Spacecraft Simulation
R2026bUse the spacecraft blocks, available in the Aerospace Blockset > Spacecraft sublibrary, to model, simulate, and visualize the dynamics of spacecraft. Use the Central Body Coordinate Transform block to transform the central body coordinate system.
Blocks
 | Attitude Dynamics | Model attitude dynamics of one or more spacecraft (Since R2023a) |
 | Attitude Profile (Nadir Pointing) | Calculate shortest quaternion rotation |
 | Cartesian State Vectors to Keplerian Orbital Elements | Calculate Keplerian orbital elements from orbital state vectors in equatorial coordinate system of celestial bodies (Since R2026a) |
 | Central Body Coordinate Transform | Transform coordinate frames between International Celestial Reference System (ICRF) and fixed-frame (Since R2026b) |
 | CubeSat Vehicle Earth (Nadir) Pointing | Model CubeSat vehicle whose primary alignment vector points towards center of Earth |
 | Keplerian Orbital Elements to Cartesian State Vectors | Calculate orbital state vectors in equatorial coordinate system of celestial bodies from Keplerian orbital elements (Since R2026a) |
 | Line of Sight Access | Determine line of sight (LOS) access between one or more source positions and one or more target positions (Since R2024b) |
 | Orbit Propagator Kepler (unperturbed) | Propagate orbit of one or more spacecraft using Kepler universal variable formulation |
 | Orbit Propagator Numerical (high precision) | Propagate orbit of one or more spacecraft using Kepler universal variable formulation |
 | Spacecraft Dynamics | Model dynamics of one or more spacecraft |
Topics
- Model Spacecraft
Model, simulate, and visualize the motion and dynamics of spacecraft using spacecraft dynamics, orbit propagator, and CubeSat blocks.
- Model and Simulate CubeSats
Model, simulate, analyze, and visualize the motion and dynamics of spacecraft.
- Orbit Propagation Methods
Analyze the motion and dynamics of aerospace vehicles with short-period requirements, boundary line, and altitude contour plots.
- Getting Started with the Spacecraft Dynamics Block
Model six degree-of-freedom rigid-body dynamics of a spacecraft or constellation of spacecraft.
- Constellation Modeling with the Orbit Propagator Block
Propagate the orbits of a constellation of satellites and compute and visualize access intervals between the individual satellites and several ground stations.
- Developing the Apollo Lunar Module Digital Autopilot
Develop Apollo Lunar Module digital autopilot using Simulink® and Aerospace Blockset™.
Featured Examples
Magnetic Control for Detumbling of Satellite
Model magnetic control for the detumbling of a CubeSat.
Model Articulating Spacecraft Solar Panels for Sun-Tracking
Model sun-tracking solar panels on a nadir pointing spacecraft.
Constellation Modeling with the Orbit Propagator Block
Propagate the orbits of a constellation of satellites and compute and visualize access intervals between the individual satellites and several ground stations.
Space Rendezvous and Docking
Maneuver a spacecraft in orbit to rendezvous and dock with another spacecraft.
Mission Analysis with the Orbit Propagator Block
Compute and visualize line-of-sight access intervals between satellites and a ground station.
Getting Started with the Spacecraft Dynamics Block
Model six degree-of-freedom rigid-body dynamics of a spacecraft or constellation of spacecraft.
Developing the Apollo Lunar Module Digital Autopilot
Develop Apollo Lunar Module digital autopilot using Simulink and Aerospace Blockset.
Lunar Mission Analysis with the Orbit Propagator Block
Compute and visualize access intervals between the Apollo Command and Service module 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:
Analyzing Spacecraft Attitude Profiles with Satellite Scenario
Propagate orbit and attitude states in Simulink and visualize computed trajectory and attitude profile in satellite scenario.
Model-Based Systems Engineering for Space-Based Applications
Explore the CubeSat Model-Based System Engineering Project template.
High Precision Orbit Propagation of the International Space Station
Propagate the order of the International Space Station (ISS) using high precision numerical orbit propagation.
Hohmann Transfer with the Spacecraft Dynamics Block
Model a Hohmann transfer of a spacecraft between two circular coplanar orbits.
Collision Avoidance Maneuver for Upcoming Conjunction
Identify and avoid upcoming conjunctions.
Deploy Flexible Solar Panel Array on CubeSat
Compute the flexible motion of a CubeSat's solar panel arrays during deployment, and their effect on CubeSat attitude and camera performance.
