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Record 1 of 4591
Fast round-trip Mars trajectories
Author and Affiliation:
Wilson, Sam(NASA Johnson Space Center, Houston, TX, United States)
Abstract: This paper is concerned with the effect of limiting the overall duration or else the one-way flight time of a round trip to Mars, as reflected in the sum of impulsive velocity increments required of the spacecraft propulsion system. Ignition-to-burnout mass ratios for a hypothetical single stage spacecraft, obtained from the rocket equation by combining these delta-V sums with appropriate values of specific impulse, are used to evaluate the relative effectiveness of four high-thrust propulsion alternatives. If the flight crew goes to the surface of Mars and stays there for the duration of their stopover, it is much cheaper (in terms of delta-V) to minimize their zero-g exposure by limiting the interplanetary transit time of a conjunction-class mission (round trip time = 800-1000 days, Mars stopover = 450-700 days) than to impose the same limit on an opposition-class mission (round trip time less than 600 days, stopover = 40 days). Using solid-core nuclear thermal propulsion to fly a conjunction-class mission, for a moderate mass penalty the interplanetary transit time (each way) probably could be limited to something in the range of 4 to 6 months, depending on the launch year.
Publication Date: Jan 01, 1990
Document ID:
19900065952
(Acquired Nov 28, 1995)
Accession Number: 90A53007
Subject Category: ASTRODYNAMICS
Report/Patent Number: AIAA PAPER 90-2934
Document Type: Conference Paper
Publication Information: (SEE A90-52957)
Publisher Information: United States
Meeting Information: AIAA/AAS Astrodynamics Conference; Aug. 20-22, 1990; Portland, OR; United States
Financial Sponsor: NASA; United States
Organization Source: NASA Johnson Space Center; Houston, TX, United States
Description: 10p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright
NASA Terms: EARTH-MARS TRAJECTORIES; MANNED MARS MISSIONS; RETURN TO EARTH SPACE FLIGHT; TRAJECTORY OPTIMIZATION; MISSION PLANNING; NUCLEAR PROPULSION; TRAJECTORY ANALYSIS
Imprint And Other Notes: IN: AIAA/AAS Astrodynamics Conference, Portland, OR, Aug. 20-22, 1990, Technical Papers. Part 1 (A90-52957 24-13). Washington, DC, American Institute of Aeronautics and Astronautics, 1990, p. 506-515.
Availability Source: Other Sources
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