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  • 1
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    Development of a Monte Carlo Mars-Gram Model for 2001 Mars Odyssey Aerobraking Simulations (2002)
    Springer
    Details
    Publication Date: 2002-06-01
    Print ISSN: 0021-9142
    Electronic ISSN: 2195-0571
    Topics: Physics
    Published by Springer
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    PAPER CURRENT
  • 2
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    The Development and Evaluation of an Operational Aerobraking Strategy for the Mars 2001 Odyssey Orbiter (2002)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Mars 2001 Odyssey Orbiter successfully completed the aerobraking phase of its mission on January 11, 2002. This paper discusses the support provided by NASA's Langley Research Center to the navigation team at the Jet Propulsion Laboratory in the planning and operational support of Mars Odyssey Aerobraking. Specifically, the development of a three-degree-of-freedom aerobraking trajectory simulation and its application to pre-flight planning activities as well as operations is described. The importance of running the simulation in a Monte Carlo fashion to capture the effects of mission and atmospheric uncertainties is demonstrated, and the utility of including predictive logic within the simulation that could mimic operational maneuver decision-making is shown. A description is also provided of how the simulation was adapted to support flight operations as both a validation and risk reduction tool and as a means of obtaining a statistical basis for maneuver strategy decisions. This latter application was the first use of Monte Carlo trajectory analysis in an aerobraking mission.
    Keywords: Computer Systems
    Type: AIAA Paper 2002-4537 , AIAA Atmospheric Flight Mechanics Conference and Exhibit; Aug 05, 2002 - Aug 08, 2002; Monterey, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    NASA Development of Aerocapture Technologies (2004)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Aeroassist technology development is a vital part of the NASA In-Space Propulsion Program (ISP), which is managed by the NASA Headquarters Office of Space Science, and implemented by the Marshall Space Flight Center in Huntsville, Alabama. Aeroassist is the general term given to various techniques to maneuver a space vehicle within an atmosphere, using aerodynamic forces in lieu of propulsive fuel. Within the ISP, the current aeroassist technology development focus is aerocapture. The objective of the ISP Aerocapture Technology Project (ATP) is to develop technologies that can enable and/or benefit NASA science missions by significantly reducing cost, mass, and/or travel times. To accomplish this objective, the ATP identifies and prioritizes the most promising technologies using systems analysis, technology advancement and peer review, coupled with NASA Headquarters Office of Space Science target requirements. Plans are focused on developing mid-Technology Readiness Level (TRL) technologies to TRL 6 (ready for technology demonstration in space).
    Keywords: Spacecraft Propulsion and Power
    Type: 36th Annual Division for Planetary Science; Nov 08, 2004 - Nov 10, 2004; Louisville, KY; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Aerocapture Technology Development Needs for Outer Planet Exploration (2002)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: The purpose of this white paper is to identify aerocapture technology and system level development needs to enable NASA future mission planning to support Outer Planet Exploration. Aerocapture is a flight maneuver that takes place at very high speeds within a planet's atmosphere that provides a change in velocity using aerodynamic forces (in contrast to propulsive thrust) for orbit insertion. Aerocapture is very much a system level technology where individual disciplines such as system analysis and integrated vehicle design, aerodynamics, aerothermal environments, thermal protection systems (TPS), guidance, navigation and control (GN&C) instrumentation need to be integrated and optimized to meet mission specific requirements. This paper identifies on-going activities, their relevance and potential benefit to outer planet aerocapture that include New Millennium ST7 Aerocapture concept definition study, Mars Exploration Program aeroassist project level support, and FY01 Aeroassist In-Space Guideline tasks. The challenges of performing aerocapture for outer planet missions such as Titan Explorer or Neptune Orbiter require investments to advance the technology readiness of the aerocapture technology disciplines for the unique application of outer planet aerocapture. This white paper will identify critical technology gaps (with emphasis on aeroshell concepts) and strategies for advancement.
    Keywords: Space Transportation and Safety
    Type: NASA/TM-2002-211386 , NAS 1.15:211386 , A-0107378
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Departure Energies, Trip Times and Entry Speeds for Human Mars Missions (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: The study examines how the mission design variables departure energy, entry speed, and trip time vary for round-trip conjunction-class Mars missions. These three parameters must be balanced in order to produce a mission that is acceptable in terms of mass, cost, and risk. For the analysis, a simple, massless-planet trajectory program was employed. The premise of this work is that if the trans-Mars and trans-Earth injection stages are designed for the most stringent opportunity in the energy cycle, then there is extra energy capability in the "easier" opportunities which can be used to decrease the planetary entry speed, or shorten the trip time. Both of these effects are desirable for a human exploration program.
    Keywords: Man/System Technology and Life Support
    Type: AAS-99-103
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Aeroassist Technology Planning for Exploration (2000)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: Now that the International Space Station is undergoing assembly, NASA is strategizing about the next logical exploration strategy for robotic missions and the next destination for humans. NASA's current efforts are in developing technologies that will both aid the robotic exploration strategy and make human flight to other celestial bodies both safe and affordable. One of these enabling technologies for future robotic and human exploration missions is aeroassist. This paper will (1) define aeroassist, (2) explain the benefits and uses of aeroassist, and (3) describe a method, currently used by the NASA Aeroassist Working Group, by which widely geographically distributed teams can assemble, present, use, and archive technology information.
    Keywords: Space Sciences (General)
    Type: AAS-00-169
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    NASA Development of Aerocapture Technologies (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Aeroassist technology development is a vital part of the NASA ln-Space Propulsion Program (ISP), which is managed by the NASA Headquarters Office of Space Science, and implemented by the Marshall Space Flight Center in Huntsville, Alabama. Aeroassist is the general term given to various techniques to maneuver a space vehicle within an atmosphere, using aerodynamic forces in lieu of propulsive fuel. Within the ISP, the current aeroassist technology development focus is aerocapture. The objective of the ISP Aerocapture Technology Project (ATP) is to develop technologies that can enable and/or benefit NASA science missions by significantly reducing cost, mass, and/or travel times. To accomplish this objective, the ATP identifies and prioritizes the most promising technologies using systems analysis, technology advancement and peer review, coupled with NASA Headquarters Office of Space Science target requirements. Plans are focused on developing mid-Technology Readiness Level (TRL) technologies to TRL 6 (ready for technology demonstration in space).
    Keywords: Spacecraft Design, Testing and Performance
    Type: 17th AIAA Aerodynamic Decelerator Systems Technology Conference; May 20, 2003 - May 22, 2003; Monterey, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Departure Energies, Trip Times and Entry Speeds for Human Mars Missions (1999)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The study examines how the mission design variables departure energy, entry speed, and trip time vary for round-trip conjunction-class Mars missions. These three parameters must be balanced in order to produce a mission that is acceptable in terms of mass, cost, and risk. For the analysis, a simple, massless- planet trajectory program was employed. The premise of this work is that if the trans-Mars and trans-Earth injection stages are designed for the most stringent opportunity in the energy cycle, then there is extra energy capability in the "easier" opportunities which can be used to decrease the planetary entry speed, or shorten the trip time. Both of these effects are desirable for a human exploration program.
    Keywords: Astronautics (General)
    Type: AAS Paper 99-103 , Space Flight Mechanics; Feb 07, 1999 - Feb 10, 1999; Breckenridge, CO; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Aerocapture Technology Project Overview (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: Aerocapture technology development is one of the highest priority investments for the NASA In-Space Propulsion Program (ISP). The ISP is managed by the NASA Headquarters Office of Space Science, and implemented by the Marshall Space Flight Center in Huntsville, Alabama. The objective of the ISP Aerocapture Technology Project (ATP) is to develop technologies that can enable and/or benefit NASA science missions by significantly reducing cost, mass, and trip times. To accomplish this objective, the ATP identifies and prioritizes the most promising technologies using systems analysis, technology advancement and peer review, coupled with NASA Headquarters Office of Space Science target requirements. Efforts are focused on developing mid-Technology Readiness Level (TRL) technologies to systems-level spaceflight validation.
    Keywords: Spacecraft Propulsion and Power
    Type: AIAA Paper 2003-4654
    Format: text
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    NASA TECHNICAL REPORTS
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