Propagate the orbits of a constellation of satellites and compute and visualize access intervals between the individual satellites and several ground stations. It uses:

Compute and visualize line-of-sight access intervals between satellite(s) and a ground station. It uses:

Model six degree-of-freedom rigid-body dynamics of a spacecraft or constellation of spacecraft with the Spacecraft Dynamics block from the Aerospace Blockset.

"Working on the design of the Lunar Module digital autopilot was the highlight of my career as an engineer. When Neil Armstrong stepped off the LM (Lunar Module) onto the moon's surface, every engineer who contributed to the Apollo program felt a sense of pride and accomplishment. We had succeeded in our goal. We had developed technology that never existed before, and through hard work and meticulous attention to detail, we had created a system that worked flawlessly." -Richard J. Gran, The Apollo 11 Moon Landing: Spacecraft Design Then and Now

Compute and visualize line-of-sight access intervals between the Apollo Command and Service module (CSM) and a rover on the lunar surface. The module's orbit is modeled using Reference Trajectory #2 from the NASA report Variations of the Lunar Orbital Parameters of the Apollo CSM-Module [2]. This is a lunar orbit studied by NASA for the Apollo program. The example uses:

Propagate orbit and attitude states in Simulink^® and visualize computed trajectory and attitude profile in a satellite scenario.

Explore the CubeSat Model-Based System Engineering Project template.