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  • Launch Vehicles and Launch Operations  (23)
  • Spacecraft Propulsion and Power  (19)
  • 2005-2009  (28)
  • 2000-2004  (13)
  • 1995-1999  (1)
  • 1935-1939
Collection
Keywords
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  • 2005-2009  (28)
  • 2000-2004  (13)
  • 1995-1999  (1)
  • 1935-1939
  • 2010-2014  (19)
Year
  • 1
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    Constellation Launch Vehicles Overview (2009)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This slide presentation reviews the current status of the launch vehicles associated with the Constellation Program. These are the Ares I and the Ares V. An overview of the Ares launch vehicles is included. The presentation stresses that the major criteria for the Ares I launcher is the safety of the crew, and the presentation reviews the various features that are designed to assure that aim. The Ares I vehicle is being built on a foundation of proven technologies, and the Ares V will give NASA unprecedented performance and payload volume that can enable a range of future missions. The CDs contain videos of scenes from various activities surrounding the design, construction and testing of the vehicles.
    Keywords: Launch Vehicles and Launch Operations
    Type: Human Space Flight Review; Jul 29, 2009; Huntsville, AL; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Thermal Analysis of the Fastrac Chamber/Nozzle (2001)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: This paper will describe the thermal analysis techniques used to predict temperatures in the film-cooled ablative rocket nozzle used on the Fastrac 60K rocket engine. A model was developed that predicts char and pyrolysis depths, liner thermal gradients, and temperatures of the bondline between the overwrap and liner. Correlation of the model was accomplished by thermal analog tests performed at Southern Research, and specially instrumented hot fire tests at the Marshall Space Flight Center. Infrared thermography was instrumental in defining nozzle hot wall surface temperatures. In-depth and outboard thermocouple data was used to correlate the kinetic decomposition routine used to predict char and pyrolysis depths. These depths were anchored with measured char and pyrolysis depths from cross-sectioned hot-fire nozzles. For the X-34 flight analysis, the model includes the ablative Thermal Protection System (TPS) material that protects the overwrap from the recirculating plume. Results from model correlation, hot-fire testing, and flight predictions will be discussed.
    Keywords: Spacecraft Propulsion and Power
    Type: The Tenth Thermal and Fluids Analysis Workshop; NASA/CP-2001-211141
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Ion Propulsion Subsystem Environmental Effects on Deep Space 1: Initial Results from the IPS Diagnostics Subsystem (2000)
    In:  Other Sources
    Details
    Publication Date: 2018-06-08
    Keywords: Spacecraft Propulsion and Power
    Type: Deep Space 1 Technology Validatation Symposium; Pasadena, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Ion Propulsion Subsystem Environmental Effects on DS1: Initial Results from the IPS Diagnostics Subsystem (2000)
    In:  Other Sources
    Details
    Publication Date: 2018-06-08
    Keywords: Spacecraft Propulsion and Power
    Type: DS1 Technology Validation Symposium; Pasadena, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Restoring Redundancy to the Wilkinson Microwave Anisotrophy Probe Propulsion System (2004)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: The Wilkinson Microwave Anisotropy Probe is a follow-on to the Differential Microwave Radiometer instrument on the Cosmic Background Explorer. Attitude control system engineers discovered sixteen months before launch that configuration changes after the critical design review had resulted in a significant migration of the spacecraft's center of mass. As a result, the spacecraft no longer had a viable backup control mode in the event of a failure of the negative pitch-axis thruster. A tiger team was formed and identified potential solutions to this problem, such as adding thruster-plume shields to redirect thruster torque, adding or removing mass from the spacecraft, adding an additional thruster, moving thrusters, bending thruster nozzles or propellant tubing, or accepting the loss of redundancy. The project considered the impacts on mass, cost, fuel budget, and schedule for each solution, and decided to bend the propellant tubing of the two roll-control thrusters to allow the pair to be used for backup control in the negative pitch axis. This paper discusses the problem and the potential solutions, and documents the hardware and software changes and verification performed. Flight data are presented to show the on-orbit performance of the propulsion system and lessons learned are described.
    Keywords: Spacecraft Propulsion and Power
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Propulsion Options for the Global Precipitation Measurement Core Satellite (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This study was conducted to evaluate several propulsion system options for the Global Precipitation Measurement (GPM) core satellite. Orbital simulations showed clear benefits for the scientific data to be obtained at a constant orbital altitude rather than with a decay/reboost approach. An orbital analysis estimated the drag force on the satellite will be 1 to 12 mN during the five-year mission. Four electric propulsion systems were identified that are able to compensate for these drag forces and maintain a circular orbit. The four systems were the UK-10/TS and the NASA 8 cm ion engines, and the ESA RMT and RITl0 EVO radio-frequency ion engines. The mass, cost, and power requirements were examined for these four systems. The systems were also evaluated for the transfer time from the initial orbit of 400 x 650 km altitude orbit to a circular 400 km orbit. The transfer times were excessive, and as a consequence a dual system concept (with a hydrazine monopropellant system for the orbit transfer and electric propulsion for drag compensation) was examined. Clear mass benefits were obtained with the dual system, but cost remains an issue because of the larger power system required for the electric propulsion system. An electrodynamic tether was also evaluated in this trade study.
