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tudat-team · Oct 11, 2024 · 0395ad4 · 0395ad4
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diff --git a/propagation/linear_sensitivity_analysis.ipynb b/propagation/linear_sensitivity_analysis.ipynb
@@ -5,7 +5,7 @@
    "id": "1fe978b0-d823-4f3e-b3e6-86a3e25cedbc",
    "metadata": {},
    "source": [
-    "# Linear sensitivity analysis of perturbed orbit\n",
+    "# Linear sensitivity analysis using variational equations\n",
     "\n",
     "## Objectives\n",
     "This example is an extension of the Perturbed Satellite Orbit Application. It adopts the simulation setup from the Perturbed Satellite Orbit, considering a slightly reduced set of perturbing accelerations for the propagation of the vehicle.\n",
@@ -14,7 +14,6 @@
     "\n",
     "Via the `estimation_setup.parameter module`, the system parameters w.r.t. which the sensitivity is to be studied are defined and a `create_variational_equations_solver` function from the numerical_simulation module is used in order to setup and integrate the system's variational equations. After obtaining the state transition matrices from the integrated variational equations, the system's response to small perturbations can be tested via simple matrix multiplication.\n",
     "\n",
-    "\n",
     "The availability of variational equations in tudat enables many more, advanced functionalities, such as covariance analysis and precise orbit determination."
    ]
   },
@@ -563,9 +562,9 @@
  ],
  "metadata": {
   "kernelspec": {
-   "display_name": "tudat-bundle",
+   "display_name": "tudat-examples",
    "language": "python",
-   "name": "tudat-bundle"
+   "name": "python3"
   },
   "language_info": {
    "codemirror_mode": {
@@ -577,7 +576,7 @@
    "name": "python",
    "nbconvert_exporter": "python",
    "pygments_lexer": "ipython3",
-   "version": "3.11.9"
+   "version": "3.10.14"
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diff --git a/propagation/reentry_trajectory.ipynb b/propagation/reentry_trajectory.ipynb
@@ -5,7 +5,7 @@
    "id": "fe6987ee-7907-4b32-b8b4-30927d4e7970",
    "metadata": {},
    "source": [
-    "# Re-entry trajectory\n",
+    "# Re-entry trajectory using custom aerodynamic guidance\n",
     "\n",
     "## Objectives\n",
     "\n",
@@ -995,9 +995,9 @@
  ],
  "metadata": {
   "kernelspec": {
-   "display_name": "tudat-bundle",
+   "display_name": "tudat-examples",
    "language": "python",
-   "name": "tudat-bundle"
+   "name": "python3"
   },
   "language_info": {
    "codemirror_mode": {
@@ -1009,7 +1009,7 @@
    "name": "python",
    "nbconvert_exporter": "python",
    "pygments_lexer": "ipython3",
-   "version": "3.11.9"
+   "version": "3.10.14"
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diff --git a/propagation/solar_system_propagation.ipynb b/propagation/solar_system_propagation.ipynb
@@ -5,7 +5,7 @@
    "id": "a22ea1d1-e56f-464d-a03e-02b2f0e27bfb",
    "metadata": {},
    "source": [
-    "# Solar System Propagation\n",
+    "# Solar System Propagation using Multi-Body Dynamics\n",
     "Copyright (c) 2010-2022, Delft University of Technology. All rights reserved. This file is part of the Tudat. Redistribution and use in source and binary forms, with or without modification, are permitted exclusively under the terms of the Modified BSD license. You should have received a copy of the license with this file. If not, please or visit: http://tudat.tudelft.nl/LICENSE.\n",
     "\n",
     "## Objectives\n",
@@ -470,7 +470,7 @@
  ],
  "metadata": {
   "kernelspec": {
-   "display_name": "Python 3 (ipykernel)",
+   "display_name": "tudat-examples",
    "language": "python",
    "name": "python3"
   },
@@ -484,7 +484,7 @@
    "name": "python",
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    "pygments_lexer": "ipython3",
-   "version": "3.11.9"
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