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  • Other Sources  (413)
  • Spacecraft Propulsion and Power  (240)
  • Spacecraft Design, Testing and Performance  (171)
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  • 2000-2004  (413)
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  • 2003  (413)
  • 1
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    Performance of the Star Tracker Lightshades on the Earth Observing Satellite (EOS) Aqua (2003)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The TRW built EOS Aqua spacecraft uses two Ball Aerospace CT-602 star trackers to provide attitude updates to the 3-axis, zero momentum, controller. Two months prior to the scheduled launch of Aqua, Ball reported an error in the design of the star tracker lightshades. The lightshades, which had been designed specifically for the EOS Common spacecraft, were not expected to meet the stray light rejection requirements of the mission, thus impacting the overall spacecraft pointing performance. What ensued was an effort to characterize the actual performance of the existing shade design, determine what could be done within the physical envelope available, and modify the hardware to meet requirements. Changes were made based on this review activity and Aqua was launched on May 4, 2002. To date the spacecraft is meeting all of its science pointing requirements. Reported here are the lightshade design predictions, test results, and the measured on orbit performance of these shades.
    Keywords: Spacecraft Design, Testing and Performance
    Type: 2003 AAS Guidance and Control Conference; Feb 05, 2003 - Feb 09, 2003; Breckenridge, CO; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    In-Space Propulsion Program Overview and Status (2003)
    In:  Other Sources
    Details
    Publication Date: 2019-08-27
    Description: NASA's In-Space Propulsion (ISP) Program is designed to develop advanced propulsion technologies that can enable or greatly enhance near and mid-term NASA science missions by significantly reducing cost, mass, and/or travel times. These technologies include: Solar Electric Propulsion, Aerocapture, Solar Sails, Momentum Exchange Tethers, Plasma Sails and other technologies such as Advanced Chemical Propulsion. The ISP Program intends to develop cost-effective propulsion technologies that will provide a broad spectrum of mission possibilities, enabling NASA to send vehicles on longer, more useful voyages and in many cases to destinations that were previously unreachable using conventional means. The ISP approach to identifying and prioritizing these most promising technologies is to use mission and system analysis and subsequent peer review. The ISP program seeks to develop technologies under consideration to Technology Readiness Level (TRL) -6 for incorporation into mission planning within 3-5 years of initiation. The NASA TRL 6 represents a level where a technology is ready for system level demonstration in a relevant environment, usually a space environment. In addition, maximum use of open competition is encouraged to seek optimum solutions under ISP. Several NASA Research Announcements (NRA's) have been released asking industry, academia and other organizations to propose propulsion technologies designed to improve our ability to conduct scientific study of the outer planets and beyond. The ISP Program is managed by NASA Headquarters Office of Space Science and implemented by the Marshall Space Flight Center in Huntsville, Alabama.
    Keywords: Spacecraft Propulsion and Power
    Type: International Electric Propulsion Conference 2003; Mar 17, 2003 - Mar 21, 2003; Toulouse; France
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Modeling and Validation of a Propellant Mixer for Controller Design (2003)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: A mixing chamber used in rocket engine testing at the NASA Stennis Space Center is modelled by a system of two nonlinear ordinary differential equations. The mixer is used to condition the thermodynamic properties of cryogenic liquid propellant by controlled injection of the same substance in the gaseous phase. The three inputs of the mixer are the positions of the valves regulating the liquid and gas flows at the inlets, and the position of the exit valve regulating the flow of conditioned propellant. Mixer operation during a test requires the regulation of its internal pressure, exit mass flow, and exit temperature. A mathematical model is developed to facilitate subsequent controller designs. The model must be simple enough to lend itself to subsequent feedback controller design, yet its accuracy must be tested against real data. For this reason, the model includes function calls to thermodynamic property data. Some structural properties of the resulting model that pertain to controller design, such as uniqueness of the equilibrium point, feedback linearizability and local stability are shown to hold under conditions having direct physical interpretation. The existence of fixed valve positions that attain a desired operating condition is also shown. Validation of the model against real data is likewise provided.
