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  • Spacecraft Propulsion and Power  (415)
  • Lunar and Planetary Science and Exploration  (389)
  • 1
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    Lessons Learned from the Design, Certification, and Operation of the Space Shuttle Integrated Main Propulsion System (IMPS) (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Space Shuttle Integrated Main Propulsion System (IMPS) consists of the External Tank (ET), Orbiter Main Propulsion System (MPS), and Space Shuttle Main Engines (SSMEs). The IMPS is tasked with the storage, conditioning, distribution, and combustion of cryogenic liquid hydrogen (LH2) and liquid oxygen (LO2) propellants to provide first and second stage thrust for achieving orbital velocity. The design, certification, and operation of the associated IMPS hardware have produced many lessons learned over the course of the Space Shuttle Program (SSP). A subset of these items will be discussed in this paper for consideration when designing, building, and operating future spacecraft propulsion systems. This paper will focus on lessons learned related to Orbiter MPS and is the first of a planned series to address the subject matter.
    Keywords: Spacecraft Propulsion and Power
    Type: JSC-CN-24087 , 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit; Jul 31, 2011 - Aug 03, 2011; San Diego, CA; United States|9th Annual International Energy Conversion Engineering Conference; Jul 31, 2011 - Aug 03, 2011; San Diego, CA; United States
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    NASA TECHNICAL REPORTS
  • 2
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    Development of an Ion Thruster and Power Processor for New Millennium's Deep Space 1 Mission (1997)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The NASA Solar Electric Propulsion Technology Applications Readiness Program (NSTAR) will provide a single-string primary propulsion system to NASA's New Millennium Deep Space 1 Mission which will perform comet and asteroid flybys in the years 1999 and 2000. The propulsion system includes a 30-cm diameter ion thruster, a xenon feed system, a power processing unit, and a digital control and interface unit. A total of four engineering model ion thrusters, three breadboard power processors, and a controller have been built, integrated, and tested. An extensive set of development tests has been completed along with thruster design verification tests of 2000 h and 1000 h. An 8000 h Life Demonstration Test is ongoing and has successfully demonstrated more than 6000 h of operation. In situ measurements of accelerator grid wear are consistent with grid lifetimes well in excess of the 12,000 h qualification test requirement. Flight hardware is now being assembled in preparation for integration, functional, and acceptance tests.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-TM-113129 , NAS 1.15:113129 , E-10899 , AIAA Paper-97-2778 , Joint Propulsion Conference; Jul 06, 1997 - Jul 09, 1997; Seattle, WA; United States
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    NASA TECHNICAL REPORTS
  • 3
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    Gale Crater and Impact Processes - Curiosity's First 364 Sols on Mars (2014)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Impact processes at all scales have been involved in the formation and subsequent evolution of Gale crater. Small impact craters in the vicinity of the Curiosity MSL landing site and rover traverse during the 364 Sols after landing have been studied both from orbit and the surface. Evidence for the effect of impacts on basement outcrops may include loose blocks of sandstone and conglomerate, and disrupted (fractured) sedimentary layers, which are not obviously displaced by erosion. Impact ejecta blankets are likely to be present, but in the absence of distinct glass or impact melt phases are difficult to distinguish from sedimentary/volcaniclastic breccia and conglomerate deposits. The occurrence of individual blocks with diverse petrological characteristics, including igneous textures, have been identified across the surface of Bradbury Rise, and some of these blocks may represent distal ejecta from larger craters in the vicinity of Gale. Distal ejecta may also occur in the form of impact spherules identified in the sediments and drift material. Possible examples of impactites in the form of shatter cones, shocked rocks, and ropy textured fragments of materials that may have been molten have been observed, but cannot be uniquely confirmed. Modification by aeolian processes of craters smaller than 40 m in diameter observed in this study, are indicated by erosion of crater rims, and infill of craters with aeolian and airfall dust deposits. Estimates for resurfacing suggest that craters less than 15 m in diameter may represent steady state between production and destruction. The smallest candidate impact crater observed is 0.6 m in diameter. The observed crater record and other data are consistent with a resurfacing rate of the order of 10 mm/Myr; considerably greater than the rate from impact cratering alone, but remarkably lower than terrestrial erosion rates.
    Keywords: Lunar and Planetary Science and Exploration
    Type: GSFC-E-DAA-TN22564 , Icarus (ISSN 0019-1035); 249; 108-128
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    NASA TECHNICAL REPORTS
  • 4
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    NASA spacecraft propulsion activities (1997)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Description: The NASA's activities in the development of spacecraft propulsion systems are reviewed, with emphasis on program directions and recent progress made in this domain. The recent trends towards the use of smaller spacecraft and launch vehicles call for new onboard propulsion systems. The NASA's efforts are conducted within the framework of the onboard propulsion program. The research and development work carried out in relation to the different propulsion system technologies are considered: electromagnetic systems; electrostatic systems; electrothermal systems; bipropellant systems; and monopropellant systems.
    Keywords: Spacecraft Propulsion and Power
    Type: ; 35-44
    Format: text
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  • 5
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    Report on the loss of the Mars Climate Orbiter Mission : JPL special review board (1999)
    In:  Other Sources
    Details
    Publication Date: 2018-06-11
    Description: The Mars Climate Orbiter (MCO) was launched on December 11, 1998. The MCO was to arrive at Mars and begin orbit insertion on September 23, 1999. The Mars Orbit Insertion (MOI) burn, a 16-minute maneuver to slow the spacecraft and enable capture into an orbit around Mars, began on schedule. Five minutes into the maneuver, and approximately 49 seconds before the anticipated time for loss of communication, the MCO was occulted by Mars. Thereafter, no contact with the spacecraft could be established. On September 24, 1999, an internal JPL team (the MCO Peer Review Team) was appointed to help investigate the reason for the loss of spacecraft signal. The Peer Review Team's findings are presented in this report.
