asteRisk (version 1.1.0)

ECEFtoLATLON: Convert coordinates from ECEF to geodetic latitude, longitude and altitude

Description

The ECEF (Earth Centered, Earth Fixed) frame of reference is a non-inertial coordinate frame, where the origin is placed at the center of mass of the Earth and the frame rotates with respect to the stars to remain fixed with respect to the Earth surface as it rotates. This function converts Cartesian coordinates in the ECEF frame to geodetic latitude, longitude and altitude.

Usage

ECEFtoLATLON(position_ECEF, degreesOutput=TRUE)

Arguments

position_ECEF

Vector with the X, Y and Z components of the position of an object in ECEF frame, in m.

degreesOutput

Logical indicating if the output should be in sexagesimal degrees. If degreesOutput=FALSE, the output will be in radians.

Value

A vector with three elements, corresponding to the latitude and longitude in degrees and the altitude in m.

References

https://arc.aiaa.org/doi/10.2514/6.2006-6753

Examples

# NOT RUN {
# The following orbital parameters correspond to an object with NORAD catalogue
# number 24208 (Italsat 2) the 26th of June, 2006 at 00:58:29.34 UTC.

n0 <- 1.007781*((2*pi)/(1440))  # Multiplication by 2pi/1440 to convert to radians/min
e0 <- 0.002664 # mean eccentricity at epoch
i0 <- 3.8536*pi/180 # mean inclination at epoch in radians
M0 <- 48.3*pi/180 # mean anomaly at epoch in radians
omega0 <- 311.0977*pi/180 # mean argument of perigee at epoch in radians
OMEGA0 <- 80.0121*pi/180 # mean longitude of ascending node at epoch in radians
Bstar <- 1e-04 # drag coefficient
epochDateTime <- "2006-06-26 00:58:29.34"

# Let<U+00B4>s calculate the position and velocity of the satellite 1 day later

state_1day_TEME <- sgdp4(n0=n0, e0=e0, i0=i0, M0=M0, omega0=omega0, OMEGA0=OMEGA0,
                         Bstar=Bstar, initialDateTime=epochDateTime, targetTime=1440)

# We can now convert the results in TEME frame to ECEF frame, previously
# multiplying by 1000 to convert the km output of sgdp4 to m

state_1day_ECEF <- TEMEtoECEF(state_1day_TEME$position, state_1day_TEME$velocity,
                              "2006-06-27 00:58:29.34")
                              
# Finally, we can convert the ECEF coordinates to geodetic latitude, longitude
# and altitude

state_1day_geodetic <- ECEFtoLATLON(state_1day_ECEF$position)
# }