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sample TLE

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Jeff Moe 2022-05-21 14:30:57 -06:00
parent 72fdf7b902
commit 4e3c8e436c
2 changed files with 80 additions and 8 deletions
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26
README.md
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@ -63,6 +63,31 @@ In Celestia name "Galileo" is used for the *other* spacecraft, not
for the EU GNSS. So the name used in development here adds `-gnss`,
ala, `galileo-gnss.ssc`, whereas the other GNSS don't.
Example `.ssc` file contents:
```
"1997-035A" "Sol/Earth" {
Class "spacecraft"
# Mesh
Radius 0.005
EllipticalOrbit {
Epoch 2459718.94467728
Period 0.49859567
SemiMajorAxis 26560.345
Eccentricity 0.0057297
Inclination 55.5062
AscendingNode 156.8049
ArgOfPericenter 51.2220
MeanAnomaly 309.3262
}
Obliquity 55.5062
EquatorAscendingNode 156.8049
RotationOffset 80.2289
# Orientation [ ]
}
```
## Galileo
Galileo 3D models are from the ESA:
@ -172,6 +197,7 @@ Crufty bad way to do it, example:
sudo cp -a extras/galileo-gnss/ /usr/share/celestia/extras-standard/
```
# Issues
`pyorbital` doesn't support geostationary orbits.
It gives the error:

62
tle2ssc
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@ -17,7 +17,7 @@ from datetime import datetime
now = datetime.utcnow()
tle = tlefile.read('GSAT0206', 'extras/galileo-gnss/galileo.txt')
tle = tlefile.read('GSAT0101', 'extras/galileo-gnss/galileo.txt')
#print(pyorbital.tlefile.SATELLITES)
#print(orbital.Orbital.get_position)
@ -27,12 +27,58 @@ satline1=tle.line1
satline2=tle.line2
satinclination=tle.inclination
orb = Orbital(satname)
# Fail:
#orb = Orbital(satname)
print('Satellite name: ', satname)
print('Line one of TLE:')
print(satline1)
print('Line two of TLE:')
print(satline2)
print('Inclination: ', satinclination)
#print('Satellite name: ', satname)
#print('Line one of TLE:')
#print(satline1)
#print('Line two of TLE:')
#print(satline2)
#print('Inclination: ', satinclination)
# Create SSC
# From TLE:
# GSAT0101 (PRN E11)
# 1 37846U 11060A 22140.09549104 -.00000093 00000+0 00000+0 0 9998
# 2 37846 56.9858 22.1062 0004117 28.0726 331.9949 1.70474933 65739
#
# Satellite name: GSAT0101
# Satellite number: 37846U
# Satellite number: 37846
# International designator: 11060A
# Inclination: 56.9858
# Epoch year and Julian day fraction: 22140.09549104
# Right ascension of ascending node: 22.1062
# Eccentricity: 0004117
# First derivative of mean motion or ballistic coefficient: -.00000093
# Argument of perigee: 28.0726
# Second derivative of mean motion: 00000+0
# Mean anomaly: 331.9949
# Drag term or radiation pressure coefficient: 00000+0
# Mean motion: 1.70474933
# Ephemeris type: 0
# Element number and checksum: 9998
# Revolution number at epoch and checksum: 65739
print('"', satname, '" ','"Sol/Earth" {',sep="")
print(' Class "spacecraft"')
print(' # Mesh "foo.3ds"')
print(' radius 0.005')
print()
print(' EllipticalOrbit {')
print(' Epoch 2459718.94467728')
print(' Period 0.49859567')
print(' SemiMajorAxis 26560.345')
print(' Eccentricity 0.0057297')
print(' Inclination', satinclination)
print(' AscendingNode 156.8049')
print(' ArgOfPericenter 51.2220')
print(' MeanAnomaly 309.3262')
print(' }')
print(' Obliquity 55.5062')
print(' EquatorAscendingNode 156.8049')
print(' RotationOffset 80.2289')
print(' # Orientation [ ]')
print('}')