    Keywords: Spacecraft Propulsion and Power
    Type: SE-2002-12-00083-SSC
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Flight Reconstruction of the Mars Pathfinder Disk-Gap-Band Parachute Drag Coefficient (2003)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: On July 4, 1997, the Mars Pathfinder (MPF) mission successfully landed on Mars. The entry, descent, and landing (EDL) scenario employed the use of a Disk-Gap-Band parachute design to decelerate the Lander. Flight reconstruction of the entry using MPF flight accelerometer data revealed that the MPF parachute decelerated faster than predicted. In the summer of 2003, the Mars Exploration Rover (MER) mission will send two Landers to the surface of Mars arriving in January 2004. The MER mission utilizes a similar EDL scenario and parachute design as that employed by MPF. As a result, characterizing the degree of underperformance of the MPF parachute system is critical for the MER EDL trajectory design. This paper provides an overview of the methodology utilized to estimate the MPF parachute drag coefficient as experienced on Mars.
    Keywords: Spacecraft Design, Testing and Performance
    Type: AIAA Paper 2003-2126 , 17th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar; May 19, 2003 - May 22, 2003; Monterey, CA; United States
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    NASA TECHNICAL REPORTS
  • 5
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    Spacecraft Formation Design Near the Sun-Earth L(sub 2) Point (2003)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Over the next two decades international space agencies including the National Aeronautics and Space Administration and the European Space Agency are proposing space missions which employ distributed spacecraft technologies to enable vast improvements in remote sensing performance as compared to fundamental performance limitations associated with fairing sizes of even the largest launch vehicles. A key initial step towards enabling such challenging missions is the development of processes and algorithms for designing the desired motion of the spacecraft formation subject to simultaneous gravitational and fuel constraints. In this paper we develop analogous methodologies for designing trajectories of relative motion near the L(sub 2) point as have been thoroughly developed for the Earth-orbiting regime. In this preliminary study, we confine ourselves to the basic assumptions of the Circular Restricted Three-Body Problem where disturbances, non-gravitational effects, and fourth and greater body affects are ignored. The focus is on determining formations that are defined primarily by the natural gravitational effects on the vehicles, such that maintenance over long-term will not require significant fuel consumption.
    Keywords: Spacecraft Design, Testing and Performance
    Type: AIAA GN and C Conference; Aug 01, 2004; Providence, RI; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Performance Expectations of Closed-Brayton-Cycle Heat Exchangers in 100-kWe Nuclear Space Power Systems (2003)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Performance expectations of closed-Brayton-cycle heat exchangers to be used in 100-kWe nuclear space power systems were forecast. Proposed cycle state points for a system supporting a mission to three of Jupiter s moons required effectiveness values for the heat-source exchanger, recuperator and rejection exchanger (gas cooler) of 0.98,0.95 and 0.97, respectively. Performance parameters such as number of thermal units (Nm), equivalent thermal conductance (UA), and entropy generation numbers (Ns) varied from 11 to 19,23 to 39 kWK, and 0.019 to 0.023 for some standard heat exchanger configurations. Pressure-loss contributions to entropy generation were significant; the largest frictional contribution was 114% of the heat-transfer irreversibility. Using conventional recuperator designs, the 0.95 effectiveness proved difficult to achieve without exceeding other performance targets; a metallic, plate-fin counterflow solution called for 15% more mass and 33% higher pressure-loss than the target values. Two types of gas-coolers showed promise. Single-pass counterflow and multipass cross-counterflow arrangements both met the 0.97 effectiveness requirement. Potential reliability-related advantages of the cross-countefflow design were noted. Cycle modifications, enhanced heat transfer techniques and incorporation of advanced materials were suggested options to reduce system development risk. Carbon-carbon sheeting or foam proved an attractive option to improve overall performance.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/TM-2003-212597 , AIAA Paper 2003-5956 , NAS 1.15:212597 , E-14139 , First International Energy Conversion Engineering Conference; Aug 17, 2003 - Aug 21, 2003; Portsmouth, VA; United States
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    NASA TECHNICAL REPORTS
  • 7
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    The Mars Exploration Rovers Entry Descent and Landing and the Use of Aerodynamic Decelerators (2003)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: The Mars Exploration Rovers (MER) project, the next United States mission to the surface of Mars, uses aerodynamic decelerators in during its entry, descent and landing (EDL) phase. These two identical missions (MER-A and MER-B), which deliver NASA s largest mobile science suite to date to the surface of Mars, employ hypersonic entry with an ablative energy dissipating aeroshell, a supersonic/subsonic disk-gap-band parachute and an airbag landing system within EDL. This paper gives an overview of the MER EDL system and speaks to some of the challenges faced by the various aerodynamic decelerators.
