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Related Experiment Videos

Radiation shielding estimates for manned Mars space flight.

V E Dudkin1, E E Kovalev, A V Kolomensky

  • 1Research Centre of Radiation Protection in the Cosmos, Moscow, U.S.S.R.

International Journal of Radiation Applications and Instrumentation. Part D, Nuclear Tracks and Radiation Measurements
|January 1, 1992
PubMed
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This study analyzes spacecraft radiation shielding for Mars missions, considering solar activity (SA) effects on cosmic rays. Combining liquid propellant and nuclear electrojet engines offers the lowest spacecraft mass, around 500-550 metric tons.

Area of Science:

  • Space exploration
  • Astrophysics
  • Radiation physics

Background:

  • Spacecraft radiation shielding is critical for Mars missions.
  • Solar activity (SA) significantly impacts cosmic ray intensity.
  • Previous studies have not fully integrated SA effects with propulsion system mass estimations.

Purpose of the Study:

  • To determine optimal radiation shielding for Mars-bound spacecraft.
  • To evaluate the influence of solar activity on radiation exposure.
  • To assess different Soviet-designed propulsion systems for Mars missions.

Main Methods:

  • Analysis of galactic and solar cosmic ray intensities under varying solar activity.
  • Review of spaceflight scenarios using liquid propellant, nuclear electrojet, and nuclear rocket engines.
Keywords:
NASA Discipline Number 00-00NASA Discipline Number 04-10NASA Discipline Radiation HealthNASA Program FlightNASA Program Radiation HealthNon-NASA Center

Related Experiment Videos

  • Mass calculations for spacecraft, including radiation shielding, based on U.S.S.R. standards.

    • Main Results:

    • Spacecraft mass estimations varied based on solar activity levels (maximum, minimum, intermediate).
    • The combination of liquid propellant engines with low- and intermediate-thrust nuclear electrojet engines yielded the lowest spacecraft mass.
    • Estimated minimum spacecraft mass, including shielding, was 500-550 metric tons.

    Conclusions:

    • A hybrid propulsion system (liquid propellant + nuclear electrojet) is most efficient for minimizing Mars spacecraft mass.
    • Radiation shielding mass is a significant factor in overall spacecraft design for Mars missions.
    • Understanding solar activity's impact is crucial for effective radiation protection strategies in deep space.