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/CR-2003-211817 , E-13510 , NAS 1.26:211817 , AIAA Paper 2002-4098 , 38th Joint Propulsion Conference and Exhibit; Jul 07, 2002 - Jul 10, 2002; Indianapolis, IN; United States
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    NASA TECHNICAL REPORTS
  • 17
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    Hall Effect Thruster Interactions Data From the Russian Express-A2 and Express-A3 Satellites (2003)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: This 12-part report documents the data obtained from various sensor measurements taken aboard the Russian Express-A2 and Express-A3 spacecraft in Geosynchronous Earth Orbit (GEO). These GEO communications satellites, which were designed and built by NPO Prikladnoy Mekhaniki (NPO PM) of Zheleznogorsk, Russia, utilize Hall thruster propulsion systems for north-south and east-west stationkeeping and as of June 2002, were still operating at 80 E. and 11 W., respectively. Express-A2 was launched on March 12, 2000, while Express-A3 was launched on June 24, 2000. The diagnostic equipment from which these data were taken includes electric field strength sensors, ion current and energy sensors, and pressure sensors. The diagnostics and the Hall thruster propulsion systems are described in detail along with lists of tabular data from those diagnostics and propulsion system and other satellite systems. Space Power, Inc., now part of Pratt & Whitney's Chemical Systems Division, under contract NAS3 99151 to the NASA Glenn Research Center, obtained these data over several periods from March 12, 2000, through September 30, 2001. Each of the 12 individual reports describe, in detail, the propulsion systems as well as the diagnostic sensors utilized. Finally, parts 11 and 12 include the requirements to which NPO PM prepared and delivered these data.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/CR-2003-212005/PT3 , E-13691-3/PT3 , NAS 1.26:212005/PT3
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 18
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    Hall Effect Thruster Interactions Data From the Russian Express-A2 and Express-A3 Satellites (2003)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: This 12-part report documents the data obtained from various sensor measurements taken aboard the Russian Express-A2 and Express-A3 spacecraft in Geosynchronous Earth Orbit (GEO). These GEO communications satellites, which were designed and built by NPO Prikladnoy Mekhaniki (NPO PM) of Zheleznogorsk, Russia, utilize Hall thruster propulsion systems for north-south and east-west stationkeeping and as of June 2002, were still operating at 80deg E. and 11deg W., respectively. Express-A2 was launched on March 12, 2000, while Express-A3 was launched on June 24, 2000. The diagnostic equipment from which these data were taken includes electric field strength sensors, ion current and energy sensors, and pressure sensors. The diagnostics and the Hall thruster propulsion systems are described in detail along with lists of tabular data from those diagnostics and propulsion system and other satellite systems. Space Power, Inc., now part of Pratt & Whitney's Chemical Systems Division, under contract NAS3-99151 to the NASA Glenn Research Center, obtained these data over several periods from March 12, 2000, through September 30, 2001. Each of the 12 individual reports describe, in detail, the propulsion systems as well as the diagnostic sensors utilized. Finally, parts 11 and 12 include the requirements to which NPO PM prepared and delivered these data.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/CR-2003-212005/PT11 , E-13691--11/PT11 , NAS 1.26:212005/PT11
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 19
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    MEMS-Based Spinning Nozzle (2003)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: A nozzle body and assembly for delivering atomized fuel to a combustion chamber. The nozzle body is rotatably mounted onto a substrate. One or more curvilinear fuel delivery channels are in flow communication with an internal fuel distribution cavity formed in the nozzle body. Passage of pressurized fuel through the nozzle body causes the nozzle body to rotate. Components of the nozzle assembly are formed of silicon carbide having surfaces etched by deep reactive ion etching utilizing MEMS (micro-electro-mechanical systems) technology. A fuel premix chamber is carried on the substrate in flow communication with a supply passage in the nozzle body.
    Keywords: Spacecraft Propulsion and Power
    Format: text
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  • 20
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    Transient Simulation of the Integrated Powerhead Demonstrator (IPD) Rocket Engine (2003)
    In:  Other Sources
    Details
    Publication Date: 2019-08-13
    Description: The IPD rocket engine is the product of a joint Air Force/NASA program to demonstrate the concept of a full-flow staged combustion power cycle. In this type of rocket engine cycle, both the entire fuel flow and the entire oxidizer flow are combusted in one of two pre-bumers and used to drive two turbopumps, thus utilizing the flow work of the total propellant flow. The basis of the IPD engine program relies on integrating newly developed and pre-existing hardware to demonstrate the component and material technologies to make this concept feasible, while simultaneously saving development time and costs. To provide insight to the project team and contractors during engine development and test phases, the engine system was modeled at MSFC using the Rocket Engine Transient Simulation (ROCETS) software to analyze system performance and determine component integration issues. The ROCETS software is used extensively a MSFC to perform steady-state power-balances and transient simulations of thermodynamic power and general fluid systems. The software is favored for its capability to solve large systems of non-linear equations, its librarie of fluid properties and flow devices, its flexibility to modify existing code to improve the physics-derived approximations of real fluid thermodynamic behavior, and the ability to add unique system constraints. The purpose of this paper is to present the methodology used to model the IPD engine system, detail the pitfalls encountered with the software, and explain the approximations made to more accurately represent engine component and fluid behavior. Engine system performance output from the model will be presented and explained in comparison with real fluid and component behavior.
    Keywords: Spacecraft Propulsion and Power
    Type: 1st Liquid Propulsion Meeting; May 10, 2004 - May 14, 2004; Las Vegas, NV; United States|JANNAF 52nd Propulsion Meeting; May 10, 2004 - May 14, 2004; Las Vegas, NV; United States
    Format: text
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