Differences between revisions 12 and 13
Revision 12 as of 2017-02-14 22:05:31
Size: 1424
Comment:
Revision 13 as of 2017-02-14 22:06:12
Size: 1432
Comment:
Deletions are marked like this. Additions are marked like this.
Line 11: Line 11:
 .1 from the altitudes and Earth's equatorial radius, compute radii  .1 - from the altitudes and Earth's equatorial radius, compute radii
Line 13: Line 13:
 .2 Given apogee and perigee and the Earth gravitational parameter, compute  .2 - Given apogee and perigee and the Earth gravitational parameter, compute
Line 17: Line 17:
 .3 Given the radius of the lower and upper bounds of the inner belt (altitudes 200 and 1000 km), compute  .3 - Given the radius of the lower and upper bounds of the inner belt (altitudes 200 and 1000 km), compute
Line 21: Line 21:
 .4 from the difference in the mean anomaly angles and the orbital angular velocity, compute transit time  .4 - from the difference in the mean anomaly angles and the orbital angular velocity, compute transit time

Radiation belt transit times to GEO and the Moon

LibreOffice spreadsheet here

Excel/97 version here. Not sure whether this will work with your version of Excel, this is the translation made by LibreOffice, and I don't have any computers that run any of the myriad versions of Windoze or Excel.

LibreOffice is available for free download here.

I used the equations here on the server sky website.

  • 1 - from the altitudes and Earth's equatorial radius, compute radii
    • assume all orbits are circular equatorial. Inclined orbits require an expensive plane change, best done after circularization
  • 2 - Given apogee and perigee and the Earth gravitational parameter, compute
    • Semimajor axis
    • Eccentricity
    • Orbit angular velocity
  • 3 - Given the radius of the lower and upper bounds of the inner belt (altitudes 200 and 1000 km), compute
    • true anomaly angle
    • eccentric anomaly angle
    • mean anomaly angle
  • 4 - from the difference in the mean anomaly angles and the orbital angular velocity, compute transit time

Conclusion: a Hohmann transfer orbit from ISS altitude to GEO takes 21.8 minutes to pass through the inner van Allen belt, and 18.2 minutes to pass through the inner belt on the way to the Moon.

belttimes (last edited 2017-02-14 22:20:28 by KeithLofstrom)