Update README.md

Author: kathyz95

Classroom Challenge Projects/Projects/Drone Payload Capacity and Structural Design Analysis/README.md

@@ -4,7 +4,7 @@
 <p>Test different drone arm designs and materials to maximize payload capacity while maintaining structural integrity by performing thrust-to-weight analysis and finite element analysis in MATLAB.</p>
 </table>
 
-**THIS GITHUB REPO IS CURRENTLY BEING EDITED 05/13/26**
+**THIS GITHUB REPO IS CURRENTLY BEING EDITED 05/14/26**
 
 ## Motivation
 As drone use becomes increasingly common, such as in aerial photography, infrastructure inspection, and package delivery, there is a critical need to design lightweight structures that can safely support increasing payload demands. This project focuses on the engineering challenge of optimizing drone arm geometry and material selection to maximize payload capacity while ensuring structural integrity under motor-induced loads. By applying force balance analysis alongside finite element modeling, the work reflects industry practices used to design reliable, high-performance components in commercial drones, aircraft structures, and automotive systems.
@@ -19,6 +19,20 @@ Through this process, students explore authentic engineering tradeoffs, such as
 ### Suggested Steps
 Open the "DroneDesign_StudentProjectTemplate.mlx" Live Script in MATLAB as a starting point for your project.
 
+1. Gather your starter assumptions and load the material properties into MATLAB.
+   - Load the provided `droneMaterials.mat` file into MATLAB. This contains a data struct with the material properties for six different materials commonly used for drones. For each material, you have been provided the following information:
+       - Density ($\rho$), in $kg/m^3$
+       - Young's Modulus ($E$) in Pa
+       - Poisson's ratio ($\nu$), unitless
+       - Yield strength, in Pa
+       - Average cost per meter in US dollars
+   - For this project, you can assume the following design parameters:
+       - Quadcopter drone with 4 motors and 4 propellers
+       - Each motor can provide up to 1kg thrust
+       - Acceleration due to gravity: $g = 9.81m/s^2$
+       - Total weight of the drone components without the arms or the payload
+2. 
+
 
 ### Expected Results for Project Solution