    Keywords: Lunar and Planetary Science and Exploration
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  • 6
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    Variable specific impulse high power ion thruster (2005)
    In:  Other Sources
    Details
    Publication Date: 2018-06-11
    Description: The power, Isp and thrust of ion thrusters are constrained by ther fixed grid gap in the ion accellerator, which limits performance and life to a limited range in Isp and thrust.
    Keywords: Spacecraft Propulsion and Power
    Type: 2005 AIAA Joint Propulsion Conference; Tucson, AZ; United States
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  • 7
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    A 3 Gyr White Dwarf with Warm Dust Discovered via the Backyard Worlds: Planet 9 Citizen Science Project (2019)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Infrared excesses due to dusty disks have been observed orbiting white dwarfs with effective temperatures between 7200 and 25,000 K, suggesting that the rate of tidal disruption of minor bodies massive enough to create a coherent disk declines sharply beyond 1 Gyr after white dwarf formation. We report the discovery that the candidate white dwarf LSPM J0207+3331, via the Backyard Worlds: Planet 9 citizen science project and Keck Observatory follow-up spectroscopy, is hydrogen dominated with a luminous compact disk (L IR/L star = 14%) and an effective temperature nearly 1000 K cooler than any known white dwarf with an infrared excess. The discovery of this object places the latest time for large-scale tidal disruption events to occur at ~3 Gyr past the formation of the host white dwarf, making new demands of dynamical models for planetesimal perturbation and disruption around post-main-sequence planetary systems. Curiously, the mid-infrared photometry of the disk cannot be fully explained by a geometrically thin, optically thick dust disk as seen for other dusty white dwarfs, but requires a second ring of dust near the white dwarf's Roche radius. In the process of confirming this discovery, we found that careful measurements of WISE source positions can reveal when infrared excesses for white dwarfs are co-moving with their hosts, helping distinguish them from confusion noise.
    Keywords: Lunar and Planetary Science and Exploration
    Type: GSFC-E-DAA-TN67863 , The Astrophysical Journal Letters; 2; 872; L25
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    NASA TECHNICAL REPORTS
  • 8
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    Coronagraphic Imaging of Debris Disks from a High-Altitude Balloon Platform (2012)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Lunar and Planetary Science and Exploration
    Type: SPIE Astronomical Telescopes and Instrumentation; Jul 01, 2012 - Jul 06, 2012; Amsterdam; Netherlands
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    NASA TECHNICAL REPORTS
  • 9
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    Post-Test Analysis of the Deep Space One Spare Flight Thruster Ion Optics (2004)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The Deep Space 1 (DSl) spare flight thruster (FT2) was operated for 30,352 hours during the extended life test (ELT). The test was performed to validate the service life of the thruster, study known and identify unknown life limiting modes. Several of the known life limiting modes involve the ion optics system. These include loss of structural integrity for either the screen grid or accelerator grid due to sputter erosion from energetic ions striking the grid, sputter erosion enlargement of the accelerator grid apertures to the point where the accelerator grid power supply can no longer prevent electron backstreaming, unclearable shorting between the grids causes by flakes of sputtered material, and rouge hole formation due to flakes of material defocusing the ion beam. Grid gap decrease, which increases the probability of electron backstreaming and of arcing between the grids, was identified as an additional life limiting mechanism after the test. A combination of accelerator grid aperture enlargement and grid gap decrease resulted in the inability to prevent electron backstreaming at full power at 26,000 hours of the ELT. Through pits had eroded through the accelerator grid webbing and grooves had penetrated through 45% of the grid thickness in the center of the grid. The upstream surface of the screen grid eroded in a chamfered pattern around the holes in the central portion of the grid. Sputter deposited material, from the accelerator grid, adhered to the downstream surface of the screen grid and did not spall to form flakes. Although a small amount of sputter deposited material protruded into the screen grid apertures, no rouge holes were found after the ELT.
    Keywords: Spacecraft Propulsion and Power
    Type: AIAA Paper 2004-3610 , 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit; Jul 11, 2004 - Jul 14, 2004; Fort Lauderdale, FL; United States
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  • 10
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    A Small Fission Power System for NASA Planetary Science Missions (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: In March 2010, the Decadal Survey Giant Planets Panel (GPP) requested a short-turnaround study to evaluate the feasibility of a small Fission Power System (FPS) for future unspecified National Aeronautics and Space Administration (NASA) science missions. FPS technology was considered a potential option for power levels that might not be achievable with radioisotope power systems. A study plan was generated and a joint NASA and Department of Energy (DOE) study team was formed. The team developed a set of notional requirements that included 1-kW electrical output, 15-year design life, and 2020 launch availability. After completing a short round of concept screening studies, the team selected a single concept for concentrated study and analysis. The selected concept is a solid block uranium-molybdenum reactor core with heat pipe cooling and distributed thermoelectric power converters directly coupled to aluminum radiator fins. This paper presents the preliminary configuration, mass summary, and proposed development program.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/TM-2011-217099 , NETS-2011-3318 , E-17606 , Nuclear and Emerging Technologies for Space (NETS-2011); Feb 07, 2011 - Feb 10, 2011; Albuquerque, NM; United States
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