Summary

Modern small Unmanned Aerial System (sUAS) control systems require an accurate determination of aerodynamic state information including angle of attack, angle of sideslip, and velocity at low speeds. This necessitates a lightweight, compact sensor system.  This project developed a method to determine the state of an sUAS using a multi-port pitot probe. In this work, a method is developed using potential flow to simulate pressure on the front of a sphere.  This simulation uses two methods to determine the aerodynamic state information. This work also contains a code to analyze the error of a given port configuration and method. This code was used to develop a more effective multi-port pitot probe configuration. This configuration resulted in a total angular accuracy of less than ±0.67° for angles of attack and sideslip of less than ±20°.