The process of creating and analyzing a fixed-wing aircraft in MATLAB® using Cessna C182 geometry and coefficient data.

Convert a fixed-wing aircraft to a linear time invariant (LTI) state-space model for linear analysis.

Construct and define a custom state for a fixed-wing aircraft.

演示如何添加带时间戳的星历表a for a constellation of 24 satellites (similar to ESA Galileo GNSS constellation) to a satellite scenario for access analysis. The example uses data generated by the Aerospace Blockset Orbit Propagator block. For more information, see the Aerospace Blockset example Constellation Modeling with the Orbit Propagator Block.

Compares the orbits predicted by the Two-Body-Keplerian, Simplified General Perturbations-4 (SGP4) and Simplified Deep-Space Perturbations-4 (SDP4) orbit propagators. An orbit propagator is a solver that calculates the position and velocity of an object whose motion is predominantly influenced by gravity from celestial bodies. The Two-Body-Keplerian orbit propagator is based on the relative two-body model that assumes a spherical gravity field for the Earth and neglects third body effects and other environmental perturbations, and hence, is the least accurate. The SGP4 orbit propagator accounts for secular and periodic orbital perturbations caused by Earth's geometry and atmospheric drag, and is applicable to near-Earth satellites whose orbital period is less than 225 minutes. The SDP4 orbit propagator builds upon SGP4 by accounting for solar and lunar gravity, and is applicable to satellites whose orbital period is greater than or equal to 225 minutes. The default orbit propagator for satelliteScenario is SGP4 for satellites whose orbital period is less than 225 minutes, and SDP4 otherwise.

Demonstrates how to set up access analysis between a ground station and conical sensors onboard a constellation of satellites. A ground station and a conical sensor belonging to a satellite are said to have access to one another if the ground station is inside the conical sensor's field of view and the conical sensor's elevation angle with respect to the ground station is greater than or equal to the latter's minimum elevation angle. The scenario involves a constellation of 40 low-Earth orbit satellites and a geographical site. Each satellite has a camera with a field of view of 90 degrees. The entire constellation of satellites is tasked with photographing the geographical site, which is located at 42.3001 degrees North and 71.3504 degrees West. The photographs are required to be taken between 12 May 2020 1:00 PM UTC and 12 May 2020 7:00 PM UTC when the site is adequately illuminated by the sun. In order to capture good quality pictures with minimal atmospheric distortion, the satellite's elevation angle with respect to the site should be at least 30 degrees (please note that 30 degrees was arbitrarily chosen for illustrative purposes). During the 6 hour interval, it is required to determine the times during which each satellite can photograph the site. It is also required to determine the percentage of time during this interval when at least one satellite's camera can see the site. This percentage quantity is termed the system-wide access percentage.

Import a Two-Line Element (TLE) file of a satellite constellation, simulate radar detections of the constellation, and track the constellation.