    Keywords: Spacecraft Propulsion and Power
    Type: AIAA Joint Propulsion Conference; Jul 20, 2003 - Jul 23, 2003; Huntsville, AL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    The MAP Propulsion Subsystem (2002)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes the requirements, design, integration, test, performance, and lessons learned of NASA's Microwave Anisotropy Probe (MAP) propulsion subsystem. MAP was launched on a Delta-II launch vehicle from NASA's Kennedy Space Center on June 30, 2001. Due to instrument thermal stability requirements, the Earth-Sun L2 Lagrange point was selected for the mission orbit. The L2 trajectory incorporated phasing loops and a lunar gravity assist. The propulsion subsystem's requirements are to manage momentum, perform maneuvers during the phasing loops to set up the lunar swingby, and perform stationkeeping at L2 for 2 years. MAP's propulsion subsystem uses 8 thrusters which are located and oriented to provide attitude control and momentum management about all axes, and delta-V in any direction without exposing the instrument to the sun. The propellant tank holds 72 kg of hydrazine, which is expelled by unregulated blowdown pressurization. Thermal management is complex because no heater cycling is allowed at L2. Several technical challenges presented themselves during I and T, such as in-situ weld repairs and in-situ bending of thruster tubes to accommodate late changes in the observatory CG. On-orbit performance has been nominal, and all phasing loop, mid-course correction, and stationkeeping maneuvers have been successfully performed to date.
    Keywords: Spacecraft Propulsion and Power
    Type: AIAA-2002-4156 , AIAA/ASME/SAE/ASEE 38th Joint Propulsion Conference; Jul 07, 2002 - Jul 10, 2002; Indianapolis, IN; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Analysis of Surface Charging for a Candidate Solar Sail Mission Using NASCAP-2K (2004)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: The characterization of the electromagnetic interaction for a solar sail in the solar wind environment, and identification of viable charging mitigation strategies, is a critical solar sail mission design task, as spacecraft charging has important implications both for science applications and for sail lifetime. To that end, we have performed surface charging calculations of a candidate 150-meter-class solar sail spacecraft for the 0.5 AU solar polar orbit and a 1.0 AU L1 orbit. We construct a model of the spacecraft with candidate materials having appropriate electrical properties using Object Toolkit and perform the spacecraft charging analysis using NASCAP-2k, the NASA/AFRL sponsored spacecraft charging analysis tool. We use nominal and atypical solar wind environments appropriate for the 0.5 AU and 1.0 AU missions to establish current collection of solar wind ions and electrons. In addition, we include a geostationary orbit case to demonstrate a bounding example of extreme (negative) charging of a solar sail spacecraft in the geostationary orbit environment. Results from the charging analysis demonstrate that minimal differential potentials (and resulting threat of electrostatic discharge) occur when the spacecraft is constructed entirely of conducting materials, as expected. Examples with dielectric materials exposed to the space environment exhibit differential potentials ranging from a few volts to extreme potentials in the kilovolt range.
    Keywords: Spacecraft Propulsion and Power
    Type: 9th Spacecraft Charging Technology Conference; Apr 04, 2005 - Apr 08, 2005; Tsukuba; Japan
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Ares I-X: On the Threshold of Exploration (2009)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Ares I-X, the first flight of the Ares I crew launch vehicle, is less than a year from launch. Ares I-X will test the flight characteristics of Ares I from liftoff to first stage separation and recovery. The flight also will demonstrate the computer hardware and software (avionics) needed to control the vehicle; deploy the parachutes that allow the first stage booster to land in the ocean safely; measure and control how much the rocket rolls during flight; test and measure the effects of first stage separation; and develop and try out new ground handling and rocket stacking procedures in the Vehicle Assembly Building (VAB) and first stage recovery procedures at Kennedy Space Center (KSC) in Florida. All Ares I-X major elements have completed their critical design reviews, and are nearing final fabrication. The first stage--four-segment solid rocket booster from the Space Shuttle inventory--incorporates new simulated forward structures to match the Ares I five-segment booster. The upper stage, Orion crew module, and launch abort system will comprise simulator hardware that incorporates developmental flight instrumentation for essential data collection during the mission. The upper stage simulator consists of smaller cylindrical segments, which were transported to KSC in fall 2008. The crew module and launch abort system simulator were shipped in December 2008. The first stage hardware, active roll control system (RoCS), and avionics components will be delivered to KSC in 2009. This paper will provide detailed statuses of the Ares I-X hardware elements as NASA's Constellation Program prepares for this first flight of a new exploration era in the summer of 2009.
    Keywords: Launch Vehicles and Launch Operations
    Type: M09-0344 , M09-0098 , M09-0401 , JANNAF Conference; Apr 14, 2008 - Apr 17, 2008; Las Vegas, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Integrated Vehicle Ground Vibration Testing in Support of Launch Vehicle Loads and Controls Analysis (2008)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: All structural systems possess a basic set of physical characteristics unique to that system. These unique physical characteristics include items such as mass distribution and damping. When specified, they allow engineers to understand and predict how a structural system behaves under given loading conditions and different methods of control. These physical properties of launch vehicles may be predicted by analysis or measured by certain types of tests. Generally, these properties are predicted by analysis during the design phase of a launch vehicle and then verified by testing before the vehicle becomes operational. A ground vibration test (GVT) is intended to measure by test the fundamental dynamic characteristics of launch vehicles during various phases of flight. During the series of tests, properties such as natural frequencies, mode shapes, and transfer functions are measured directly. These data will then be used to calibrate loads and control systems analysis models for verifying analyses of the launch vehicle. NASA manned launch vehicles have undergone ground vibration testing leading to the development of successful launch vehicles. A GVT was not performed on the inaugural launch of the unmanned Delta III which was lost during launch. Subsequent analyses indicated had a GVT been performed, it would have identified instability issues avoiding loss of the vehicle. This discussion will address GVT planning, set-up, execution and analyses, for the Saturn and Shuttle programs, and will also focus on the current and on-going planning for the Ares I and V Integrated Vehicle Ground Vibration Test (IVGVT).
    Keywords: Launch Vehicles and Launch Operations
    Type: MSFC-826 , Joint Army-Navy-NASA-Air Force (JANNAF) Conference; May 12, 2008 - May 16, 2008; Massachusetts; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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