Orbital elements: Difference between revisions
Content added Content deleted
m (→{{header|J}}: try to be less misleading for the unexperienced eye) |
m (→{{header|J}}: move parameter declaration to opening line) |
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norm=: % %:@X~ |
norm=: % %:@X~ |
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orbitalStateVectors=: {{ |
orbitalStateVectors=: {{ 'a e i Om w f'=. y |
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NB. a: semi-major axis |
NB. a: semi-major axis |
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NB. e: eccentricity |
NB. e: eccentricity |
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| Line 753: | Line 753: | ||
NB. w: argument of Periapsis (the other "omega") |
NB. w: argument of Periapsis (the other "omega") |
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NB. f: true anomaly |
NB. f: true anomaly |
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'a e i Om w f'=. y |
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L=. a*2:`]@.*1-*:e |
L=. a*2:`]@.*1-*:e |
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'c s'=. 2{.,F=. 2 R f |
'c s'=. 2{.,F=. 2 R f |
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| Line 760: | Line 759: | ||
ijk=. F X (2 R w)X(0 R i)X(2 R Om) |
ijk=. F X (2 R w)X(0 R i)X(2 R Om) |
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position=. ra*{.ijk |
position=. ra*{.ijk |
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speed=. (%:(2%ra)-%a)*norm |
speed=. (%:(2%ra)-%a)*norm(rp,ra,0) X ijk |
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position,:speed |
position,:speed |
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}}</lang> |
}}</lang> |
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