deviation of semi-major axis
If I calculate the semi-major axis of Molniya-1T with
$a = sqrt[3]{dfrac{GM}{n^2}}$ with $n=3.18683728text{ }d^{-1}$
, I get another apoapsis ($a=19505.7$ km) as noted at heavens above :
apogee height: 25659 km
perigee height: 595 km
which is $a=frac{25659+595}{2}=13127$ km.
This is my approach in octave/matlab:
# computes the Semi major axis a from n with constant GM
# @params:
# GM constant (cubic km per square second)
# n: mean motion (revs/day)
# @return:
# a: semi major axis (km)
function a = getSemiMajorAxis(GM,n)
n = n*2*pi/(24*60*60); #conversion (revs/day) --> (rad/s)
a = (GM/(power(n,2))).^(1./3);
endfunction
getSemiMajorAxis(398600.44,3.18683728) # test with Molniya-1T
So, what is the origin of the deviation? Isn't apogee the same as apoapsis basically?
orbital-mechanics orbit orbital-elements
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If I calculate the semi-major axis of Molniya-1T with
$a = sqrt[3]{dfrac{GM}{n^2}}$ with $n=3.18683728text{ }d^{-1}$
, I get another apoapsis ($a=19505.7$ km) as noted at heavens above :
apogee height: 25659 km
perigee height: 595 km
which is $a=frac{25659+595}{2}=13127$ km.
This is my approach in octave/matlab:
# computes the Semi major axis a from n with constant GM
# @params:
# GM constant (cubic km per square second)
# n: mean motion (revs/day)
# @return:
# a: semi major axis (km)
function a = getSemiMajorAxis(GM,n)
n = n*2*pi/(24*60*60); #conversion (revs/day) --> (rad/s)
a = (GM/(power(n,2))).^(1./3);
endfunction
getSemiMajorAxis(398600.44,3.18683728) # test with Molniya-1T
So, what is the origin of the deviation? Isn't apogee the same as apoapsis basically?
orbital-mechanics orbit orbital-elements
New contributor
sequoia is a new contributor to this site. Take care in asking for clarification, commenting, and answering.
Check out our Code of Conduct.
add a comment |
If I calculate the semi-major axis of Molniya-1T with
$a = sqrt[3]{dfrac{GM}{n^2}}$ with $n=3.18683728text{ }d^{-1}$
, I get another apoapsis ($a=19505.7$ km) as noted at heavens above :
apogee height: 25659 km
perigee height: 595 km
which is $a=frac{25659+595}{2}=13127$ km.
This is my approach in octave/matlab:
# computes the Semi major axis a from n with constant GM
# @params:
# GM constant (cubic km per square second)
# n: mean motion (revs/day)
# @return:
# a: semi major axis (km)
function a = getSemiMajorAxis(GM,n)
n = n*2*pi/(24*60*60); #conversion (revs/day) --> (rad/s)
a = (GM/(power(n,2))).^(1./3);
endfunction
getSemiMajorAxis(398600.44,3.18683728) # test with Molniya-1T
So, what is the origin of the deviation? Isn't apogee the same as apoapsis basically?
orbital-mechanics orbit orbital-elements
New contributor
sequoia is a new contributor to this site. Take care in asking for clarification, commenting, and answering.
Check out our Code of Conduct.
If I calculate the semi-major axis of Molniya-1T with
$a = sqrt[3]{dfrac{GM}{n^2}}$ with $n=3.18683728text{ }d^{-1}$
, I get another apoapsis ($a=19505.7$ km) as noted at heavens above :
apogee height: 25659 km
perigee height: 595 km
which is $a=frac{25659+595}{2}=13127$ km.
This is my approach in octave/matlab:
# computes the Semi major axis a from n with constant GM
# @params:
# GM constant (cubic km per square second)
# n: mean motion (revs/day)
# @return:
# a: semi major axis (km)
function a = getSemiMajorAxis(GM,n)
n = n*2*pi/(24*60*60); #conversion (revs/day) --> (rad/s)
a = (GM/(power(n,2))).^(1./3);
endfunction
getSemiMajorAxis(398600.44,3.18683728) # test with Molniya-1T
So, what is the origin of the deviation? Isn't apogee the same as apoapsis basically?
orbital-mechanics orbit orbital-elements
orbital-mechanics orbit orbital-elements
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sequoia is a new contributor to this site. Take care in asking for clarification, commenting, and answering.
Check out our Code of Conduct.
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edited 1 hour ago
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asked 2 hours ago
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Ok, that's embarrassing:
You just have to add earth's radii of about 6378 to the a calculated from the apogee/perigee.
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Ok, that's embarrassing:
You just have to add earth's radii of about 6378 to the a calculated from the apogee/perigee.
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sequoia is a new contributor to this site. Take care in asking for clarification, commenting, and answering.
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Ok, that's embarrassing:
You just have to add earth's radii of about 6378 to the a calculated from the apogee/perigee.
New contributor
sequoia is a new contributor to this site. Take care in asking for clarification, commenting, and answering.
Check out our Code of Conduct.
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Ok, that's embarrassing:
You just have to add earth's radii of about 6378 to the a calculated from the apogee/perigee.
New contributor
sequoia is a new contributor to this site. Take care in asking for clarification, commenting, and answering.
Check out our Code of Conduct.
Ok, that's embarrassing:
You just have to add earth's radii of about 6378 to the a calculated from the apogee/perigee.
New contributor
sequoia is a new contributor to this site. Take care in asking for clarification, commenting, and answering.
Check out our Code of Conduct.
New contributor
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answered 1 hour ago
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