From a3ffeaadfef79c7388b9abf04657e0844272e6d7 Mon Sep 17 00:00:00 2001
From: Gabriele Ghia <gabriele.ghia@skywarder.eu>
Date: Wed, 19 Feb 2025 17:54:06 +0000
Subject: [PATCH] Update file READMEnewApogee.md
---
apogeeAnalysis/READMEnewApogee.md | 84 -------------------------------
1 file changed, 84 deletions(-)
delete mode 100644 apogeeAnalysis/READMEnewApogee.md
diff --git a/apogeeAnalysis/READMEnewApogee.md b/apogeeAnalysis/READMEnewApogee.md
deleted file mode 100644
index b11a2b52..00000000
--- a/apogeeAnalysis/READMEnewApogee.md
+++ /dev/null
@@ -1,84 +0,0 @@
----
-
-### 3️⃣ **Review Output**
-
-The simulation results are saved into structured variables for analysis and visualization. The following metrics are included:
-
-#### **Standard Analysis Results**
-- **Apogee**: Maximum altitude achieved.
-- **Maximum Acceleration**: Peak acceleration during flight, limited to 15g.
-- **Launchpad Exit Velocity**: Velocity at launchpad exit, limited to 20 m/s.
-- **Computation Time**: Time taken for the simulation.
-
-#### **Engine Cut Analysis Results**
-- **Apogee**: Maximum altitude with engine cut-off considered.
-- **Cut-Off Timing Variations**: Evaluates performance with up to 5 variations around 80% engine cut-off time.
-- **Launchpad Exit Velocity**: Initial velocity, limited to 20 m/s.
-- **Computation Time**: Time taken for the simulation.
-
-**Example Output**:
-```matlab
-standardResults = struct('apogee', 3100, 'maxAcceleration', 14.5, 'exitVelocity', 25, 'compTime', 2.7);
-engineCutResults = struct('apogee', 2800, 'cutOffTimeVariations', 5, 'exitVelocity', 22, 'compTime', 3.1);
-
-
-## 📊 **Output Metrics**
-
-### **Standard Results**
-The following metrics are calculated during the standard apogee analysis:
-- **Apogee**: Maximum altitude reached by the rocket in meters.
-- **Maximum Acceleration**: The highest acceleration experienced by the rocket during flight in g's.
-- **Launchpad Exit Velocity**: The velocity of the rocket at the moment of launchpad exit in meters per second.
-- **Computational Time**: Time taken to execute the simulation.
-
-### **Engine Cut Results**
-For the engine cut scenario, the same metrics are calculated but with additional analysis on the effect of engine cutoff during flight:
-- **Apogee**: Maximum altitude reached with engine cutoff simulated.
-- **Maximum Acceleration**: The highest acceleration experienced with engine cutoff simulated.
-- **Launchpad Exit Velocity**: The velocity at the moment of launchpad exit, simulating the effect of engine cutoff.
-- **Computational Time**: Time taken to execute the engine cut simulation.
-
-### **Plots**
-The following plots are generated based on the configuration settings:
-- **Acceleration Plot**: Shows the rocket’s acceleration over time.
-- **Launchpad Exit Velocity Plot**: Displays the rocket’s exit velocity against time.
-- **Apogee Distribution Plot**: Displays the distribution of apogee values for all simulation runs, including uncertainties.
-
-
----
-
-## ⚠️ **Troubleshooting Output Issues**
-
-If the output data is not as expected, consider the following:
-
-1. **Check Configurations**: Ensure that motor settings, uncertainties, and environmental parameters are correctly specified in the `configApogee.m` file. Incorrect or missing configuration values could lead to unexpected results or errors during the simulation.
-
-2. **Inspect Simulation Logs**: Errors or warnings during the simulation will appear in the MATLAB command window. These logs provide helpful insights into what went wrong. Pay attention to any messages related to motor selection, uncertainties, or configuration issues that may require adjustment.
-
-3. **Verify Data Integrity**: If the simulation finishes successfully but the results appear invalid (e.g., unrealistic apogee or acceleration), ensure that the input data, such as motor properties, uncertainties, and environmental conditions, are reasonable and correctly configured.
-
-4. **Plot Visibility**: If plots are not displaying as expected, verify that the plotting options are enabled in the `configApogee.m` file. Additionally, ensure that the plot generation conditions (e.g., valid data for acceleration and exit velocity) are met.
-
-5. **Examine File Paths**: Make sure that the results and plot saving paths are correctly specified and accessible. Missing or incorrect file paths can prevent the saving of output data or plots.
-
----
-
-## 📝 **Further Analysis and Customization**
-
-You can further customize the post-simulation process and analysis:
-
-- **Modify Plotting Functions**: You can adjust the existing plotting functions in the `mainApogeeAnalysis.m` file to generate additional visualizations. For example, you could create additional plots for other metrics or different stages of the rocket flight.
-
-- **Sensitivity and Uncertainty Analysis**: If you want to analyze how different parameters affect the outcome, consider performing sensitivity analysis by adjusting one or more parameters, such as motor thrust or environmental conditions. This will help identify which factors have the greatest impact on apogee or acceleration.
-
-- **Advanced Statistical Analysis**: You can incorporate more advanced statistical tools to interpret the simulation results, such as Monte Carlo simulations, if you want to study the effect of uncertainty propagation in the system.
-
-- **Automate Comparison**: If you're running multiple simulations with different configurations, consider writing a MATLAB script that automatically compares the results and generates summary statistics or plots for easy interpretation.
-
----
-
-## 🛠 **License and Support**
-
-This simulation framework is developed and maintained by **Skyward Experimental Rocketry** and is licensed under the **GPL-3.0-or-later** license.
-For support, collaborations, or further inquiries, please contact us at [support@skywardrocket.com](mailto:support@skywardrocket.com).
-
--
GitLab