Question

I need a full MATLAB code on Earth observation satellite is designed to fly in a circular sun-synchronous orbit with a local time of 13:00 +- 15 minutes and an altitude of 650 km over the Earth equator. The control of the mission has to assure that the satellite is always within the local time defined by the mission requirements. Assuming that, on average, the inclination increases 0.05 degrees in a year, determine: a) The nominal value of the inclination of the orbit. b) The maximum variation in inclination that the control of the mission can allow. c) The time between maneuvers and the impulse required in each one of these maneuvers. Where should this maneuver be performed? d) The mean inclination of the orbit after the station-keeping maneuver is performed. The evolution of the variation of inclination and right ascension of the ascending node with respect to the sun-synchronous values. Provide a plot for each one of these variables where the x-axis contains the time after a maneuver in days, and the y-axis, the mean variation of the orbital element. Note: apart from the perturbation in the inclination, consider only J2 as the perturbation affecting the mission. Using MATLAB codes.

          I need a full MATLAB code on Earth observation satellite is designed to fly in a circular sun-synchronous orbit with a local time of 13:00 +- 15 minutes and an altitude of 650 km over the Earth equator. The control of the mission has to assure that the satellite is always within the local time defined by the mission requirements. Assuming that, on average, the inclination increases 0.05 degrees in a year, determine:
a) The nominal value of the inclination of the orbit.
b) The maximum variation in inclination that the control of the mission can allow.
c) The time between maneuvers and the impulse required in each one of these maneuvers. Where should this maneuver be performed?
d) The mean inclination of the orbit after the station-keeping maneuver is performed.
The evolution of the variation of inclination and right ascension of the ascending node with respect to the sun-synchronous values. Provide a plot for each one of these variables where the x-axis contains the time after a maneuver in days, and the y-axis, the mean variation of the orbital element.
Note: apart from the perturbation in the inclination, consider only J2 as the perturbation affecting the mission. Using MATLAB codes.

Added by Timothy R.

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