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  • 1
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    Mission Analysis for High Specific Impulse Deep Space Exploration (2002)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes trajectory calculations for high specific impulse engines. Specific impulses on the order of 10,000 to 100,000 sec are predicted in a variety of fusion powered propulsion systems. This paper and its companion paper seek to build on analyses in the literature to yield an analytical routine for determining time of flight and payload fraction to a predetermined destination. The companion paper will compare the results of this analysis to the trajectories determined by several trajectory codes. The major parameters that affect time of flight and payload fraction will be identified and their sensitivities quantified. A review of existing fusion propulsion concepts and their capabilities will also be tabulated.
    Keywords: Astronautics (General)
    Type: 28th International Electric Propulsion Conference (IEPC); Mar 17, 2003 - Mar 21, 2003; Toulouse; France
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Emerging Technologies for Mars Exploration: Entry, Descent, and Landing (2019)
    In:  CASI
    Details
    Publication Date: 2019-07-20
    Description: No abstract available
    Keywords: Lunar and Planetary Science and Exploration; Spacecraft Design, Testing and Performance
    Type: MSFC-E-DAA-TN66423 , IEEE Aerospace Conference; Mar 02, 2019 - Mar 09, 2019; Big Sky, MT; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Simulation of Trajectories for High Specific Impulse Deep Space Exploration (2002)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: Difficulties in approximating flight times and deliverable masses for continuous thrust propulsion systems have complicated comparison and evaluation of proposed propulsion concepts. These continuous thrust propulsion systems are of interest to many groups, not the least of which are the electric propulsion and fusion communities. Several charts plotting the results of well-known trajectory simulation codes were developed and are contained in this paper. These charts illustrate the dependence of time of flight and payload ratio on jet power, initial mass, specific impulse and specific power. These charts are intended to be a tool by which people in the propulsion community can explore the possibilities of their propulsion system concepts. Trajectories were simulated using the tools VARITOP and IPOST. VARITOP is a well known trajectory optimization code that involves numerical integration based on calculus of variations. IPOST has several methods of trajectory simulation; the one used in this paper is Cowell's method for full integration of the equations of motion. The analytical method derived in the companion paper was also used to simulate the trajectory. The accuracy of this method is discussed in the paper.
    Keywords: Astronautics (General)
    Type: 28th International Electric Propulsion Conference; Mar 17, 2003 - Mar 21, 2003; Toulouse; France
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Human Mars Entry, Descent and Landing Architecture Study (EDLAS): Rigid Decelerators (2018)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Develop two evolutionary rigid vehicle concepts to deliver human-scale payloads (20 metric tons) to the surface of Mars: Capsule; Lifting body, mid-range lift-to-drag ratio (Mid L/D). Determine vehicle configurations for various mission flight phases. Determine vehicle performance: Integrated system mass; Ability to meet landing constraints; Payload packaging and surface access. Provide technology investment recommendations to NASAs Space Technology Mission Directorate.
    Keywords: Lunar and Planetary Science and Exploration; Spacecraft Design, Testing and Performance
    Type: MSFC-E-DAA-TN61432 , Space and Astronautics Forum (AIAA SPACE Forum 2018); Sep 17, 2018 - Sep 19, 2018; Orlando, FL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Human Mars Ascent Vehicle Performance Sensitivities (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Human Mars mission architecture studies have shown that the ascent vehicle mass drives performance requirements for the descent and in-space transportation elements. Understanding the sensitivity of Mars ascent vehicle (MAV) mass to various mission and vehicle design choices enables overall transportation system optimization. This paper presents the results of a variety of sensitivity trades affecting MAV performance including: landing site latitude, target orbit, initial thrust to weight ratio, staging options, specific impulse, propellant type and engine design.
    Keywords: Astronautics (General)
    Type: M16-5125 , AIAA Space and Astronautics Forum and Exposition (SPACE 2016); Sep 13, 2016 - Sep 16, 2016; Long Beach, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Human Landing System for Lunar Exploration (2019)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: No abstract available
    Keywords: Astronautics (General)
    Type: MSFC-E-DAA-TN70178 , International Planetary Probe Workshop; Jul 11, 2019
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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