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fix: remove duplicated subtraction of ephemeris reference time

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pedromiguelcp
2025-08-13 14:36:04 +01:00
parent 4549f62c7d
commit 867d67180e
1 changed files with 3 additions and 6 deletions
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9
utils/skyplot/skyplot.py
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@@ -205,15 +205,12 @@ def calculate_satellite_position(ephemeris, transmit_time):
# Semi-major axis # Semi-major axis
a = ephemeris['sqrt_a'] ** 2 a = ephemeris['sqrt_a'] ** 2
# Time difference from ephemeris reference time
tk = transmit_time - ephemeris['toe']
# Corrected mean motion # Corrected mean motion
n0 = sqrt(mu / (a ** 3)) n0 = sqrt(mu / (a ** 3))
n = n0 + ephemeris['delta_n'] n = n0 + ephemeris['delta_n']
# Mean anomaly # Mean anomaly
mk = ephemeris['m0'] + n * tk mk = ephemeris['m0'] + n * transmit_time
# Solve Kepler's equation for eccentric anomaly (Ek) # Solve Kepler's equation for eccentric anomaly (Ek)
ek = mk ek = mk
@@ -237,7 +234,7 @@ def calculate_satellite_position(ephemeris, transmit_time):
# Corrected argument of latitude, radius and inclination # Corrected argument of latitude, radius and inclination
uk = phi_k + delta_uk uk = phi_k + delta_uk
rk = a * (1 - ephemeris['ecc'] * cos(ek)) + delta_rk rk = a * (1 - ephemeris['ecc'] * cos(ek)) + delta_rk
ik = ephemeris['i0'] + delta_ik + ephemeris['idot'] * tk ik = ephemeris['i0'] + delta_ik + ephemeris['idot'] * transmit_time
# Positions in orbital plane # Positions in orbital plane
xk_prime = rk * cos(uk) xk_prime = rk * cos(uk)
@@ -246,7 +243,7 @@ def calculate_satellite_position(ephemeris, transmit_time):
# Corrected longitude of ascending node # Corrected longitude of ascending node
omega_k = ( omega_k = (
ephemeris['omega0'] ephemeris['omega0']
+ (ephemeris['omega_dot'] - omega_e_dot) * tk + (ephemeris['omega_dot'] - omega_e_dot) * transmit_time
- omega_e_dot * ephemeris['toe'] - omega_e_dot * ephemeris['toe']
) )