Orbit Calculation

Application ID: 109301

This model is an introduction to defining and verifying a satellite orbit, and computing the solar, albedo, and Earth infrared thermal loads. A 1U CubeSat is in a circular orbit at 400km altitude, inclination of 50°, and longitude of ascending node of 0°. The satellite is rotating slowly about its nadir-pointing axis. One orbital period is analyzed, during the Winter Solstice. The total irradiation and the radiative loads from all environmental sources is computed. This type of analysis is usually performed prior to computing the temperature evolution within the structure of the satellite.

This model example illustrates applications of this type that would nominally be built using the following products: