09-29-2022, 02:48 PM
This HP Prime program can be used to estimate the delta-v required to reach the moon. The algorithm assumes the translunar injection occurs impulsively from a circular Earth orbit.
The user provides an initial departure calendar date according to
// departure calendar date
month := 9;
day := 1;
year := 2013;
The park orbit semimajor axis and orbital inclination are also required; for example
/////////////////////
// initial park orbit
/////////////////////
// semimajor axis (kilometers)
oev_po(1) := req + 185.32;
// orbital eccentricity (non-dimensional)
oev_po(2) := 0.0;
// orbital inclination (degrees)
oev_po(3) := 28.5 * dtr;
Finally, the software requires the user to define the transfer time from Earth to the moon in hours.
// time-of-flight in hours
tof_hours := 84.0;
The PDF document included with the zip archive explains the assumptions and algorithms used to solve this classic orbital transfer problem.
The user provides an initial departure calendar date according to
// departure calendar date
month := 9;
day := 1;
year := 2013;
The park orbit semimajor axis and orbital inclination are also required; for example
/////////////////////
// initial park orbit
/////////////////////
// semimajor axis (kilometers)
oev_po(1) := req + 185.32;
// orbital eccentricity (non-dimensional)
oev_po(2) := 0.0;
// orbital inclination (degrees)
oev_po(3) := 28.5 * dtr;
Finally, the software requires the user to define the transfer time from Earth to the moon in hours.
// time-of-flight in hours
tof_hours := 84.0;
The PDF document included with the zip archive explains the assumptions and algorithms used to solve this classic orbital transfer problem.