    Keywords: Spacecraft Design, Testing and Performance
    Type: AIAA Paper 2003-2125 , AIAA ADS Conference; May 20, 2003 - May 22, 2003; Monterey, CA; United States
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    NASA TECHNICAL REPORTS
  • 8
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    Meteoroid/Debris Shielding (2003)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: This report provides innovative, low-weight shielding solutions for spacecraft and the ballistic limit equations that define the shield's performance in the meteoroid/debris environment. Analyses and hypervelocity impact testing results are described that have been used in developing the shields and equations. Spacecraft shielding design and operational practices described in this report are used to provide effective spacecraft protection from meteoroid and debris impacts. Specific shield applications for the International Space Station (ISS), Space Shuttle Orbiter and the CONTOUR (Comet Nucleus Tour) space probe are provided. Whipple, Multi-Shock and Stuffed Whipple shield applications are described.
    Keywords: Spacecraft Design, Testing and Performance
    Type: NASA/TP-2003-210788 , S-898 , NAS 1.60:210788
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    NASA TECHNICAL REPORTS
  • 9
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    Human Support Technology Research to Enable Exploration (2003)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Contents include the following: Advanced life support. System integration, modeling, and analysis. Progressive capabilities. Water processing. Air revitalization systems. Why advanced CO2 removal technology? Solid waste resource recovery systems: lyophilization. ISRU technologies for Mars life support. Atmospheric resources of Mars. N2 consumable/make-up for Mars life. Integrated test beds. Monitoring and controlling the environment. Ground-based commercial technology. Optimizing size vs capability. Water recovery systems. Flight verification topics.
    Keywords: Spacecraft Design, Testing and Performance
    Type: Results of the Workshop on Two-Phase Flow, Fluid Stability and Dynamics: Issues in Power, Propulsion, and Advanced Life Support Systems; 91-121; NASA/TM-2003-212598
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  • 10
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    Evolutionary Design of an X-Band Antenna for NASA's Space Technology 5 Mission (2003)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: We present an evolved X-band antenna design and flight prototype currently on schedule to be deployed on NASA s Space Technology 5 spacecraft in 2004. The mission consists of three small satellites that wall take science measurements in Earth s magnetosphere. The antenna was evolved to meet a challenging set of mission requirements, most notably the combination of wide beamwidth for a circularly-polarized wave and wide bandwidth. Two genetic algorithms were used: one allowed branching an the antenna arms and the other did not. The highest performance antennas from both algorithms were fabricated and tested. A handdesigned antenna was produced by the contractor responsible for the design and build of the mission antennas. The hand-designed antenna is a quadrifilar helix, and we present performance data for comparison to the evolved antennas. As of this writing, one of our evolved antenna prototypes is undergoing flight qualification testing. If successful, the resulting antenna would represent the first evolved hardware in space, and the first deployed evolved antenna.
    Keywords: Spacecraft Design, Testing and Performance
    Type: 2003 NASA/DoD Conference on Evolvable Hardware; Jan 01, 2003; Unknown
    Format: application/pdf
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